US3734650A - Exhaust-gas driven turbochargers - Google Patents
Exhaust-gas driven turbochargers Download PDFInfo
- Publication number
- US3734650A US3734650A US00139156A US13915671A US3734650A US 3734650 A US3734650 A US 3734650A US 00139156 A US00139156 A US 00139156A US 13915671 A US13915671 A US 13915671A US 3734650 A US3734650 A US 3734650A
- Authority
- US
- United States
- Prior art keywords
- wheel
- blades
- exhaust gas
- turbine
- turbine wheel
- 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.)
- Expired - Lifetime
Links
- 239000007789 gas Substances 0.000 claims abstract description 101
- 238000002485 combustion reaction Methods 0.000 claims abstract description 10
- 230000005484 gravity Effects 0.000 claims description 5
- 230000002349 favourable effect Effects 0.000 abstract description 3
- 230000015572 biosynthetic process Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 9
- 239000002699 waste material Substances 0.000 description 3
- 206010065929 Cardiovascular insufficiency Diseases 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000004035 construction material Substances 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 239000002912 waste gas Substances 0.000 description 1
Images
Classifications
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/026—Scrolls for radial machines or engines
-
- 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
Definitions
- An exhaust gas turbocharger for use in connection with internal combustion engines has a turbine wheel and a compressor wheel which are arranged on a common drive shaft.
- the turbine wheel is provided with guide blades structured to be traversed by gases diagonally from the outside (periphery) of the wheel to ward the inside (center) thereof.
- the blades have inlet edges and outlet edges whereby the inlet edges are substantially inclined, so that an entering gas flow is directed substantially perpendicularly to each inlet edge when the same is projected in the meridian plane, the cross section of the turbine wheel blades being arranged radially in sectional planes perpendicular to the wheel axis.
- the blades of the turbine wheel form at the inlet edge an entrance angle of less than 90 with respect to the wheel axis.
- the turbine has a housing constructed to constitute a single-flow spiral casing for gas admission over the entire circumferential sur face of the turbine wheel, at the entrance portions of which there are provided at least two exhaust gas con duits, which are joined in such a way that their inlet cross section to the spiral casing is only slightly larger than the cross section at the respective ends of the gas conduits.
- the inlet edges of the blades of the turbine wheel assume a most favorable aerodynamic formation and are streamlined in profile.
- the mean wheel diameter at the outlet edge of each blade of the compressor wheel is less than approximately 88 percent of the maximum outer diameter of the blades of the turbine wheel.
- the gas flow through the compressor wheel is diagonally directed for traversal of the wheel from the inside toward the outside thereof.
- the invention concerns a waste or exhaust gas turbocharger for use in connection with internal combustion engines in which a turbo-charger is operatively connected a turbineand a compressor wheel, preferably via a common drive shaft.
- waste gas turbo-superchargers for internal combustion engines are adjusted to the average energy per time unit of the exhaust gases which emanate from respective cylinders of an internal combustion engine.
- the turbine of the gas turbo-charger is designed as a centripetal turbine, which is traversed in radial direction from the outside or exterior to the inner part of the turbine blade wheel from where these gases issue axially.
- centripetal turbines are not adapted to a periodically greatly varying or changing energy supply in order to achieve optimal employment thereof.
- the form of the blade wheel in particular the form of its blades and those of the compressor wheel, is designed and developed according to certain viewpoints taking into consideration only turbines to which gases of constant energy are fed and administered.
- Compressor wheels of known gas turbosuperchargers of this kind are designed generally as radial wheels whose diameters according to the state of the art should be as far as possible equal to the diameter of the turbine wheel.
- the gasturbo-supercharger according to the invention is lighter in weight and smaller than known structures of gas turbo-superchargers.
- the reduction in weight has the further advantage that smaller quantities of expensive construction material is employed, so that the exhaust gas turbo-supercharger according to the invention is more economical and less expensive to produce than known exhaust gas aggregates of this type.
- Gas turbo-superchargers for supercharging pistondriven internal combustion engines where the turbineand the compressor wheels are arranged on a common shaft, are known in the art, but there remains still the problem to be solved pursuant to this invention, namely, that the turbine wheel is to be traversed diagonally from the exterior to the inner part thereof so that the inlet edges of the blades of the turbine wheel, projected in meridian planes, extend substantially perpendicularly to the direction of the entering gas current, projected into the same meridian plane, and further, that the blade cross sections of the turbine wheel are radially arranged in sectional planes normal to the axis.
- the blades of the turbine wheel form at the inlet edge an entrance angle of less than 90
- the turbine housing is designed as a single-flow spiral housing or casing admitting the contemplated medium or fluid to the turbine wheel over its entire circumferential surface, on whose entrance part are joined at least two exhaust gas pipe lines emanating from the cylinders of the internal combustion engine in such a way that the inlet cross-section at a tongue-shaped guide edge of the single flow spiral casing is only slightly larger than the cross-section at the discharge end of each individual exhaust gas pipe lines.
- FIG. 1 is an axial section through an exhaust gas turbo-charger embodying the invention.
- FIG. 2 shows, in a diagram, pressure conditions of the exhaust gas arriving at the turbine as related to the crank angle.
- FIG. 3 is a schematic representation of the entrance part of a set of blades of a known radial flow turbine and its associated velocity vector diagram.
- FIG. 4 illustrates schematically the dependence of the efficiency on the characteristic of a radial flowturbine according to FIG. 3.
- FIG. 5 is a schematic representation of the entrance part of a blade set for a diagonal-flow turbine pursuant to the invention, as well as the velocity vector diagrams associated therewith.
- FIG. 6 shows, in a diagram, the dependence of the efficiency on a speed coefficient of an exhaust gas turbocharger according to FIG. 5.
- FIG. 7 is a section taken along the line 7 7 of FIG.
- FIG. 8 is a section taken along line 88 of FIG. 7.
- FIG. 9 shows a detail on an enlarged scale of a lefthand portion of FIG. I, to which reference is had in the description.
- FIG. 10 illustrates a velocity vector diagram derived from FIG. 9.
- FIG. 11 shows, in development, a portion of the blade wheel of FIG. 9.
- FIG. 1 there is disclosed a turbine wheel 1 with blades 2.
- the broken line 3 denotes the path of a central filamentous flow line, (circularly projected in axial section of FIG. 1 Gas admission to turbine wheel 1 occurs diagonally in the direction 36.
- the flow passage likewise takes place substantially diagonally to the represented meridian section.
- the turbine wheel 1 projects, at the inlet edge 4 of blade 2, by an amount LU in the direction of bearing 14 with respect to the'rear wall 5 of wheel 1, so that the wheel length L is extremely small in the direction of the axis and the center of gravity of wheel 2 is displaced tol.
- the mean diameter D1 at the inlet edge 4 is kept smaller than the maximum diameter D at the outlet edge 16', and further 2.
- the length L of the wheel is reduced by the difference between the length of the inlet edge 4 and the measure of projection in respect to the axis thereof, so that material will be saved.
- the outside diameter D2 of outlet edge 16 of turbine wheel 1 is the maximum diameter of wheel 1.
- the mean diameter D1 is smaller than the outside diameter (maximum diameter) D2 of outlet edge 16. This is due to the fact (as pointed out herein above) that the inlet edge 4 is obliquely cut off at an angle B.
- the spiral casing 7 is thus kept smaller and cheaper in its construction.
- FIG. 1 shows the compressor wheel 37 with blades 12 for air flow traversal from the inside toward the peripheral edge 13 or outside.
- the mean diameter D12 of outlet edge 13 of blades 12 should not be greater than 88 percent of the outer diameter (maximum diameter) D2 of the outlet edge 16 of turbine wheel 1.
- the compressor wheel 37 as shown, is traversed by air diagonally, i.e., it is administered axially, the flow taking place between edge 26 and outlet edge 13 in diagonal direction 38.
- the outlet edge 13 is so inclined relative to the direction of the axis of rotation by an angle B4 that it extends perpendicularly to the direction 38 of the escaping or outflowing air.
- the outlet edge 13 of blade 12 of compressor wheel 13 could also project, with respect to the rear wall of this wheel, by a certain amount in the direction of bearing 14 so as to obtain an extremely small axial length of the wheel, a displacement of the center of gravity of blades 12 toward the bearing 14 of shaft 15 and an improved quietness during running of compressor wheel 37.
- the maximum diameter (outer diameter) D11 of inlet edge 26 of blades 12 of compressor wheel 37 is also greater than the mean diameter D12 of outlet edge 13. This has the advantage as already pointed out, that the maximum diameter (outer diameter) D2 of the outlet edge 16 of the turbine wheel is greater than the mean diameter D1 of the inlet edge 4.
- FIG. 2 shows the pressure P in front of the turbine as a function of the crank angle (from 630to 180) of one of the cylinders of the internal combustion engine connected to the exhaust gas turbo-supercharger.
- Each individual cylinder yields a pressure course with periodically recurring maximum and minimum.
- the entire pressure course ahead of the turbine is obtained by superpositions of these pressure curves present in the individual cylinders.
- the course of the curve can be approximated by a step-like curve whose steps are designated with A, B, C, and D.
- the upper dead center is designated with OT and the lower dead center with UT.
- FIG. 2 Based on the periodically changing energy supply, according to FIG. 2, the utilization of the energy supplies for a known blade cascade (FIGS. 3, 4) and for a blade cascade according to the invention (FIGS. 5, 6) are compared.
- FIG. 3 shows schematically, in the lower portion, the entrance portion of the cascade of a conventional radial flow turbine (centripetal turbine).
- centripetal turbine centripetal turbine
- C is,according to FIG. 2, the mean pressure.
- the known radial flow turbine is constructed according to this mean pressure C.
- the aim of the present invention is therefore to improve the energy yield of the turbo-supercharger.
- the turbine wheel blades 2 are so inclined at their entrance portions 2a that this angle of inclination is equal to the angle B1 of the relative velocity WIA at the time of arrival of the energy surge (corresponding to the highest pressure stage A). Furthermore, the circumferential velocity U1 at the inlet edges of the blades is,according to the invention, higher than the corresponding circumferential velocity U1 of a known radial wheel according to FIG. 3.
- each blade 2 is given a profile which is streamlined.
- the degree of efficiency K is still very high even at small deviations of the entrance angle from the ideal entrance angle B1 in respect to the relative velocity W.
- the efficiency curve according to FIG. 6 this can be seen to show that the range of the maximum degree of efficiency of the impeller wheel according to the invention is much wider than that of the maximum degree of efficiency K of a known execution of a radial wheel according to FIG. 3.
- the blades 2 are curved in the range of their inlet edges in cylinder sections and so cut off (angle B3) that the inlet edge 4 in the meridian plane is substantially perpendicular to the relative velocity W1 (direction 36). Consequently, the blade cross sections can be arranged radially in sectional planes perpendicular to the axis, though the entering angle B1 is less than 90.
- FIG. 7 shows a section taken along line 77 through the right half of the turbine of FIG. 1.
- the mean radius r1 of wheel 1 which is equal to half the diameter D1 shown in FIG. 1.
- FIG. 8 shows a section tbrough FIG. 7 along line 8-8.
- FIG. 8 shows how the cross sections Fp of the two gas lines 40 and 41, which are separated by the partition 40a, pass over into the feed cross section Fsp of the single-flow spiral casing 7 on tongue-like guide edge 30.
- the feed cross section Fsp at tongue edge 30 of the single-flow spiral casing 7 should be equal to each of the cross sections Fp of the two exhaust gas conduits or lines 40 and 41, so that the velocity Cp in cross section Fp passes over unchanged, that is, without any substantial delay or acceleration and without any substantial change in direction, directly into the velocity cl (see also FIG. 5) in the feed cross section Fsp of spiral casing 7.
- the smallest distance r, of the direction of the gas current entering with the velocity Cp from the axis of rotation should be at most equal to the 1.0 to the 1.4 fold of the mean wheel radius r in order to avoid greater velocity variations of the waste or exhaust gas current until it enters wheel 1.
- FIG. 9 shows a detail of the left-hand portion of FIG. 1, hence from the compressor wheel.
- This compressor wheel 37 carries wheel blades 12 with the beveled or obliquely cut off (,84) outlet edge 13.
- FIG. 10 shows a velocity vector diagram at point E of outlet edge 14.
- U is the circumferential velocity at point E, C2 the absolute air outlet velocity, and W2 the relative velocity of the outflowing air.
- the exit angle [32 is, according to the invention, less than i.e., the blades are inclined toward the rear at outlet edge 13 and against the circumferential direction.
- Compressor blades inclined toward the rear at the outlet [32 less than 90) have the advantage that the charging pressure depends less on the volume current than in blades with radially terminating ends.
- the blades of the compressor wheel 37 are so designed that the blade cross sections are arranged radially in sectional planes perpendicular to the axis. That this is possible in the compressor wheel traversed diagonally according to the invention, in contrast to the conventional radial wheels, though [32 is less than 90, will be explained on the basis of FIGS. 9, l0 and 11, where FIG. 11 shows a portion of the circumference of the wheel of FIG. 9 in developed form. 4
- E is the point of outlet edge 13 on blade root 42.
- the velocity vector diagram represented in FIG. 10 was turned about W2m into the plane in which the velocity W2, with which the air issues from the compressor wheel (relative velocity), appears in correct size.
- blade root 42 is straight, in the represented meridian section, between the points E and E.
- From the projection of E into the plane of the velocity vector diagram (FIG. results in FIG. 10 the direction of W2, that is, the angle B2, which is less than 90.
- point F for example, is arranged radially above E, as it is illustrated in FIG. 11, that is, the blade cross sections are arranged radially in sectional planes perpendicular to the axis.
- An exhaust gas turbocharger for use with internal combustion engines, comprising turbine and compressor wheels arranged on a common shaft; said turbine wheel having guide blades structured to be traversed by gases diagonally from the outside of said turbine wheel to the inside thereof; said blades having inlet edges substantially inclined, so that the direction of an entering gas flow, as projected in a meridian plane, is perpendicular to said inlet edges, as projected in the same meridian plane; the cross-section of said turbine wheel guide blades being arranged radially in sectional planes perpendicular to the turbine wheel axis; said turbine wheel guide blades forming, at the inlet edge, an entrance angle of less than 90 with respect to the turbine wheel axis; a housing for said turbine wheel in the form of a single-flow spiral casing for gas admission to said turbine wheel over the entire circumferential surface thereof; and at least two gas conduits connecting respective engine cylinders into said single-flow spiral casing, said gas conduits being joined at said spiral casing in a manner such that the combined inlet
- An exhaust gas turbocharger according to claim 1, which in that the smallest distance r0 of the direction of the entering gas flow from the axis of rotation is at most equal to 1.0 to 1.4 times the mean wheel radius (rl) at the inlet ledge (4) of said blades (2) of said turbine wheel (1) 7.
- An exhaust gas turbocharger according to claim 10, in which the compressor wheel (37) is diagonally traversed from the center to the periphery of said wheel.
- An exhaust gas turbocharger in which the cross sections of the blades (12) of the compressor wheel (37) are arranged radially in sectional planes perpendicular to the wheel axis.
- each of the blades (12) of the compressor wheel (37) forms at the respective outlet edge (13) an outlet angle [32 of less than 90.
- each outlet edge of said compressor wheel and each inlet edge of said turbine wheel projects axially inwardly beyond the axially inner wall of the respective wheel.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19702021601 DE2021601A1 (de) | 1970-05-02 | 1970-05-02 | Abgasturbolader zur Aufladung von Kolbenverbrennungsmotoren |
DE19702021602 DE2021602A1 (de) | 1970-05-02 | 1970-05-02 | Abgasturbolader |
DE19702040901 DE2040901A1 (de) | 1970-08-18 | 1970-08-18 | Abgasturbolader |
Publications (1)
Publication Number | Publication Date |
---|---|
US3734650A true US3734650A (en) | 1973-05-22 |
Family
ID=27182570
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US00139156A Expired - Lifetime US3734650A (en) | 1970-05-02 | 1971-04-30 | Exhaust-gas driven turbochargers |
Country Status (7)
Country | Link |
---|---|
US (1) | US3734650A (zh) |
JP (1) | JPS5035604B1 (zh) |
ES (1) | ES195737Y (zh) |
FR (1) | FR2091094A5 (zh) |
GB (1) | GB1320854A (zh) |
NL (1) | NL7105769A (zh) |
SE (1) | SE360144B (zh) |
Cited By (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4101243A (en) * | 1975-02-28 | 1978-07-18 | Vsesohuzny nauchno-issledovatelsku I Proktno-Konstruk torsky institut. Dobychi Uglya Grdravlicheskin Sposobom "Vnllgidrougal" | Centrifugal two-stage pump |
FR2415200A2 (fr) * | 1977-01-24 | 1979-08-17 | Semt | Procede et dispositif d'amenagement de l'ecoulement des gaz dans un collecteur d'echappement d'un moteur a combustion interne |
EP0021738A1 (en) * | 1979-06-19 | 1981-01-07 | Household Manufacturing, Inc. | Floating ring bearing structure and turbocharger employing same |
WO1984004136A1 (en) * | 1983-04-11 | 1984-10-25 | William E Woollenweber | Internal combustion engine turbocharger |
US4541786A (en) * | 1982-09-03 | 1985-09-17 | Ford Motor Company | Ceramic turbocharger |
US4822242A (en) * | 1987-06-09 | 1989-04-18 | Yoichi Yamazaki | Variable capacity turbo supercharger |
EP0395825A1 (en) * | 1989-05-02 | 1990-11-07 | AlliedSignal Inc. | Turbocharger bearing assembly |
US5025629A (en) * | 1989-03-20 | 1991-06-25 | Woollenweber William E | High pressure ratio turbocharger |
US5372485A (en) * | 1992-11-14 | 1994-12-13 | Mercedes-Benz Ag | Exhaust-gas turbocharger with divided, variable guide vanes |
US5749707A (en) * | 1995-09-20 | 1998-05-12 | Unisia Jecs Corporation | Water pumps |
EP0781908A3 (en) * | 1995-12-26 | 1998-05-20 | Ishikawajima-Harima Heavy Industries Co., Ltd. | Turbocharger construction |
US6709235B2 (en) * | 2001-09-14 | 2004-03-23 | Honeywell International Inc. | Turbine housing for high exhaust temperature |
US6742989B2 (en) * | 2001-10-19 | 2004-06-01 | Mitsubishi Heavy Industries, Ltd. | Structures of turbine scroll and blades |
US20060177325A1 (en) * | 2004-01-16 | 2006-08-10 | Peterson David J Jr | Motor-driven pump for pool or spa |
WO2010100348A1 (fr) * | 2009-03-03 | 2010-09-10 | Melchior Jean F | Moteur a combustion interne suralimente |
CN1920260B (zh) * | 2001-10-19 | 2010-09-29 | 三菱重工业株式会社 | 透平涡形管道和动翼的构造 |
US20100247304A1 (en) * | 2009-03-31 | 2010-09-30 | General Electric Company | Exhaust plenum for a turbine engine |
US20110088379A1 (en) * | 2009-10-15 | 2011-04-21 | General Electric Company | Exhaust gas diffuser |
US7931437B1 (en) * | 2007-09-21 | 2011-04-26 | Florida Turbine Technologies, Inc. | Turbine case with inlet and outlet volutes |
US20130136590A1 (en) * | 2011-01-27 | 2013-05-30 | Hirotaka Higashimori | Radial turbine |
US9249687B2 (en) | 2010-10-27 | 2016-02-02 | General Electric Company | Turbine exhaust diffusion system and method |
US20160186568A1 (en) * | 2013-06-13 | 2016-06-30 | Continental Automotive Gmbh | Turbocharger With a Radial-Axial Turbine Wheel |
US9488070B2 (en) | 2012-06-21 | 2016-11-08 | Honeywell International Inc. | Turbine end intake structure for turbocharger, and turbocharger comprising the same |
US20170022830A1 (en) * | 2013-12-16 | 2017-01-26 | Cummins Ltd | Turbine housing |
DE102020202967A1 (de) | 2020-03-09 | 2021-09-09 | Vitesco Technologies GmbH | Abgasturbolader mit Integralgehäuse |
WO2023061641A1 (de) * | 2021-10-14 | 2023-04-20 | Vitesco Technologies GmbH | Turboladergehäuse und abgasturbolader mit integral-turborotorgehäuse und verdichtergehäusedeckel |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2701528A (en) * | 1948-08-31 | 1955-02-08 | Thompson Prod Inc | Turbine driven fuel pump |
GB750387A (en) * | 1953-03-18 | 1956-06-13 | Thompson Prod Inc | Improvements in or relating to pump assemblies |
DE1057137B (de) * | 1958-03-07 | 1959-05-14 | Maschf Augsburg Nuernberg Ag | Schaufelspaltdichtung bei Kreiselradmaschinen mit deckband- oder deckenscheibenlosenLaufraedern |
US3270495A (en) * | 1963-08-14 | 1966-09-06 | Caterpillar Tractor Co | Apparatus for controlling speed and vibration of engine turbochargers |
-
1971
- 1971-04-27 ES ES1971195737U patent/ES195737Y/es not_active Expired
- 1971-04-27 JP JP46027302A patent/JPS5035604B1/ja active Pending
- 1971-04-28 NL NL7105769A patent/NL7105769A/xx not_active Application Discontinuation
- 1971-04-30 US US00139156A patent/US3734650A/en not_active Expired - Lifetime
- 1971-04-30 SE SE05656/71A patent/SE360144B/xx unknown
- 1971-05-03 FR FR7115814A patent/FR2091094A5/fr not_active Expired
- 1971-05-03 GB GB1250971*[A patent/GB1320854A/en not_active Expired
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2701528A (en) * | 1948-08-31 | 1955-02-08 | Thompson Prod Inc | Turbine driven fuel pump |
GB750387A (en) * | 1953-03-18 | 1956-06-13 | Thompson Prod Inc | Improvements in or relating to pump assemblies |
DE1057137B (de) * | 1958-03-07 | 1959-05-14 | Maschf Augsburg Nuernberg Ag | Schaufelspaltdichtung bei Kreiselradmaschinen mit deckband- oder deckenscheibenlosenLaufraedern |
US3270495A (en) * | 1963-08-14 | 1966-09-06 | Caterpillar Tractor Co | Apparatus for controlling speed and vibration of engine turbochargers |
Cited By (36)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4101243A (en) * | 1975-02-28 | 1978-07-18 | Vsesohuzny nauchno-issledovatelsku I Proktno-Konstruk torsky institut. Dobychi Uglya Grdravlicheskin Sposobom "Vnllgidrougal" | Centrifugal two-stage pump |
FR2415200A2 (fr) * | 1977-01-24 | 1979-08-17 | Semt | Procede et dispositif d'amenagement de l'ecoulement des gaz dans un collecteur d'echappement d'un moteur a combustion interne |
EP0021738A1 (en) * | 1979-06-19 | 1981-01-07 | Household Manufacturing, Inc. | Floating ring bearing structure and turbocharger employing same |
US4541786A (en) * | 1982-09-03 | 1985-09-17 | Ford Motor Company | Ceramic turbocharger |
WO1984004136A1 (en) * | 1983-04-11 | 1984-10-25 | William E Woollenweber | Internal combustion engine turbocharger |
GB2149858A (en) * | 1983-04-11 | 1985-06-19 | William E Woollenweber | Internal combustion engine turbocharger |
US4565505A (en) * | 1983-04-11 | 1986-01-21 | Woollenweber William E | Combination flow turbine for internal combustion engine turbochargers |
US4822242A (en) * | 1987-06-09 | 1989-04-18 | Yoichi Yamazaki | Variable capacity turbo supercharger |
US5025629A (en) * | 1989-03-20 | 1991-06-25 | Woollenweber William E | High pressure ratio turbocharger |
EP0395825A1 (en) * | 1989-05-02 | 1990-11-07 | AlliedSignal Inc. | Turbocharger bearing assembly |
US5372485A (en) * | 1992-11-14 | 1994-12-13 | Mercedes-Benz Ag | Exhaust-gas turbocharger with divided, variable guide vanes |
US5749707A (en) * | 1995-09-20 | 1998-05-12 | Unisia Jecs Corporation | Water pumps |
EP0781908A3 (en) * | 1995-12-26 | 1998-05-20 | Ishikawajima-Harima Heavy Industries Co., Ltd. | Turbocharger construction |
US6709235B2 (en) * | 2001-09-14 | 2004-03-23 | Honeywell International Inc. | Turbine housing for high exhaust temperature |
US6742989B2 (en) * | 2001-10-19 | 2004-06-01 | Mitsubishi Heavy Industries, Ltd. | Structures of turbine scroll and blades |
CN1920260B (zh) * | 2001-10-19 | 2010-09-29 | 三菱重工业株式会社 | 透平涡形管道和动翼的构造 |
EP1304445A3 (en) * | 2001-10-19 | 2007-10-24 | Mitsubishi Heavy Industries, Ltd. | Structure of radial turbine scroll and blades |
CN100447373C (zh) * | 2001-10-19 | 2008-12-31 | 三菱重工业株式会社 | 透平涡形管道和动翼的构造 |
US20090100589A1 (en) * | 2004-01-16 | 2009-04-23 | Peterson Jr David J | Motor-driven pump for pool or spa |
US20060177325A1 (en) * | 2004-01-16 | 2006-08-10 | Peterson David J Jr | Motor-driven pump for pool or spa |
US7931437B1 (en) * | 2007-09-21 | 2011-04-26 | Florida Turbine Technologies, Inc. | Turbine case with inlet and outlet volutes |
WO2010100348A1 (fr) * | 2009-03-03 | 2010-09-10 | Melchior Jean F | Moteur a combustion interne suralimente |
FR2942850A1 (fr) * | 2009-03-03 | 2010-09-10 | Melchior Jean F | Moteur a combustion interne suralimente |
US20100247304A1 (en) * | 2009-03-31 | 2010-09-30 | General Electric Company | Exhaust plenum for a turbine engine |
US8109720B2 (en) * | 2009-03-31 | 2012-02-07 | General Electric Company | Exhaust plenum for a turbine engine |
US20110088379A1 (en) * | 2009-10-15 | 2011-04-21 | General Electric Company | Exhaust gas diffuser |
US9249687B2 (en) | 2010-10-27 | 2016-02-02 | General Electric Company | Turbine exhaust diffusion system and method |
US8845278B2 (en) * | 2011-01-27 | 2014-09-30 | Mitsubishi Heavy Industries, Ltd. | Radial turbine |
US20130136590A1 (en) * | 2011-01-27 | 2013-05-30 | Hirotaka Higashimori | Radial turbine |
US9488070B2 (en) | 2012-06-21 | 2016-11-08 | Honeywell International Inc. | Turbine end intake structure for turbocharger, and turbocharger comprising the same |
US20160186568A1 (en) * | 2013-06-13 | 2016-06-30 | Continental Automotive Gmbh | Turbocharger With a Radial-Axial Turbine Wheel |
US10190415B2 (en) * | 2013-06-13 | 2019-01-29 | Continental Automotive Gmbh | Turbocharger with a radial-axial turbine wheel |
US20170022830A1 (en) * | 2013-12-16 | 2017-01-26 | Cummins Ltd | Turbine housing |
US10487676B2 (en) * | 2013-12-16 | 2019-11-26 | Cummins Ltd. | Turbine housing |
DE102020202967A1 (de) | 2020-03-09 | 2021-09-09 | Vitesco Technologies GmbH | Abgasturbolader mit Integralgehäuse |
WO2023061641A1 (de) * | 2021-10-14 | 2023-04-20 | Vitesco Technologies GmbH | Turboladergehäuse und abgasturbolader mit integral-turborotorgehäuse und verdichtergehäusedeckel |
Also Published As
Publication number | Publication date |
---|---|
ES195737U (es) | 1975-03-01 |
SE360144B (zh) | 1973-09-17 |
FR2091094A5 (zh) | 1972-01-14 |
NL7105769A (zh) | 1971-11-04 |
ES195737Y (es) | 1975-07-16 |
GB1320854A (en) | 1973-06-20 |
JPS5035604B1 (zh) | 1975-11-18 |
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