US20130004291A1 - Turbomachine Fluid-Conduit Housing Coupling System and Method - Google Patents
Turbomachine Fluid-Conduit Housing Coupling System and Method Download PDFInfo
- Publication number
- US20130004291A1 US20130004291A1 US13/531,577 US201213531577A US2013004291A1 US 20130004291 A1 US20130004291 A1 US 20130004291A1 US 201213531577 A US201213531577 A US 201213531577A US 2013004291 A1 US2013004291 A1 US 2013004291A1
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- US
- United States
- Prior art keywords
- fluid
- centerbody
- housing
- conduit housing
- radial
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
- F01D25/265—Vertically split casings; Clamping arrangements therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
- F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/024—Units comprising pumps and their driving means the driving means being assisted by a power recovery turbine
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T137/00—Fluid handling
- Y10T137/0318—Processes
- Y10T137/0402—Cleaning, repairing, or assembling
Definitions
- FIG. 1 illustrates an isometric view of a first aspect of an internal combustion engine comprising a pair of cylinder heads and a corresponding pair of turbocharger cores integrated therewith;
- FIG. 2 illustrates an isometric view of a cylinder head and turbocharger core from the first aspect of an internal combustion engine illustrated in FIG. 1 ;
- FIG. 3 illustrates first cross-sectional view through the cylinder head and turbocharger core illustrated in FIG. 2 ;
- FIG. 4 illustrates an isometric view of the turbocharger core as used in the embodiments illustrated in FIGS. 1-3 ;
- FIG. 5 illustrates an isometric view of a nozzle cartridge assembly from the turbocharger core illustrated in FIG. 2 ;
- FIG. 6 illustrates a second cross-sectional view through the cylinder head and turbocharger core illustrated in FIG. 2 ;
- FIG. 7 illustrates a transverse cross-sectional view through a turbine nozzle portion of the turbocharger core illustrated in FIG. 4 ;
- FIG. 8 illustrates a transverse cross-sectional view through a bearing housing portion of the turbocharger core illustrated in FIG. 4 ;
- FIG. 9 illustrates third cross-sectional view through the cylinder head and turbocharger core illustrated in FIG. 2 ;
- FIG. 10 illustrates an expanded view of a portion of the third cross-sectional view through the cylinder head and turbocharger core illustrated in FIG. 9 ;
- FIG. 11 illustrates a schematic view of a first alternative embodiment of an interface of a plurality of exhaust runners from each of a plurality of cylinders with a cavity in a cylinder head adapted to receive a turbocharger core;
- FIG. 12 illustrates a schematic view of a second alternative embodiment of an interface of a plurality of exhaust runners from each of a plurality of cylinders with a cavity in a cylinder head adapted to receive a turbocharger core;
- FIG. 13 illustrates an isometric view of a portion of a second aspect of an internal combustion engine incorporating a first embodiment of a first aspect of a turbocharger assembly operatively coupled to an associated exhaust manifold;
- FIG. 14 illustrates an exploded view of portions of the first embodiment of the first aspect of the turbocharger assembly and associated housing used with the second aspect of the internal combustion engine illustrated in FIG. 13 ;
- FIG. 15 illustrates a longitudinal cross-sectional exploded view of the first embodiment of the first aspect of the turbocharger assembly and associated housing used with the second aspect of the internal combustion engine illustrated in FIG. 13 ;
- FIG. 16 illustrates a fragmentary longitudinal cross-sectional view of a second embodiment of the first aspect of a turbocharger assembly in accordance with the second aspect an internal combustion engine
- FIG. 17 illustrates a transverse cross-sectional view of the second embodiment of the first aspect of the turbocharger assembly illustrated in FIG. 16 ;
- FIG. 18 illustrates a third embodiment of the first aspect of a turbocharger assembly incorporating a second aspect of an associated turbocharger core having an associated radial-flow turbine, in accordance with the second aspect of an internal combustion engine;
- FIG. 19 illustrates an isometric partially exploded view of a first embodiment of a second aspect of a turbocharger assembly useable with the second aspect an internal combustion engine, illustrating a first embodiment of associated radial pins that provide for coupling the associated exhaust housing to the associated centerbody, and that provide for maintaining a concentricity the exhaust housing relative to the centerbody of the turbocharger assembly;
- FIG. 20 illustrates a portion of a longitudinal cross-section of the first embodiment of a second aspect of a turbocharger assembly illustrated in FIG. 19 , illustrating a corresponding turbine portion in relation to the corresponding centerbody portion;
- FIG. 21 illustrates an aft-looking radial cross-section of the first embodiment of the second aspect of a turbocharger assembly illustrated in FIGS. 19 and 20 through a transverse plane intersecting the centers of a plurality of associated radial pins;
- FIG. 22 illustrates a fragmentary longitudinal cross-section of the first embodiment of the second aspect of a turbocharger assembly illustrated in FIGS. 19-21 , illustrating a first embodiment of an associated seal between the centerbody and exhaust housing of the turbocharger assembly;
- FIGS. 23 a and 23 b schematically illustrate a thermal expansion of an internal cylindrical surface of an exhaust housing relative to an external cylindrical surface of a centerbody, illustrating the plurality of associate radial pins maintaining the relative concentricity of the internal and external cylindrical surfaces for two different conditions of relative thermal expansion;
- FIG. 24 illustrates a forward-looking radial cross-section of a second embodiment of the second aspect of a turbocharger assembly similar to that illustrated in FIG. 19 , through a transverse plane intersecting the centers of a plurality of associated radial pins, for a second embodiment of the radial pins;
- FIG. 25 illustrates a fragmentary longitudinal cross-section of a third embodiment of the second aspect of a turbocharger assembly similar to that illustrated in FIG. 19 , illustrating a second embodiment of the associated seal between the centerbody and exhaust housing of the turbocharger assembly;
- FIG. 26 illustrates a fragmentary longitudinal cross-section of a fourth embodiment of the second aspect of a turbocharger assembly similar to that illustrated in FIG. 19 , illustrating a third embodiment of the associated seal between the centerbody and exhaust housing of the turbocharger assembly;
- FIG. 27 illustrates a fragmentary longitudinal cross-section of a fifth embodiment of the second aspect of a turbocharger assembly similar to that illustrated in FIG. 19 , illustrating a fourth embodiment of the associated seal between the centerbody and exhaust housing of the turbocharger assembly;
- FIG. 28 illustrates a fragmentary longitudinal cross-section of a sixth embodiment of the second aspect of a turbocharger assembly, illustrating a second aspect of an associated volute portion of the exhaust housing of the turbocharger assembly.
- a pair of turbocharger cores 10 are integrated with a corresponding pair of cylinder head assemblies 12 of a first aspect of an internal combustion engine 14 , 14 . 1 of a V-type configuration, for example, a V-6 internal combustion engine 14 , 14 . 1 ′.
- each turbocharger core 10 comprises a compressor 16 driven by an exhaust-powered turbine 18 , wherein when the turbocharger core 10 is attached to the internal combustion engine 14 , 14 .
- each associated turbine 18 is inserted in and cooperates with a cavity 20 , for example, a cylindrical cavity 20 ′ or a volute cavity 20 ′′, in the corresponding cylinder head assembly 12 adapted to receive exhaust gases 21 from the associated cylinder or cylinders 22 associated therewith via associated exhaust runners 24 .
- the turbocharger core 10 incorporates an axial-flow turbine 18 , which can be configured with a relatively low associated moment of inertia so as to provide for a relatively rapid dynamic response to changes in the associated operating condition of the internal combustion engine 14 , 14 . 1 .
- the first aspect of the internal combustion engine 14 , 14 In the first aspect of the internal combustion engine 14 , 14 .
- the exhaust runners 24 from each cylinder 22 communicate with a common first exhaust port 26 in the side of the cavity 20 at a location off-axis relative to the central axis 28 of the cavity 20 so as to induce a circulation of the exhaust gases 21 flowing thereinto.
- the turbocharger core 10 comprises a turbine rotor 30 of a turbocharger rotor assembly 31 operatively coupled to an aft end 32 . 1 of a rotor shaft 32 of the turbocharger rotor assembly 31 that is rotationally supported by rotor shaft support assembly 33 , also known as a centerbody 33 , comprising an aft journal bearing 34 and a forward rolling element bearing 36 located within an associated bearing housing 38 and spaced apart from one another along the rotor shaft 32 .
- the bearing housing 38 incorporates a cooling jacket 40 therewithin in fluid communication with inlet 42 and outlet 44 ports that are adapted to receive a flow of cooling water from the water cooling system 46 of the internal combustion engine 14 , 14 .
- An oil inlet port 48 is adapted to receive a supply of pressurized engine oil from an oil pump of the internal combustion engine 14 , 14 . 1 and distribute this oil to the aft journal bearing 34 and the forward rolling element bearing 36 via associated oil distribution passages 50 .
- Oil draining from aft journal bearing 34 and the forward rolling element bearing 36 is gravity collected in an oil scavenge cavity 52 within the base of the bearing housing 38 , and is returned to the internal combustion engine 14 , 14 . 1 via an associated oil scavenge line 54 (illustrated in FIG. 13 ) connected to an associated oil scavenge port 54 ′ at the base of the bearing housing 38 .
- the rotor shaft support assembly 33 is not limited to the combination of an aft journal bearing 34 and a forward rolling element bearing 36 , but the rotor shaft support assembly 33 could alternatively comprise any combination of journal and rolling element bearings, or conceivably a single extended-length journal bearing.
- the compressor 16 of the turbocharger core 10 comprises a compressor rotor 56 of the turbocharger rotor assembly 31 operatively coupled to the forward end 32 . 2 of the rotor shaft 32 and adapted to rotate therewith about a central axis 28 ′ of the turbocharger core 10 , which is substantially aligned with the central axis 28 of the cavity 20 .
- the compressor rotor 56 in accordance with what is known as a boreless hub,—incorporates an aftward extending internally threaded boss 58 that threads onto the forward end 32 . 2 of the rotor shaft 32 , and the turbine rotor 30 is welded to the aft end 32 .
- the forward rolling element bearing 36 comprises an outer race 62 and forward 64 and aft 66 inner races located on the rotor shaft 32 between a shoulder 32 . 3 and the compressor rotor 56 , which provides for positioning the rotor shaft 32 within the bearing housing 38 .
- the bearing housing 38 incorporates forward 70 and aft 72 seals that provide for preventing leakage of oil from the bearing housing 38 into either the turbine 18 or compressor 16 of the turbocharger core 10 .
- the turbocharger core 10 further comprises a turbine nozzle cartridge assembly 74 operatively coupled to the aft side 38 . 1 of the bearing housing 38 .
- the turbine nozzle cartridge assembly 74 comprises a forward nozzle wall 76 , an aft nozzle wall 78 aftwardly separated therefrom, a plurality of vanes 80 disposed between the forward 76 and aft 78 nozzle walls, a turbine rotor shroud portion 82 extending aftward from the aft nozzle wall 78 , and a nozzle exhaust portion 84 extending aftward from the throat portion 82 .
- the nozzle exhaust portion 84 is illustrated with a relatively expanded diameter so as to provide for at least partially diffusing the associated exhaust gases, the nozzle exhaust portion 84 need not necessarily be relatively expanded in diameter relative to the associated turbine rotor shroud portion 82 .
- the forward nozzle wall 76 is formed as a first sheet metal element and the combination of the aft nozzle wall 78 and turbine rotor shroud 82 and nozzle exhaust 84 portions is formed as a second sheet metal element,—for example, each by stamping or spinning;—and the vanes 80 are each formed from sheet metal—, for example, by stamping,—and inserted in and then welded or brazed to a plurality of corresponding slots 86 in each of the forward 76 and aft 78 nozzle walls.
- the aft nozzle wall 78 , the turbine rotor shroud portion 82 and the nozzle exhaust portion 84 are each formed from two or more separate sheet metal pieces that that are then joined together, for example, by welding, brazing and/or by press-fitting.
- the turbine nozzle cartridge assembly 74 may be cast or sintered, for example, laser sintered.
- the turbine nozzle cartridge assembly 74 is constructed of a material that can withstand high temperature exhaust gases 21 , for example, of a nickel alloy, for example, stainless steel with a relatively high nickel content, for example, 310 stainless steel, that provides for high temperature oxidation resistance and strength.
- the remainder of the turbocharger core 10 can be constructed of less exotic and more economical materials, such as aluminum or cast iron.
- the cylinder head assembly 12 may be adapted with water cooling passages in thermal communication with the exhaust housing portion 88 thereof so as to provide using relatively low-cost materials, such as aluminum, for the construction thereof.
- the separate turbine nozzle cartridge assembly 74 of the turbocharger core 10 provides for an overall more economical use of high-temperature-tolerant materials—for example, limited to the turbine nozzle cartridge assembly 74 —than would otherwise be possible, and also provides for integrating the turbocharger core 10 into the cylinder head assembly 12 .
- the combined amount of raw material needed to make the turbine nozzle cartridge assembly 74 and the relatively more simple associated exhaust housing portion 88 of the cylinder head assembly 12 would be less than the amount of material needed to make an equivalent conventional turbocharger exhaust housing.
- the turbine rotor shroud portion 82 of the turbine nozzle cartridge assembly 74 is reinforced with a containment sleeve 90 that provides for containing the turbine rotor 30 in the event of a failure of the associated turbine blades 92 thereof.
- the turbine nozzle cartridge assembly 74 extends through the cavity 20 , 20 ′, 20 ′′ in the cylinder head assembly 12 .
- exhaust gases 21 from the cylinder or cylinders 22 flow through the associated exhaust runners 24 into the first exhaust port 26 , i.e. a cavity inlet exhaust port 26 , leading into the cavity 20 , 20 ′, 20 ′′, wherein the off-axis location of the first exhaust port 26 relative to the cavity 20 , 20 ′, 20 ′′ causes a swirl of the exhaust gases 21 flowing within the cavity 20 , 20 ′, 20 ′′.
- the exhaust gases 21 then flow with swirl into the peripheral inlet 93 of the turbine nozzle cartridge assembly 74 along the vanes 80 thereof, and against the turbine blades 92 of the turbine rotor 30 , thereby driving the turbine rotor 30 that in turn rotates the rotor shaft 32 and the compressor rotor 56 attached thereto.
- the exhaust gases 21 then flow through the nozzle exhaust portion 84 of the turbine nozzle cartridge assembly 74 before being exhausted into and through a second exhaust port 94 , i.e. a cavity outlet exhaust port 94 , that extends from a counterbore 96 in the aft end 20 .
- the cylinder head assembly 12 can incorporate a wastegate valve 99 operative between an exhaust runner 24 and the second exhaust port 94 so as to provide for bypassing exhaust gases 21 directly to the engine exhaust system 98 without first flowing through the turbine nozzle cartridge assembly 74 and associated turbine rotor 30 .
- the forward 76 and aft 78 nozzle walls of the turbine nozzle cartridge assembly 74 redirect and accelerate the circumferentially swirling exhaust gases 21 —flowing within the cavity 20 , 20 ′, 20 ′′ outside of the turbine nozzle cartridge assembly 74 —radially inward and axially aftward, and the resulting axially-aftward-flowing swirling exhaust gases 21 then impinge upon the turbine blades 92 of the turbine rotor 30 , thereby driving the turbine rotor 30
- the associated vanes 80 in cooperation with the forward 76 and aft 78 nozzle walls are adapted to provide for the proper vector orientation of the impinging exhaust gases 21 relative to the turbine rotor 30 so as to maximize the efficiency of the turbine 18 .
- the aft end 84 . 1 of the nozzle exhaust portion 84 of the turbine nozzle cartridge assembly 74 incorporates an external sealing surface 102 that cooperates with a seal ring 104 —for example, a piston-ring-type seal ring 104 ′′—located in an internal groove 106 in the counterbore 96 so as to provide for sealing the discharge end 108 of the turbine nozzle cartridge assembly 74 to the exhaust housing portion 88 of the cylinder head assembly 12 so that substantially all of the exhaust gases 21 are discharged from the turbine nozzle cartridge assembly 74 into and through the second exhaust port 94 and into the associated engine exhaust system 98 , thereby substantially isolating the exhaust gases 21 in the cavity 20 , 20 ′, 20 ′′ upstream of the turbine nozzle cartridge assembly 74 from the exhaust gases 21 discharged from the turbine nozzle cartridge assembly 74 .
- a seal ring 104 for example, a piston-ring-type seal ring 104 ′′—located in an internal groove 106 in the counterbore 96 so as
- the seal ring 104 in cooperation with the external sealing surface 102 provides for enabling discharge end 108 of the turbine nozzle cartridge assembly 74 to both slide in an axial direction and expand or contract in a radial direction, responsive to thermally-induced expansion or contraction thereof, while maintaining the sealing condition at the discharge end 108 of the turbine nozzle cartridge assembly 74 , without substantial associated thermally-induced loading of the turbine nozzle cartridge assembly 74 .
- the forward end 76 . 2 of the forward nozzle wall 76 comprises a cylindrical lip 110 that fits over a corresponding cylindrical step 112 that extends aftwardly from the aft side 38 . 1 of the bearing housing 38 .
- the turbine nozzle cartridge assembly 74 is retained on the bearing housing 38 by a plurality of radial pins 114 that extend through corresponding radial holes 116 in the cylindrical lip 110 and into corresponding blind radial holes 118 in the cylindrical step 112 .
- the radial pins 114 and associated radial holes 116 , 118 are located symmetrically around the circumferences of the cylindrical lip 110 and the cylindrical step 112 .
- the inside diameter of the cylindrical lip 110 and the outside diameter of the cylindrical step 112 may be adapted so that at ambient temperature, the cylindrical lip 110 has an interference fit with the cylindrical step 112 .
- the forward nozzle wall 76 and associated cylindrical lip 110 are free to thermally expand relative to cylindrical step 112 responsive to differences in temperature or thermal expansion rates of the forward nozzle wall 76 and bearing housing 38 , respectively, in which case, the engagement of the cylindrical lip 110 by the radial pins 114 provides for retaining the turbine nozzle cartridge assembly 74 to the bearing housing 38 , and the symmetric arrangement of the associated radial pins 114 and associated radial holes 116 , 118 provides for keeping the turbine nozzle cartridge assembly 74 substantially concentric with the central axis 28 ′′ of the turbocharger core 10 over the thermal operating range thereof.
- the turbine nozzle cartridge assembly 74 would heat up relatively more quickly, and to a substantially higher temperature, than the bearing housing 38 , and as a result the inside diameter of the cylindrical lip 110 would typically expand so as to be greater than the outside diameter of the cylindrical step 112 , so as to transition from a possible interference at ambient temperature to a substantially loose fit at elevated temperatures, under which circumstances, the radial pins 114 would provide for symmetrically and concentrically retaining the cylindrical lip 110 on the cylindrical step 112 , so as to preserve the relative alignment of the turbine nozzle cartridge assembly 74 with the associated turbine rotor 30 .
- the forward end 76 . 2 of the forward nozzle wall 76 can be centered on the bearing housing 38 with a plurality of aftwardly-extending axial pins or bolts extending from the aft side 38 . 1 of the bearing housing 38 through corresponding radial slots in the forward end 76 . 2 of the forward nozzle wall 76 , and retained on the bearing housing 38 either by the bolts or by a step in the forward end of the cavity 20 .
- the turbine blades 92 of the turbine rotor 30 are located within the turbine rotor shroud portion 82 of the turbine nozzle cartridge assembly 74 , which turbine rotor shroud portion 82 accordingly functions as a turbine tip shroud 82 ′, wherein the inside diameter of the turbine tip shroud 82 ′ is adapted to provide for about 0.01 inch of tip clearance 212 to the tips 120 of the turbine blades 92 , which relatively tight tolerance provides for improved efficiency of the turbine 18 that might otherwise be possible had the clearance been larger.
- the turbine tip shroud 82 ′ a part the turbine nozzle cartridge assembly 74 that is retained on the bearing housing 38 and free to float within the counterbore 96 in the cavity 20 , 20 ′, 20 ′′
- the turbine tip shroud 82 ′ is unaffected by the exhaust housing portion 88 of the cylinder head assembly 12 , for example, by thermally-induced stresses therein or therefrom, or external mechanical loads thereto, that might otherwise result in interference with the tip 120 of the turbine blades 92 , so that a relatively small clearance between the turbine tip shroud 82 ′ and the tip 120 of the turbine blades 92 can be readily realized using production hardware and processes.
- the turbocharger core 10 is assembled to the cylinder head assembly 12 with a plurality of bolts 122 through a corresponding plurality of holes 124 in an associated flange 126 or set of flanges 126 ′ of or extending from the bearing housing 38 , through an adapter bushing 128 , and into corresponding threaded holes 130 in the forward portion 132 of the exhaust housing portion 88 of cylinder head assembly 12 around the periphery of the of the cavity 20 , 20 ′, 20 ′′, so that when mounted to the cylinder head assembly 12 , the bearing housing 38 of the turbocharger core 10 provides for closing the forward end of the cavity 20 , which is sealed at the junction of the bearing housing 38 and adapter bushing 128 and the junction of the adapter bushing 128 and the forward portion 132 of the exhaust housing portion 88 of cylinder head assembly 12 around the periphery of the of the cavity 20 , 20 ′, 20 ′′ for example, either by mating flat surfaces—as illustrated—or by mating conical surfaces.
- the inside diameter of the adapter bushing 128 is sufficiently greater that the outside diameter of the cylindrical lip 110 of the forward nozzle wall 76 of the turbine nozzle cartridge assembly 74 so as to provide for uninhibited thermally induced expansion of the cylindrical lip 110 within the gap 134 therebetween, so as to prevent a thermally-induced mechanical stress of the turbine nozzle cartridge assembly 74 that would otherwise occur if the outward radial expansion of the cylindrical lip 110 were otherwise restrained by the adapter bushing 128 .
- the adapter bushing 128 also provides for capturing the radial pins 114 within their radial holes 118 in the cylindrical step 112 .
- the aft surface 136 of the adapter bushing 128 is located and shaped so as to provide for a relatively smooth transition from the inside surface 138 of the cavity 20 ′, 20 ′′ to the forward nozzle wall 76 so as to facilitate the flow of exhaust gases 21 from the cavity 20 ′, 20 ′′ into the turbine nozzle cartridge assembly 74 .
- the aft surface 136 of the adapter bushing 128 comprises a portion of a concave toroidal surface 136 that in cross-section provides for a quarter-round fillet between the inside surface 138 and the forward nozzle wall 76 .
- the adapter bushing 128 can be replaced by incorporating the material thereof directly into the exhaust housing portion 88 of the cylinder head assembly 12 .
- the turbocharger core 10 may be mounted to the forward portion 132 of the exhaust housing portion 88 of cylinder head assembly 12 with a V-clamp rather than bolts 122 .
- exhaust gases 21 from the first exhaust port 26 are first collected in the annulus 140 defined by portion of the cavity 20 , 20 ′, 20 ′′ of the exhaust housing portion 88 of the cylinder head assembly 12 on the outside of the turbine nozzle cartridge assembly 74 , and then accelerated therefrom by the turbine nozzle cartridge assembly 74 into the turbine blades 92 of the turbine rotor 30 .
- the turbine nozzle cartridge assembly 74 provides for directing and accelerating exhaust flow into the turbine blades 92 of the turbine rotor 30 , and controlling the associated mass flow of these exhaust gases 21 .
- the turbine nozzle cartridge assembly 74 can be configured—independent of the design of the cavity 20 , 20 ′, 20 ′′ or the associated exhaust housing portion 88 of the cylinder head assembly 12 , for example, by adjusting the area/radius ratio (A/R) of the passage 140 through the turbine nozzle cartridge assembly 74 —so as to adapt to the particular turbocharging requirements of a given internal combustion engine 14 , 14 . 1 , which provides for simplifying the process of tuning the turbocharger core 10 to the internal combustion engine 14 , 14 . 1 because the only component to be changed in that process would be the turbine nozzle cartridge assembly 74 .
- A/R area/radius ratio
- the forward 76 and aft 78 nozzle walls comprise corresponding forward 76 ′ and aft 78 ′ curved swept surfaces, the shapes of which may be adapted in cooperation with the associated vanes 80 to provide for tuning the turbocharger core 10 .
- the turbine rotor 30 of the turbine 18 of the turbocharger core 10 drives the rotor shaft 32 that rotates in the aft journal bearing 34 and forward rolling element bearing 36 in the bearing housing 38 and in turn drives the compressor rotor 56 that rotates within an associated compressor housing 142 of the associated compressor 16 , which provides for compressing air from a central inlet 144 to the compressor housing 142 , and discharging the compressed air through a volute diffuser 146 surrounding the compressor rotor 56 .
- the compressed air is discharged from the compressor 16 into a conduit 148 that is coupled to an inlet plenum 150 , for example, coupled to or surrounding a throttle body 152 coupled to an inlet manifold 154 of the internal combustion engine 14 , 14 . 1 .
- the cavity 20 , 20 ′, 20 ′′ of the exhaust housing portion 88 of the cylinder head assembly 12 may be configured to receive exhaust gases 21 from a plurality of first exhaust ports 26 , 26 . 1 , 26 . 2 , 26 . 3 , each operatively associated with one or more associated exhaust runners 24 , 24 . 1 , 24 . 2 , 24 . 3 , each exhaust runner 24 operatively associated with one or more cylinders 22 of the internal combustion engine 14 , 14 . 1 , wherein for each first exhaust port 26 , 26 . 1 , 26 . 2 , 26 . 3 , each corresponding associated exhaust runner 24 , 24 .
- the cavity 20 , 20 ′, 20 ′′ is coupled to each of three different cylinders with three different exhaust runners 24 , 24 . 1 , 24 . 2 , 24 .
- the cavity 20 , 20 ′, 20 ′′ is coupled to each of three different cylinders with three different exhaust runners 24 , 24 .
- the turbocharger core 10 By incorporating the turbocharger core 10 in the associated cylinder head assembly 12 , and providing for water-cooling the bearing housing 38 and the associated exhaust housing portion 88 of the cylinder head assembly 12 that surrounds the associated cavity 20 , 20 ′, 20 ′′ of the turbocharger core 10 , the turbocharger core 10 provides for reducing the amount of high-temperature tolerant material, for example a relatively high nickel content alloy, than would otherwise be required for a corresponding comparable stand-alone turbocharger assembly, which provides for reducing cost in comparison with a stand-alone turbocharger assembly. Furthermore, the incorporation of the turbocharger core 10 in the associated cylinder head assembly 12 provides for more closely coupling the exhaust from the cylinders 22 of the internal combustion engine 14 , 14 . 1 to the turbocharger core 10 , which provides for improved efficiency than would otherwise be possible with a corresponding comparable stand-alone turbocharger assembly.
- high-temperature tolerant material for example a relatively high nickel content alloy
- the associated turbocharger core 10 cooperates with a separate turbocharger exhaust housing 158 , an inlet 160 of which is operatively coupled to the exhaust manifold 162 of an internal combustion engine 14 , 14 . 2 , for example, with a plurality of bolts 164 through a first flange 166 at the outlet 168 of the exhaust manifold 162 into a second flange 170 at the inlet 160 of the turbocharger exhaust housing 158 .
- the inlet 160 is in fluid communication with a cavity 20 ′′ in the turbocharger exhaust housing 158 via a first exhaust port 26 ′ located so as to direct associated exhaust gases 21 off-center of the so as to induce a swirling flow of exhaust gases 21 therein.
- the bearing housing 38 of the turbocharger core 10 with the turbine nozzle cartridge assembly 74 attached thereto as described hereinabove, is bolted to a peripheral face 172 of the turbocharger exhaust housing 158 surrounding the cavity 20 ′′ with a plurality of bolts 174 through the bearing housing 38 and into associated threaded sockets 176 on the turbocharger exhaust housing 158 around the peripheral face 172 , so that the associated turbine nozzle cartridge assembly 74 extends through the cavity 20 ′′ and into an associated second exhaust port 94 ′ on the opposite side of the cavity 20 ′′.
- the second exhaust port 94 ′ incorporates a seal ring 104 in an internal groove 106 that cooperates with the associated external sealing surface 102 on the aft end 84 . 1 of the nozzle exhaust portion 84 of the turbine nozzle cartridge assembly 74 , so as to provide for sealing the discharge end 108 of the turbine nozzle cartridge assembly 74 to the turbocharger exhaust housing 158 so that substantially all of the exhaust gases 21 are discharged from the turbine nozzle cartridge assembly 74 into and through the second exhaust port 94 and into the associated engine exhaust system 98 , thereby substantially isolating the exhaust gases 21 in the cavity 20 ′′ upstream of the turbine nozzle cartridge assembly 74 from the exhaust gases 21 discharged from the turbine nozzle cartridge assembly 74 .
- the seal ring 104 in cooperation with the external sealing surface 102 provides for enabling discharge end 108 of the turbine nozzle cartridge assembly 74 to both slide in an axial direction and expand or contract in a radial direction, responsive to thermally-induced expansion or contraction thereof, while maintaining the sealing condition at the discharge end 108 of the turbine nozzle cartridge assembly 74 , without substantial associated thermally-induced loading of the turbine nozzle cartridge assembly 74 .
- exhaust gases 21 from the exhaust manifold 162 flow into the inlet 160 of the turbocharger exhaust housing 158 and then into the associated cavity 20 ′′.
- the exhaust gases 21 swirl about the outside of the turbine nozzle cartridge assembly 74 within the cavity 20 ′′, and then flow with swirl into the peripheral inlet 93 of the turbine nozzle cartridge assembly 74 along the vanes 80 thereof, and against the turbine blades 92 of the turbine rotor 30 , thereby driving the turbine rotor 30 that in turn rotates the rotor shaft 32 and the compressor rotor 56 attached thereto.
- the exhaust gases 21 then flow through the nozzle exhaust portion 84 of the turbine nozzle cartridge assembly 74 before being exhausted into and through the second exhaust port 94 ′ in the turbocharger exhaust housing 158 , and then into the engine exhaust system 98 , which, for example, may include one or more exhaust treatment devices 100 , for example, one or more catalytic converters or mufflers.
- the turbocharger exhaust housing 158 could be constructed of the same type of material, for example cast iron, or alternatively, cast with a relatively-high-nickel-content alloy, as could be used for the exhaust manifold 162 .
- the turbocharger core 10 may be tuned to a particular engine by modifying the turbine nozzle cartridge assembly 74 , independently of the design of the turbocharger exhaust housing 158 and the associated cavity 20 ′′.
- the associated turbocharger exhaust housing 158 incorporates an internal heat shield 178 , for example, constructed from a sheet-metal material that can withstand high temperature exhaust gases 21 , for example, of a nickel alloy, for example, stainless steel with a relatively high nickel content, for example, 310 stainless steel, that provides for high temperature oxidation resistance and strength. Exhaust gases 21 within the turbocharger exhaust housing 158 are substantially contained within the inside surface 178 .
- the internal heat shield 178 provides for both radiative and conductive heat shielding.
- an internal heat shield 178 can be particularly beneficial in the context of the first aspect the internal combustion engine 14 , 14 . 1 , i.e. integrated with an associated cylinder head assembly 12 , so as to provide for substantially reducing the amount of heat transferred from the exhaust gases 21 to the cylinder head assembly 12 that would otherwise need to be removed by the associated water cooling system 46 of the internal combustion engine 14 , 14 . 1 .
- the first aspect of the internal combustion engine 14 , 14 in one simulated embodiment of the first aspect of the internal combustion engine 14 , 14 .
- the turbocharger core 10 has been illustrated hereinabove configured with an axial-flow turbine 18 ′, wherein the exhaust gases 21 discharged from a nozzle portion 74 . 1 of the turbine nozzle cartridge assembly 74 are directed in a substantially axial-aftwards direction 184 aftward onto and against the turbine blades 92 of the associated axial-flow turbine 18 ′ located aftward of the forward nozzle wall 76 , vanes 80 , and nozzle portion 74 . 1 of the turbine nozzle cartridge assembly 74 .
- a third embodiment of the first aspect of a turbocharger assembly 200 . 1 ′′ adapted in accordance with the second aspect of an internal combustion engine is illustrated incorporating a second aspect of an associated turbocharger core 10 ′ having an associated radial-flow turbine 18 ′′ and a corresponding associated turbine nozzle cartridge assembly 74 ′ that provides for discharging the associated exhaust gases 21 in a substantially radial-inwards direction 186 from the nozzle portion 74 . 1 ′ of the turbine nozzle cartridge assembly 74 onto and against the turbine blades 92 ′ of the associated radial-flow turbine 18 ′′ located radially inboard of the forward nozzle wall 76 , vanes 80 , and nozzle portion 74 . 1 ′ of the turbine nozzle cartridge assembly 74 ′.
- the turbocharger core 10 may be adapted with a mixed-flow turbine, i.e. a combined radial-flow and axial-flow turbine, with an associated turbine nozzle cartridge assembly 74 adapted to cooperate therewith, but otherwise generally configured as described hereinabove, with the associated mixed-flow turbine rotor located aft and radially inboard of the forward nozzle wall 76 , vanes 80 , and nozzle portion 74 . 1 of the turbine nozzle cartridge assembly 74 , with an associated conical boundary therebetween.
- a mixed-flow turbine i.e. a combined radial-flow and axial-flow turbine
- an associated turbine nozzle cartridge assembly 74 adapted to cooperate therewith, but otherwise generally configured as described hereinabove, with the associated mixed-flow turbine rotor located aft and radially inboard of the forward nozzle wall 76 , vanes 80 , and nozzle portion 74 . 1 of the turbine nozzle cartridge assembly 74 , with an associated conical boundary therebetween.
- first or second aspects of the associated internal combustion engine 14 , 14 . 1 , 14 . 2 described hereinabove may be adapted to provide for a wastegate valve 99 to provide for bypassing exhaust gases 21 from the internal combustion engine 14 , 14 . 1 , 14 . 2 around the turbocharger core 10 , i.e. to as to enable some or all of the exhaust gases 21 to flow from the exhaust runners 24 or exhaust manifold 162 to the engine exhaust system 98 without flowing through the turbine 18 .
- the turbine nozzle cartridge assembly 74 provides for readily matching or tuning the turbocharger core 10 to a particular internal combustion engine 14 , 14 . 1 , 14 . 2 , because other components of the turbocharger core 10 —particularly the associated exhaust housing portion 88 of the cylinder head assembly 12 or the associated turbocharger exhaust housing 158 —would not typically need to be modified during that process.
- production versions of the turbocharger core 10 can be adapted to work with relatively smaller clearances between the turbine tip shroud 82 and the tips 120 of the turbine blades 92 without danger of interference therebetween during the operation of the turbocharger core 10 over the life thereof.
- a turbocharger assembly 200 . 2 i usable in cooperation with a second aspect of an internal combustion engine 14 , 14 . 2 comprises a centerbody 33 , a compressor 16 and a turbine 18 .
- the centerbody 33 comprises a bearing housing 38 , at least one bearing 34 , 36 within and operatively coupled to the bearing housing 38 , and a rotor shaft 32 rotationally supported by the at least one bearing 34 . 36 spaced therealong, wherein the rotor shaft 32 is part of an associated turbocharger rotor assembly 31 .
- the compressor 16 of the turbocharger core 10 comprises a compressor rotor 56 —also part of the turbocharger rotor assembly 31 —within an associated compressor housing 142 that is operatively coupled to a forward side 33 . 2 of the centerbody 33 .
- the compressor rotor 56 is operatively coupled to the forward end 32 . 2 of the rotor shaft 32 and adapted to rotate therewith about an axis of rotation 202 ′ of the turbocharger rotor assembly 31 .
- the turbine 18 comprises a turbine rotor 30 —also part of the turbocharger rotor assembly 31 —within an associated turbocharger exhaust housing 158 that is operatively coupled to an aft side 33 . 1 of the centerbody 33 .
- the turbine rotor 30 is operatively coupled to—for example, welded to—the aft end 32 . 1 of the rotor shaft 32 along the periphery of a cavity 60 between the forward end of the turbine rotor 30 and the aft end 32 . 1 of the rotor shaft 32 that provides for reducing heat transfer from the turbine rotor 30 to the rotor shaft 32 .
- An inlet 160 of the turbocharger exhaust housing 158 provides for operatively coupling to, and receiving exhaust gases 21 from, an exhaust manifold 162 of an internal combustion engine 14 , 14 . 2 .
- the inlet 160 of the turbocharger exhaust housing 158 is operatively coupled to the exhaust manifold 162 with a plurality of bolts 164 through a first flange 166 at the outlet 168 of the exhaust manifold 162 into a second flange 170 at the inlet 160 of the turbocharger exhaust housing 158 .
- the inlet 160 is in fluid communication with a first aspect of a volute 204 i in a first aspect of a volute portion 204 i ′ of the turbocharger exhaust housing 158 that provides for discharging exhaust gases 21 onto the turbine rotor 30 .
- At least a portion of an aft boundary 206 i of the volute portion 204 i ′ comprises a surface of revolution 206 i ′ about the axis of rotation 202 of the turbine rotor 30 .
- the aft boundary 206 i is located further from the centerbody 33 than a corresponding opposing forward boundary 207 i of the volute portion 204 i ′.
- the surface of revolution 206 i ′ comprises a planar surface 206 i ′′ that is substantially perpendicular to the axis of rotation 202 ′.
- the exhaust gases 21 are discharged from the outlet 208 of the volute 204 i onto the turbine rotor 30 so as to provide for driving the turbine rotor 30 , which in turn drives the associated turbocharger rotor assembly 31 .
- a portion of the turbine rotor 30 is concentrically surrounded by a shroud portion 210 of the turbocharger exhaust housing 158 , wherein the radius of the shroud portion 210 of the turbocharger exhaust housing 158 exceeds that of the corresponding radius of the turbine rotor 30 by a corresponding tip clearance 212 .
- the efficiency of the turbine 18 is generally improved with decreasing tip clearance 212 as a result of a corresponding associated reduction in exhaust gases 21 bypassing the turbine blades 92 , 92 ′ through the annular region between the tips 120 of the turbine blades 92 , 92 ′ and the shroud portion 210 of the turbocharger exhaust housing 158 .
- the turbocharger exhaust housing 158 comprises a corresponding fluid conduit 216 between the inlet 160 and the outlet 208 thereof, through which the exhaust gases 21 flow, and within which the associated turbine rotor 30 operates.
- a forward end 158 . 2 of the turbocharger exhaust housing 158 incorporates an internal cylindrical surface 218 that mates with a corresponding external cylindrical surface 220 on the aft side 33 . 1 of the centerbody 33 .
- An axis 202 ′′ of the external cylindrical surface 220 is substantially concentric with an axis of rotation 202 ′ of the turbine rotor 30 and with an axis 202 of the internal cylindrical surface 218 .
- the turbocharger exhaust housing 158 is operatively coupled to the centerbody 33 with a plurality of radial pins 222 , each of which extends radially across a junction 224 between the internal 218 and external 220 cylindrical surfaces and engages both the centerbody 33 and a wall 226 of the turbocharger exhaust housing 158 so as to prevent more than insubstantial relative axial movement therebetween.
- Each radial pin 222 is slideably engaged with at least one of a corresponding radial bore 228 in the turbocharger exhaust housing 158 and a corresponding radial bore 228 in the centerbody 33 so that the internal cylindrical surface 218 is free to thermally expand radially relative to the external cylindrical surface 220 .
- the radial bore 228 in the turbocharger exhaust housing 158 is closed to the fluid conduit 216 .
- the plurality of radial pins 222 are arranged around the centerbody 33 so as to provide for the internal 218 and external 220 cylindrical surfaces to remain substantially concentric regardless of a thermal expansion of the turbocharger exhaust housing 158 relative to the centerbody 33 , and so as to provide for the shroud portion 210 of the turbocharger exhaust housing 158 to remain substantially concentric regardless of a thermal expansion of the turbocharger exhaust housing 158 relative to the turbine rotor 30 .
- the diameter 230 of the internal cylindrical surface 218 is less than the diameter 232 of the external cylindrical surface 220 at room temperature so as to provide for an interference fit therebetween in a non-operative state of the turbocharger assembly 200 . 2 i .
- the plurality of radial pins 222 in cooperation with the corresponding plurality of radialbores 228 to provide for a radial thermal expansion of the turbocharger exhaust housing 158 relative to the centerbody 33 that is substantially without constraint other than as to the maintenance of concentricity of the internal 218 and external 220 cylindrical surfaces, the second aspect of the turbocharger assembly 200 .
- the plurality of radial pins 222 may be either symmetrically located or equi-spaced—or both—around the junction 224 between the centerbody 33 and around the associated turbocharger exhaust housing 158 .
- FIG. 21 illustrates a plurality of six radial pins 222 that are equi-spaced from one another and are in a symmetrical arrangement with respect to one another.
- the plurality of radial pins 222 would comprise at least three radial pins 222 .
- exhaust gases 21 from the exhaust manifold 162 flow into the inlet 160 of the turbocharger exhaust housing 158 , through the associated volute 204 i , and then discharge from the outlet 208 thereof onto the turbine blades 92 , 92 ′ of the turbine rotor 30 , thereby driving the turbine rotor 30 that in turn rotates the rotor shaft 32 and the compressor rotor 56 attached thereto.
- the exhaust gases 21 then flow through the shroud portion 210 of the turbocharger exhaust housing 158 before being exhausted through the associated exhaust outlet 214 , and then into the engine exhaust system 98 , which, for example, may include one or more exhaust treatment devices 100 , for example, one or more catalytic converters or mufflers.
- the turbocharger exhaust housing 158 could be constructed of the same type of material, for example cast iron, or alternatively, cast with a relatively-high-nickel-content alloy, as could be used for the exhaust manifold 162 of the internal combustion engine 14 , 14 . 2 .
- the exhaust gases 21 heat the turbocharger exhaust housing 158 upon flowing through the associated fluid conduit 216 thereof, thereby causing the turbocharger exhaust housing 158 to thermally expand relative to the centerbody 33 , thereby causing a gap 234 between the internal 218 and external 220 cylindrical surfaces, the latter of which remain substantially concentric as a result of the constraining action of the radial pins 222 spaced around the junction 224 therebetween, which slide within the corresponding associated radial bores 228 , as illustrated in FIGS. 23 a and 23 b for relatively less thermal expansion and relatively more thermal expansion, respectively.
- each radial pin 222 is slideably engaged with both a first radial bore 228 . 1 in the centerbody 33 , and a second radial bore 228 . 2 in the wall 226 of the turbocharger exhaust housing 158 , so that each radial pin 222 can slide relative to either or both the first 228 . 1 or second 228 . 2 radial bores responsive to a thermal expansion of the turbocharger exhaust housing 158 relative to the centerbody 33 .
- the radial pin 222 could be radially restrained in one of the centerbody 33 and wall 226 of the turbocharger exhaust housing 158 , but slideably engaged with a corresponding radial bore 228 in the other of the centerbody 33 and wall 226 of the turbocharger exhaust housing 158 .
- the radial pin 222 could be installed with an interference fit in the first radial bore 228 . 1 in the centerbody 33 , but slideably engaged in the second radial bore 228 . 2 in the wall 226 of the turbocharger exhaust housing 158 , or the radial pin 222 could be installed with an interference fit in the second radial bore 228 .
- each radial pins 222 ′ incorporates a threaded end portion 236 that engages a corresponding internal thread 238 in the centerbody 33 extending radially inwards from a corresponding radial counterbore 228 . 1 ′ in the centerbody 33 , the latter of which engages the body 239 of the radial pin 222 ′ so as to provide for rotationally aligning the radial counterbores 228 . 1 ′ in the centerbody 33 with the corresponding second radial bores 228 .
- one or more radial pins 222 could be threaded near the corresponding head portion 240 so as to provide for engaging a corresponding threaded, counterbored portion radially outwards of a corresponding second radial bore 228 . 2 in the wall 226 of the turbocharger exhaust housing 158 , wherein the body 239 of the radial pin 222 then is slideably engaged with the first 228 . 1 and second 228 . 2 radial bores for purposes of assembly, and slideably engaged with the first radial bore 228 . 1 in the centerbody 33 during operation of the turbocharger assembly 200 . 2 ii so as to provide for substantially centering the internal 218 and external 220 cylindrical surfaces with respect to one another regardless of thermal expansion of the turbocharger exhaust housing 158 relative to the centerbody 33 .
- each radial pin 222 is slideably engaged with both the first 228 . 1 and second 228 . 2 radial bores at least during assembly, but is retained to the turbocharger assembly 200 . 2 i either by a weld 242 to the turbocharger exhaust housing 158 , or by staking a radially outboard portion 244 of the second radial bore 228 .
- the first embodiment of the associated second aspect of the turbocharger assembly 200 . 2 i further incorporates a seal 246 operative between the centerbody 33 and an end face 248 of the turbocharger exhaust housing 158 —for example, optionally operative within a groove 250 in the end face 248 of the turbocharger exhaust housing 158 —that provides for preventing the exhaust gases 21 from escaping the turbocharger exhaust housing 158 from gaps 234 , 252 between the turbocharger exhaust housing 158 and the centerbody 33 , wherein the seal 246 is configured so as to provide for accommodating thermal expansion or contraction of the turbocharger exhaust housing 158 relative to the centerbody 33 .
- the seal 246 may comprise either a thermal gasket 254 —for example, as illustrated in FIGS.
- a metallic seal 256 for example, comprising a radial cross-section selected from the group consisting of a V-shaped cross-section 258 and a first aspect of a C-shaped cross-section 260 ′, for example, as illustrated in FIGS. 25 and 26 , respectively for the third and fourth embodiments of the associated second aspect of the turbocharger assembly 200 . 2 iii , 200 . 2 iv , respectively, wherein the associated seals 246 are operative across an axial gap 252 .
- the associated seals 246 are operative across an axial gap 252 .
- the external cylindrical surface 220 is stepped into a corresponding side 33 . 1 of the centerbody 33 , and the seal 246 is operative between the end face 248 and a radial surface 262 extending radially outwards from the external cylindrical surface 220 stepped into the corresponding side 33 .
- V-shaped cross-section 258 and the first aspect of the C-shaped cross-section 260 metallic seals 256 have associated sealing surfaces and are oriented so that these sealing surfaces are axially spring-biased respectively against the associated radial surface 262 of the centerbody 33 and the associated end face 248 of the turbocharger exhaust housing 158 so as to provide for sealing the gap 252 therebetween while also providing for a radial movement of the end face 248 relative to the radial surface 262 responsive to a thermal expansion or contraction of the of the turbocharger exhaust housing 158 relative to the centerbody 33 .
- a fifth embodiment of the second aspect of a turbocharger assembly 200 . 2 v the seal 246 is operative across a radial gap 234 between the centerbody 33 and the turbocharger exhaust housing 158 , for example, by incorporating a metallic seal 256 incorporating a second aspect of a C-shaped cross-section 260 ′′ that is oriented so that the associated sealing surfaces are radially spring-biased respectively against an the external cylindrical surface 220 of the centerbody 33 and an associated internal cylindrical surface 263 of an associated counterbore 265 at the forward end 158 .
- turbocharger exhaust housing 158 so as to provide for sealing the associated radial gap 234 ′ therebetween regardless of a radial movement of the end face 248 relative to the radial surface 262 responsive to a thermal expansion or contraction of the of the turbocharger exhaust housing 158 relative to the centerbody 33 .
- the plurality of radial bores 228 are match-drilled through the wall 226 and internal cylindrical surface 218 of the turbocharger exhaust housing 158 , through the external cylindrical surface 220 of the centerbody 33 , and into the centerbody 33 after fully sliding the internal cylindrical surface 218 of the turbocharger exhaust housing 158 onto the external cylindrical surface 220 of the centerbody 33 with sufficient force to compress the seal 246 sufficiently enough to provide for sealing the end face 248 of the turbocharger exhaust housing 158 against the corresponding radial surface 262 of the centerbody 33 under all subsequent anticipated operating conditions for the design life of the turbocharger assembly 200 . 2 .
- the use of the plurality of radial pins 222 in cooperation with the corresponding plurality of associated radial bores 228 to operatively couple the turbocharger exhaust housing 158 to the centerbody 33 for example, rather than a V-clamp as might be used in a conventional turbocharger—provides for locating the associated volute 204 i forward of an aft boundary 206 i of an outlet 208 thereof onto the bladed rotor 30 so as to provide for a direction of flow 264 of the exhaust gases 21 onto the bladed rotor 30 that is either substantially radially inwards or at least partially axially aftward from the centerbody 33 with decreasing distance from the bladed rotor 30 .
- a heat shield 266 is operative between the centerbody 33 and the turbine rotor 30 within an axial bore 268 in the turbocharger exhaust housing 158 , wherein the axial bore 268 has a diameter in excess of a maximum diameter of the turbine rotor 30 so as to provide for assembling the turbocharger exhaust housing 158 over the turbine rotor 30 , the latter of which is preassembled as part of the centerbody 33 .
- An outer rim 270 of the heat shield 266 is retained axially between the centerbody 33 and the turbocharger exhaust housing 158 , and is keyed to the centerbody 33 with an axial pin 272 extending therefrom through a corresponding axial hole 274 through the outer rim 270 of the heat shield 266 —so as to prevent a rotation of the heat shield 266 —and, in one embodiment, into an axial bore 276 in a corresponding forward portion 278 of the turbocharger exhaust housing 158 so as to provide for roughly aligning the turbocharger exhaust housing 158 with the centerbody 33 during assembly, wherein the radial clearance around the axial pin 272 within the axial bore 276 in the corresponding forward portion 278 of the turbocharger exhaust housing 158 is sufficient so as to not interfere with a thermal expansion of the internal cylindrical surface 218 of the turbocharger exhaust housing 158 relative to the centerbody 33 .
- a sixth embodiment of the second aspect of a turbocharger assembly 200 . 2 vi incorporates a second aspect of a volute 204 ii and associated second aspect of the volute portion 204 i ′ of the turbocharger exhaust housing 158 —but is otherwise similar to the first aspect of the turbocharger assembly 200 . 2 i described hereinabove—wherein at least a portion of a forward boundary 207 ii of the volute portion 204 i ′ comprises a surface of revolution 207 ii ′ about the axis of rotation 202 of the turbine rotor 30 .
- a corresponding opposing aft boundary 206 ii is located further from the centerbody 33 than the forward boundary 207 ii of the volute portion 204 ii ′.
- the surface of revolution 207 ii ′ comprises a planar surface 207 i ′′ that is substantially perpendicular to the axis of rotation 202 .
- the exhaust gases 21 are discharged from the outlet 208 of the volute 204 i onto the turbine rotor 30 so as to provide for driving the turbine rotor 30 , which in turn drives the associated turbocharger rotor assembly 31 .
- compressor housing 142 of the associated compressor 16 of the turbocharger assembly 200 . 2 could also be operatively coupled to the centerbody 33 with a plurality of radial pins 222 in cooperation with a corresponding plurality of associated radial bores 228 similarly as described hereinabove for the turbine 18 of the turbocharger assembly 200 . 2 .
- turbomachines for example, superchargers, turbines, pumps, or compressors, so as to provide for maintaining the concentricity of an associated fluid-conduit housing 74 , 74 ′, 142 , 158 with respect to a centerbody 33 so as to provide for provide for maintaining the concentricity of a shroud portion 82 , 82 ′, 210 of the fluid-conduit housing 74 , 74 ′, 142 , 158 with respect to a corresponding bladed rotor 30 , 56 regardless of a thermal expansion of the fluid-conduit housing 74 , 74 ′, 142 , 158 with respect to the centerbody 33 , wherein the term fluid is intended to include gases, vapors and liquids, and the associated fluid 21 flows either entirely within the associated fluid-conduit housing 142 , 158 , or within the fluid-conduit housing 74 , 74 ′ that in turn is operative within another fluid-conduit housing 20
- a turbomachine apparatus comprises a centerbody 33 , at least one bladed rotor 30 , 56 and at least one fluid-conduit housing 74 , 74 ′, 142 , 158 in cooperation therewith.
- the centerbody 33 comprises a bearing housing 38 , at least one bearing 34 , 36 within and operatively coupled to the bearing housing 38 ; and a rotor shaft 32 rotationally supported by the at least one bearing 34 , 36 spaced along the rotor shaft 32 .
- the at least one bladed rotor 30 , 56 is operatively coupled to the rotor shaft 32 supported by the centerbody 33 .
- Each bladed rotor 30 , 56 is operative within a corresponding fluid conduit 216 defined by the fluid-conduit housing 74 , 74 ′, 142 , 158 .
- the at least one fluid-conduit housing 74 , 74 ′, 142 , 158 incorporates an inlet 144 , 160 to provide for receiving a corresponding fluid 21 within the fluid conduit 216 that provides for either driving or being driven, pumped or compressed by a corresponding bladed rotor 30 , 56 responsive to an interaction of the corresponding fluid 21 with a plurality of blades 92 , 92 ′ of the bladed rotor 30 , 56 .
- the at least one fluid-conduit housing 74 , 74 ′, 142 , 158 comprises an internal cylindrical surface 110 , 218 at an end 158 . 2 thereof that mates with a corresponding external cylindrical surface 112 , 220 on a corresponding side 33 . 1 of the centerbody 33 .
- An axis 202 ′′ of the external cylindrical surface 112 , 220 is substantially concentric with an axis of rotation 202 ′ of the bladed rotor 30 , 56 and with an axis 202 of the internal cylindrical surface 110 , 218 .
- the fluid-conduit housing 74 , 74 ′, 142 , 158 is operatively coupled to the centerbody 33 with a plurality of radial pins 114 , 222 , so that the internal cylindrical surface 110 , 218 is free to thermally expand relative to the external cylindrical surface 112 , 220 , each radial pin 114 , 222 of the plurality of radial pins 114 , 222 being slideably engaged with at least one of a corresponding radial bore 116 , 228 , 228 . 2 in the fluid-conduit housing 74 , 74 ′, 142 , 158 and a corresponding radial bore 118 , 228 , 228 . 1 in the centerbody 33 .
- the radial bore 228 , 228 . 2 in the fluid-conduit housing 142 , 158 is closed to the fluid conduit 216 .
- Each the radial pin 114 , 222 is oriented radially with respect to both the internal cylindrical surface 110 , 218 and the external cylindrical surface 112 , 220 .
- the plurality of radial pins 114 , 222 are arranged around the centerbody 33 so as to provide for the internal 110 , 218 and external 112 , 220 cylindrical surfaces to remain substantially concentric regardless of a thermal expansion of the fluid-conduit housing 74 , 74 ′, 142 , 158 relative to the centerbody 33 , and at least a portion of the fluid-conduit housing 74 , 74 ′, 142 , 158 comprises a shroud portion 82 , 82 ′, 210 that substantially concentrically surrounds a portion of the bladed rotor 30 , 56 .
- the internal 110 , 218 and external 112 , 220 cylindrical surfaces are mated with an interference fit at room temperature.
- the plurality of radial pins 114 , 222 are either substantially symmetrically located or substantially equi-spaced—or both—around the centerbody 33 and around the associated fluid-conduit housing 74 , 74 ′, 142 , 158 .
- the plurality of radial pins 114 , 222 comprise at least three radial pins 114 , 222 .
- At least one the radial pin 114 , 222 is slideably engaged with both the corresponding radial bore 116 , 228 , 228 . 2 in the at least one fluid-conduit housing 74 , 74 ′, 142 , 158 and the corresponding radial bore 118 , 228 , 228 . 1 in the centerbody 33 .
- the radial pins 114 , 222 are retained in cooperation with both the centerbody 33 and the corresponding fluid-conduit housing 74 , 74 ′, 142 , 158 , for example, by either staking or welding 242 to the fluid-conduit housing 142 , 158 , by an interference fit in the radial bore 228 , 228 . 1 , 228 . 2 in either the fluid-conduit housing 142 , 158 or centerbody 33 , or by engagement of a screw thread portion 236 of the radial pin 114 , 222 with a corresponding screw thread portion in one of the fluid-conduit housing 142 , 158 and the centerbody 33 .
- the at least one bladed rotor 30 , 56 comprises at least one of the group selected from a bladed compressor rotor 56 and a turbine rotor 30 , for example, the compressor rotor 56 of a compressor 16 portion of a turbocharger assembly 200 . 2 or a compressor portion of a supercharger, and/or the turbine rotor 30 of turbine 18 a turbocharger assembly 200 . 2 .
- a minimum tip clearance 212 between the shroud portion 82 , 82 ′, 210 of the fluid-conduit housing 74 , 74 ′, 142 , 158 and at least one tip 120 of the at least one bladed rotor 30 , 56 is less than 4 percent of a radius of the at least one bladed rotor 30 , 56 at the at least one tip 120 of the bladed rotor 30 , 56 at a location of minimum tip clearance 212 to the shroud portion 82 , 82 ′, 210 of the fluid-conduit housing 74 , 74 ′, 142 , 158 .
- the bladed rotor 30 comprises the turbine rotor 30 of the turbocharger assembly 200 .
- the fluid-conduit housing 158 comprises an turbocharger exhaust housing 158 configured to receive exhaust gases 21 from an internal combustion engine 14 , 14 . 2
- a portion of the turbocharger exhaust housing 158 comprises the shroud portion 210 that substantially concentrically surrounds the portion of the turbine rotor 30 .
- the turbocharger exhaust housing 158 comprises a volute portion 204 i ′ of the fluid conduit 216 that is operative between the inlet 160 and the turbine rotor 30 , at least a portion of an aft boundary 206 i of the volute portion 204 i ′ comprises a surface of revolution 206 i ′ about the axis of rotation 202 ′ of the turbine rotor 30 where the fluid 21 is discharged from the volute portion 204 i ′ onto the turbine rotor 30 during operation of the turbocharger assembly 200 . 2 , and the aft boundary 206 i is located further from the centerbody 33 than a corresponding opposing forward boundary 207 i of the volute portion 204 i ′.
- the surface of revolution 206 i ′ comprises a planar surface that is substantially perpendicular to the axis of rotation 202 .
- Each radial pin 222 being slideable in at least one of a corresponding radial bore 228 in the turbocharger exhaust housing 158 and a corresponding radial bore 228 in the centerbody 33 provides for maintaining the concentricity of the shroud portion 210 of the turbocharger exhaust housing 158 relative to the turbine rotor 30 regardless of thermal expansion of the turbocharger exhaust housing 158 relative to the centerbody 33 , so that at room temperature, the tip clearance 212 between the shroud portion 210 of the turbocharger exhaust housing 158 and at least one tip 120 of the turbine rotor 30 at an aft portion thereof can be less than 4 percent of a radius of the turbine rotor 30 at the at least one tip 120 of the turbine rotor 30 at the aft portion thereof.
- the seal 246 may comprise either a thermal gasket 254 , or a metallic seal 256 , for example, comprising a radial cross-section selected from the group consisting of a V-shaped cross-section 258 and a C-shaped cross-section 260 .
- the external cylindrical surface 220 is stepped into the corresponding side 33 . 1 of the centerbody 33
- the seal 246 is operative between the end face 248 and a radial surface 262 extending radially outwards from the external cylindrical surface 220 that is stepped into the corresponding side 33 . 1 of the centerbody 33 .
- a heat shield 266 is operative between the centerbody 33 and the turbine rotor 30 within an axial bore 268 in the turbocharger exhaust housing 158 , wherein the axial bore 268 has a diameter in excess of a maximum diameter of the turbine rotor 30 .
- the at least one bladed rotor 56 comprises the bladed compressor rotor 56 and the at least one fluid-conduit housing 142 comprises a compressor housing 142 surrounding the compressor rotor 56 , wherein the compressor housing 142 comprises central inlet 144 and a volute diffuser 146 .
- a method of operatively coupling a fluid-conduit housing 74 , 74 ′, 142 , 158 to a centerbody 33 comprises:
- the method further comprises forming at least one of the corresponding radial bore 116 , 228 , 228 . 2 in the fluid-conduit housing 74 , 74 ′, 142 , 158 and the corresponding radial bore 118 , 228 , 228 . 1 in the centerbody 33 after the operation of sliding the internal cylindrical surface 110 , 218 over the corresponding external cylindrical surface 112 , 220 .
- the method further comprising providing a volute portion 204 i ′ of a fluid conduit 216 within the fluid-conduit housing 142 , 158 that extends forward of an aft boundary 206 i of an outlet 208 of the fluid conduit 216 onto the bladed rotor 30 so as to provide for either a) a nominal direction of flow 264 of a fluid 21 onto or from the bladed rotor 30 that is substantially radial, b) for flow onto the bladed rotor 30 , a nominal direction of flow 264 of a fluid 21 that is at least partially axially aftward relative to the centerbody 33 with decreasing distance from the bladed rotor 30 or, c) for flow from the bladed rotor 30 , a nominal direction of flow 264 of a fluid 21 that is at least partially axially forward relative to the centerbody 33 with increasing distance from the bladed rotor 30 .
- a method of operating a bladed rotor 30 , 56 in cooperation with an associated fluid-conduit housing 74 , 74 ′, 142 , 158 , comprises
- the fluid-conduit housing 158 comprises an turbocharger exhaust housing 158 of the turbocharger assembly 200 . 2
- the bladed rotor 30 comprises a turbine rotor 30 of a turbocharger assembly 200 . 2 driven by exhaust gases 21 of an internal combustion engine 14 , 14 .
- the fluid-conduit housing 142 comprises a compressor housing 142 of a turbocharger assembly 200 . 2
- the bladed rotor 56 comprises a compressor rotor 56 of the turbocharger assembly 200 . 2 that provides for compressing and pumping air into a portion of a fluid conduit 216 within the compressor housing 142 and then into an internal combustion engine 14 , 14 . 2 .
- any reference herein to the term “or” is intended to mean an “inclusive or” or what is also known as a “logical OR”, wherein when used as a logic statement, the expression “A or B” is true if either A or B is true, or if both A and B are true, and when used as a list of elements, the expression “A, B or C” is intended to include all combinations of the elements recited in the expression, for example, any of the elements selected from the group consisting of A, B, C, (A, B), (A, C), (B, C), and (A, B, C); and so on if additional elements are listed.
- indefinite articles “a” or “an” and the corresponding associated definite articles “the’ or “said”, are each intended to mean one or more unless otherwise stated, implied, or physically impossible.
- expressions “at least one of A and B, etc.”, “at least one of A or B, etc.”, “selected from A and B, etc.” and “selected from A or B, etc.” are each intended to mean either any recited element individually or any combination of two or more elements, for example, any of the elements from the group consisting of “A”, “B”, and “A AND B together”, etc.
Abstract
A shroud portion of a fluid-conduit housing provides for concentrically shrouding a portion of bladed rotor operatively coupled to a rotor shaft rotationally supported by at least one bearing operatively coupled to the centerbody. An internal cylindrical surface at an end of the fluid-conduit housing mates with a corresponding external cylindrical surface on a corresponding side of the centerbody. The fluid-conduit housing is operatively coupled to the centerbody with a plurality of radial pins, wherein each radial pin slideably engages with at least one of a corresponding radial bore in the fluid-conduit housing or a corresponding radial bore in the centerbody so as to provide for substantially maintaining the concentricity of the shroud portion of the fluid-conduit housing relative to the bladed rotor regardless of a thermal expansion of the fluid-conduit housing relative to the centerbody.
Description
- The instant application claims the benefit of prior U.S. Provisional Application Ser. No. 61/501,891 filed on 28 Jun. 2011, which is incorporated by reference herein in its entirety.
- In the accompanying drawings:
-
FIG. 1 illustrates an isometric view of a first aspect of an internal combustion engine comprising a pair of cylinder heads and a corresponding pair of turbocharger cores integrated therewith; -
FIG. 2 illustrates an isometric view of a cylinder head and turbocharger core from the first aspect of an internal combustion engine illustrated inFIG. 1 ; -
FIG. 3 illustrates first cross-sectional view through the cylinder head and turbocharger core illustrated inFIG. 2 ; -
FIG. 4 illustrates an isometric view of the turbocharger core as used in the embodiments illustrated inFIGS. 1-3 ; -
FIG. 5 illustrates an isometric view of a nozzle cartridge assembly from the turbocharger core illustrated inFIG. 2 ; -
FIG. 6 illustrates a second cross-sectional view through the cylinder head and turbocharger core illustrated inFIG. 2 ; -
FIG. 7 illustrates a transverse cross-sectional view through a turbine nozzle portion of the turbocharger core illustrated inFIG. 4 ; -
FIG. 8 illustrates a transverse cross-sectional view through a bearing housing portion of the turbocharger core illustrated inFIG. 4 ; -
FIG. 9 illustrates third cross-sectional view through the cylinder head and turbocharger core illustrated inFIG. 2 ; -
FIG. 10 illustrates an expanded view of a portion of the third cross-sectional view through the cylinder head and turbocharger core illustrated inFIG. 9 ; -
FIG. 11 illustrates a schematic view of a first alternative embodiment of an interface of a plurality of exhaust runners from each of a plurality of cylinders with a cavity in a cylinder head adapted to receive a turbocharger core; -
FIG. 12 illustrates a schematic view of a second alternative embodiment of an interface of a plurality of exhaust runners from each of a plurality of cylinders with a cavity in a cylinder head adapted to receive a turbocharger core; -
FIG. 13 illustrates an isometric view of a portion of a second aspect of an internal combustion engine incorporating a first embodiment of a first aspect of a turbocharger assembly operatively coupled to an associated exhaust manifold; -
FIG. 14 illustrates an exploded view of portions of the first embodiment of the first aspect of the turbocharger assembly and associated housing used with the second aspect of the internal combustion engine illustrated inFIG. 13 ; -
FIG. 15 illustrates a longitudinal cross-sectional exploded view of the first embodiment of the first aspect of the turbocharger assembly and associated housing used with the second aspect of the internal combustion engine illustrated inFIG. 13 ; -
FIG. 16 illustrates a fragmentary longitudinal cross-sectional view of a second embodiment of the first aspect of a turbocharger assembly in accordance with the second aspect an internal combustion engine; -
FIG. 17 illustrates a transverse cross-sectional view of the second embodiment of the first aspect of the turbocharger assembly illustrated inFIG. 16 ; -
FIG. 18 illustrates a third embodiment of the first aspect of a turbocharger assembly incorporating a second aspect of an associated turbocharger core having an associated radial-flow turbine, in accordance with the second aspect of an internal combustion engine; -
FIG. 19 illustrates an isometric partially exploded view of a first embodiment of a second aspect of a turbocharger assembly useable with the second aspect an internal combustion engine, illustrating a first embodiment of associated radial pins that provide for coupling the associated exhaust housing to the associated centerbody, and that provide for maintaining a concentricity the exhaust housing relative to the centerbody of the turbocharger assembly; -
FIG. 20 illustrates a portion of a longitudinal cross-section of the first embodiment of a second aspect of a turbocharger assembly illustrated inFIG. 19 , illustrating a corresponding turbine portion in relation to the corresponding centerbody portion; -
FIG. 21 illustrates an aft-looking radial cross-section of the first embodiment of the second aspect of a turbocharger assembly illustrated inFIGS. 19 and 20 through a transverse plane intersecting the centers of a plurality of associated radial pins; -
FIG. 22 illustrates a fragmentary longitudinal cross-section of the first embodiment of the second aspect of a turbocharger assembly illustrated inFIGS. 19-21 , illustrating a first embodiment of an associated seal between the centerbody and exhaust housing of the turbocharger assembly; -
FIGS. 23 a and 23 b schematically illustrate a thermal expansion of an internal cylindrical surface of an exhaust housing relative to an external cylindrical surface of a centerbody, illustrating the plurality of associate radial pins maintaining the relative concentricity of the internal and external cylindrical surfaces for two different conditions of relative thermal expansion; -
FIG. 24 illustrates a forward-looking radial cross-section of a second embodiment of the second aspect of a turbocharger assembly similar to that illustrated inFIG. 19 , through a transverse plane intersecting the centers of a plurality of associated radial pins, for a second embodiment of the radial pins; -
FIG. 25 illustrates a fragmentary longitudinal cross-section of a third embodiment of the second aspect of a turbocharger assembly similar to that illustrated inFIG. 19 , illustrating a second embodiment of the associated seal between the centerbody and exhaust housing of the turbocharger assembly; -
FIG. 26 illustrates a fragmentary longitudinal cross-section of a fourth embodiment of the second aspect of a turbocharger assembly similar to that illustrated inFIG. 19 , illustrating a third embodiment of the associated seal between the centerbody and exhaust housing of the turbocharger assembly; -
FIG. 27 illustrates a fragmentary longitudinal cross-section of a fifth embodiment of the second aspect of a turbocharger assembly similar to that illustrated inFIG. 19 , illustrating a fourth embodiment of the associated seal between the centerbody and exhaust housing of the turbocharger assembly; and -
FIG. 28 illustrates a fragmentary longitudinal cross-section of a sixth embodiment of the second aspect of a turbocharger assembly, illustrating a second aspect of an associated volute portion of the exhaust housing of the turbocharger assembly. - Referring to
FIG. 1 , a pair ofturbocharger cores 10 are integrated with a corresponding pair ofcylinder head assemblies 12 of a first aspect of an internal combustion engine 14, 14.1 of a V-type configuration, for example, a V-6 internal combustion engine 14, 14.1′. For example, the internal combustion engine 14, 14.1 can be any of a variety of designs operating on one or more of a variety of types of fuels, including but not limited to gasoline, diesel, bio-diesel, natural gas, including LNG and CNG, propane including LP gas, ethanol or methanol, in accordance with any one of a variety of thermodynamic cycles, including, but not limited to, for example, the Otto cycle, the Diesel cycle, the Atkinson cycle, the Miller cycle or a two-stroke cycle. Referring also toFIGS. 2-10 , eachturbocharger core 10 comprises acompressor 16 driven by an exhaust-poweredturbine 18, wherein when theturbocharger core 10 is attached to the internal combustion engine 14, 14.1, for example, through an intercooler, each associatedturbine 18 is inserted in and cooperates with acavity 20, for example, acylindrical cavity 20′ or avolute cavity 20″, in the correspondingcylinder head assembly 12 adapted to receiveexhaust gases 21 from the associated cylinder orcylinders 22 associated therewith via associatedexhaust runners 24. For example, theturbocharger core 10 incorporates an axial-flow turbine 18, which can be configured with a relatively low associated moment of inertia so as to provide for a relatively rapid dynamic response to changes in the associated operating condition of the internal combustion engine 14, 14.1. In the first aspect of the internal combustion engine 14, 14.1, theexhaust runners 24 from eachcylinder 22 communicate with a commonfirst exhaust port 26 in the side of thecavity 20 at a location off-axis relative to thecentral axis 28 of thecavity 20 so as to induce a circulation of theexhaust gases 21 flowing thereinto. - The
turbocharger core 10 comprises aturbine rotor 30 of aturbocharger rotor assembly 31 operatively coupled to an aft end 32.1 of arotor shaft 32 of theturbocharger rotor assembly 31 that is rotationally supported by rotorshaft support assembly 33, also known as acenterbody 33, comprising an aft journal bearing 34 and a forward rolling element bearing 36 located within an associated bearinghousing 38 and spaced apart from one another along therotor shaft 32. The bearinghousing 38 incorporates acooling jacket 40 therewithin in fluid communication withinlet 42 andoutlet 44 ports that are adapted to receive a flow of cooling water from thewater cooling system 46 of the internal combustion engine 14, 14.1 and thereby provide for cooling the aft journal bearing 34 and the forward rolling element bearing 36, wherein one set ofinlet 42 andoutlet 44 ports is used for one side of the internal combustion engine 14, 14.1, and the other one set ofinlet 42′ andoutlet 44′ ports is used for the other side of the internal combustion engine 14, 14.1, with the unused set ofinlet 42′, 42 andoutlet 44′, 44 ports on either side being plugged. Anoil inlet port 48 is adapted to receive a supply of pressurized engine oil from an oil pump of the internal combustion engine 14, 14.1 and distribute this oil to the aft journal bearing 34 and the forward rolling element bearing 36 via associatedoil distribution passages 50. Oil draining from aft journal bearing 34 and the forward rolling element bearing 36 is gravity collected in anoil scavenge cavity 52 within the base of thebearing housing 38, and is returned to the internal combustion engine 14, 14.1 via an associated oil scavenge line 54 (illustrated inFIG. 13 ) connected to an associatedoil scavenge port 54′ at the base of the bearinghousing 38. - It should be understood that the rotor
shaft support assembly 33 is not limited to the combination of an aft journal bearing 34 and a forward rolling element bearing 36, but the rotorshaft support assembly 33 could alternatively comprise any combination of journal and rolling element bearings, or conceivably a single extended-length journal bearing. - The
compressor 16 of theturbocharger core 10 comprises acompressor rotor 56 of theturbocharger rotor assembly 31 operatively coupled to the forward end 32.2 of therotor shaft 32 and adapted to rotate therewith about acentral axis 28′ of theturbocharger core 10, which is substantially aligned with thecentral axis 28 of thecavity 20. For example, in one embodiment, thecompressor rotor 56—in accordance with what is known as a boreless hub,—incorporates an aftward extending internally threadedboss 58 that threads onto the forward end 32.2 of therotor shaft 32, and theturbine rotor 30 is welded to the aft end 32.1 of therotor shaft 32 along the periphery of acavity 60 between the forward end of theturbine rotor 30 and the aft end 32.1 of therotor shaft 32 that provides for reducing heat transfer from theturbine rotor 30 to therotor shaft 32. The forward rolling element bearing 36 comprises anouter race 62 and forward 64 andaft 66 inner races located on therotor shaft 32 between a shoulder 32.3 and thecompressor rotor 56, which provides for positioning therotor shaft 32 within thebearing housing 38. The bearinghousing 38 incorporates forward 70 andaft 72 seals that provide for preventing leakage of oil from thebearing housing 38 into either theturbine 18 orcompressor 16 of theturbocharger core 10. - Referring to
FIGS. 4 , 5 6 and 8-10, theturbocharger core 10 further comprises a turbinenozzle cartridge assembly 74 operatively coupled to the aft side 38.1 of the bearinghousing 38. The turbinenozzle cartridge assembly 74 comprises aforward nozzle wall 76, anaft nozzle wall 78 aftwardly separated therefrom, a plurality ofvanes 80 disposed between the forward 76 andaft 78 nozzle walls, a turbinerotor shroud portion 82 extending aftward from theaft nozzle wall 78, and anozzle exhaust portion 84 extending aftward from thethroat portion 82. Although thenozzle exhaust portion 84 is illustrated with a relatively expanded diameter so as to provide for at least partially diffusing the associated exhaust gases, thenozzle exhaust portion 84 need not necessarily be relatively expanded in diameter relative to the associated turbinerotor shroud portion 82. - For example, in one embodiment, the
forward nozzle wall 76 is formed as a first sheet metal element and the combination of theaft nozzle wall 78 andturbine rotor shroud 82 andnozzle exhaust 84 portions is formed as a second sheet metal element,—for example, each by stamping or spinning;—and thevanes 80 are each formed from sheet metal—, for example, by stamping,—and inserted in and then welded or brazed to a plurality ofcorresponding slots 86 in each of the forward 76 andaft 78 nozzle walls. In another embodiment, theaft nozzle wall 78, the turbinerotor shroud portion 82 and thenozzle exhaust portion 84 are each formed from two or more separate sheet metal pieces that that are then joined together, for example, by welding, brazing and/or by press-fitting. Alternatively, the turbinenozzle cartridge assembly 74 may be cast or sintered, for example, laser sintered. The turbinenozzle cartridge assembly 74 is constructed of a material that can withstand hightemperature exhaust gases 21, for example, of a nickel alloy, for example, stainless steel with a relatively high nickel content, for example, 310 stainless steel, that provides for high temperature oxidation resistance and strength. The remainder of theturbocharger core 10—being either water- or oil-cooled,—can be constructed of less exotic and more economical materials, such as aluminum or cast iron. For example, in addition to the water-cooled bearinghousing 38, thecylinder head assembly 12 may be adapted with water cooling passages in thermal communication with theexhaust housing portion 88 thereof so as to provide using relatively low-cost materials, such as aluminum, for the construction thereof. Accordingly, the separate turbinenozzle cartridge assembly 74 of theturbocharger core 10 provides for an overall more economical use of high-temperature-tolerant materials—for example, limited to the turbinenozzle cartridge assembly 74—than would otherwise be possible, and also provides for integrating theturbocharger core 10 into thecylinder head assembly 12. For example, the combined amount of raw material needed to make the turbinenozzle cartridge assembly 74 and the relatively more simple associatedexhaust housing portion 88 of thecylinder head assembly 12 would be less than the amount of material needed to make an equivalent conventional turbocharger exhaust housing. - In yet another embodiment, the turbine
rotor shroud portion 82 of the turbinenozzle cartridge assembly 74 is reinforced with acontainment sleeve 90 that provides for containing theturbine rotor 30 in the event of a failure of the associatedturbine blades 92 thereof. - The turbine
nozzle cartridge assembly 74 extends through thecavity cylinder head assembly 12. In operation,exhaust gases 21 from the cylinder orcylinders 22 flow through the associatedexhaust runners 24 into thefirst exhaust port 26, i.e. a cavityinlet exhaust port 26, leading into thecavity first exhaust port 26 relative to thecavity exhaust gases 21 flowing within thecavity exhaust gases 21 then flow with swirl into theperipheral inlet 93 of the turbinenozzle cartridge assembly 74 along thevanes 80 thereof, and against theturbine blades 92 of theturbine rotor 30, thereby driving theturbine rotor 30 that in turn rotates therotor shaft 32 and thecompressor rotor 56 attached thereto. Theexhaust gases 21 then flow through thenozzle exhaust portion 84 of the turbinenozzle cartridge assembly 74 before being exhausted into and through asecond exhaust port 94, i.e. a cavityoutlet exhaust port 94, that extends from acounterbore 96 in the aft end 20.1 of thecavity second exhaust port 94 is connected to theengine exhaust system 98, which, for example, may include one or more exhaust treatment devices 100, for example, one or more catalytic converters or mufflers. Thecylinder head assembly 12 can incorporate awastegate valve 99 operative between anexhaust runner 24 and thesecond exhaust port 94 so as to provide for bypassingexhaust gases 21 directly to theengine exhaust system 98 without first flowing through the turbinenozzle cartridge assembly 74 and associatedturbine rotor 30. Accordingly, the forward 76 and aft 78 nozzle walls of the turbinenozzle cartridge assembly 74 redirect and accelerate the circumferentially swirlingexhaust gases 21—flowing within thecavity nozzle cartridge assembly 74—radially inward and axially aftward, and the resulting axially-aftward-flowingswirling exhaust gases 21 then impinge upon theturbine blades 92 of theturbine rotor 30, thereby driving theturbine rotor 30, wherein in one embodiment, the associatedvanes 80 in cooperation with the forward 76 and aft 78 nozzle walls are adapted to provide for the proper vector orientation of the impingingexhaust gases 21 relative to theturbine rotor 30 so as to maximize the efficiency of theturbine 18. - The aft end 84.1 of the
nozzle exhaust portion 84 of the turbinenozzle cartridge assembly 74 incorporates anexternal sealing surface 102 that cooperates with aseal ring 104—for example, a piston-ring-type seal ring 104″—located in aninternal groove 106 in thecounterbore 96 so as to provide for sealing thedischarge end 108 of the turbinenozzle cartridge assembly 74 to theexhaust housing portion 88 of thecylinder head assembly 12 so that substantially all of theexhaust gases 21 are discharged from the turbinenozzle cartridge assembly 74 into and through thesecond exhaust port 94 and into the associatedengine exhaust system 98, thereby substantially isolating theexhaust gases 21 in thecavity nozzle cartridge assembly 74 from theexhaust gases 21 discharged from the turbinenozzle cartridge assembly 74. Theseal ring 104 in cooperation with theexternal sealing surface 102 provides for enabling discharge end 108 of the turbinenozzle cartridge assembly 74 to both slide in an axial direction and expand or contract in a radial direction, responsive to thermally-induced expansion or contraction thereof, while maintaining the sealing condition at thedischarge end 108 of the turbinenozzle cartridge assembly 74, without substantial associated thermally-induced loading of the turbinenozzle cartridge assembly 74. - The forward end 76.2 of the
forward nozzle wall 76 comprises acylindrical lip 110 that fits over a correspondingcylindrical step 112 that extends aftwardly from the aft side 38.1 of the bearinghousing 38. The turbinenozzle cartridge assembly 74 is retained on the bearinghousing 38 by a plurality ofradial pins 114 that extend through correspondingradial holes 116 in thecylindrical lip 110 and into corresponding blindradial holes 118 in thecylindrical step 112. The radial pins 114 and associatedradial holes cylindrical lip 110 and thecylindrical step 112. The inside diameter of thecylindrical lip 110 and the outside diameter of thecylindrical step 112 may be adapted so that at ambient temperature, thecylindrical lip 110 has an interference fit with thecylindrical step 112. However, at elevated operating temperatures, theforward nozzle wall 76 and associatedcylindrical lip 110 are free to thermally expand relative tocylindrical step 112 responsive to differences in temperature or thermal expansion rates of theforward nozzle wall 76 and bearinghousing 38, respectively, in which case, the engagement of thecylindrical lip 110 by the radial pins 114 provides for retaining the turbinenozzle cartridge assembly 74 to the bearinghousing 38, and the symmetric arrangement of the associatedradial pins 114 and associatedradial holes nozzle cartridge assembly 74 substantially concentric with thecentral axis 28″ of theturbocharger core 10 over the thermal operating range thereof. For example, during normal operation, the turbinenozzle cartridge assembly 74 would heat up relatively more quickly, and to a substantially higher temperature, than the bearinghousing 38, and as a result the inside diameter of thecylindrical lip 110 would typically expand so as to be greater than the outside diameter of thecylindrical step 112, so as to transition from a possible interference at ambient temperature to a substantially loose fit at elevated temperatures, under which circumstances, the radial pins 114 would provide for symmetrically and concentrically retaining thecylindrical lip 110 on thecylindrical step 112, so as to preserve the relative alignment of the turbinenozzle cartridge assembly 74 with the associatedturbine rotor 30. - Alternatively, the forward end 76.2 of the
forward nozzle wall 76 can be centered on the bearinghousing 38 with a plurality of aftwardly-extending axial pins or bolts extending from the aft side 38.1 of the bearinghousing 38 through corresponding radial slots in the forward end 76.2 of theforward nozzle wall 76, and retained on the bearinghousing 38 either by the bolts or by a step in the forward end of thecavity 20. - When the turbine
nozzle cartridge assembly 74 is assembled to the bearinghousing 38, theturbine blades 92 of theturbine rotor 30 are located within the turbinerotor shroud portion 82 of the turbinenozzle cartridge assembly 74, which turbinerotor shroud portion 82 accordingly functions as aturbine tip shroud 82′, wherein the inside diameter of theturbine tip shroud 82′ is adapted to provide for about 0.01 inch oftip clearance 212 to thetips 120 of theturbine blades 92, which relatively tight tolerance provides for improved efficiency of theturbine 18 that might otherwise be possible had the clearance been larger. Accordingly, with theturbine tip shroud 82′ a part the turbinenozzle cartridge assembly 74 that is retained on the bearinghousing 38 and free to float within thecounterbore 96 in thecavity turbine tip shroud 82′ is unaffected by theexhaust housing portion 88 of thecylinder head assembly 12, for example, by thermally-induced stresses therein or therefrom, or external mechanical loads thereto, that might otherwise result in interference with thetip 120 of theturbine blades 92, so that a relatively small clearance between theturbine tip shroud 82′ and thetip 120 of theturbine blades 92 can be readily realized using production hardware and processes. - The
turbocharger core 10 is assembled to thecylinder head assembly 12 with a plurality ofbolts 122 through a corresponding plurality ofholes 124 in an associatedflange 126 or set offlanges 126′ of or extending from the bearinghousing 38, through anadapter bushing 128, and into corresponding threadedholes 130 in theforward portion 132 of theexhaust housing portion 88 ofcylinder head assembly 12 around the periphery of the of thecavity cylinder head assembly 12, the bearinghousing 38 of theturbocharger core 10 provides for closing the forward end of thecavity 20, which is sealed at the junction of the bearinghousing 38 andadapter bushing 128 and the junction of theadapter bushing 128 and theforward portion 132 of theexhaust housing portion 88 ofcylinder head assembly 12 around the periphery of the of thecavity adapter bushing 128 is sufficiently greater that the outside diameter of thecylindrical lip 110 of theforward nozzle wall 76 of the turbinenozzle cartridge assembly 74 so as to provide for uninhibited thermally induced expansion of thecylindrical lip 110 within thegap 134 therebetween, so as to prevent a thermally-induced mechanical stress of the turbinenozzle cartridge assembly 74 that would otherwise occur if the outward radial expansion of thecylindrical lip 110 were otherwise restrained by theadapter bushing 128. Theadapter bushing 128 also provides for capturing the radial pins 114 within theirradial holes 118 in thecylindrical step 112. The aft surface 136 of theadapter bushing 128 is located and shaped so as to provide for a relatively smooth transition from theinside surface 138 of thecavity 20′, 20″ to theforward nozzle wall 76 so as to facilitate the flow ofexhaust gases 21 from thecavity 20′, 20″ into the turbinenozzle cartridge assembly 74. For example, in one embodiment, the aft surface 136 of theadapter bushing 128 comprises a portion of a concave toroidal surface 136 that in cross-section provides for a quarter-round fillet between theinside surface 138 and theforward nozzle wall 76. Alternatively, theadapter bushing 128 can be replaced by incorporating the material thereof directly into theexhaust housing portion 88 of thecylinder head assembly 12. Furthermore, alternatively, theturbocharger core 10 may be mounted to theforward portion 132 of theexhaust housing portion 88 ofcylinder head assembly 12 with a V-clamp rather thanbolts 122. - In operation of the
turbocharger core 10,exhaust gases 21 from thefirst exhaust port 26 are first collected in theannulus 140 defined by portion of thecavity exhaust housing portion 88 of thecylinder head assembly 12 on the outside of the turbinenozzle cartridge assembly 74, and then accelerated therefrom by the turbinenozzle cartridge assembly 74 into theturbine blades 92 of theturbine rotor 30. The turbinenozzle cartridge assembly 74 provides for directing and accelerating exhaust flow into theturbine blades 92 of theturbine rotor 30, and controlling the associated mass flow of theseexhaust gases 21. Accordingly, the turbinenozzle cartridge assembly 74 can be configured—independent of the design of thecavity exhaust housing portion 88 of thecylinder head assembly 12, for example, by adjusting the area/radius ratio (A/R) of thepassage 140 through the turbinenozzle cartridge assembly 74—so as to adapt to the particular turbocharging requirements of a given internal combustion engine 14, 14.1, which provides for simplifying the process of tuning theturbocharger core 10 to the internal combustion engine 14, 14.1 because the only component to be changed in that process would be the turbinenozzle cartridge assembly 74. For example, in one set of embodiments, the forward 76 and aft 78 nozzle walls comprise corresponding forward 76′ and aft 78′ curved swept surfaces, the shapes of which may be adapted in cooperation with the associatedvanes 80 to provide for tuning theturbocharger core 10. - Responsive to exhaust
gases 21 impinging thereupon, theturbine rotor 30 of theturbine 18 of theturbocharger core 10 drives therotor shaft 32 that rotates in the aft journal bearing 34 and forward rolling element bearing 36 in the bearinghousing 38 and in turn drives thecompressor rotor 56 that rotates within an associatedcompressor housing 142 of the associatedcompressor 16, which provides for compressing air from acentral inlet 144 to thecompressor housing 142, and discharging the compressed air through avolute diffuser 146 surrounding thecompressor rotor 56. The compressed air is discharged from thecompressor 16 into aconduit 148 that is coupled to an inlet plenum 150, for example, coupled to or surrounding athrottle body 152 coupled to aninlet manifold 154 of the internal combustion engine 14, 14.1. - Referring to
FIGS. 11 and 12 , in accordance with respective first and second alternative embodiments, thecavity exhaust housing portion 88 of thecylinder head assembly 12 may be configured to receiveexhaust gases 21 from a plurality offirst exhaust ports 26, 26.1, 26.2, 26.3, each operatively associated with one or more associatedexhaust runners 24, 24.1, 24.2, 24.3, eachexhaust runner 24 operatively associated with one ormore cylinders 22 of the internal combustion engine 14, 14.1, wherein for eachfirst exhaust port 26, 26.1, 26.2, 26.3, each corresponding associatedexhaust runner 24, 24.1, 24.2, 24.3 is oriented so as to introduceexhaust gases 21 substantially tangentially into thecavity exhaust gases 21 in thecavity first exhaust port 26, 26.1, 26.2, 26.3 swirls in acommon swirl direction 156. For example, referring toFIG. 11 , in the first alternative embodiment, thecavity different exhaust runners 24, 24.1, 24.2, 24.3, each of which dischargesexhaust gases 21 into thecavity first exhaust port 26, 26.1, 26.2, 26.3, wherein the associatedexhaust runners 24, 24.1, 24.2, 24.3 are oriented so that all of thefirst exhaust port 26, 26.1, 26.2, 26.3discharge exhaust gases 21 tangentially into thecavity common swirl direction 156. Furthermore, referring toFIG. 12 , in the second alternative embodiment, thecavity different exhaust runners 24, 24.1, 24.2, 24.3, two of whichexhaust runners 24, 24.1, 24.2discharge exhaust gases 21 into thecavity first exhaust port 26, 26.1, 26.2, the third of whichexhaust runners 24, 24.3 dischargesexhaust gases 21 into thesecond exhaust runner 24, 24.2, which in turn discharges theexhaust gases 21 into thecavity first exhaust ports 26, 26.2, wherein the associatedexhaust runners 24, 24.1, 24.2 are oriented so that both the first 26, 26.1 and second 26, 26.2 exhaust ports dischargeexhaust gases 21 tangentially into thecavity common swirl direction 156. - By incorporating the
turbocharger core 10 in the associatedcylinder head assembly 12, and providing for water-cooling the bearinghousing 38 and the associatedexhaust housing portion 88 of thecylinder head assembly 12 that surrounds the associatedcavity turbocharger core 10, theturbocharger core 10 provides for reducing the amount of high-temperature tolerant material, for example a relatively high nickel content alloy, than would otherwise be required for a corresponding comparable stand-alone turbocharger assembly, which provides for reducing cost in comparison with a stand-alone turbocharger assembly. Furthermore, the incorporation of theturbocharger core 10 in the associatedcylinder head assembly 12 provides for more closely coupling the exhaust from thecylinders 22 of the internal combustion engine 14, 14.1 to theturbocharger core 10, which provides for improved efficiency than would otherwise be possible with a corresponding comparable stand-alone turbocharger assembly. - Referring to
FIGS. 13-15 , in accordance with a second aspect of an internal combustion engine and a first embodiment of an associated first aspect of a turbocharger assembly 200.1′, the associatedturbocharger core 10 cooperates with a separateturbocharger exhaust housing 158, aninlet 160 of which is operatively coupled to theexhaust manifold 162 of an internal combustion engine 14, 14.2, for example, with a plurality ofbolts 164 through afirst flange 166 at theoutlet 168 of theexhaust manifold 162 into asecond flange 170 at theinlet 160 of theturbocharger exhaust housing 158. Theinlet 160 is in fluid communication with acavity 20″ in theturbocharger exhaust housing 158 via afirst exhaust port 26′ located so as to direct associatedexhaust gases 21 off-center of the so as to induce a swirling flow ofexhaust gases 21 therein. The bearinghousing 38 of theturbocharger core 10, with the turbinenozzle cartridge assembly 74 attached thereto as described hereinabove, is bolted to aperipheral face 172 of theturbocharger exhaust housing 158 surrounding thecavity 20″ with a plurality ofbolts 174 through the bearinghousing 38 and into associated threadedsockets 176 on theturbocharger exhaust housing 158 around theperipheral face 172, so that the associated turbinenozzle cartridge assembly 74 extends through thecavity 20″ and into an associatedsecond exhaust port 94′ on the opposite side of thecavity 20″. Thesecond exhaust port 94′ incorporates aseal ring 104 in aninternal groove 106 that cooperates with the associatedexternal sealing surface 102 on the aft end 84.1 of thenozzle exhaust portion 84 of the turbinenozzle cartridge assembly 74, so as to provide for sealing thedischarge end 108 of the turbinenozzle cartridge assembly 74 to theturbocharger exhaust housing 158 so that substantially all of theexhaust gases 21 are discharged from the turbinenozzle cartridge assembly 74 into and through thesecond exhaust port 94 and into the associatedengine exhaust system 98, thereby substantially isolating theexhaust gases 21 in thecavity 20″ upstream of the turbinenozzle cartridge assembly 74 from theexhaust gases 21 discharged from the turbinenozzle cartridge assembly 74. Theseal ring 104 in cooperation with theexternal sealing surface 102 provides for enabling discharge end 108 of the turbinenozzle cartridge assembly 74 to both slide in an axial direction and expand or contract in a radial direction, responsive to thermally-induced expansion or contraction thereof, while maintaining the sealing condition at thedischarge end 108 of the turbinenozzle cartridge assembly 74, without substantial associated thermally-induced loading of the turbinenozzle cartridge assembly 74. - In operation,
exhaust gases 21 from theexhaust manifold 162 flow into theinlet 160 of theturbocharger exhaust housing 158 and then into the associatedcavity 20″. Theexhaust gases 21 swirl about the outside of the turbinenozzle cartridge assembly 74 within thecavity 20″, and then flow with swirl into theperipheral inlet 93 of the turbinenozzle cartridge assembly 74 along thevanes 80 thereof, and against theturbine blades 92 of theturbine rotor 30, thereby driving theturbine rotor 30 that in turn rotates therotor shaft 32 and thecompressor rotor 56 attached thereto. Theexhaust gases 21 then flow through thenozzle exhaust portion 84 of the turbinenozzle cartridge assembly 74 before being exhausted into and through thesecond exhaust port 94′ in theturbocharger exhaust housing 158, and then into theengine exhaust system 98, which, for example, may include one or more exhaust treatment devices 100, for example, one or more catalytic converters or mufflers. - The
turbocharger exhaust housing 158 could be constructed of the same type of material, for example cast iron, or alternatively, cast with a relatively-high-nickel-content alloy, as could be used for theexhaust manifold 162. As for the first aspect of an internal combustion engine, theturbocharger core 10 may be tuned to a particular engine by modifying the turbinenozzle cartridge assembly 74, independently of the design of theturbocharger exhaust housing 158 and the associatedcavity 20″. - Referring to
FIGS. 16 and 17 , in accordance with a second embodiment of an associated first aspect of a turbocharger assembly 200.1′ adapted for use with the second aspect of an internal combustion engine 14, 14.2, the associatedturbocharger exhaust housing 158 incorporates aninternal heat shield 178, for example, constructed from a sheet-metal material that can withstand hightemperature exhaust gases 21, for example, of a nickel alloy, for example, stainless steel with a relatively high nickel content, for example, 310 stainless steel, that provides for high temperature oxidation resistance and strength.Exhaust gases 21 within theturbocharger exhaust housing 158 are substantially contained within the inside surface 178.1 of theinternal heat shield 178, the latter of which incorporates a plurality externally-protrudingdimples 180 that provide for separating the outside surface 178.2 of theinternal heat shield 178 from theinside surface 158′ of theturbocharger exhaust housing 158 with an associatedair gap 182 that provides for reducing conductive heat transfer from theinternal heat shield 178 to theturbocharger exhaust housing 158. Accordingly, theinternal heat shield 178 provides for both radiative and conductive heat shielding. - Although the
internal heat shield 178 is illustrated in the context of a second aspect of the internal combustion engine 14, 14.2, i.e. external of an associatedcylinder head assembly 12, aninternal heat shield 178 can be particularly beneficial in the context of the first aspect the internal combustion engine 14, 14.1, i.e. integrated with an associatedcylinder head assembly 12, so as to provide for substantially reducing the amount of heat transferred from theexhaust gases 21 to thecylinder head assembly 12 that would otherwise need to be removed by the associatedwater cooling system 46 of the internal combustion engine 14, 14.1. For example, in one simulated embodiment of the first aspect of the internal combustion engine 14, 14.1 with an associated aluminumcylinder head assembly 12 incorporating acavity 20 having a 6 mm wall thickness and lined with a 1.5 mm thickinternal heat shield 178 in cooperation with an associatedturbocharger core 10, forexhaust gases 21 at 1050 degrees Celsius, the associated heat transfer was reduced from 8.20 Kilowatts to 1.80 Kilowatts, and the associated heat transfer coefficient was reduced from about 9 Watts per degree Kelvin to about 2 Watts per degree Kelvin, with theinternal heat shield 178 operating at about 904 degrees Celsius. - The
turbocharger core 10 has been illustrated hereinabove configured with an axial-flow turbine 18′, wherein theexhaust gases 21 discharged from a nozzle portion 74.1 of the turbinenozzle cartridge assembly 74 are directed in a substantially axial-aftwards direction 184 aftward onto and against theturbine blades 92 of the associated axial-flow turbine 18′ located aftward of theforward nozzle wall 76,vanes 80, and nozzle portion 74.1 of the turbinenozzle cartridge assembly 74. - Alternatively, referring to
FIG. 18 , a third embodiment of the first aspect of a turbocharger assembly 200.1″ adapted in accordance with the second aspect of an internal combustion engine is illustrated incorporating a second aspect of an associatedturbocharger core 10′ having an associated radial-flow turbine 18″ and a corresponding associated turbinenozzle cartridge assembly 74′ that provides for discharging the associatedexhaust gases 21 in a substantially radial-inwards direction 186 from the nozzle portion 74.1′ of the turbinenozzle cartridge assembly 74 onto and against theturbine blades 92′ of the associated radial-flow turbine 18″ located radially inboard of theforward nozzle wall 76,vanes 80, and nozzle portion 74.1′ of the turbinenozzle cartridge assembly 74′. - Furthermore, alternatively, the
turbocharger core 10 may be adapted with a mixed-flow turbine, i.e. a combined radial-flow and axial-flow turbine, with an associated turbinenozzle cartridge assembly 74 adapted to cooperate therewith, but otherwise generally configured as described hereinabove, with the associated mixed-flow turbine rotor located aft and radially inboard of theforward nozzle wall 76,vanes 80, and nozzle portion 74.1 of the turbinenozzle cartridge assembly 74, with an associated conical boundary therebetween. - Furthermore, it should be understood that either the first or second aspects of the associated internal combustion engine 14, 14.1, 14.2 described hereinabove may be adapted to provide for a
wastegate valve 99 to provide for bypassingexhaust gases 21 from the internal combustion engine 14, 14.1, 14.2 around theturbocharger core 10, i.e. to as to enable some or all of theexhaust gases 21 to flow from theexhaust runners 24 orexhaust manifold 162 to theengine exhaust system 98 without flowing through theturbine 18. - The turbine
nozzle cartridge assembly 74 provides for readily matching or tuning theturbocharger core 10 to a particular internal combustion engine 14, 14.1, 14.2, because other components of theturbocharger core 10—particularly the associatedexhaust housing portion 88 of thecylinder head assembly 12 or the associatedturbocharger exhaust housing 158—would not typically need to be modified during that process. Furthermore, with the turbinenozzle cartridge assembly 74 separate from and free to float relative to the associatedexhaust housing portion 88 of thecylinder head assembly 12 or the associatedturbocharger exhaust housing 158, production versions of theturbocharger core 10 can be adapted to work with relatively smaller clearances between theturbine tip shroud 82 and thetips 120 of theturbine blades 92 without danger of interference therebetween during the operation of theturbocharger core 10 over the life thereof. - Referring to
FIGS. 19-22 , a first embodiment of an associated second aspect, a turbocharger assembly 200.2 i usable in cooperation with a second aspect of an internal combustion engine 14, 14.2 comprises acenterbody 33, acompressor 16 and aturbine 18. - The
centerbody 33 comprises a bearinghousing 38, at least onebearing housing 38, and arotor shaft 32 rotationally supported by the at least onebearing 34. 36 spaced therealong, wherein therotor shaft 32 is part of an associatedturbocharger rotor assembly 31. - The
compressor 16 of theturbocharger core 10 comprises acompressor rotor 56—also part of theturbocharger rotor assembly 31—within an associatedcompressor housing 142 that is operatively coupled to a forward side 33.2 of thecenterbody 33. Thecompressor rotor 56 is operatively coupled to the forward end 32.2 of therotor shaft 32 and adapted to rotate therewith about an axis ofrotation 202′ of theturbocharger rotor assembly 31. - The
turbine 18 comprises aturbine rotor 30—also part of theturbocharger rotor assembly 31—within an associatedturbocharger exhaust housing 158 that is operatively coupled to an aft side 33.1 of thecenterbody 33. Theturbine rotor 30 is operatively coupled to—for example, welded to—the aft end 32.1 of therotor shaft 32 along the periphery of acavity 60 between the forward end of theturbine rotor 30 and the aft end 32.1 of therotor shaft 32 that provides for reducing heat transfer from theturbine rotor 30 to therotor shaft 32. Aninlet 160 of theturbocharger exhaust housing 158 provides for operatively coupling to, and receivingexhaust gases 21 from, anexhaust manifold 162 of an internal combustion engine 14, 14.2. For example, as illustrated inFIG. 13 , theinlet 160 of theturbocharger exhaust housing 158 is operatively coupled to theexhaust manifold 162 with a plurality ofbolts 164 through afirst flange 166 at theoutlet 168 of theexhaust manifold 162 into asecond flange 170 at theinlet 160 of theturbocharger exhaust housing 158. Theinlet 160 is in fluid communication with a first aspect of a volute 204 i in a first aspect of a volute portion 204 i′ of theturbocharger exhaust housing 158 that provides for dischargingexhaust gases 21 onto theturbine rotor 30. At least a portion of an aft boundary 206 i of the volute portion 204 i′ comprises a surface of revolution 206 i′ about the axis ofrotation 202 of theturbine rotor 30. The aft boundary 206 i is located further from thecenterbody 33 than a corresponding opposing forward boundary 207 i of the volute portion 204 i′. For example, in one embodiment the surface of revolution 206 i′ comprises a planar surface 206 i″ that is substantially perpendicular to the axis ofrotation 202′. Theexhaust gases 21 are discharged from theoutlet 208 of the volute 204 i onto theturbine rotor 30 so as to provide for driving theturbine rotor 30, which in turn drives the associatedturbocharger rotor assembly 31. - A portion of the
turbine rotor 30 is concentrically surrounded by ashroud portion 210 of theturbocharger exhaust housing 158, wherein the radius of theshroud portion 210 of theturbocharger exhaust housing 158 exceeds that of the corresponding radius of theturbine rotor 30 by acorresponding tip clearance 212. The efficiency of theturbine 18 is generally improved with decreasingtip clearance 212 as a result of a corresponding associated reduction inexhaust gases 21 bypassing theturbine blades tips 120 of theturbine blades shroud portion 210 of theturbocharger exhaust housing 158. Upon discharge from theturbine rotor 30, theexhaust gases 21 are then discharged through anexhaust outlet 214 at an aft end 158.1 of theturbocharger exhaust housing 158 and into the associatedengine exhaust system 98. Accordingly, theturbocharger exhaust housing 158 comprises a correspondingfluid conduit 216 between theinlet 160 and theoutlet 208 thereof, through which theexhaust gases 21 flow, and within which the associatedturbine rotor 30 operates. - A forward end 158.2 of the
turbocharger exhaust housing 158 incorporates an internalcylindrical surface 218 that mates with a corresponding externalcylindrical surface 220 on the aft side 33.1 of thecenterbody 33. Anaxis 202″ of the externalcylindrical surface 220 is substantially concentric with an axis ofrotation 202′ of theturbine rotor 30 and with anaxis 202 of the internalcylindrical surface 218. - The
turbocharger exhaust housing 158 is operatively coupled to thecenterbody 33 with a plurality ofradial pins 222, each of which extends radially across ajunction 224 between the internal 218 and external 220 cylindrical surfaces and engages both thecenterbody 33 and awall 226 of theturbocharger exhaust housing 158 so as to prevent more than insubstantial relative axial movement therebetween. Eachradial pin 222 is slideably engaged with at least one of a corresponding radial bore 228 in theturbocharger exhaust housing 158 and a corresponding radial bore 228 in thecenterbody 33 so that the internalcylindrical surface 218 is free to thermally expand radially relative to the externalcylindrical surface 220. The radial bore 228 in theturbocharger exhaust housing 158 is closed to thefluid conduit 216. The plurality ofradial pins 222 are arranged around thecenterbody 33 so as to provide for the internal 218 and external 220 cylindrical surfaces to remain substantially concentric regardless of a thermal expansion of theturbocharger exhaust housing 158 relative to thecenterbody 33, and so as to provide for theshroud portion 210 of theturbocharger exhaust housing 158 to remain substantially concentric regardless of a thermal expansion of theturbocharger exhaust housing 158 relative to theturbine rotor 30. For example, as illustrated inFIG. 22 , for one set of embodiment, thediameter 230 of the internalcylindrical surface 218 is less than thediameter 232 of the externalcylindrical surface 220 at room temperature so as to provide for an interference fit therebetween in a non-operative state of the turbocharger assembly 200.2 i. By incorporating the plurality ofradial pins 222 in cooperation with the corresponding plurality ofradialbores 228 to provide for a radial thermal expansion of theturbocharger exhaust housing 158 relative to thecenterbody 33 that is substantially without constraint other than as to the maintenance of concentricity of the internal 218 and external 220 cylindrical surfaces, the second aspect of the turbocharger assembly 200.2 provides for configuring the diameter of theshroud portion 210 of theturbocharger exhaust housing 158 in relation to that of theturbine rotor 30 so to provide for an associatedtip clearance 212 at room temperature that is less than 4 percent of the radius of theturbine rotor 30 at the aft portion thereof. - For example, the plurality of
radial pins 222 may be either symmetrically located or equi-spaced—or both—around thejunction 224 between the centerbody 33 and around the associatedturbocharger exhaust housing 158. For example,FIG. 21 illustrates a plurality of sixradial pins 222 that are equi-spaced from one another and are in a symmetrical arrangement with respect to one another. Generally, the plurality ofradial pins 222 would comprise at least threeradial pins 222. - In operation of the turbocharger assembly 200.2 i,
exhaust gases 21 from theexhaust manifold 162 flow into theinlet 160 of theturbocharger exhaust housing 158, through the associated volute 204 i, and then discharge from theoutlet 208 thereof onto theturbine blades turbine rotor 30, thereby driving theturbine rotor 30 that in turn rotates therotor shaft 32 and thecompressor rotor 56 attached thereto. Theexhaust gases 21 then flow through theshroud portion 210 of theturbocharger exhaust housing 158 before being exhausted through the associatedexhaust outlet 214, and then into theengine exhaust system 98, which, for example, may include one or more exhaust treatment devices 100, for example, one or more catalytic converters or mufflers. Theturbocharger exhaust housing 158 could be constructed of the same type of material, for example cast iron, or alternatively, cast with a relatively-high-nickel-content alloy, as could be used for theexhaust manifold 162 of the internal combustion engine 14, 14.2. Theexhaust gases 21 heat theturbocharger exhaust housing 158 upon flowing through the associatedfluid conduit 216 thereof, thereby causing theturbocharger exhaust housing 158 to thermally expand relative to thecenterbody 33, thereby causing agap 234 between the internal 218 and external 220 cylindrical surfaces, the latter of which remain substantially concentric as a result of the constraining action of theradial pins 222 spaced around thejunction 224 therebetween, which slide within the corresponding associated radial bores 228, as illustrated inFIGS. 23 a and 23 b for relatively less thermal expansion and relatively more thermal expansion, respectively. - For example, in accordance with the first embodiment of an associated second aspect of the turbocharger assembly 200.2 i illustrated in
FIGS. 19-22 , eachradial pin 222 is slideably engaged with both a first radial bore 228.1 in thecenterbody 33, and a second radial bore 228.2 in thewall 226 of theturbocharger exhaust housing 158, so that eachradial pin 222 can slide relative to either or both the first 228.1 or second 228.2 radial bores responsive to a thermal expansion of theturbocharger exhaust housing 158 relative to thecenterbody 33. Alternatively, for at least one or all of the radial pins 222, theradial pin 222 could be radially restrained in one of thecenterbody 33 andwall 226 of theturbocharger exhaust housing 158, but slideably engaged with a correspondingradial bore 228 in the other of thecenterbody 33 andwall 226 of theturbocharger exhaust housing 158. For example, alternatively, theradial pin 222 could be installed with an interference fit in the first radial bore 228.1 in thecenterbody 33, but slideably engaged in the second radial bore 228.2 in thewall 226 of theturbocharger exhaust housing 158, or theradial pin 222 could be installed with an interference fit in the second radial bore 228.2 in thewall 226 of theturbocharger exhaust housing 158, but slideably engaged in the first radial bore 228.1 in thecenterbody 33, so as to provide for retaining theradial pin 222 in the turbocharger assembly 200.2 i. - Yet further alternatively, referring to
FIG. 24 , in accordance with a second embodiment of the second aspect of a turbocharger assembly 200.2 ii that incorporates a second embodiment of associatedradial pins 222′, each radial pins 222′ incorporates a threadedend portion 236 that engages a correspondinginternal thread 238 in thecenterbody 33 extending radially inwards from a corresponding radial counterbore 228.1′ in thecenterbody 33, the latter of which engages thebody 239 of theradial pin 222′ so as to provide for rotationally aligning the radial counterbores 228.1′ in thecenterbody 33 with the corresponding second radial bores 228.2 in thewall 226 of theturbocharger exhaust housing 158, which in cooperation with theradial pins 222′ provides for substantially centering the internal 218 and external 220 cylindrical surfaces with respect to one another, while theradial pin 222′ is retained to thecenterbody 33 by engagement of the threadedend portion 236 with theinternal thread 238 in thecenterbody 33, wherein thehead portions 240 of theradial pins 222′ are adapted to provide for installing the radial pins 222′ during assembly of the turbocharger assembly 200.2 ii. - Alternatively, one or more
radial pins 222 could be threaded near the correspondinghead portion 240 so as to provide for engaging a corresponding threaded, counterbored portion radially outwards of a corresponding second radial bore 228.2 in thewall 226 of theturbocharger exhaust housing 158, wherein thebody 239 of theradial pin 222 then is slideably engaged with the first 228.1 and second 228.2 radial bores for purposes of assembly, and slideably engaged with the first radial bore 228.1 in thecenterbody 33 during operation of the turbocharger assembly 200.2 ii so as to provide for substantially centering the internal 218 and external 220 cylindrical surfaces with respect to one another regardless of thermal expansion of theturbocharger exhaust housing 158 relative to thecenterbody 33. - In accordance with the first embodiment of the associated second aspect of the turbocharger assembly 200.2 i illustrated in
FIGS. 19-22 , eachradial pin 222 is slideably engaged with both the first 228.1 and second 228.2 radial bores at least during assembly, but is retained to the turbocharger assembly 200.2 i either by aweld 242 to theturbocharger exhaust housing 158, or by staking a radiallyoutboard portion 244 of the second radial bore 228.2 in thewall 226 of theturbocharger exhaust housing 158, either with theradial pin 222 extending therethrough as illustrated, or, alternatively, with a relatively shorterradial pin 222 that is inserted radially within the radiallyoutboard portion 244. - The first embodiment of the associated second aspect of the turbocharger assembly 200.2 i further incorporates a
seal 246 operative between the centerbody 33 and anend face 248 of theturbocharger exhaust housing 158—for example, optionally operative within agroove 250 in theend face 248 of theturbocharger exhaust housing 158—that provides for preventing theexhaust gases 21 from escaping theturbocharger exhaust housing 158 fromgaps turbocharger exhaust housing 158 and thecenterbody 33, wherein theseal 246 is configured so as to provide for accommodating thermal expansion or contraction of theturbocharger exhaust housing 158 relative to thecenterbody 33. For example, theseal 246 may comprise either athermal gasket 254—for example, as illustrated inFIGS. 20 and 22 for the first embodiment of the associated second aspect of the turbocharger assembly 200.2 i, or a metallic seal 256, for example, comprising a radial cross-section selected from the group consisting of a V-shaped cross-section 258 and a first aspect of a C-shaped cross-section 260′, for example, as illustrated inFIGS. 25 and 26 , respectively for the third and fourth embodiments of the associated second aspect of the turbocharger assembly 200.2 iii, 200.2 iv, respectively, wherein the associatedseals 246 are operative across anaxial gap 252. In one set of embodiments, for example, as illustrated inFIGS. 20 , 22, 25 and 26, the externalcylindrical surface 220 is stepped into a corresponding side 33.1 of thecenterbody 33, and theseal 246 is operative between theend face 248 and aradial surface 262 extending radially outwards from the externalcylindrical surface 220 stepped into the corresponding side 33.1 of thecenterbody 33, wherein the V-shaped cross-section 258 and the first aspect of the C-shaped cross-section 260 metallic seals 256 have associated sealing surfaces and are oriented so that these sealing surfaces are axially spring-biased respectively against the associatedradial surface 262 of thecenterbody 33 and the associatedend face 248 of theturbocharger exhaust housing 158 so as to provide for sealing thegap 252 therebetween while also providing for a radial movement of theend face 248 relative to theradial surface 262 responsive to a thermal expansion or contraction of the of theturbocharger exhaust housing 158 relative to thecenterbody 33. - Referring to
FIG. 27 a fifth embodiment of the second aspect of a turbocharger assembly 200.2 v theseal 246 is operative across aradial gap 234 between the centerbody 33 and theturbocharger exhaust housing 158, for example, by incorporating a metallic seal 256 incorporating a second aspect of a C-shaped cross-section 260″ that is oriented so that the associated sealing surfaces are radially spring-biased respectively against an the externalcylindrical surface 220 of thecenterbody 33 and an associated internalcylindrical surface 263 of an associatedcounterbore 265 at the forward end 158.2 of theturbocharger exhaust housing 158 so as to provide for sealing the associatedradial gap 234′ therebetween regardless of a radial movement of theend face 248 relative to theradial surface 262 responsive to a thermal expansion or contraction of the of theturbocharger exhaust housing 158 relative to thecenterbody 33. - In accordance with one set of embodiments, the plurality of
radial bores 228 are match-drilled through thewall 226 and internalcylindrical surface 218 of theturbocharger exhaust housing 158, through the externalcylindrical surface 220 of thecenterbody 33, and into thecenterbody 33 after fully sliding the internalcylindrical surface 218 of theturbocharger exhaust housing 158 onto the externalcylindrical surface 220 of thecenterbody 33 with sufficient force to compress theseal 246 sufficiently enough to provide for sealing theend face 248 of theturbocharger exhaust housing 158 against the correspondingradial surface 262 of thecenterbody 33 under all subsequent anticipated operating conditions for the design life of the turbocharger assembly 200.2. - Referring to
FIG. 20 , the use of the plurality ofradial pins 222 in cooperation with the corresponding plurality of associated radial bores 228 to operatively couple theturbocharger exhaust housing 158 to thecenterbody 33—for example, rather than a V-clamp as might be used in a conventional turbocharger—provides for locating the associated volute 204 i forward of an aft boundary 206 i of anoutlet 208 thereof onto thebladed rotor 30 so as to provide for a direction offlow 264 of theexhaust gases 21 onto thebladed rotor 30 that is either substantially radially inwards or at least partially axially aftward from thecenterbody 33 with decreasing distance from thebladed rotor 30. - In another set of embodiments, also illustrated in
FIGS. 20 and 21 , aheat shield 266 is operative between the centerbody 33 and theturbine rotor 30 within anaxial bore 268 in theturbocharger exhaust housing 158, wherein theaxial bore 268 has a diameter in excess of a maximum diameter of theturbine rotor 30 so as to provide for assembling theturbocharger exhaust housing 158 over theturbine rotor 30, the latter of which is preassembled as part of thecenterbody 33. Anouter rim 270 of theheat shield 266 is retained axially between the centerbody 33 and theturbocharger exhaust housing 158, and is keyed to thecenterbody 33 with anaxial pin 272 extending therefrom through a correspondingaxial hole 274 through theouter rim 270 of theheat shield 266—so as to prevent a rotation of theheat shield 266—and, in one embodiment, into anaxial bore 276 in a correspondingforward portion 278 of theturbocharger exhaust housing 158 so as to provide for roughly aligning theturbocharger exhaust housing 158 with thecenterbody 33 during assembly, wherein the radial clearance around theaxial pin 272 within theaxial bore 276 in the correspondingforward portion 278 of theturbocharger exhaust housing 158 is sufficient so as to not interfere with a thermal expansion of the internalcylindrical surface 218 of theturbocharger exhaust housing 158 relative to thecenterbody 33. - Referring to
FIG. 28 a sixth embodiment of the second aspect of a turbocharger assembly 200.2 vi incorporates a second aspect of a volute 204 ii and associated second aspect of the volute portion 204 i′ of theturbocharger exhaust housing 158—but is otherwise similar to the first aspect of the turbocharger assembly 200.2 i described hereinabove—wherein at least a portion of a forward boundary 207 ii of the volute portion 204 i′ comprises a surface of revolution 207 ii′ about the axis ofrotation 202 of theturbine rotor 30. A corresponding opposing aft boundary 206 ii is located further from thecenterbody 33 than the forward boundary 207 ii of the volute portion 204 ii′. For example, in one embodiment the surface of revolution 207 ii′ comprises a planar surface 207 i″ that is substantially perpendicular to the axis ofrotation 202. Theexhaust gases 21 are discharged from theoutlet 208 of the volute 204 i onto theturbine rotor 30 so as to provide for driving theturbine rotor 30, which in turn drives the associatedturbocharger rotor assembly 31. - Although not illustrated in the drawings, it should be understood that the
compressor housing 142 of the associatedcompressor 16 of the turbocharger assembly 200.2 could also be operatively coupled to thecenterbody 33 with a plurality ofradial pins 222 in cooperation with a corresponding plurality of associated radial bores 228 similarly as described hereinabove for theturbine 18 of the turbocharger assembly 200.2. - Furthermore, it should also be understood that the arrangement of the plurality of
radial pins turbine 18 of the turbocharger assembly 200.2 can be used in other types of turbomachines, for example, superchargers, turbines, pumps, or compressors, so as to provide for maintaining the concentricity of an associated fluid-conduit housing centerbody 33 so as to provide for provide for maintaining the concentricity of ashroud portion conduit housing bladed rotor conduit housing centerbody 33, wherein the term fluid is intended to include gases, vapors and liquids, and the associatedfluid 21 flows either entirely within the associated fluid-conduit housing conduit housing conduit housing - A turbomachine apparatus comprises a
centerbody 33, at least onebladed rotor conduit housing - Although, for purposes of illustration, the reference signs referred to hereinbelow are associated with the turbocharger embodiments illustrated herein, it should be understood that the term turbomachine is not limited to a turbocharger. The
centerbody 33 comprises a bearinghousing 38, at least onebearing housing 38; and arotor shaft 32 rotationally supported by the at least onebearing rotor shaft 32. The at least onebladed rotor rotor shaft 32 supported by thecenterbody 33. Eachbladed rotor fluid conduit 216 defined by the fluid-conduit housing conduit housing inlet fluid 21 within thefluid conduit 216 that provides for either driving or being driven, pumped or compressed by a correspondingbladed rotor fluid 21 with a plurality ofblades bladed rotor conduit housing cylindrical surface cylindrical surface centerbody 33. Anaxis 202″ of the externalcylindrical surface rotation 202′ of thebladed rotor axis 202 of the internalcylindrical surface conduit housing centerbody 33 with a plurality ofradial pins cylindrical surface cylindrical surface radial pin radial pins radial bore conduit housing radial bore centerbody 33. In one set of embodiments, theradial bore 228, 228.2 in the fluid-conduit housing fluid conduit 216. Each theradial pin cylindrical surface cylindrical surface radial pins centerbody 33 so as to provide for the internal 110, 218 and external 112, 220 cylindrical surfaces to remain substantially concentric regardless of a thermal expansion of the fluid-conduit housing centerbody 33, and at least a portion of the fluid-conduit housing shroud portion bladed rotor - Regarding the relative size of the internal 110, 218 and external 112, 220 cylindrical surfaces, in one set of embodiments, the internal 110, 218 and external 112, 220 cylindrical surfaces are mated with an interference fit at room temperature.
- Regarding the plurality and location of the radial pins 114, 222, the plurality of
radial pins centerbody 33 and around the associated fluid-conduit housing radial pins radial pins - Regarding the operation of the radial pins 114, 222, in one set of embodiments, at least one the
radial pin radial bore conduit housing radial bore centerbody 33. - In one set of embodiments, the radial pins 114, 222 are retained in cooperation with both the
centerbody 33 and the corresponding fluid-conduit housing conduit housing radial bore 228, 228.1, 228.2 in either the fluid-conduit housing centerbody 33, or by engagement of ascrew thread portion 236 of theradial pin conduit housing centerbody 33. - For example, in one set of embodiments, the at least one
bladed rotor bladed compressor rotor 56 and aturbine rotor 30, for example, thecompressor rotor 56 of acompressor 16 portion of a turbocharger assembly 200.2 or a compressor portion of a supercharger, and/or theturbine rotor 30 of turbine 18 a turbocharger assembly 200.2. - At room temperature, a
minimum tip clearance 212 between theshroud portion conduit housing tip 120 of the at least onebladed rotor bladed rotor tip 120 of thebladed rotor minimum tip clearance 212 to theshroud portion conduit housing - When incorporated in the
turbine portion 18 of a turbocharger assembly 200.2, thebladed rotor 30 comprises theturbine rotor 30 of the turbocharger assembly 200.2, the fluid-conduit housing 158 comprises anturbocharger exhaust housing 158 configured to receiveexhaust gases 21 from an internal combustion engine 14, 14.2, and a portion of theturbocharger exhaust housing 158 comprises theshroud portion 210 that substantially concentrically surrounds the portion of theturbine rotor 30. In one set of embodiments, theturbocharger exhaust housing 158 comprises a volute portion 204 i′ of thefluid conduit 216 that is operative between theinlet 160 and theturbine rotor 30, at least a portion of an aft boundary 206 i of the volute portion 204 i′ comprises a surface of revolution 206 i′ about the axis ofrotation 202′ of theturbine rotor 30 where the fluid 21 is discharged from the volute portion 204 i′ onto theturbine rotor 30 during operation of the turbocharger assembly 200.2, and the aft boundary 206 i is located further from thecenterbody 33 than a corresponding opposing forward boundary 207 i of the volute portion 204 i′. For example, in one embodiment the surface of revolution 206 i′ comprises a planar surface that is substantially perpendicular to the axis ofrotation 202. Eachradial pin 222 being slideable in at least one of a corresponding radial bore 228 in theturbocharger exhaust housing 158 and a corresponding radial bore 228 in thecenterbody 33 provides for maintaining the concentricity of theshroud portion 210 of theturbocharger exhaust housing 158 relative to theturbine rotor 30 regardless of thermal expansion of theturbocharger exhaust housing 158 relative to thecenterbody 33, so that at room temperature, thetip clearance 212 between theshroud portion 210 of theturbocharger exhaust housing 158 and at least onetip 120 of theturbine rotor 30 at an aft portion thereof can be less than 4 percent of a radius of theturbine rotor 30 at the at least onetip 120 of theturbine rotor 30 at the aft portion thereof. Aseal 246 operative between anend face 248 of theturbocharger exhaust housing 158 and thecenterbody 33—for example, operative within agroove 250 in theend face 248 of theturbocharger exhaust housing 158—provides for preventing theexhaust gases 21 from escaping theturbocharger exhaust housing 158 from agap turbocharger exhaust housing 158 and thecenterbody 33, wherein theseal 246 is configured so as to provide for accommodating thermal expansion or contraction of theturbocharger exhaust housing 158 relative to thecenterbody 33. For example, theseal 246 may comprise either athermal gasket 254, or a metallic seal 256, for example, comprising a radial cross-section selected from the group consisting of a V-shaped cross-section 258 and a C-shaped cross-section 260. In one set of embodiments, the externalcylindrical surface 220 is stepped into the corresponding side 33.1 of thecenterbody 33, and theseal 246 is operative between theend face 248 and aradial surface 262 extending radially outwards from the externalcylindrical surface 220 that is stepped into the corresponding side 33.1 of thecenterbody 33. In another set of embodiments, aheat shield 266 is operative between the centerbody 33 and theturbine rotor 30 within anaxial bore 268 in theturbocharger exhaust housing 158, wherein theaxial bore 268 has a diameter in excess of a maximum diameter of theturbine rotor 30. - When incorporated in the
compressor portion 16 of a turbocharger assembly 200.2 or a supercharger, the at least onebladed rotor 56 comprises the bladedcompressor rotor 56 and the at least one fluid-conduit housing 142 comprises acompressor housing 142 surrounding thecompressor rotor 56, wherein thecompressor housing 142 comprisescentral inlet 144 and avolute diffuser 146. - A method of operatively coupling a fluid-
conduit housing centerbody 33 comprises: -
- a. sliding an internal
cylindrical surface cylindrical surface cylindrical surface conduit housing cylindrical surface centerbody 33; - b. operatively coupling the fluid-
conduit housing centerbody 33 using a plurality ofradial pins radial pin radial pins junction 224 between the internalcylindrical surface cylindrical surface radial pin centerbody 33 and awall conduit housing radial pin radial pins conduit housing centerbody 33; - c. providing for retaining each the
radial pin centerbody 33 and thewall conduit housing - d. shrouding a portion of a
bladed rotor 30 with a portion of the fluid-conduit housing bladed rotor 30 is rotatable with respect to thecenterbody 33 about anaxis 202′ that is substantially concentric with respect to the externalcylindrical surface conduit housing bladed rotor 30.
- a. sliding an internal
- In one set of embodiments, the method further comprises forming at least one of the corresponding
radial bore conduit housing radial bore centerbody 33 after the operation of sliding the internalcylindrical surface cylindrical surface - In another set of embodiments, the method further comprising providing a volute portion 204 i′ of a
fluid conduit 216 within the fluid-conduit housing outlet 208 of thefluid conduit 216 onto thebladed rotor 30 so as to provide for either a) a nominal direction offlow 264 of a fluid 21 onto or from thebladed rotor 30 that is substantially radial, b) for flow onto thebladed rotor 30, a nominal direction offlow 264 of a fluid 21 that is at least partially axially aftward relative to thecenterbody 33 with decreasing distance from thebladed rotor 30 or, c) for flow from thebladed rotor 30, a nominal direction offlow 264 of a fluid 21 that is at least partially axially forward relative to thecenterbody 33 with increasing distance from thebladed rotor 30. - A method of operating a
bladed rotor conduit housing -
- a. rotating a
bladed rotor rotor shaft 32 rotationally supported from acenterbody 33; - b. concentrically surrounding a portion of the
bladed rotor shroud portion conduit housing bladed rotor tip clearance 212; and - c. causing the fluid-
conduit housing centerbody 33, thereby thermally expanding the fluid-conduit housing centerbody 33 in a radial direction by action of a plurality ofradial pins conduit housing radial pins conduit housing centerbody 33, the plurality ofradial pins conduit housing centerbody 33, and the plurality ofradial pins shroud portion conduit housing bladed rotor conduit housing
- a. rotating a
- In one set of embodiments, the fluid-
conduit housing 158 comprises anturbocharger exhaust housing 158 of the turbocharger assembly 200.2, thebladed rotor 30 comprises aturbine rotor 30 of a turbocharger assembly 200.2 driven byexhaust gases 21 of an internal combustion engine 14, 14.2 directed through a portion of afluid conduit 216 within theturbocharger exhaust housing 158 onto theturbine rotor 30, for example, through a volute 204 i in a region that extends forward of an aft boundary 206 i of anoutlet 208 of the volute 204 i onto theturbine rotor 30 so as to provide for a direction offlow 264 of theexhaust gases 21 onto theturbine rotor 30 that is either substantially radially inwards or at least partially axially aftward from thecenterbody 33 with decreasing distance from theturbine rotor 30. - In another set of embodiments, the fluid-
conduit housing 142 comprises acompressor housing 142 of a turbocharger assembly 200.2, and thebladed rotor 56 comprises acompressor rotor 56 of the turbocharger assembly 200.2 that provides for compressing and pumping air into a portion of afluid conduit 216 within thecompressor housing 142 and then into an internal combustion engine 14, 14.2. - While specific embodiments have been described in detail in the foregoing detailed description and illustrated in the accompanying drawings, those with ordinary skill in the art will appreciate that various modifications and alternatives to those details could be developed in light of the overall teachings of the disclosure. It should be understood, that any reference herein to the term “or” is intended to mean an “inclusive or” or what is also known as a “logical OR”, wherein when used as a logic statement, the expression “A or B” is true if either A or B is true, or if both A and B are true, and when used as a list of elements, the expression “A, B or C” is intended to include all combinations of the elements recited in the expression, for example, any of the elements selected from the group consisting of A, B, C, (A, B), (A, C), (B, C), and (A, B, C); and so on if additional elements are listed. Furthermore, it should also be understood that the indefinite articles “a” or “an” and the corresponding associated definite articles “the’ or “said”, are each intended to mean one or more unless otherwise stated, implied, or physically impossible. Yet further, it should be understood that the expressions “at least one of A and B, etc.”, “at least one of A or B, etc.”, “selected from A and B, etc.” and “selected from A or B, etc.” are each intended to mean either any recited element individually or any combination of two or more elements, for example, any of the elements from the group consisting of “A”, “B”, and “A AND B together”, etc. Yet further, it should be understood that the expressions “one of A and B, etc.” and “one of A or B, etc.” are each intended to mean any of the recited elements individually alone, for example, either A alone or B alone, etc., but not A AND B together. Furthermore, it should also be understood that unless indicated otherwise or unless physically impossible, that the above-described embodiments and aspects can be used in combination with one another and are not mutually exclusive. Accordingly, the particular arrangements disclosed are meant to be illustrative only and not limiting as to the scope of the invention, which is to be given the full breadth of the appended claims, and any and all equivalents thereof.
Claims (35)
1. An apparatus, comprising:
a. a centerbody, wherein said centerbody comprises:
i. a bearing housing;
ii. at least one bearing within and operatively coupled to said bearing housing; and
iii. a rotor shaft rotationally supported by said at least one bearing spaced along said rotor shaft;
b. at least one bladed rotor operatively coupled to said rotor shaft supported by said centerbody; and
c. at least one fluid-conduit housing in cooperation with said at least one bladed rotor, wherein said at least one bladed rotor is operative within a corresponding fluid conduit defined by said fluid-conduit housing, said at least one fluid-conduit housing incorporates an inlet to provide for receiving a corresponding fluid within said fluid conduit that provides for either driving or being pumped by a corresponding said at least one bladed rotor responsive to an interaction of said corresponding fluid with a plurality of blades of said at least one bladed rotor, said at least one fluid-conduit housing comprises an internal cylindrical surface at an end thereof that mates with a corresponding external cylindrical surface on a corresponding side of said centerbody, an axis of said external cylindrical surface is substantially concentric with an axis of rotation of said at least one bladed rotor and with an axis of said internal cylindrical surface, said at least one fluid-conduit housing is operatively coupled to said centerbody with a plurality of radial pins, so that said internal cylindrical surface is free to thermally expand relative to said external cylindrical surface, each radial pin of said plurality of radial pins is slideably engaged with at least one of a corresponding radial bore in said at least one fluid-conduit housing or a corresponding radial bore in said centerbody, said radial bore in said fluid-conduit housing is closed to said fluid conduit; each said radial pin is oriented radially with respect to both said internal cylindrical surface and said external cylindrical surface, said plurality of radial pins are arranged around said centerbody so as to provide for said internal and external cylindrical surfaces to remain substantially concentric regardless of a thermal expansion of said at least one fluid-conduit housing relative to said centerbody, and at least a portion of said at least one fluid-conduit housing comprises a shroud portion that substantially concentrically surrounds a portion of said at least one bladed rotor.
2. A apparatus as recited in claim 1 , wherein said at least one bladed rotor comprises at least one of the group selected from a compressor rotor and a turbine rotor.
3. A apparatus as recited in claim 1 , wherein said internal and external cylindrical surfaces are mated with an interference fit at room temperature.
4. A apparatus as recited in claim 1 , wherein said plurality of radial pins are symmetrically located around said centerbody and around said at least one fluid-conduit housing.
5. A apparatus as recited in claim 1 , wherein said plurality of radial pins are equi-spaced around said centerbody and around said at least one fluid-conduit housing.
6. A apparatus as recited in claim 1 , wherein said plurality of radial pins comprise at least three radial pins.
7. A apparatus as recited in claim 1 , wherein at least one said radial pin is slideably engaged with both said corresponding radial bore in said at least one fluid-conduit housing and said corresponding radial bore in said centerbody, and at least one said radial pin is retained to said at least one fluid-conduit housing by either staking or welding.
8. A apparatus as recited in claim 1 , wherein at least one said radial pin is retained to said at least one fluid-conduit housing by an interference fit in said radial bore in said at least one fluid-conduit housing.
9. A apparatus as recited in claim 1 , wherein at least one said radial pin is retained by engagement of a screw thread portion of at least one said radial pin with a corresponding screw thread portion in one of said at least one fluid-conduit housing and said centerbody.
10. A apparatus as recited in claim 2 , wherein said at least one bladed rotor comprises said turbine rotor of a turbocharger, said fluid-conduit housing comprises an exhaust housing configured to receive exhaust gases from an internal combustion engine, and a portion of said exhaust housing comprises said shroud portion that substantially concentrically surrounds said portion of said turbine rotor.
11. A apparatus as recited in claim 10 , wherein said exhaust housing comprises a volute portion of said fluid conduit that is operative between said inlet and said turbine rotor, an aft boundary of said volute portion comprises a surface of revolution about said axis of rotation of said turbine rotor where said fluid is discharged from said volute portion onto said turbine rotor during operation of said turbocharger, and said aft boundary is located further from said centerbody than a corresponding opposing forward boundary of said volute portion.
12. A apparatus as recited in claim 11 , wherein said surface of revolution comprises a planar surface that is substantially perpendicular to said axis of rotation.
13. A apparatus as recited in claim 10 , wherein a tip clearance between said shroud portion of said exhaust housing and at least one tip of said turbine rotor is less than 4 percent of a radius of said turbine rotor at said at least one tip of said turbine rotor at room temperature.
14. A apparatus as recited in claim 10 , further comprising a seal operative between an end face of said exhaust housing and said centerbody, so as to provide for preventing said exhaust gases from escaping said exhaust housing from a gap between said exhaust housing and said centerbody, wherein said seal is configured so as to provide for accommodating thermal expansion or contraction of said exhaust housing relative to said centerbody.
15. A apparatus as recited in claim 14 , wherein said seal is operative within a groove in said end face of said exhaust housing.
16. A apparatus as recited in claim 15 , wherein said seal comprises a thermal gasket.
17. A apparatus as recited in claim 15 , wherein said seal comprises a metallic seal comprising a radial cross-section selected from the group consisting of a V-shaped cross-section and a C-shaped cross-section.
18. A apparatus as recited in claim 14 , wherein said external cylindrical surface is stepped into said corresponding side of said centerbody, and said seal is operative between said end face and a radial surface extending radially outwards from said external cylindrical surface that is stepped into said corresponding side of said centerbody.
19. A apparatus as recited in claim 10 , further comprising a heat shield operative between said centerbody and said turbine rotor within an axial bore wherein said exhaust housing, wherein said axial bore has a diameter in excess of a maximum diameter of said turbine rotor.
20. A apparatus as recited in claim 2 , wherein said at least one bladed rotor comprises said compressor rotor of a turbocharger, and said at least one fluid-conduit housing comprises a compressor housing surrounding said compressor rotor, wherein said compressor housing comprises:
a. a central inlet; and
b. a volute diffuser.
21. A method of operatively coupling a fluid-conduit housing to a centerbody, comprising:
a. sliding an internal cylindrical surface over a corresponding external cylindrical surface, wherein said internal cylindrical surface is located at an end of a fluid-conduit housing, and said external cylindrical surface is located on a side of a centerbody;
b. operatively coupling said fluid-conduit housing to said centerbody using a plurality of radial pins, wherein each radial pin of said plurality of radial pins extends radially across a junction between said internal cylindrical surface and said external cylindrical surface, each said radial pin engages both said centerbody and a wall of said fluid-conduit housing so as to prevent more than insubstantial relative axial movement therebetween, and each radial pin of said plurality of radial pins is slideably engaged with at least one of a corresponding radial bore in said fluid-conduit housing or a corresponding radial bore in said centerbody;
c. providing for retaining each said radial pin in engagement with both said centerbody and said wall of said fluid-conduit housing; and
d. shrouding a portion of a bladed rotor with a portion of said fluid-conduit housing, wherein said bladed rotor is rotatable with respect to said centerbody about an axis that is substantially concentric with respect to said external cylindrical surface and with respect to said portion of said fluid-conduit housing that shrouds said bladed rotor.
22. A method of operatively coupling a fluid-conduit housing to a centerbody as recited in claim 21 , wherein at room temperature a diameter of said corresponding external cylindrical surface exceeds a corresponding diameter of said internal cylindrical surface so as to provide for an interference fit therebetween when both said centerbody and said fluid-conduit housing are at said room temperature.
23. A method of operatively coupling a fluid-conduit housing to a centerbody as recited in claim 21 , further comprising forming at least one of said corresponding radial bore in said fluid-conduit housing or said corresponding radial bore in said centerbody after the operation of sliding said internal cylindrical surface over said corresponding external cylindrical surface.
24. A method of operatively coupling a fluid-conduit housing to a centerbody as recited in claim 21 , further comprising slideably engaging at least one said radial pin with both said corresponding radial bore in said fluid-conduit housing and said corresponding radial bore in said centerbody.
25. A method of operatively coupling a fluid-conduit housing to a centerbody as recited in claim 21 , further comprising retaining at least one said radial pin is retained to said fluid-conduit housing by either staking or welding.
26. A method of operatively coupling a fluid-conduit housing to a centerbody as recited in claim 21 , further comprising retaining at least one said radial pin is retained to said fluid-conduit housing by an interference fit in said radial bore in said fluid-conduit housing.
27. A method of operatively coupling a fluid-conduit housing to a centerbody as recited in claim 21 , further comprising retaining at least one said radial pin by engaging a screw thread portion of at least one said radial pin with a corresponding screw thread portion in one of said fluid-conduit housing and said centerbody.
28. A method of operatively coupling a fluid-conduit housing to a centerbody as recited in claim 21 , further comprising installing a heat shield operative between a portion of said side of said centerbody and said bladed rotor, wherein said heat shield provides for substantially filling an annulus located between a portion of said centerbody proximate to said bladed rotor and an axial bore in said fluid-conduit housing that provides for receiving said bladed rotor therethrough during the operation of sliding said internal cylindrical surface of said fluid-conduit housing over said corresponding external cylindrical surface of said centerbody.
29. A method of operatively coupling a fluid-conduit housing to a centerbody as recited in claim 21 , further comprising providing a volute portion of a fluid conduit within said fluid-conduit housing that extends forward of an aft boundary of an outlet of said fluid conduit onto said bladed rotor so as to provide for a direction of flow of a fluid onto or from said bladed rotor that is either substantially radially inwards or at least partially axially aftwards from said centerbody with decreasing distance from said bladed rotor.
30. A method of operatively coupling a fluid-conduit housing to a centerbody as recited in claim 21 , further comprising sealing a gap between a portion of an end face of said fluid-conduit housing and a portion of said side of said centerbody, wherein the operation of sealing said gap provides for relative radial movement of said portion of said end face of said fluid-conduit housing relative to said centerbody responsive to a thermal expansion of said fluid-conduit housing.
31. A method of operating a bladed rotor in cooperation with an associated fluid-conduit housing, comprising:
a. rotating a bladed rotor with a rotor shaft rotationally supported from a centerbody;
b. concentrically surrounding a portion of said bladed rotor with a shroud portion of a fluid-conduit housing that is radially separated from said bladed rotor by an associated tip clearance; and
c. causing said fluid-conduit housing to be heated relative to said centerbody, thereby thermally expanding said fluid-conduit housing relative to said centerbody in a radial direction by action of a plurality of radial pins operative between said centerbody and said fluid-conduit housing, wherein said plurality of radial pins provide for unrestrained relative radial movement of said fluid-conduit housing relative to said centerbody, said plurality of radial pins provide for axially retaining said fluid-conduit housing against said centerbody, and said plurality of radial pins provides for substantially maintaining a concentricity of said shroud portion of said fluid-conduit housing relative to said portion of said bladed rotor responsive to the operation of thermally expanding said fluid-conduit housing.
32. A method of operating a bladed rotor in cooperation with an associated fluid-conduit housing as recited in claim 31 , wherein said fluid-conduit housing comprises an exhaust housing of a turbocharger, and said bladed rotor comprises a turbine rotor of said turbocharger driven by exhaust gases of an internal combustion engine directed through a portion of a fluid conduit within said exhaust housing onto said turbine rotor.
33. A method of operating a bladed rotor in cooperation with an associated fluid-conduit housing as recited in claim 32 , wherein said portion of said fluid conduit comprises a volute, further comprising causing said exhaust gases to flow within said volute in a region that extends forward of an aft boundary of an outlet of said volute onto said turbine rotor so as to provide for a direction of flow of said exhaust gases onto said turbine rotor that is either substantially radially inwards or at least partially axially aftwards from said centerbody with decreasing distance from said turbine rotor.
34. A method of operating a bladed rotor in cooperation with an associated fluid-conduit housing as recited in claim 31 , wherein said fluid-conduit housing comprises a compressor housing of a turbocharger, and said bladed rotor comprises a compressor rotor of said turbocharger that provides for compressing and pumping air into a portion of a fluid conduit within said compressor housing and then into an internal combustion engine.
35. A method of operating a bladed rotor in cooperation with an associated fluid-conduit housing as recited in claim 31 , further comprising sealing a gap between a portion of an end face of said fluid-conduit housing and a portion of said side of said centerbody, wherein the operation of sealing said gap provides for relative radial movement of said portion of said end face of said fluid-conduit housing relative to said centerbody responsive to a thermal expansion of said fluid-conduit housing.
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/531,577 US20130004291A1 (en) | 2011-06-28 | 2012-06-24 | Turbomachine Fluid-Conduit Housing Coupling System and Method |
PCT/US2012/043925 WO2013003251A1 (en) | 2011-06-28 | 2012-06-25 | Turbomachine fluid-conduit housing coupling system and method |
US13/845,429 US20130219884A1 (en) | 2009-01-20 | 2013-03-18 | Internal Combustion Engine Cylinder Head With Integral Exhaust Runners And Turbocharger Housing |
US14/475,778 US9010108B2 (en) | 2009-01-20 | 2014-09-03 | Turbocharger compressor rotor alignment system |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201161501891P | 2011-06-28 | 2011-06-28 | |
US13/531,577 US20130004291A1 (en) | 2011-06-28 | 2012-06-24 | Turbomachine Fluid-Conduit Housing Coupling System and Method |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/690,767 Continuation-In-Part US8418458B2 (en) | 2009-01-20 | 2010-01-20 | Turbocharger core |
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Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/845,429 Continuation US20130219884A1 (en) | 2009-01-20 | 2013-03-18 | Internal Combustion Engine Cylinder Head With Integral Exhaust Runners And Turbocharger Housing |
Publications (1)
Publication Number | Publication Date |
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US20130004291A1 true US20130004291A1 (en) | 2013-01-03 |
Family
ID=47390861
Family Applications (3)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/531,577 Abandoned US20130004291A1 (en) | 2009-01-20 | 2012-06-24 | Turbomachine Fluid-Conduit Housing Coupling System and Method |
US13/845,429 Abandoned US20130219884A1 (en) | 2009-01-20 | 2013-03-18 | Internal Combustion Engine Cylinder Head With Integral Exhaust Runners And Turbocharger Housing |
US14/475,778 Active US9010108B2 (en) | 2009-01-20 | 2014-09-03 | Turbocharger compressor rotor alignment system |
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Application Number | Title | Priority Date | Filing Date |
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US13/845,429 Abandoned US20130219884A1 (en) | 2009-01-20 | 2013-03-18 | Internal Combustion Engine Cylinder Head With Integral Exhaust Runners And Turbocharger Housing |
US14/475,778 Active US9010108B2 (en) | 2009-01-20 | 2014-09-03 | Turbocharger compressor rotor alignment system |
Country Status (2)
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US (3) | US20130004291A1 (en) |
WO (1) | WO2013003251A1 (en) |
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US20140157750A1 (en) * | 2011-07-28 | 2014-06-12 | Nuovo Pignone S.P.A | Turbo-compressor train with rolling bearings and related assembly method |
US20160265554A1 (en) * | 2015-03-09 | 2016-09-15 | Caterpillar Inc. | Turbocharger with dual-use mounting holes |
US20160369645A1 (en) * | 2015-06-11 | 2016-12-22 | General Electric Company | Methods and system for a turbocharger |
US9657596B2 (en) | 2014-09-26 | 2017-05-23 | Electro-Motive Diesel, Inc. | Turbine housing assembly for a turbocharger |
WO2017174287A1 (en) * | 2016-04-06 | 2017-10-12 | Continental Automotive Gmbh | Turbocharger for an internal combustion engine |
WO2017190884A1 (en) * | 2016-05-04 | 2017-11-09 | Continental Automotive Gmbh | Turbine housing for a turbocharger of an internal combustion engine, and turbocharger |
US20180163620A1 (en) * | 2014-07-04 | 2018-06-14 | Volvo Truck Corporation | A turbocharger unit |
US20180230850A1 (en) * | 2015-08-07 | 2018-08-16 | Borgwarner Inc. | A pulse-separated axial turbine stage with radial-axial inlet guide vanes |
US11555439B2 (en) * | 2019-05-02 | 2023-01-17 | Fca Us Llc | Cylinder head with integrated turbocharger |
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US9689397B2 (en) | 2014-06-13 | 2017-06-27 | GM Global Technology Operations LLC | Turbine outlet diffuser |
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US20140157750A1 (en) * | 2011-07-28 | 2014-06-12 | Nuovo Pignone S.P.A | Turbo-compressor train with rolling bearings and related assembly method |
US10794269B2 (en) * | 2014-07-04 | 2020-10-06 | Volvo Truck Corporation | Turbocharger unit |
US20180163620A1 (en) * | 2014-07-04 | 2018-06-14 | Volvo Truck Corporation | A turbocharger unit |
US9657596B2 (en) | 2014-09-26 | 2017-05-23 | Electro-Motive Diesel, Inc. | Turbine housing assembly for a turbocharger |
US20160265554A1 (en) * | 2015-03-09 | 2016-09-15 | Caterpillar Inc. | Turbocharger with dual-use mounting holes |
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US20180230850A1 (en) * | 2015-08-07 | 2018-08-16 | Borgwarner Inc. | A pulse-separated axial turbine stage with radial-axial inlet guide vanes |
WO2017174287A1 (en) * | 2016-04-06 | 2017-10-12 | Continental Automotive Gmbh | Turbocharger for an internal combustion engine |
WO2017190884A1 (en) * | 2016-05-04 | 2017-11-09 | Continental Automotive Gmbh | Turbine housing for a turbocharger of an internal combustion engine, and turbocharger |
CN109072717A (en) * | 2016-05-04 | 2018-12-21 | 大陆汽车有限公司 | The turbine cylinder and turbocharger of turbocharger for internal combustion engine |
US11098614B2 (en) | 2016-05-04 | 2021-08-24 | Vitesco Technologies GmbH | Turbine housing for a turbocharger of an internal combustion engine, and turbocharger |
US11555439B2 (en) * | 2019-05-02 | 2023-01-17 | Fca Us Llc | Cylinder head with integrated turbocharger |
Also Published As
Publication number | Publication date |
---|---|
US20130219884A1 (en) | 2013-08-29 |
US20140366526A1 (en) | 2014-12-18 |
WO2013003251A1 (en) | 2013-01-03 |
US9010108B2 (en) | 2015-04-21 |
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