US20050123394A1 - Compressor diffuser - Google Patents
Compressor diffuser Download PDFInfo
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- US20050123394A1 US20050123394A1 US10/914,562 US91456204A US2005123394A1 US 20050123394 A1 US20050123394 A1 US 20050123394A1 US 91456204 A US91456204 A US 91456204A US 2005123394 A1 US2005123394 A1 US 2005123394A1
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- Prior art keywords
- compressor according
- diffuser
- impeller
- compressor
- vane
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- Abandoned
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- 230000003993 interaction Effects 0.000 claims abstract description 4
- 238000013022 venting Methods 0.000 claims description 16
- 241000826860 Trapezium Species 0.000 claims description 2
- 230000000295 complement effect Effects 0.000 claims description 2
- 230000007246 mechanism Effects 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 3
- 239000000411 inducer Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000007373 indentation Methods 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Images
Classifications
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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
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
- F04D29/422—Discharge tongues
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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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
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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
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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
- F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
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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
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
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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
- F05D2250/00—Geometry
- F05D2250/50—Inlet or outlet
- F05D2250/52—Outlet
Abstract
A compressor diffuser for a vehicle engine turbocharger, the diffuser comprising: a diffuser housing having a gas flow path having a side wall connecting a gas inlet to a gas outlet; a plurality of pivotally mounted diffuser vanes arranged in the flow path to control gas flow, and a vane angle control device for adjusting the angle of each of the plurality of vanes in the flow path; the control device comprising a unison ring coupled to the plurality of vanes in such a way that rotation of the unison ring pivots each of the vanes by interaction of a cam surface with a respective cam follower.
Description
- The present invention relates to a diffuser for a compressor for a vehicle engine turbocharger.
- A turbocharger for an internal combustion engine comprises a turbine side receiving exhaust gas from the engine to drive a turbine wheel connected to a shaft on which is mounted a compressor impeller wheel. Exhaust gas from the engine turns the turbine wheel and thus the shaft and causes rotation of the compressor impeller wheel. Intake air is drawn into the impeller wheel and its pressure boosted before it is fed to the engine and mixed with fuel for the combustion process. The increased pressure of the engine intake air increases the performance of the engine.
- A turbocharger compressor operates at relatively low temperatures but relatively high pressure compared to the turbine.
- It is important to control the flow of gas in turbochargers to ensure a steady flow and avoid surges and stalls. A diffuser typically is positioned in the flow path from the compressor wheel to the air outlet to control the flow of air by means of vanes in the gas flow path which even out or diffuse the air flow.
- These vanes may be fixed in position or may be arranged to be moveable to vary their angle so as to better suit the gas flow in the diffuser to the operating conditions of the engine.
- According to one aspect of the present invention there is provided a compressor for a vehicle engine turbocharger. The compressor comprises a diffuser assembly and an impeller assembly. The diffuser assembly comprises: a diffuser housing having a gas flow path having a side wall connecting a gas inlet to a gas outlet; a plurality of pivotally mounted diffuser vanes arranged in the flow path to control gas flow, and a vane angle control device for adjusting the angle of each of the plurality of vanes in the flow path; the control device comprising a unison ring coupled to the plurality of vanes in such a way that rotation of the unison ring relative to the vanes pivots each of the vanes by interaction of a cam surface with a respective cam follower. The impeller assembly, located upstream of the diffuser, comprises an impeller wheel and a plurality of impeller blades, a venting chamber and a shroud wall extending around the impeller blades, separating the blades from said venting chamber, wherein the shroud wall comprises at least one vent pneumatically connecting the impeller to said venting chamber.
- Venting in the shroud wall acts to pull extra air into the compressor when the compressor is in a choke condition and to recirculate the air flow back toward the intake when the compressor is in surge condition. This suction and recirculation action is driven by pressure differentials between the intake and diffuser section. The larger the pressure differential, the larger the flow of air through the venting hole(s).
- Some of the impeller blades may extend only partially across the space between the impeller wheel and the shroud wall. This form of the blades is known as “splitter blades”. The “splitter blades” form of impeller is generally considered to have a better flow range, i.e. operates over a wider range of operating conditions, because the removal of part, typically about half, of the blade, opens up the throat area of the inducer and allows the flow to adjust itself in choking conditions.
- While such splitter blades can be used with the present invention, the impeller blades in the present invention are preferably all full blades, extending from the wheel across the flow path to substantially adjacent the shroud wall.
- This has been found to increase the frequency of noise to levels above human sensitivity, and to reduce the noise level of the compressor because blade loading is decreased. Also, surprisingly, to have a flow range comparable with that of an impeller having splitter blades. This may be at least partly because the full blades cause a larger pressure change in the inducer throat region when the inducer is choked and thus causes increased suction to compensate the choke flow. It has also been found that when vents are provided in the shroud wall the full bladed impeller is more effective in the surge region than splitter blades.
- In one of the more advanced embodiments of the present invention, there are two or more vents in the shroud wall and the air flow through them is controlled, advantageously independently of each other, for example by a sliding or rotating cover.
- The design can be further simplified by having the unison ring comprise a substantial part of the flow path side wall, for example between 40-80% of the distance between the trailing edge of the impeller blade and the diffuser exit.
- According to a preferred embodiment of the present invention the unison ring is mounted for rotation in a recess in the diffuser housing such that the side of the ring exposed to the gas path is generally flush with the remainder of the diffuser housing making up the flow path side wall.
- Preferably each diffuser vane comprises a leading end and a trailing end and is pivotally mounted about a pivot point close to the leading edge.
- The unison ring is coupled to the plurality of vanes in such a way that rotation of the unison ring pivots each of the vanes by interaction of a cam surface with a respective cam follower, and the cam follower has a generally elongate oval shape in cross section to engage the cam surface over a contact surface. The cam follower may be formed as a tab on each vane and the respective cam surfaces are formed as an internal surface of an elongate slot in the unison ring. The slot preferably has an arcuate form. The elongated oval shape of the cam follower may comprise a central generally rectangular region and two curved end regions, and a region having a trapezium cross-section formed between the rectangular region and each curved end section, so as to present at least three generally planar sides on each side of the cam follower. The cam surface is preferably contoured to be complementary to the engaging surface of the cam follower so as to maximize the area of the contact surface between the cam and the cam follower. Each vane may have an elongate isosceles triangle shape with the apex of the triangle forming said one end, wherein the angle subtended at the apex of the triangle is between about 5 degrees and 15 degrees, preferably about 10 degrees. At least one side of each vane may be curved or straight. The vane angle control device preferably further comprises a rack and pinion driven crank shaft, and a spring biased variable current solenoid, wherein the crank shaft is coupled to the solenoid via a cam on the crank shaft to provide direct position feedback to the solenoid. Each vane may be pivotally mounted by means of a pivot pin on the vane which engages with a hole in the diffuser housing. The pivot pin may be formed by grinding and may be mounted on the same side of the vane as the cam follower with the pivot pin extending beyond the tab formed by injection molding.
- According to another aspect of the invention there is provided a compressor for a turbocharger, comprising a diffuser assembly and an impeller assembly, the diffuser assembly comprising a diffuser housing having a gas flow path having a side wall connecting a gas inlet to a gas outlet and a plurality of diffuser vanes arranged in the flow path to control gas flow. The impeller assembly, located upstream of the diffuser assembly, has a plurality of impeller blades mounted on an impeller wheel, a venting chamber and a shroud wall extending around the impeller blades and separating them from said venting chamber, wherein the shroud wall comprises at least one vent pneumatically connecting the impeller to said venting chamber. Preferably the impeller blades are all full blades extending from substantially adjacent the base of the impeller wheel to substantially adjacent the shroud wall extending to an inlet portion of the shroud wall.
- The invention can provide for a more robust and controllable compressor with better operating conditions and performance. It can be used for compressor wheels with or without splitter blades but it works most efficiently for compressor wheels without splitter blades.
- For a better understanding of the present invention and to show how the same may be carried into effect, reference is made to the accompanying drawings in which:
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FIG. 1 is a cross-section of a vehicle engine turbocharger compressor incorporating a diffuser according to the present invention; -
FIG. 2 is a plan view of a part of the compressor diffuser shown inFIG. 1 ; -
FIG. 3 is a plan view of a vane forming part of the compressor diffuser inFIGS. 1 and 2 illustrating its path of movement; -
FIG. 4 is a plan view of an alternative design shape for the vane; -
FIG. 5 is a cross-sectional view of the vane ofFIG. 3 ; -
FIGS. 6 a and 6 b are cross-sectional views of alternative arrangements of the vane ofFIG. 3 . -
FIG. 7 is a graph showing pressure ratio plotted against corrected air flow for the embodiment ofFIG. 1 . -
FIG. 8 is a perspective view, from the side, of a compressor wheel used in a preferred embodiment of the invention. -
FIG. 9 is a front view of a compressor wheel which may be used in an alternative embodiment of the invention. - In
FIG. 1 a turbine housing 12 is adapted to receive exhaust gas from a vehicle engine and channel the gas to aturbine wheel 14 coupled to one end of ashaft 16. The exhaust gas drives theturbine wheel 14 and thus rotates theshaft 16. The other end of theshaft 16 is connected to acompressor wheel 18, which is mounted in acompressor housing 19. Thecompressor wheel 18 rotates with theshaft 16 and draws in air through theintake 20. The pressure of this air is boosted by thecompressor wheel 18 and channeled through adiffuser section 22 of the compressor to anair outlet 24 and ultimately to the vehicle engine for use in the combustion process. -
Compressor wheel 18 comprises a hub to whichimpeller blades 40 are attached. Theblades 40 may be what are known in the industry as full blades or splitter blades. Full blades are shown inFIG. 8 and a mixture of full and splitter blades is shown inFIG. 9 . Thefull impeller blades 40 occupy the gap between the hub and aninner shroud wall 41 and have an outer edge substantially matching the profile of the inner surface of theshroud wall 41 to ensure a close tolerance.Splitter blades 50 do not extend as far axially forward as full blades. They are typically located between thefull blades 40 as shown inFIG. 9 . Compressors with splitter blades tend to be noisier than the compressors with full blades because the frequency of the noise is in the audible range and the noise level higher due to the extra loading on the blades. Returning toFIG. 1 , there is anouter shroud wall 42 surrounding theinner shroud wall 41 and forming anannular venting chamber 43.FIG. 1 illustrates asingle vent 44 that connects the ventingchamber 43 to the impeller chamber within theinner shroud wall 41. Such a venting arrangement provides a bleed path and improve the surge characteristics of the compressor by providing a vent path for back to return a small amount of pressurized gas to the intake. This arrangement is known as a ported shroud. More than one vent may be provided and each vent may take many forms such as individual bores or circumferential slots (with bridging support struts). Such vents may be arranged so that the airflow through them can be varied, for example with moveable covers so as to optimize the compressor performance depending upon operating conditions. These covers may be slidable or rotatable depending upon the form of the vents. - The compressor wheel may comprise splitter blades or full blades but full blades may be preferred in applications where the noises generated by the vents in the shroud wall are of concern. It has also been found that full bladed compressor wheel also makes the vented shroud more effective in improving the flow range of the compressor.
- An arrangement of variable position vanes 26 is disposed in the
diffuser section 22 and these cooperate with aunison ring 28 which controls their orientation relative to the air flow path. Theunison ring 28 is rotatably disposed within thecompressor housing 19 and is arranged to engage and rotate all of the compressor vanes in unison by cooperation ofslots 32 in theunison ring 28 withtabs 34 on thevanes 26 acting as cam members. - The
unison ring 28 is set into a recess in the wall of thediffuser section 22 and forms a part of the wall thereof. Since the diffuser effectively has two faces we are referring here to one half of the diffuser wall. This provides for a more robust arrangement and is more cost effective since less parts are required. Also theunison ring 28 has a pressure gradient across it which tends to move it axially toward thevanes 26 thus effectively eliminating any clearance gap between the vane side and the diffuser housing. Such a gap is a source of efficiency loss in known arrangements. Theunison ring 28 may effectively be located radially inside of the vanes. It does not open to the gas path, that is to say that its outer peripheral edge is totally located within the recess and the side adjacent the gas path is arranged flush with the rest of the diffuser wall. - The
unison ring 28 is a robust and hard wearing item which has a thickness of about 5% of the compressor wheel tip diameter. A thicker ring tends to reduce the effects of wear through contact but a thinner one reduces wear through vibration. - On the opposite wall of the
diffuser section 22 aninsert ring 30 is located, again set in an indentation in thecompressor housing 19. - The arrangement of the
vanes 26 and theunison ring 28 is shown more clearly inFIG. 2 . Thevanes 26 are wedge shaped i.e. are relatively narrow tapering triangular members, each pivoted atpivot point 36 close to the apex of the triangle. Each has atab 34 acting as a cam member to cooperate with theslot 32 on theunison ring 28. Eachcam member tab 34 has a relatively large surface area configured to provide a maximum area contact with theslots 32 on theunison ring 28. In particular thetabs 34 are generally larger than pins and has a generally elongate oval shape. Theslots 32 are shaped to match the shape of thetabs 34. Such a tab and slot arrangement does not wear out as quickly as a pin and slot arrangement and provides better and more accurate connection and thus more accurate movement of the vanes. The major axis of eachtab 34 is set at an inclined angle with respect to the longitudinal axis of each of thevanes 26 and the angle of eachslot 32 in theunison ring 28 is adapted accordingly. - This is shown more clearly in
FIG. 3 which illustrates a series of positions which thetab 34 occupies in theslot 32 as it slides along the slot in response to the unison ring being rotated. This pivots thevane 26 aboutpivot point 36, close to its leading edge. - An alternative shape and configuration of the
tabs 34 is shown inFIG. 4 . In this embodiment thevanes 26 are curved or cambered and take the shape of a fin with a wide end at the trailing edge where thetab 34 is located, tapering to a narrow end at the leading edge where thepivot 36 is located. Thetab 34, or cam follower, may be molded with thevane 26. - The
pivot point 36 of eachvane 26 is set close to the apex of the triangle to ensure higher efficiency. It is generally desired to locate the pivot point of each vane within 10% of the apex and preferably within 10% of the trailing edges of the compressor wheel. This ensures that the leading edge of thevanes 26 is always at approximately the same distance from thecompressor wheel 18 regardless of the angle of orientation of the vane and improves performance. - The
pivot point 36 of eachvane 34 is made as close to the apex of the triangular wedge as is practically possible to assist the aerodynamic loading of thevanes 34, reducing stress on thevanes 34 under high compressor pressures. - The arrangement of the present invention provides a relatively simple and robust operating mechanism with relatively few parts, making it more hard wearing and cost effective to produce and assemble. Control of the vanes is particularly accurate and sensitive since a wider angle of rotation of the unison ring is required for a given rotation of the vanes.
- The
unison ring 28 is rotated by acrank mechanism 38 to alter the angle of thevanes 34. One possible version of this crankmechanism 38 is described in U.S. 2003/0167767, which is incorporated herein by reference. Thecrank mechanism 38 is located at the top of thediffuser section 22. -
FIG. 5 is a cross-sectional representation of avane 26 showing thetab 34 close to the trailing edge, engaged in aslot 32 in theunison ring 28. Thepivot 36 is close to the leading edge of the vane and is on the opposite side of the vane to thetab 34. However, the pivot pin could be mounted on the same side of the vane as thetab 34 as shown inFIG. 6 a, in which thepivot pin 36 is formed integrally with thevane 26, andFIG. 6 b, in which thepivot pin 36 is fixed to thevane 26 and less space is available for theunison ring 28. - Adjusting the angle of the
vanes 26 in the diffuser by rotating theunison ring 28, causes the diffuser inlet and outlet areas to be adjusted and thus the diffuser flow area can be set at different values to suit different air mass flow rates. This helps to stabilize the diffuser flow and delay a compressor surge and thus extends the operating range of the compressor. - A combination of at least one
vent 44 in theshroud wall 41 and thevariable vanes 26 in the diffuser improves the operating range of the compressor and improves stability at higher compressor pressure ratios. Improved choke flows are also achievable with such an arrangement. - Referring to
FIG. 7 , it will be seen that the combination of ported shroud and variable vanes produces a more advantageous performance map than would otherwise be expected. The lines 50-56 joining the solid point markers represent the performance of a compressor using a variable diffuser and a vented shroud for compressor corrected speeds between 95,000 and 210,000 rpm. The lines 60-66 joining the shaded point markers, represent the performance of a compressor without a vented shroud for the same values of corrected compressor speeds. The corrected speed is the compressor physical speed corrected to a standard reference inlet condition. The numbers 62% to 75% on the Figure show compressor total to total efficiency. - It will clearly be seen that the results for the combination of the vented shroud and the variable values shown by the compressor map comprising lines 50-56 provides higher pressure ratios for given airflows and given corrected compressor speeds and thus results in superior performance, particularly at high compressor speeds.
- Normally at higher pressure ratios, it is very difficult to achieve a wide flow range, but the
vent 44 reduces the surge flow and increases the choke flow and thus improves the flow range whilst increasing the attainable compressor pressure ratios, and its efficiency. The combination also addresses the known problem of vaned diffusers having a tendency toward instability in that thevent 44 tends to make the compressor more stable.
Claims (27)
1. A compressor for a turbocharger comprising:
a diffuser assembly comprising a diffuser housing defining a gas inlet and a gas outlet pneumatically connected by a gas flow path, a plurality of pivotally mounted diffuser vanes arranged in the flow path, and a vane angle control device for adjusting the angle of the diffuser vanes wherein the vane control device further comprises a unison ring coupled to the diffuser vanes in such a way that rotation of the unison ring pivots each of the diffuser vanes by interaction of a cam surface with a respective cam follower; and,
an impeller assembly positioned adjacent the diffuser assembly, the impeller assembly comprising an impeller wheel having a plurality of impeller blades adjoined thereto, a shroud wall extending circumferentially around the impeller blades, a venting chamber defined by the shroud wall and removed from the impeller wheel, wherein the shroud wall comprises at least one vent pneumatically connecting the impeller wheel to said venting chamber.
2. A compressor according to claim 1 further comprising means for controlling the airflow through each vent.
3. A compressor according to claim 2 wherein the means for controlling the airflow through the or each vent comprises a sliding cover.
4. A compressor according to claim 2 wherein the means for controlling the airflow through the or each vent comprises a rotatable cover.
5. A compressor according to claim 2 wherein the airflow through the or each vent is independently controllable.
6. A compressor according to claim 1 wherein a portion of the plurality of impeller blades comprise splitter blades and the remainder of plurality of impeller blade comprise full blades, wherein said full blades extend greater axial distance from the impeller wheel than the splitter blades.
7. A compressor according to claim 1 wherein all of said plurality of impeller blades are full blades.
8. A compressor according to claim 1 wherein the unison ring is mounted for rotation in a recess in the diffuser housing such that the side of the unison ring exposed to the gas flow in the gas path is generally flush with the remainder of the diffuser housing making up a side wall of the flow path, so that the exterior circumferential edge of the ring is not in the flow path.
9. A compressor according to claim 8 wherein the impeller wheel has a diameter and the unison ring has a thickness about 5% of the impeller wheel diameter.
10. A compressor according to claim 1 wherein each diffuser vane comprises a leading end and a trailing end and each is pivotally mounted about a pivot point adjacent the leading end.
11. A compressor according to claim 1 wherein the cam follower has a generally elongate oval shape in cross section to engage the cam surface over a contact surface.
12. A compressor according to claim 1 wherein the cam follower is formed as a tab on each vane and the respective cam surfaces are formed on the unison ring.
13. A compressor diffuser according to claim 1 wherein each cam surface is formed as an internal surface of an elongate slot in the unison ring, and wherein the slot has an arcuate form.
14. A compressor according to claim 11 wherein the elongate oval shape of the cam follower comprises a central generally rectangular region and two curved end regions.
15. A compressor according to claim 14 wherein the elongate oval shape of the cam follower further comprises a region having a trapezium cross-section formed between the rectangular region and each curved end section, so as to present at least three generally planar sides on each side of the cam follower.
16. A compressor according to claim 11 wherein the cam surface is contoured to be complementary to the engaging surface of the cam follower so as to maximize the area of the contact surface between the cam and the cam follower.
17. A compressor according to claim 1 wherein each vane has an elongate isosceles triangle shape with the apex of the triangle forming said one end, and the angle subtended at the apex of the triangle is between about 5 degrees and 15 degrees.
18. A compressor according to claim 1 wherein at least one side of each vane is curved.
19. A compressor according to claim 1 wherein the vane angle control device further comprises a rack and pinion driven crank shaft.
20. A compressor according to claim 19 wherein the vane angle control device further comprises a spring biased variable current solenoid.
21. A compressor according to claim 20 wherein the crank shaft is coupled to the solenoid via a cam on the crank shaft to provide direct position feedback to the solenoid.
22. A compressor according to claim 1 wherein each vane is pivotally mounted by means of a pivot pin on the vane which engages with a hole in the diffuser housing, and wherein the pivot pin and the cam follower are mounted on the same side of the vane and the pivot pin extends beyond the tab.
23. A turbocharger comprising a compressor according to claim 1 .
24. A turbocharger according to claim 23 further comprising means for controlling the airflow through the or each vent.
25. A compressor for a turbocharger, comprising a diffuser assembly adjoined to an impeller assembly,
the diffuser comprising:
a diffuser housing defining a gas flow path having a side wall connecting a gas inlet to a gas outlet and a plurality of diffuser vanes arranged in the flow path to control gas flow; and, the impeller assembly comprising:
an impeller wheel having a plurality of impeller blades attached thereto, a venting chamber and a compressor housing shroud wall extending around the impeller blades and separating the impeller wheel from said venting chamber, wherein the shroud wall comprises at least one vent pneumatically connecting the impeller wheel to said venting chamber.
26. A compressor according to claim 25 wherein all of said plurality of impeller blades are full blades extending from the impeller wheel to a similar axial position.
27. A compressor according to claim 26 wherein the diffuser vanes are pivotally mounted such that their angle relative to the flow path can be adjusted.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
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US10/914,562 US20050123394A1 (en) | 2003-12-03 | 2004-08-09 | Compressor diffuser |
PCT/US2004/040751 WO2005057018A1 (en) | 2003-12-03 | 2004-12-03 | Compressor diffuser |
EP04813122A EP1700040A1 (en) | 2003-12-03 | 2004-12-03 | Compressor diffuser |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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US10/727,845 US20050123397A1 (en) | 2003-12-03 | 2003-12-03 | Compressor diffuser |
US10/914,562 US20050123394A1 (en) | 2003-12-03 | 2004-08-09 | Compressor diffuser |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US10/727,845 Continuation-In-Part US20050123397A1 (en) | 2003-12-03 | 2003-12-03 | Compressor diffuser |
Publications (1)
Publication Number | Publication Date |
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US20050123394A1 true US20050123394A1 (en) | 2005-06-09 |
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ID=34681731
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US10/914,562 Abandoned US20050123394A1 (en) | 2003-12-03 | 2004-08-09 | Compressor diffuser |
Country Status (3)
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US (1) | US20050123394A1 (en) |
EP (1) | EP1700040A1 (en) |
WO (1) | WO2005057018A1 (en) |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1867840A2 (en) * | 2006-06-13 | 2007-12-19 | Honeywell International Inc. | Variable nozzle device |
US20100080694A1 (en) * | 2008-10-01 | 2010-04-01 | Kansas State University Research Foundation | Variable geometry turbocharger |
US20100098532A1 (en) * | 2007-02-14 | 2010-04-22 | Borgwarner Inc. | Compressor housing |
DE102008059616A1 (en) | 2008-11-28 | 2010-06-02 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Charging device, particularly exhaust gas turbocharger for internal combustion engine of motor vehicle, has variable turbine- or supercharger geometry and blade bearing ring with rotatably mounted guide blades |
CN101786143A (en) * | 2010-03-02 | 2010-07-28 | 中国农业大学 | Adjustable mold of spiral case and seat ring of micro hydraulic turbine |
US20120082539A1 (en) * | 2010-06-18 | 2012-04-05 | Khimani Mohiki | Variable geometry turbine |
US20180274376A1 (en) * | 2017-03-27 | 2018-09-27 | General Electric Company | Diffuser-deswirler for a gas turbine engine |
US20190345838A1 (en) * | 2018-05-11 | 2019-11-14 | Rolls-Royce Corporation | Variable diffuser having a respective penny for each vane |
US11326619B2 (en) * | 2017-08-18 | 2022-05-10 | Abb Schweiz Ag | Diffuser for a radial compressor |
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US7478991B2 (en) | 2006-03-06 | 2009-01-20 | Honeywell International, Inc. | Variable nozzle device |
DE102007025128A1 (en) * | 2007-05-30 | 2008-12-04 | Mahle International Gmbh | loader |
DE102008027157B4 (en) * | 2008-06-06 | 2014-07-17 | Pierburg Pump Technology Gmbh | Adjustable coolant pump for the cooling circuit of an internal combustion engine |
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CN101786143A (en) * | 2010-03-02 | 2010-07-28 | 中国农业大学 | Adjustable mold of spiral case and seat ring of micro hydraulic turbine |
US20120082539A1 (en) * | 2010-06-18 | 2012-04-05 | Khimani Mohiki | Variable geometry turbine |
US20180274376A1 (en) * | 2017-03-27 | 2018-09-27 | General Electric Company | Diffuser-deswirler for a gas turbine engine |
US10718222B2 (en) * | 2017-03-27 | 2020-07-21 | General Electric Company | Diffuser-deswirler for a gas turbine engine |
US11098601B2 (en) | 2017-03-27 | 2021-08-24 | General Electric Company | Diffuser-deswirler for a gas turbine engine |
US11326619B2 (en) * | 2017-08-18 | 2022-05-10 | Abb Schweiz Ag | Diffuser for a radial compressor |
US20190345838A1 (en) * | 2018-05-11 | 2019-11-14 | Rolls-Royce Corporation | Variable diffuser having a respective penny for each vane |
US10883379B2 (en) * | 2018-05-11 | 2021-01-05 | Rolls-Royce Corporation | Variable diffuser having a respective penny for each vane |
Also Published As
Publication number | Publication date |
---|---|
EP1700040A1 (en) | 2006-09-13 |
WO2005057018A1 (en) | 2005-06-23 |
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