CN101899993A - Turbomachine - Google Patents
Turbomachine Download PDFInfo
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- CN101899993A CN101899993A CN200910258443XA CN200910258443A CN101899993A CN 101899993 A CN101899993 A CN 101899993A CN 200910258443X A CN200910258443X A CN 200910258443XA CN 200910258443 A CN200910258443 A CN 200910258443A CN 101899993 A CN101899993 A CN 101899993A
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- Prior art keywords
- turbine wheel
- shell body
- body wall
- turbo machine
- turbine
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- 238000006243 chemical reaction Methods 0.000 claims description 4
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- 238000002485 combustion reaction Methods 0.000 description 10
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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
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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
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
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- 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
- 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
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- 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
- F05D2240/00—Components
- F05D2240/55—Seals
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- 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
- F05D2260/84—Redundancy
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- 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
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
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- 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
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/09—Purpose of the control system to cope with emergencies
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
Abstract
A turbomachine such as a turbocharger comprises a housing 3 defining a bearing cavity and a turbine wheel 4 mounted to a shaft 8 for rotation about an axis. A housing wall 3a is disposed between the bearing cavity and the turbine wheel 4, the shaft 8 extending into the bearing cavity through a shaft passage 20 provided in the housing wall 3a. The housing wall 3a comprises a first portion defining an air gap with the turbine wheel 4 and a second annular portion 3b defining the opening to the shaft passage 20 and which is axially spaced from said turbine wheel 4 by a minimum distance D. The housing wall 3a further comprises at least one third portion 32, such as an annular rib, radially spaced from the first portion 3a. The third portion is configured to bear load from a turbine wheel rotating off axis in a failure condition.
Description
Technical field
The present invention relates to a kind of turbo machine, for example be used for the power turbine or the turbosupercharger of internal-combustion engine.More specifically, the present invention relates to restriction low cycle fatigue to the damage that cause, that occur in turbosupercharger of losing efficacy by the low cycle fatigue of turbine or turbine wheel.
Background technique
Turbosupercharger is well-known being used for to provide the device of air to the suction tude of internal-combustion engine with the pressure (boosting or supercharging) that is higher than atmosphere.Traditional turbosupercharger generally includes turbine or the turbine wheel that is installed in exhaust gas drive on the rotatable shaft that is positioned at the inside, turbo machine chamber that is limited by turbine shroud.The compressor impeller of the other end of the axle of the rotation drive installation of turbine or turbine wheel in compressor housing.Compressor impeller is delivered to the intake manifold of internal-combustion engine with pressurized air, increases the power of internal-combustion engine or motor with this.
The axle of turbosupercharger is supported by axle journal (journal) and thrust bearing usually, comprises suitable lubrication system, is positioned at the intermediate bearing housing that connects turbine and compressor housing.As everyone knows, providing effective sealing system is debatable or not solution in order to prevent that oil from entering in the turbine shroud from the leakage of intermediate bearing housing.Yet, preventing that the oil leakage from entering in the turbine shroud is important, oil will mix with exhaust and increase exhaust emissions and can cause for example damage of catalytic converter of parts in downstream in turbine shroud.
The turbine leaf comprises main body or wheel hub, and it has back of the body end face or the back side of face towards bearing housing.Turbine blade radially extends and usually with respect to the ear end face coaxial extension from wheel hub usually.Turbine wheel can friction welding on the seal boss (boss) of turbosupercharger shaft end, seal boss has the diameter bigger than axle, is used for rotating in the passage by shell body wall that bearing housing and turbine shroud are separated.Known oil sealing device comprises seal ring, and the sealing ring is around the seal boss setting of channel interior, provides sealing in the mode of piston ring.
In addition, common many thermal shield layers of being made by thin sheet of metal are arranged in the middle of turbine wheel and the shell body wall, so that reduce the amount of the heat transmission (because high-temperature exhaust air produces) to bearing housing.
As everyone knows, the part of turbosupercharger, particularly turbine, on heat load and/or mechanical load situation can cause the associated materials premature damage.Our fatigue of knowing that Here it is.One type fatigue is called as low cycle fatigue, and low cycle fatigue is normally caused by the duty cycle that repeats when turbosupercharger changes variation between low motion speed and high motion speed.Low cycle fatigue can cause that turbine wheel lost efficacy even fracture in some cases, and this will cause catastrophic destruction to turbosupercharger.Especially destruction or the damage to bearing housing can cause oil to enter the turbine from the bearing bore leakage, and this will cause fire.
Summary of the invention
Target of the present invention is, avoids or eliminates or alleviate owing to turbine or the turbine wheel problem that oil that the bearing housing from turbosupercharger that causes reveals enters the turbocharger turbine chamber that lost efficacy.
According to the present invention, a kind of turbo machine that provides comprises:
Housing, it limits bearing bore;
Turbine wheel, it is installed on the axle of axis rotation;
Shell body wall, it is arranged between bearing bore and the turbine wheel; Axle, described axle extends in the bearing bore by the axis channel that is arranged in the described shell body wall; This shell body wall comprises:
First portion, it limits air gap between shell body wall and turbine wheel;
Second portion, it enters described air gap ringwise and from first portion's projection to be limited to the opening of described passage; And
At least one third part, it radially enters described air gap away from second portion and from described first portion projection;
Wherein the third part configuration is used for will being applied to the radial load of annular second portion so that reduce at least thus by axle at the failure state lower support turbine wheel of turbine wheel from the axle rotation under this failure state.
Therefore, the third part of shell body wall is configured to, and for example size becomes with position configuration, on second annular portion that reduces to act on the shell body wall by axle successively under the failure state of axle load, carrying (directly or indirectly) is from the load of turbine wheel.In some embodiments, turbine or turbine wheel can directly contact with the third part of shell body wall.In other embodiments, thermal shield layer can be arranged between third part and the turbine wheel, and thermal shield layer was sandwiched between third part and the turbine wheel when turbine loses efficacy.
Turbine wheel can experience the low cycle fatigue of asymmetrical form.When fatigue be derived from the ear end face (closing on bearing housing usually) of turbine wheel or when the major part (for example blade) of turbine wheel is unclamped or is come off especially like this.Can think that when such inefficacy took place, the remainder of turbine wheel (still the transfer axle connects) was reacted in the mode that the rotating shaft with respect to turbine wheel moves radially, and after this became extremely uneven.Act on the high moment of torsion on the axle even can cause aixs cylinder so to rupture.Turbine wheel can be used as lever with the axle that is connected, especially when axle has fractureed, this will apply force to the oil seal structure in shell body wall and/or the axis channel by shell body wall, thereby cause breaking and/or the inefficacy or the destruction of oil seal structure of possible shell body wall around this passage.Bearing housing breaks or the inefficacy of oil seal structure will cause that high pressure oil in the bearing bore is revealed and enter turbine and mix with blast air.Just as previously mentioned, gas outlet means or device that this can the severe contamination downstream, but fire hazard also.
The third part (or a plurality of part) of the present invention by housing is set reduces the possibility of this catastrophic failure of turbo machine so that certain support to be provided to the turbine wheel of the inefficacy that may rotate in asymmetric mode.Such support can reduce any type of put on second portion on the shell body wall of axis channel (and put on the axis channel any sealing configuration) from axle power, or lever, reduce the risk of the inefficacy (or destruction of sealing configuration) of shell body wall thus, reveal the possibility that enters turbo machine thereby reduce oil.
In some embodiments, the present invention also makes its second portion that strengthens the housing of limiting hole axle reduce the catastrophic failure of turbo machine or the possibility of destruction by the third part of configuration housing.That is to say that any axial force that is applied by axle that causes from the axle rotation by turbine wheel all can be delivered to reinforcing section or each enhancing part.Third part or each third part can for example be positioned to any this power is delivered to part firmer on the housing, for example have the shell body wall of at least one firm parts that extend vertically.
In some embodiments, third part or each third part can be configured to strengthen second portion, and needn't directly support turbine under failure conditions.One aspect of the present invention provides a kind of turbo machine, comprising:
Housing, it limits bearing bore;
Turbine wheel, it is installed to axle and is used for around the axis rotation;
Shell body wall, it is arranged between bearing bore and the turbine wheel; Axle, it extends in the bearing bore by the axis channel that is arranged in the described shell body wall; This shell body wall comprises:
First portion, it limits air gap between shell body wall and turbine wheel;
Second portion, it enters described air gap ringwise and from first portion's projection to limit the opening of described passage; And
At least one third part, it enters described air gap from described first portion projection;
Wherein the second portion of the housing of limiting hole axle is strengthened in third part configuration in order to (for example size and position configuration in order to).
For example, the third part of housing or each third part can comprise floor or rib or gusset or web or the muscle limit that the second portion of housing is connected to the other parts of housing first portion or housing.
Second portion can be limited by the cardinal principle dome portion of shell body wall.
Third part or each third part can be positioned at the radius that is less than or equal to the turbine wheel radius.
Second portion can separate minimum separable D at interval with turbine wheel and third part or each third part are separated minimum separable d at interval with turbine wheel, and wherein d is less than or equal to D.
In some embodiments, turbo machine can comprise bearing housing, and described bearing housing is limited to the small part bearing bore, and turbine, and described turbine limits the turbine chamber of turbine wheel portion's rotation within it.Shell body wall can be the wall of bearing housing that the turbine chamber that bearing bore and turbine wheel rotate is within it separated, the transmission of heat to bearing housing of having slowed down of the air gap between the two.In this embodiment, thermal shield layer can be arranged in the air gap between shell body wall and the turbine wheel.Any such thermal shield layer is preferably spaced apart with the heat transfer of restriction to housing with the second portion of shell body wall.In other mode of execution, shell body wall itself just can comprise thermal shield layer, for example has the cast inblock of bearing housing.
The third part of shell body wall or each third part can be annular.
The third part of shell body wall or each third part can be limited towards the projection that turbine wheel has highly extension from shell body wall by floor or other.For example third part or each third part can be to leave the floor that shell body wall first portion extends with what have a certain-length along straight line or direction of a curve.Such floor extends to the second portion of housing, or can stop in the position of leaving housing second portion certain intervals.
The height of third part or each third part can be inconsistent or irregular, a zone that will preferentially be out of shape when being subjected to clashing into to be formed on or a plurality of zones of each third part.
Third part or each third part can be along being substantially the second portion of radial direction extension away from shell body wall.In some embodiments, at least one third part can be along tangentially extending to first portion substantially.
Shell body wall can comprise a plurality of described third parts, and it can for example center on described second portion circumference.
But in some embodiments, third part or each third part can limit by discrete convex parts, for example floor or similar structure, and it is arranged on the surface of shell body wall, in other embodiments, third part or each third part are limited by the exterior contour of shell body wall.
A kind of typical turbine wheel can comprise central body or the wheel hub that supports the turbine wheel blade, and wheel hub has the ear end face of face towards shell body wall.The turbine wheel of other form can comprise backboard or back plate or the dunnage that supports impeller blade, and this backboard or back plate or dunnage limit the ear end face of impeller.Can between the third part of shell body wall or each third part and turbine wheel ear end face, limit minimum separable d.
The third part of shell body wall or each third part can limit contact surface (it was touched) when turbine loses efficacy, contact surface is positioned at roughly on the plane with orthogonal axe, or it is consistent with the lost efficacy direction of turbine wheel of back asymmetric rotational of above-mentioned turbine wheel approx to be arranged in the conical surface that roughly limits about axis-for example.
Shell body wall limits the bearing bore part in some embodiments, and axle can leak into turbine wheel to prevent or to block oil by described passage with respect to described channel seal.
In other mode of executions, shell body wall comprises the thermal shield layer that has second shell body wall, and second shell body wall limits the part that is arranged on the bearing bore between bearing bore and the thermal shield layer.Axle can seal with respect to the second channel by described second shell body wall to prevent or to block oil leakage to turbine wheel.
The third part of shell body wall can be radially be opened with dome or other significant intervals of limiting second portion, but described second portion can be by the feature qualification of the shell body wall that contact with dome.
Shell body wall can limit by the housing that comprises another wall, perhaps links to each other with the housing that comprises another wall, and this another wall extends along the direction with the active constituent that is parallel to described axis.Another wall can intersect with described shell body wall in the radial position consistent with the radial position of shell body wall third part or contact, and makes any substantial axial power that acts on the shell body wall second portion all be passed to another shell body wall part.Another shell body wall part is when being clashed into by turbine wheel, with third part or each third part of support shell body wall.
The third part of shell body wall or each third part can be with the feature of shell body wall one (for example with the shell body wall cast inblock or be worked in the shell body wall) or make independent parts that it is connected with shell body wall subsequently.
Turbo machine can be turbosupercharger or for example be power turbine.
Other preferably will become apparent because of following description with useful feature among the present invention.
Description of drawings
The detailed mode of execution of the present invention will be described below, only as example, with reference to the following drawings, wherein:
Fig. 1 is the cross-sectional view of the turbosupercharger of prior art;
Fig. 2 is the unfolded drawing of the turbine end bearing and the oil seal assembly of turbosupercharger shown in Figure 1;
Fig. 3 illustrates the part of part of the turbo-charger bearing shell construction of another prior art;
Fig. 4 illustrates the dome portion of fracture of the turbosupercharger of prior art;
Fig. 5 a and 5b illustrate the part of the first embodiment of the present invention;
Fig. 6 is the cross-sectional view according to the turbosupercharger of the embodiment of the invention;
Fig. 7 is the sectional view according to the simplification of the amplification of turbine wheel of the present invention and bearing housing;
Fig. 8 is the end elevation according to the bearing housing of second embodiment of the invention; And
Fig. 9 is according to the turbine wheel of the embodiment of the invention shown in Figure 6 and the cross-sectional view of bearing housing.
Embodiment
See figures.1.and.2, illustrated turbosupercharger comprises the turbo machine that is connected to compressor 21 by intermediate bearing housing 3.Turbo machine 1 is included in the turbine wheel 4 of rotation in the turbine shroud 5.Same, compressor 2 is included in the compressor impeller 6 of rotation in the compressor housing 7.Turbine wheel 4 and compressor impeller 6 are installed in the relative two ends of the common turbo-charger shaft 8 that extends through intermediate bearing housing 3.
Turbine shroud 5 has around the exhaust entrance volute chamber 9 of turbine wheel 4 settings and axial exhaust outlet 10.Compressor housing 7 has axial gas-entered passageway 11 and is positioned at the compressed air outlet volute chamber of arranging around compressor impeller 6 12.
Between turbine wheel 4 and bearing housing 3 or the centre thermal shield layer 13a is arranged, make with tinsel, be installed in the rear of turbine wheel 4 in the turbine shroud 5.The purposes of thermal shield layer 13a is to cause the overheated of bearing housing 3 that the exhaust of the heat in the turbine shroud 5 of the oil cokeization in the turbine shroud 5 brings in order to prevent or to stop by meeting (for example).Thermal shield layer 13a and turbine wheel 4 are spaced apart, not only make thermal shield layer 13a can not disturb the motion of turbine wheel 4, and make heat can not be directly transferred to thermal shield layer 13a from turbine wheel 4.The part of thermal shield layer 13a is also spaced apart to minimize the transmission of heat to bearing housing with bearing housing 3.
Usually, turbine wheel 4 comprises columniform substantially main body or wheel hub 4a, and it has the ear end face 4c towards bearing housing/thermal shield layer.A plurality of turbine blades radially extend and extend vertically with respect to ear end face basically from wheel hub basically.
In use, turbine wheel 4 rotates by exhaust passing through from annular vent inlet 9 to exhaust outlet 10, it rotates compressor impeller 6 successively, sucks thus by the suction air of suction port of compressor 11 and by compressor outlet volute chamber 12 and transmits the inlet of air to internal-combustion engine that boost.
Turbosupercharging arbor 8 is in rotation on the full floating axle journal bearing (journal bearing) 13 and 14 that the turbine end and the compressor end of bearing housing are installed respectively.Compressor end bearing unit 14 also comprises and the interactional thrust bearing 15 of oil seal assembly that comprises oil thrower 16.Compressor end bearing and oil-tightening details are inessential for understanding the present invention, therefore will not describe in further detail.Oil supplies to bearing housing by oil-in 17 from the oil system of internal-combustion engine, and supplies with to bearing unit by oily passage 18.
(especially referring to Fig. 2) in more detail, the passage 20 by cartridge housing body wall 3a radially is step-like, and it has the inside part 20a and relative large diameter external lateral portion 20b of narrow relatively diameter.This will provide the annular adjacency for the seal ring 21 that is arranged in the circular groove 23 that is arranged on seal boss 19 outer surfaces or engage convex shoulder 22.Seal ring 21 is static with respect to bearing housing 3, and is provided and is used for preventing that gas/oil from leaking by passage 20.In abutting connection with or engage convex shoulder 22 prevent seal ring 21 in the inboard towards bearing housing 3 wrigglings or slide.For the sudden change of diameter that passage 20 is provided, non-fillet changes, and cuts out undersized annular groove 24 on the surface of passage 20 to limit convex shoulder 22.
Turbine end shaft bearing 13 is between back-up ring 25 and 26.Oil is supplied with by oily passage 18 and is given bearing 13, and bearing 13 is provided with the radial hole of opening along the circle spacing 27 and is used for oil by passing to the axle 8 of turbosupercharger.The radially recessed contiguous cartridge housing body wall that passes through the passage 20 of shell body wall 3a of annular oil-return groove 28.Oil-return groove 28 twisted rotary shafts 8 and have the inlet 29.
The internal surface that seal boss 19 extends beyond cartridge housing body wall 3a a bit enters in the bearing housing 18, and overlaps the inlet 29 of oil groove 28 in the axial direction.The inner of seal boss 19 forms the radially shoulder around axle 8 with annular end face 30.When the axle 8 of pressurized machine rotated, the oil that arrives annular end face 30 was dispersed diametrically, and is driven into oil groove 28 from the end face 30 of seal boss 19, and oil flows back to into the crankcase to internal-combustion engine by oil drainage hole 31 (shown in Fig. 1) from oil groove 28.Therefore oil groove 28 is set prevents oil accumulation or accumulation in passage 20 zones, and similarly, assurance boss 19 projectioies have guaranteed that oil is entered oil groove 28 by impelling in bearing housing 3, rather than impelling is in the annular space that boss 19 limits by passage 20.
Fig. 3 shows the part of another existing pressurized machine.Same reference character is with top described corresponding.For the turbosupercharger of representing among Fig. 3, can see that the dome structure 3b of bearing housing is much more obvious than the case design among Fig. 1 and Fig. 2.
Can find, under concrete fatigue condition, for example low cycle fatigue, turbine wheel 4 may lose efficacy or damage when in use.This inefficacy may comprise breaking of turbine wheel 4, and perhaps when limit situation, can disintegrate is polylith.Such inefficacy or damage are tended to substantial asymmetric, take place to lose efficacy from the ear end face of turbine wheel 4 or when damaged or the major part of turbine wheel (for example blade 4b) is unclamped or when coming off especially like this.
Bearing housing breaks or the inefficacy or the damage of fracture or seal arrangement all can cause the high pressure oil in the bearing housing to enter turbine shroud, enters the vent systems of internal-combustion engine subsequently.As previously mentioned, the venting gas appliance in this meeting severe contamination downstream, but or fire hazard.
The result of this inefficacy or damage is that the turbine 4 and the axle 8 that cause rotating become unstable.Turbine 4 and axle 8 are subjected to active force, and this active force causes that they are extremely uneven and radially outwards moves with respect to their normal rotation axiss.Power that produced by the moment of this mobile generation and turbine wheel 4 and axle 8 by contiguous turbine shroud 5 and/or bearing housing 3 combine, and can cause that axle 8 fractures or is out of shape, and therefore will cause system extremely uneven.Axle 8 distortion or the zone (especially the turbine end bearing 13) that betides shaft bearing 13,14 usually or of fractureing in dome structure 3b inside.In case axle 8 is out of shape or fractures, impeller 4 and any other parts that are connected to axle 8 can radially continue outside mobile.This can apply radial effect power to interior bearing housing and/or the seal ring 21 in passage 20 zones.Radially outside when mobile at turbine 4, axle 8 can effectively form lever, causes huge masterpiece to use on the dome 3b, the inefficacy that this will break dome and/or cause seal arrangement 21.
Fig. 4 shows the dome structure 3b that breaks in top described mode.If dome structure 3b or seal arrangement 21 are damaged, by enter the mouth 17 and passage 18 supply with the high pressure oil of giving bearing 13 and will flow into turbo machine and mix with the exhaust phase of heat.Usually it is potential danger that the internal combustion engine exhaust system that is in high temperature is exposed to oil, because oil can be lighted.In addition, the inlet that oil enters the vent systems of internal-combustion engine can cause outside oil leakage and/or pollute the venting gas appliance in downstream, for example catalytic converter.
Fig. 5 a and 5b show the turbo-charger bearing housing according to first embodiment of the invention.Illustrated shell construction according to the present invention is the improvement to structure shown in Figure 3, and identical reference character is used in corresponding part.According to the present invention,, the floor or the supporter 3c that radially extend of projection above shell body wall change bearing housing by being provided.In the example that provides in the drawings, the height of floor 3c more than shell body wall is lower than the height of dome 3b, and the height of floor 3c can be equal to or greater than the height of dome 3b in other embodiments.If the turbine of the sort of type of top discussion lost efficacy or damage takes place, adjacency or access node that radially any and/or lever of the attachment portion on turbine 4 and the axle 8 moves the turbine 4 that all will be had floor 3c close restriction or inhibition.Floor 3c protrudes enough distances towards turbine 4, make any motion of spiraling of the turbine 4 that lost efficacy or damage all will cause turbine 4 in abutting connection with floor 3c, this inhibition or stoped between the ear end face of dome structure 3b and turbine 4 and take place effectively to contact.The radial motion of inhibition or restriction turbine wheel 4 reduces, even can prevent to affact on dome structure 3b and/or the seal ring 21 from the axle active force.This can prevent that dome structure 3b from breaking and/or prevent that seal ring from being destroyed, and can prevent that also for example axle 8 ruptures.So this will prevent under the situation of turbine inefficacy or damage or the minimum oil leakage enters vent systems.
Further, in this embodiment, floor 3c in the illustrated embodiment is arranged in order to strengthening dome structure 3b and to arrange in order to will be by the radial outside transmission towards housing of the power of the shell body wall carrying of extending vertically substantially, therefore bearing load or load better.Test confirms that embodiments of the invention can greatly reduce the trend of any dome structure fracture under turbine wheel inefficacy or situation about damaging.
Fig. 6 illustrates turbosupercharger according to a second embodiment of the present invention, and wherein bearing housing 3 has projection or the projection annular portion 32 that is arranged on dome structure 3b radial outside.Equally, in suitable part, identical reference character in order to the expression with each figure of front in identical feature.Because the protrusion domed shape of bearing housing 3, the spacing between the ear end face of turbine wheel 4 and the bearing housing 3 increases with the radial distance of the axis that leaves axle 8.According to the radial position difference of annular portion, annular portion 32 protrudes towards the ear end face of turbine wheel 4 or the blade 4b of turbine wheel 4 from bearing housing 3.In an illustrated embodiment, part 32 is annular and concentric with turbine wheel 4.Thermal shield layer 13a occupy between restricted part 32 and the turbine wheel 4.The expectation be, go out as shown, restricted part 32 makes it not contact with thermal shield layer 13a, making does not have direct transmission of heat between them.
If the damage of turbo machine generation the above-mentioned type, turbine 4 all will be limited by the contiguous engagement of turbine 4 with annular portion 32 (even by thermal shield layer 13a) with radially any and/or lever motion of the attachment portion of rotating shaft 8.Be similar to the situation of the floor 3c among the embodiment of front, annular portion 32 protrudes enough distances towards turbine 4, any motion of spiraling of the turbine 4 that make to lose efficacy or damaged all can cause turbine 4 contiguous engagement annular portions 32, this inhibition or stop between the ear end face of dome structure 3b and turbine 4 and take place effectively to contact.As mentioned above, the radial motion by this way of restriction turbine wheel 4 reduces, even can prevent to act on dome structure 3b and/or the seal ring 21 from axle power, therefore prevent breaking and/or preventing that sealing configuration from suffering to destroy (and the fracture that can also prevent rotating shaft 8) of dome structure 3b.
As discussed earlier, turbine wheel 4 comprises the main body 4a with ear end face 4c and blade 4b.As from Fig. 6, can seeing easily, if turbine 4 lost efficacy or damaged, the size of annular portion 32 and position form make turbine wheel 4 and annular portion 32 in abutting connection with or engage, the ear end face of the wheel hub 4a of turbine wheel 4 is with restricted part 32 adjacency or engage subsequently.Be favourable like this, because main body 4a can stand bigger power than blade 4b.Similarly, can apply bigger active force to turbine wheel 4, so that the turbine 4 radially outer power that lost efficacy or damaged are ordered about in opposing by annular portion 32.Annular portion 32 can for example be positioned on the radius identical with the outer rim of turbine wheel ear end face 4c.Alternatively, in other mode of execution, annular portion 32 can be positioned at the radially inner side or the outside of the outer rim of turbine wheel ear end face.
In some embodiments, for example in the mode of execution shown in Fig. 6 and Fig. 7, make turbine 4 inefficacies or damage and apply active force if the size and dimension of annular portion 32 forms to annular portion 32, the transmission of described power will be undertaken by a wall portion 3c of bearing housing 3, and this wall portion is generally along axially extending away from the turbine direction.Thereby any power that passes over has and is parallel to the big or important component of direction that sidewall 3c leaves the extension of turbine, as shown by arrow A.It is favourable that any anti-power of work is transmitted by this way, because the risk that its load lower shell body 3 that is minimized in the turbine 4 that lost efficacy or damaged breaks.
In another mode of execution of the present invention shown in Fig. 8 and Fig. 9, convex portion comprises a plurality of parallel floors 33 rather than annular plate 32.The contiguous dome structure 3b of floor 33, and have and connect floor 33a that radially extends from dome on it and the floor 33b that tangentially extends to dome 3b.Dome structure 3b comprises central protrusion part 34, and the surface of this protrusion part is roughly parallel to the ear end face of turbine wheel 4.The axial height of floor 33 is identical with protrusion part 34.The size of single floor 33 and position (with respect to turbine wheel 4 and each other) form and make the turbine 4 that lost efficacy or damaged will cause turbine 4 with restricted part 32 adjacency or engage along spiraling of any direction.Put down in writing in the mode of execution as front of the present invention, the adjacency of turbine 4 and floor 33 or engage suppress or stoped turbine wheel lost efficacy or situation about damaging under put in dome structure 3b and the sealing 21 significantly from axle power.This structure allows to adopt two traditional step casting methods to come cast bearing housing economically.
In the above in Ji Zai the mode of execution, the shell body wall 3a that the chamber and the bearing bore of turbine wheel 4 separated is provided by bearing housing 3.In other mode of execution, described shell body wall can be provided by turbine shroud 5.In a mode of execution again, thermal shield layer 13a can be provided with enough firmly so that bear the load or the load of turbine wheel inefficacy or that damage.For example in some mode of execution, thermal shield layer can be the wall with the bearing housing integrally casting, and same, can be the shell body wall that is provided with part 32 or floor 33 etc.
Though having, embodiments of the present invention recited above are arranged to the supporting part that shell body wall protrudes, but can expect that this supporting part can be provided by the shape of cartridge housing body wall 3a or the less projection or the protruding feature of structure in other mode of execution of the present invention.For example, if present, wall 3a can have bending or the curved surface towards the spill substantially of turbine wheel on the radial location that surpasses passage 20 or dome structure 3b.Yet discrete projection is preferred, because they bring little increase only for usually the weight of turbosupercharging wall.
As mentioned above, the reinforcing section of shell body wall can be different with top illustrated embodiment of the present invention with the configuration of supporting part and position.For example annular protrusion or protruding part 32 can be substituted by the discrete projection of opening along the circle spacing or the annular array of projection.For example this discrete projection can be the arc floor that is positioned on the circle that limits according to axis, maybe can be substantially towards or away from the floor curve of the axis on the turbine wheel sense of rotation.Annular protrusion or projection, or any such floor, radial width can change, the same any such projection or the surface direction of projection also can change.For example annular protrusion or projection can limit a surface towards turbine wheel, turbine wheel be approximately perpendicular to the axis setting or be positioned at suppose its inefficacy or damage with turbine wheel and the conical surface that the direction when contacting with projection or projection is consistent on.
Projection/the rib array of the projection/floor of annular or annular can be positioned at roughly consistent with the circumference of turbine ear end face radial location, or between the circumference of ear end face and the axis or between the outboard end of the circumference of ear end face and turbine wheel blade.In some embodiments, can obviously not increase under the situation of more or bigger leaf destruction or risk of distortion, the one or more projectioies or the projection that are positioned on the radius consistent with the radius of the main body 4a of turbine wheel 4 are being the most effective aspect the maximum reaction force that allows to be applied on the turbine wheel 4 inefficacy or that damage.In some embodiments, projection or other enhancing part or supporting part can be limited by other structure characteristic on bearing housing, turbine shroud and/or the thermal shield layer.
Comprise in the mode of execution of floor at supporting part, such floor can radially extend (being similar to the floor 33a shown in Fig. 6) away from axis, or, perhaps extend along the direction between the above-mentioned both direction along the tangent direction extension (being similar to the floor 33b shown in Fig. 6) that with the axis is the circle at center.This floor can limit towards the surface of turbine wheel, on the conical surface that this turbine wheel is positioned at that turbine wheel on the plane with axis normal is supposed its inefficacy or damage and the direction when contacting with projection or projection is consistent.In some embodiments, such floor can combine with one or more annular protrusions or projection, or combines with one or more similar projectioies above-mentioned.Have at the cartridge housing body wall under the situation of dome structure, as shown in the figure, floor can contact dome or separate with dome diametrically.
Comprise one or more projectioies or projection in the supporting portion, this projection or projection can form (for example casting or machining) with shell body wall is whole.Alternatively, projection or projection can comprise individually the structure of processing, and it is being connected (for example connect by welding or bolt, rivet or with the fastener connection etc.) subsequently with shell body wall.To for example allow projection or projection to make by enough materials different like this, and can allow the greater flexibility that disposes of projection with shell body wall.
It will also be appreciated that the cross-sectional profiles of the projection of the part of any formation reinforcing section or supporting part (perpendicular to its longitudinal axis) can have different shapes.Above the projection of described mode of execution or projection have the sidewall (intersecting with the cartridge housing body wall or the contacting point is radiating type or fillet form) of the almost parallel that extends along axis and face arc end surfaces towards turbine wheel.Alternatively, end surfaces can be flat so that increase the surface area that will contact and support the turbine wheel that lost efficacy or damaged.This not only can propagate into all reaction forces that applied by reinforcing section and supporting part turbine wheel 4 bigger zones, but also the moving radially of restriction or the turbine 4 that suppressed to lose efficacy or damage.In addition, should cause stopping of turbine wheel 4 rotations if wish the adjacency of the turbine wheel 4 of reinforcing section or supporting part and inefficacy or damage, the stopping distance of the turbine wheel 4 of inefficacy or damage will be reduced.The flat profile of the head portion of projection or projection can for example be perpendicular to the axis of axle 8 rotations, perhaps can become tilt fixing with respect to the spin axis of axle 8, and this axle with turbine 4 ear end faces of above-mentioned imaginary inefficacy or damage is consistent.
Can it will also be appreciated that the projection of the part of any formation supporting part can make its radial distance that leaves axle 8 axis reduce to turbine wheel 4 extensions with it.This can improve impact force (or reaction force) to the supporting part of housing 3 (for example housing sidewall 3c) or the transmission of bearing load part.
In Ji Zai some mode of executions, the minimum axial gap between supporting part and the turbine wheel 4 is less than the protrusion part (for example limiting the part of the dome structure of passage 20 openings) of dome structure 3b and the minimum axial gap between the turbine wheel 4 in the above.The difference in gap can be different in different mode of executions.In some embodiments, described difference can be relatively little, and can be relatively large in other mode of execution.Suitable difference can be determined by the housing feature that the configuration of bearing housing and/or thermal shield layer and/or the distance between turbine wheel and the shell body wall and/or turbine wheel limit reinforcing section with respect to diameter or other of the radial position of projection or projection to a certain extent.
In some embodiments, form the projection of supporting part or projection or other housing feature and can comprise " wrinkle district or texturing zone (crumple zone) ", promptly the turbine wheel 4 that lost efficacy or damaged impact or during the bump supporting part with the part of finite deformation.This wrinkle district or texturing zone can for example adopt the form of the part of projection or projection, or other has the feature of the axial height big or bigger slightly than the neighbouring part of projection or projection or other support feature (promptly extending to more close turbine wheel).This wrinkle district or texturing zone can for example flatten when being clashed into the absorption portion impact force.
Although description of the invention relates to the turbine of turbosupercharger, should recognize that the present invention also can be applied to the turbo machine of other turbocharger, for example power turbine etc.Those skilled in the art know that power turbine is that drive transmission or other coupling device are used as the power source outputting power, and are not to drive a compressor impeller.
About other possible improvement of the present invention with use apparent to those skilled in the art.
Claims (16)
1. turbo machine comprises:
Housing, it limits bearing bore;
Turbine wheel, it is installed to and is used on the axle rotating around axis;
Shell body wall, it is arranged between bearing bore and the turbine wheel; Described axle extends in the bearing bore by the axis channel that is arranged in the described shell body wall; Described shell body wall comprises:
First portion, it limits air gap between described shell body wall and described turbine wheel;
Second portion, its ringwise and from described first portion to described air gap projection to be limited to the described opening of described passage; And
At least one third part, its radially separate at interval with second portion and from described first portion to described air gap projection;
Wherein said third part structure is used at the failure state lower support turbine wheel of described impeller from the axle rotation, so that reduce to be applied to by axle the radial load of the second portion of annular thus at least under failure state.
2. turbo machine as claimed in claim 1, wherein said second portion limits by the cardinal principle dome portion of described shell body wall.
3. turbo machine as claimed in claim 2, wherein said third part or each third part are limited by the feature that axle applies any radial load on it so that directly strengthen described dome portion opposing by extending to dome portion on the described shell body wall.
4. each described turbo machine in the claim as described above, wherein said third part or each third part are positioned in the radial position of the radius that is less than or equal to described turbine wheel.
5. each described turbo machine in the claim as described above, wherein said second portion separates minimum interval D at interval with described turbine wheel, and described third part or each third part are separated minimum interval d at interval with turbine wheel, and wherein d is less than or equal to D.
6. each described turbo machine in the claim as described above, wherein said third part or each third part be at least substantially annular and at least substantially around described second portion.
7. each described turbo machine in the claim as described above, the described third part of wherein said shell body wall or each third part comprise floor or have other convex portion of the height that extends towards described turbine wheel from described shell body wall.
8. as each described turbo machine in the claim 1 to 5, the third part of wherein said shell body wall or each third part comprise floor or have other convex portion of the height that extends towards described turbine wheel from described shell body wall, and described third part or each third part have the length of extending away from described second portion along straight line or direction of a curve.
9. turbo machine as claimed in claim 8, wherein at least one third part is along radial direction or tangential direction are extended away from described second portion substantially.
10. each described turbo machine in the claim as described above, it comprises a plurality of described third parts.
11. each described turbo machine in the claim as described above, wherein said turbine wheel comprises the central body that supports turbine blade, and wherein said central body limits ear end face, limits minimum interval d between the described third part of described bearing housing or each third part and described turbine wheel ear end face.
It is that 12. each described turbo machine in the claim as described above, the described third part of wherein said shell body wall or each third part limit the plane that is positioned at the described axis of perpendicular or be positioned at turbine wheel surface of contact on the conical surface of described axis qualification.
13. each described turbo machine in the claim as described above, wherein said shell body wall limits the part of described bearing bore, and wherein said axle is sealed with respect to described passage, is leaked to described turbine wheel to stop or to block oil by described passage.
14. each described turbo machine in the claim as described above, wherein said shell body wall is limited by the housing that comprises another wall section, or be connected with the housing that comprises another wall section, described another wall section extends along the direction with the active constituent that is parallel to described axis.
15. turbo machine as claimed in claim 14, wherein said another wall section is intersecting with described shell body wall with the corresponding radial position of radial location of the described third part of described shell body wall or each third part or contact, and feasible described third part that puts on described shell body wall or the axial force on each third part are by described another wall section reaction.
16. each described turbo machine in the claim as described above, wherein said turbo machine is turbosupercharger or power turbine.
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0820952.0 | 2008-11-15 | ||
| GB0820952A GB0820952D0 (en) | 2008-11-15 | 2008-11-15 | Turbomachine |
| GB0822771A GB0822771D0 (en) | 2008-12-13 | 2008-12-13 | Turbomachine |
| GB0822771.2 | 2008-12-13 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101899993A true CN101899993A (en) | 2010-12-01 |
Family
ID=41509313
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910258443XA Pending CN101899993A (en) | 2008-11-15 | 2009-11-16 | Turbomachine |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US20100124496A1 (en) |
| CN (1) | CN101899993A (en) |
| GB (1) | GB2465279B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105065679A (en) * | 2015-09-10 | 2015-11-18 | 无锡康明斯涡轮增压技术有限公司 | Oil seal structure for supercharger |
| CN109653804A (en) * | 2017-10-12 | 2019-04-19 | 博格华纳公司 | Turbocharger with modified turbine wheel |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130014503A1 (en) * | 2011-07-15 | 2013-01-17 | GM Global Technology Operations LLC | Housing assembly for forced air induction system |
| KR102037892B1 (en) * | 2012-07-10 | 2019-10-29 | 보르그워너 인코퍼레이티드 | Exhaust-gas turbocharger |
| DE102014213641A1 (en) * | 2014-01-17 | 2015-08-06 | Borgwarner Inc. | Method for connecting a compressor wheel with a shaft of a charging device |
| DE102017120338A1 (en) * | 2017-09-05 | 2019-03-07 | Man Diesel & Turbo Se | turbocharger |
| FR3084919B1 (en) * | 2018-08-07 | 2020-12-11 | Cryostar Sas | MULTI-STAGE TURBOMACHINE |
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| US4256441A (en) * | 1979-06-19 | 1981-03-17 | Wallace-Murray Corporation | Floating ring bearing structure and turbocharger employing same |
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| JPS59157538U (en) * | 1983-04-06 | 1984-10-23 | マツダ株式会社 | turbo supercharger |
| US5454646A (en) * | 1994-10-27 | 1995-10-03 | Caterpillar Inc. | Journal bearing for use with high speed shafting |
| US6739845B2 (en) * | 2002-05-30 | 2004-05-25 | William E. Woollenweber | Compact turbocharger |
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- 2009-11-13 GB GB0919877.1A patent/GB2465279B/en active Active
- 2009-11-16 CN CN200910258443XA patent/CN101899993A/en active Pending
- 2009-11-16 US US12/618,938 patent/US20100124496A1/en not_active Abandoned
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| US4142608A (en) * | 1975-07-10 | 1979-03-06 | Wallace Murray Corporation | Turbocharger lubrication and exhaust system |
| JPS61108843U (en) * | 1984-12-21 | 1986-07-10 | ||
| JPS61205334A (en) * | 1985-03-07 | 1986-09-11 | Mazda Motor Corp | Turbocharger |
| US20080138196A1 (en) * | 2002-12-02 | 2008-06-12 | Abb Turbo Systems Ag | Exhaust-gas-turbine casing |
| GB2427248A (en) * | 2005-06-16 | 2006-12-20 | Malcolm George Leavesley | Turbocharger apparatus having a bearing housing with an integral heat shield |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105065679A (en) * | 2015-09-10 | 2015-11-18 | 无锡康明斯涡轮增压技术有限公司 | Oil seal structure for supercharger |
| CN109653804A (en) * | 2017-10-12 | 2019-04-19 | 博格华纳公司 | Turbocharger with modified turbine wheel |
Also Published As
| Publication number | Publication date |
|---|---|
| GB0919877D0 (en) | 2009-12-30 |
| US20100124496A1 (en) | 2010-05-20 |
| GB2465279A (en) | 2010-05-19 |
| GB2465279B (en) | 2014-09-24 |
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Application publication date: 20101201 |