HOUSING ASSEMBLY FOR A TURBOCHARGER
A compressor housing assembly is disclosed. The compressor housing assembly includes a compressor housing including a compressor housing flange. The compressor housing assembly may include a bearing housing. The bearing housing may include a body portion and a web. The web may extend outward from the body portion to a web end. The bearing housing may also include a bearing housing flange extending radially outward from the web. The compressor housing assembly may also include a clamping plate having a generally annular shape. The clamping plate may abut on the compressor housing flange and the bearing housing flange. In addition, the compressor housing assembly may include a fastener configured to attach the clamping plate to the compressor housing flange and the bearing housing flange.
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The present disclosure relates generally to a housing assembly and, more particularly, to a housing assembly for a turbocharger.
BACKGROUNDInternal combustion engines, for example, diesel engines, gasoline engines, or natural gas engines employ turbochargers to deliver compressed air for combustion in the engine. A turbocharger compresses air flowing into the engine, helping to force more air into combustion chambers of the engine. The increased supply of air allows for increased fuel combustion in the combustion chambers, resulting in increased power output from the engine.
A typical turbocharger includes a shaft, a turbine wheel connected to one end of the shaft, a compressor wheel connected to the other end of the shaft, and bearings to support the shaft. Often a turbine housing surrounds the turbine wheel and a separate compressor housing surrounds the compressor impeller. In addition, the turbocharger may include a bearing housing that surrounds the bearings and includes features that help prevent leakage of bearing lubrication oil into the turbine housing or the compressor housing. The turbine housing, the compressor housing, and the bearing housing are attached to each other via fasteners or other clamping mechanisms.
Hot exhaust from the engine flows through the turbine housing and expands over the turbine wheel, rotating the turbine wheel and the shaft connected to the turbine wheel. The shaft in turn rotates the compressor impeller. Relatively cool air from the ambient flows through the compressor housing where the compressor impeller compresses the air and drives the compressed air into the combustion chambers of the engine. Because the exhaust from the engine is significantly hotter than the ambient air, the turbine housing can experience temperatures significantly higher than the compressor housing. The bearing housing, lying between the turbine housing and the compressor housing, experiences temperatures relatively lower than that of the turbine housing and relatively higher than that of the compressor housing. Because of the different temperatures of the turbine housing, the compressor housing, and the bearing housing, these components may experience different amounts of thermal expansion. The differential thermal expansion causes relative motion between the turbine housing, the compressor housing, and the bearing housing, making it difficult to keep these components securely fastened to each other during operation of the turbocharger. Moreover, the relative motion may also induce mechanical fatigue in the connecting fasteners, reducing the useful life of the fasteners.
U.S. Patent Application Publication No. 2013/0259661 of Shudo et al. that published on Oct. 3, 2013 (“the '661 publication”) discloses a sealing structure for sealing joint surfaces of a turbine housing and a bearing housing of a turbocharger. In particular, the '661 publication discloses a turbine housing that has an end face including an inner end face that makes contact with a bearing housing. The '661 publication discloses that the bearing housing has a flange that has a height difference relative to the end face of the turbine housing. The '661 publication also discloses that a flanged bolt engages with the turbine housing to connect the bearing housing and the turbine housing such that a flange of the bearing housing is sandwiched between the flange portion of the bolt and the inner end face of the turbine housing. The '661 publication also discloses an embodiment which uses a washer abutting on the turbine housing and bearing housing surfaces. A flanged bolt passes through the washer to engage with the turbine housing such that the bearing housing is sandwiched between the flange portion of the bolt and the inner end face of the turbine housing. Although the '661 publication discloses a flanged bolt with or without a washer to attach a turbine housing and a bearing housing of a turbocharger, the disclosed method of assembly may still not be optimal. For example, both the flange portion of the bolt and the washer may induce bending loads on the bolt, which in turn may cause failure in the bolt.
The housing assembly of the present disclosure solves one or more of the problems set forth above and/or other problems of the prior art.
SUMMARYIn one aspect, the present disclosure is directed to a compressor housing assembly. The compressor housing assembly includes a compressor housing including a compressor housing flange. The compressor housing assembly may include a bearing housing. The bearing housing may include a body portion and a web. The web may extend outward from the body portion to a web end. The bearing housing may also include a bearing housing flange extending radially outward from the web. The compressor housing assembly may also include a clamping plate having a generally annular shape. The clamping plate may abut on the compressor housing flange and the bearing housing flange. In addition, the compressor housing assembly may include a fastener configured to attach the clamping plate to the compressor housing flange and the bearing housing flange.
In another aspect, the present disclosure is directed to a turbine housing assembly. The turbine housing assembly may include a turbine housing wall. The turbine housing assembly may also include a bearing housing including a bearing housing flange. The turbine housing assembly may further include a clamping plate having a generally annular shape. The clamping plate may abut on the turbine housing wall and the bearing housing flange. In addition, the turbine housing assembly may include at least one fastener configured to attach the clamping plate to the turbine housing wall and the bearing housing flange.
In yet another aspect, the present disclosure is directed to a turbocharger. The turbocharger may include a turbine housing including a turbine housing wall. The turbocharger may also include a turbine wheel disposed within the turbine housing and configured to be driven by exhaust received from an engine. Further, the turbocharger may include a compressor housing including a compressor housing flange. The turbocharger may also include a compressor impeller disposed within the compressor housing. The turbocharger may include a shaft connecting the turbine wheel and the compressor impeller. In addition, the turbocharger may include a bearing housing. The bearing housing may include a first bearing housing flange configured to be attached to the compressor housing flange. The bearing housing may also include a second bearing housing flange configured to be attached to the turbine housing wall. The turbocharger may include a first clamping plate having a generally annular shape. The first clamping plate may abut on the compressor housing flange and the first bearing housing flange. The turbocharger may also include a second clamping plate having a generally annular shape. The second clamping plate may abut on the turbine housing wall and the second bearing housing flange. The turbocharger may further include a first fastener configured to attach the first clamping plate to the compressor housing flange and the first bearing housing flange. In addition, the turbocharger may include a second fastener configured to attach the second clamping plate to the turbine housing wall and the second bearing housing flange.
Compressor stage 12 may be enclosed by compressor housing 40. Turbine stage 14 may be enclosed by turbine housing 42. Bearing housing 44 may enclose bearings (not shown) that may support shaft 18. Bearing housing 44 may be attached to compressor housing 40 via bolts 46. Likewise, bearing housing 44 may be attached to turbine housing 42 via bolts 48. Compressor impeller 16, shaft 18, turbine wheel 34, compressor housing 40, turbine housing 42, and bearing housing 44 may be disposed around rotational axis 50 of turbocharger 10.
Exhaust gases exiting the engine (not shown) may enter turbine housing 42 via turbine inlet 52 and exit turbine housing 42 via turbine outlet 54. The hot exhaust gases may move through turbine housing 42, expanding against turbine blades 38, rotating turbine wheel 34. Rotation of turbine wheel 34 may rotate shaft 18, which in turn may rotate compressor impeller 16. Air may enter compressor housing 40 via compressor inlet 56 and exit compressor housing 40 via compressor outlet 58. As air moves through compressor stage 12, compressor impeller 16 may spin and accelerate the air. Compressor stage 12 may include diffuser ring 60, which may help slow down the air, causing an increase in the pressure of the air within compressor stage 12. Compressed air from compressor stage 12 may be directed into the engine.
As further illustrated in
As also illustrated in
Bearing housing flange 106 may extend radially outward from web end 108 to bearing housing flange end 110. In one exemplary embodiment as illustrated in
Bearing housing flange 106 may also include a flange recess 120, which may extend axially inwards from flange front face 112 towards flange rear face 114. Flange recess 120 may extend radially from adjacent web end 108 to recess outer edge 122. In one exemplary embodiment as illustrated in
Web 104 may include a first web face 126, ledge 128, and second web face 130. First web face 126 may extend outward from adjacent outer edge 78 of third row 32 to ledge 128 disposed between outer edge 78 and web end 108. First web face 126 may be inclined at an angle “θ2” relative to an axial plane disposed generally orthogonal to rotational axis 50. First web face 126 may be disposed opposite to and axially spaced apart from inner wall 132 of diffuser portion 70 of compressor housing 40. Inner wall 132 may be inclined at an angle “θ3” relative to an axial plane disposed generally orthogonal to rotational axis 50. First web face 126 and inner wall 132 may form passageway 134. First web face 126 and inner wall 132 may have a smooth shape that may help ensure that air can travel from outer edges 78 of compressor blades 26 through passageway 134 without significantly altering a velocity or direction of the air. In one exemplary embodiment, first web face 126 may have a smooth curvilinear shape that may conform to a shape of compressor blades 26. Likewise, inner wall 132 may have a smooth curvilinear shape that may conform to a surface defined by outer edges 78 of compressor blades 26 in first, second, and third rows 28, 30, 32.
Ledge 128 may have a generally cylindrical ledge outer surface 136, which may have a radius “R5” relative to rotational axis 50. Ledge outer surface 136 may extend axially from first web face 126 to ledge end 138 disposed between first web face 126 and compressor rear end 64. Radius R5 of ledge outer surface 136 may be larger than a radius “R2” of outer edges 78 of compressor blades 26 in third row 32. Ledge outer surface 136 may also include a generally annular groove 140. Ledge 128 may include ledge axial face 142 that may be axially spaced apart from first web face 126. Ledge axial face 142 may be disposed at ledge end 138. Ledge axial face 142 may extend radially outward from ledge outer surface 136 to second web face 130. In one exemplary embodiment as illustrated in
Diffuser ring 60 may be disposed between inner wall 132 of compressor housing 40 and second web face 130 of bearing housing 44. Diffuser ring 60 may include back plate 146 and one or more vanes 148. In one exemplary embodiment as illustrated in
Top face 156 of back plate 146 may extend axially from front face 154 to axial rear face 162 disposed adjacent recess seating surface 124. Top face 156 may have a generally cylindrical shape. Top face 156 may be disposed adjacent inner face 166 of volute rear wall 100. Inner face 166 of volute rear wall 100 may also have a generally cylindrical shape. Top face 156 of back plate 146 may be radially separated from inner face 166 by a radial gap 168. Bottom face 158 of back plate 146 may extend axially from front face 154 towards inclined rear face 160 disposed adjacent second web face 130. Bottom face 158 may abut on ledge outer surface 136. Bottom face 158 may have a generally cylindrical shape. It is contemplated, however, that bottom face 158 may have a non-cylindrical shape. Seal member 170 may be disposed in groove 140 between ledge outer surface 136 and bottom face 158. In one exemplary embodiment as illustrated in
Axial rear face 162 of back plate 146 may be axially separated from front face 154 of back plate 146. Axial rear face 162 may extend radially inward from top face 156 to adjacent web end 108. Axial rear face 162 may connect top face 156 with inclined rear face 160. In one exemplary embodiment as shown in
Recess 164 may be disposed adjacent bottom face 158 and between bottom face 158 and inclined rear face 160. Recess 164 may include recess upper face 174 and recess side face 176. Recess upper face 174 may have a generally cylindrical shape and may extend axially from inclined rear face 160 towards front face 154. Recess upper face 174 may be radially separated from ledge outer surface 136. In one exemplary embodiment as illustrated in
Vane 148 may extend radially and axially outward from front face 154 of back plate 146 to vane tip 178. In one exemplary embodiment as illustrated in
Wave spring 184 may be disposed in recess 164 between ledge axial face 142 and recess side face 176 of recess 164 in back plate 146. Wave spring 184 may have a generally annular shape having an inner radius, which may be larger than a radius R5 of ledge outer surface 136. Wave spring 184 may include a plurality of waves on axial face 186 of wave spring 184. In one exemplary embodiment, wave spring 184 may have about 11 waves. Wave spring 184 may have an axial thickness ranging from 2 mm to 4 mm. In an assembled configuration as illustrated in the exemplary embodiment of
As also illustrated in
Vaneless space 200 may be inclined at an angle “θ6” relative to an axial plane disposed generally orthogonal to rotational axis 50. Angle θ6 may be measured between an axis 206 of vaneless space 200 and an axial plane disposed generally orthogonal to rotational axis 50. For example, axis 206 of vaneless space 200 may be defined as a line connecting midpoints 202 and 204 of passageway 134. Midpoint 202 may be disposed adjacent an outer edge 78 of compressor blades 26. Midpoint 204 may be disposed adjacent a vane leading edge 180. As used in this disclosure midpoint 202 may be disposed within passageway 134 halfway between inner wall 132 and second web face 130. Similarly, midpoint 204 may be disposed within passageway 134 halfway between inner wall 132 and front face 154 of back plate 146. One of ordinary skill in the art would recognize that axis 206 may not always be disposed parallel to inner wall 132 and/or second web face 130. As also illustrated in
The above description refers to angles θ1, θ2, θ3, θ4, θ5, and θ6. It is contemplated that angles θ1, θ2, θ3, θ4, θ5, and θ6 may be equal or unequal. In one exemplary embodiment, each of angles θ1, θ2, θ3, θ4, θ5, or θ6 may range from about 0° to about 45°.
As illustrated in
As further illustrated in
Returning to
An axial distance “B” (see
Compressor housing 40 may have a compressor housing flange 270 attached to volute top wall 98 and volute rear wall 100. Compressor housing flange 270 may have a generally cylindrical flange outer surface 272. Flange outer surface 272 may have a radius “R7” relative to rotational axis 50. Compressor housing flange 270 may also include flange inner surface 274, which may have a radius “R8” relative to rotational axis 50. Radius R8 may be larger than or about equal to radius R3 of flange outer surface 116 of bearing housing flange 106. Radius R8 may also be smaller than radius R7. Flange inner surface 274 may be disposed adjacent to and may abut on flange outer surface 116 of bearing housing flange 106 of bearing housing 44. Compressor housing flange 270 may include a clamping face 276, which may extend radially from flange inner surface 274 at radius R8 to flange outer surface 272 at radius R7. Clamping face 276 may have a radial width “W2,” which may be smaller than a width W1 of clamping plate 262.
Clamping face 276 of compressor housing flange 270 may include compressor flange recess 278 and compressor flange lip 280. Compressor flange recess 278 may extend axially inwards from clamping face 276 towards compressor front end 62 forming compressor flange lip 280 on clamping face 276. Compressor flange recess 278 may extend radially outward from flange inner surface 274 to recess outer edge 282 disposed between flange inner surface 274 and flange outer surface 272. Compressor flange recess 278 may have a radial width “W3,” which may be smaller than a radial width W2 of clamping face 276. In one exemplary embodiment width W3 may range from about 70% to about 90% of width W2. As illustrated in
Recess surface 284 of compressor housing flange 270 may include a plurality of holes 286. Like holes 268, holes 286 may be circumferentially spaced from each other. A circumferential spacing between holes 286 may be uniform or non-uniform. Holes 286 may be arranged so as to align with holes 268. Holes 286 may also be threaded. Bolts 46 may pass through holes 268 and may be threadingly received in holes 286 to help connect clamping plate 262 with compressor housing flange 270. In some exemplary embodiments, bolts 46 may be also threadingly received in holes 268. Although
Clamping plate 262 may include clamping plate overhang portion 288, which may extend radially inward from adjacent flange inner surface 274. Overhang portion 288 may include a front face portion 290 that may abut on flange rear surface 114 of bearing housing flange 106. As illustrated in
Turbine housing 42 may have a turbine housing wall 320. Turbine housing wall 320 may include a notch 322. Notch 322 may have a notch inner surface 324 and a notch rear wall 326. Notch inner surface 324 may have a generally cylindrical shape disposed around rotational axis 50. Notch rear wall 326 may extend radially inward from notch inner surface 324 and may be disposed generally orthogonal to rotational axis 50. Turbine housing wall 320 may also include turbine inner surface 328, which may enclose turbine wheel 34 (see
Clamping face 330 of turbine housing wall 320 may include turbine flange recess 334 and turbine wall lip 336. Turbine flange recess 334 may extend axially inwards from clamping face 330 towards turbine inner surface 328 forming turbine wall lip 336. Turbine flange recess 334 may extend radially outward from notch inner surface 324 to recess outer edge 338 disposed between notch inner surface 324 and turbine wall outer end 332. Turbine flange recess 334 may have a radial width “W5,” which may be smaller than a radial width W4 of clamping plate 312. In one exemplary embodiment radial width W5 may range from about 70% to about 90% of width W4. As illustrated in
Bearing housing 44 may include a bearing housing flange 344. Bearing housing flange 344 may have front face 346, rear face 348 disposed opposite front face 346, and bearing flange outer surface 350. Bearing housing flange 344 may abut on notch rear wall 326 of turbine housing wall 320 such that bearing flange outer surface 350 may be disposed adjacent to and may abut on notch inner surface 324. Clamping plate 312 may include an overhang portion 352, which may extend radially inward from holes 318. Overhang portion 352 may include a rear face portion 354 that may abut on front face 346 of bearing housing flange 344. As illustrated in
Bolts 48 may pass through holes 318 and may be threadingly received in holes 342 to help connect clamping plate 312 with turbine housing wall 320 and bearing housing flange 344. In some exemplary embodiments, bolts 48 may be also threadingly received in holes 318. Although
The disclosed compressor assembly 90 may be implemented to help reduce or eliminate leakage of air through gaps between vane tips 178 of compressor diffuser ring 60 and inner wall 132 of compressor housing 40. Compressor assembly 90 may also be implemented to help improve an efficiency of compressor stage 12 by using shim 246 dimensionally matched to turbocharger cartridge 256 to help reduce or eliminate gaps between vane tips 178 and inner wall 132.
Additionally, compressor assembly 90 may be implemented to reduce or eliminate failure of compressor blades induced by excitation of compressor blades 26 caused by pressure wakes generated by vanes 148 in diffuser ring 60. Further, compressor assembly 90 may be implemented to help ensure that compressor housing 40, bearing housing 44, and turbine housing 42 may be assembled without inducing bending loads on bolts 46, 48. The disclosed compressor assembly 90 may also be implemented help reduce wear on internal components of compressor assembly 90 caused by thermally induced relative movement between the components.
Referring to
Compressor assembly 90 may include numerous features that help to reduce or eliminate gaps between vane tips 178 and inner wall 132 of compressor housing 40. For example, compressor assembly 90 may include a wave spring 184 disposed between second web face 130 and back plate 146 of diffuser ring 60. Wave spring 184 may exert an axial force on back plate 146 forcing diffuser ring 60 to move towards compressor front end 62 and pushing vane tips 178 to firmly come into contact with inner wall 132 of compressor housing 40. By forcing vane tips 178 to firmly abut on inner wall 132, wave spring 184 may help reduce or eliminate gaps between vane tips 178 and inner wall 132 at all operating conditions of turbocharger 10. Wave spring 184 may also help reduce or eliminate damage caused to vanes 148 when the turbocharger is not operational by helping to urge vane tips 178 to come into contact with inner wall 132. Allowing vane tips 178 to remain in contact with inner wall 132 in this manner may help prevent excessive vibration of vanes 148, which in turn may help reduce or eliminate damage to vanes 148.
Furthermore, during operation of turbocharger 10, high pressure air from volute 72 may bleed through radial gap 168 into cavity 172. The high pressure air may help push back plate 146 away from second web face 130 toward compressor front end 62, which in turn may urge vane tips 178 to firmly come into contact with inner wall 132 of compressor housing 40. By forcing vane tips 178 to firmly abut on inner wall 132, bleed air in cavity 172 may help reduce or eliminate gaps between vane tips 178 and inner wall 132 during high pressure operation of compressor stage 12.
Radial gap 168 and seal member 170 may also help back plate 146 of diffuser ring 60 to freely expand thermally during operation of compressor stage 12. For example, diffuser ring 60 may be made of aluminum, aluminum alloy, or other alloys, which has a relatively high coefficient of thermal expansion compared to compressor housing 40 and bearing housing 44, both of which may be made of an iron alloy or other alloys. The radial gap 168 and the compressive nature of seal member 170 may allow back plate 146 to expand without coming into contact with or interfering with inner face 166 of volute rear wall 100 of bearing housing 44. Moreover, because seal member 170 is disposed on ledge outer surface 136, which is disposed generally orthogonal to wave spring 184, the axial force exerted by wave spring 184 may not diminish the compressive forces generated in seal member 170. As a result operation of wave spring 184 may not diminish the strength of the seal generated by seal member 170 between ledge outer surface 136 and bottom face 158 of back plate 146. Consequently, seal member 170 may be able to maintain a very effective seal, preventing recirculation of air from volute 72 through cavity 172 and into passageway 134 during the entire range of operation of turbocharger 10, helping to improve the efficiency of compressor stage 12.
Referring to
Referring to
Referring to
Additionally, when turbocharger 10 with four tabs 226 is mounted on a horizontal surface with the gravitational direction being generally orthogonal to the horizontal surface, first and second diametrical axes 237 and 238 may be positioned symmetrically about the gravitational direction. Positioning first and second diametrical axes 237, 238 in this manner may allow an entire weight of turbocharger 10 to be about equally distributed on each of the four tabs 226. Furthermore, such an arrangement may also allow additional radial loads generated by the operation of turbocharger 10 to be distributed about equally between the four tabs 226.
Referring to
Referring to
It will be apparent to those skilled in the art that various modifications and variations can be made to the disclosed compressor assembly. Other embodiments will be apparent to those skilled in the art from consideration of the specification and practice of the disclosed compressor assembly. It is intended that the specification and examples be considered as exemplary only, with a true scope being indicated by the following claims and their equivalents.
Claims
1. A compressor housing assembly, comprising:
- a compressor housing including a compressor housing flange;
- a bearing housing, including: a body portion; a web extending outward from the body portion to a web end, the web; and a bearing housing flange extending radially outward from the web;
- a clamping plate having a generally annular shape abutting on the compressor housing flange and the bearing housing flange; and
- a fastener configured to attach the clamping plate to the compressor housing flange and the bearing housing flange.
2. The compressor housing assembly of claim 1, wherein
- the compressor housing flange includes a threaded hole, and
- the fastener includes threads that engage with the threaded hole.
3. The compressor housing assembly of claim 1, wherein
- the compressor housing flange includes: a generally cylindrical flange inner surface; a generally cylindrical flange outer surface; and a clamping face extending radially from the flange inner surface to the flange outer surface,
- the bearing housing flange includes a flange rear surface, and
- the clamping face is disposed generally coplanar with the flange rear surface.
4. The compressor housing assembly of claim 3, wherein
- the clamping face includes: a compressor flange recess extending radially outward from the flange inner surface to a recess outer edge disposed between the flange inner surface and the flange outer surface; and a compressor flange lip extending radially from the recess outer edge to the flange outer surface, and
- the clamping plate is configured to abut on the compressor flange lip and the flange rear surface.
5. The compressor housing assembly of claim 1, wherein the clamping plate includes a plurality of clamping plate segments disposed circumferentially relative to a rotational axis of the compressor housing assembly.
6. The compressor housing assembly of claim 5, wherein a number of the clamping plate segments is 3.
7. The compressor housing assembly of claim 1, wherein the clamping plate segments include:
- a first clamping plate segment spanning over a first circumferential angle;
- a second clamping plate segment spanning over a second circumferential angle; and
- a third clamping plate segment spanning over a third circumferential angle.
8. The compressor housing assembly of claim 7, wherein the first circumferential angle is about equal to the second circumferential angle.
9. The compressor housing assembly of claim 7, wherein
- the first clamping plate segment has a first thickness, and
- the second clamping plate segment has a second thickness different from the first thickness.
10. A turbine housing assembly, comprising:
- a turbine housing including a turbine housing wall;
- a bearing housing, including a bearing housing flange;
- a clamping plate having a generally annular shape abutting on the turbine housing wall and the bearing housing flange; and
- at least one fastener configured to attach the clamping plate to the turbine housing wall and the bearing housing flange.
11. The turbine housing assembly of claim 10, wherein
- the turbine housing wall includes: a turbine inner surface configured to enclose a turbine wheel; and a clamping face disposed opposite the turbine inner surface,
- the bearing housing flange includes: a front face; a rear face disposed opposite the front face; and a bearing flange outer surface, and
- the clamping face is disposed generally coplanar with the front face.
12. The turbine housing assembly of claim 11, wherein
- the clamping face includes: a turbine flange recess extending axially inward from the clamping face towards the turbine inner surface; and a turbine wall lip disposed adjacent the turbine flange recess, and
- the clamping plate is configured to abut on the turbine wall lip and the front face of the bearing housing flange.
13. The turbine housing assembly of claim 12 further including a plurality of fasteners, wherein
- the turbine flange recess includes a plurality of circumferentially spaced holes, and
- the fasteners are configured to be threadingly received in the holes.
14. The turbine housing assembly of claim 13, wherein a circumferential spacing between the holes is non-uniform.
15. The turbine housing assembly of claim 10, wherein the clamping plate includes a plurality of clamping plate segments disposed circumferentially relative to a rotational axis of the turbine housing assembly.
16. A turbocharger, comprising:
- a turbine housing including a turbine housing wall;
- a turbine wheel disposed within the turbine housing and configured to be driven by exhaust received from an engine;
- a compressor housing including a compressor housing flange;
- a compressor impeller disposed within the compressor housing;
- a shaft connecting the turbine wheel and the compressor impeller;
- a bearing housing, including: a first bearing housing flange configured to be attached to the compressor housing flange; a second bearing housing flange configured to be attached to the turbine housing wall;
- a first clamping plate having a generally annular shape abutting on the compressor housing flange and the first bearing housing flange;
- a second clamping plate having a generally annular shape abutting on the turbine housing wall and the second bearing housing flange;
- a first fastener configured to attach the first clamping plate to the compressor housing flange and the first bearing housing flange; and
- a second fastener configured to attach the second clamping plate to the turbine housing wall and the second bearing housing flange.
17. The turbocharger of claim 16, wherein
- the first clamping plate has a first thickness, and
- the second clamping plate has a second thickness different from the first thickness.
18. The turbocharger of claim 17, wherein
- the compressor housing flange includes: a compressor flange recess; and a compressor flange lip disposed adjacent the compressor flange recess, and
- the first clamping plate abuts on the compressor flange lip and the first bearing housing flange.
19. The turbocharger of claim 17, wherein
- the turbine housing wall includes: a turbine flange recess; and a turbine wall lip disposed adjacent the turbine flange recess, and
- the second clamping plate abuts on the turbine wall lip and the second bearing housing flange.
20. The turbocharger of claim 19, wherein
- the first clamping plate includes a first plurality of clamping plate segments, and
- the second clamping plate includes a second plurality of clamping plate segments.
Type: Application
Filed: Mar 9, 2015
Publication Date: Sep 15, 2016
Applicant: CATERPILLAR INC. (Peoria, IL)
Inventors: Richard E. ANNATI (Lafayette, IN), Gary W. POWERS (Lafayette, IN), Jeffrey W. McCORMACK (Fishers, IN), Steven J. O'HARA (Zionsville, IN)
Application Number: 14/642,358