Turbocharger

Abstract

A turbocharger includes a gripping unit gripping a turbine-housing side flange portion and a bearing-housing side flange portion to couple a turbine housing and a bearing housing. In a state where the turbine housing and the bearing housing are coupled by the gripping unit, an elastic force in a direction to separate the turbine-housing side flange portion and the bearing-housing side flange portion from each other is applied to each of the turbine housing and the bearing housing.

Claims

1. A turbocharger, comprising: a turbine rotor; a turbine housing which includes a turbine-housing side flange portion on a radially outer side, and which accommodates the turbine rotor; a bearing device rotatably supporting a shaft connected to the turbine rotor; and a bearing housing which includes, on a radially outer side, a bearing-housing side flange portion facing the turbine-housing side flange portion, and which accommodates the bearing device; and a clamp gripping the turbine-housing side flange portion and the bearing-housing side flange portion to couple the turbine housing and the bearing housing, wherein, in a state where the turbine housing and the bearing housing are coupled by the clamp, an elastic force in a direction to separate the turbine-housing side flange portion and the bearing-housing side flange portion from each other is applied to each of the turbine housing and the bearing housing, wherein the turbocharger further comprises a biasing member disposed between the turbine housing and the bearing housing, and configured to bias the turbine housing and the bearing housing so as to apply the elastic force to the turbine housing and the bearing housing, wherein the biasing member is a back plate disposed between the turbine rotor and the bearing housing, wherein at least a part of the back plate is held between the turbine housing and the bearing housing in an elastically deformed state, wherein the back plate is supported on the turbine housing from a first side in an axial direction of the turbine rotor and is supported on the bearing housing from a second side in the axial direction, wherein the back plate is configured to satisfy an expression dfdi<01, where is a step in the axial direction between a back-plate side first supported portion of the back plate supported on the turbine housing, and a back-plate side second supported portion of the back plate supported on the bearing housing, 0 is the step in a natural state of the back plate, 1 is an initial step of the step in an initial state after the back plate is mounted, d is a distance in the axial direction between a turbine-housing side support portion of the turbine housing supporting the back-plate side first supported portion and a bearing-housing side support portion of the bearing housing supporting the back-plate side second supported portion, di is the distance d in the initial state, and df is the distance d at the time when the turbocharger is at full load, wherein the turbine housing supports a radially outer portion of the back plate in the axial direction of the turbine rotor from a side of the turbine rotor against the elastic force, wherein the bearing housing supports the radially outer portion of the back plate in the axial direction from a side opposite to the turbine rotor against the elastic force, and wherein an inner peripheral edge of the back plate is a free end separated from the bearing housing.

2. The turbocharger according to claim 1, wherein the radially outer portion of the back plate has a cross-sectional shape along the axial direction which is a V shape, a C shape, a rectangular U shape, or an oblique shape intersecting with the axial direction.

3. The turbocharger according to claim 2, wherein a cross-sectional shape of the radially outer portion of the back plate along the axial direction is a V shape, a C shape, or a rectangular U shape, and an opening of the V shape, an opening of the C shape, or an opening of the rectangular U shape is open toward an inner side or an outer side in a radial direction of the turbine rotor.

4. The turbocharger according to claim 1, wherein the radially outer portion of the back plate is elastically deformed opposite to the turbine rotor in the axial direction of the turbine rotor, and wherein the turbine housing supports the back plate on a radially outer side of a position where the radially outer portion is supported by the bearing housing.

5. The turbocharger according to claim 1, wherein the radially outer portion of the back plate is elastically deformed toward the turbine rotor in the axial direction of the turbine rotor, and wherein the turbine housing supports the back plate on a radially inner side of a position where the radially outer portion is supported by the bearing housing.

6. The turbocharger according to claim 1, wherein, in a state where the turbine housing and the bearing housing are coupled by the clamp, the turbine-housing side flange portion and the bearing-housing side flange portion are in contact after the back plate is mounted.

Description

BRIEF DESCRIPTION OF DRAWINGS

(1) FIG. 1 is a schematic cross-sectional view of a turbocharger 100 according to an embodiment of the present invention, taken along the rotational axis of the turbocharger 100.

(2) FIG. 2 is a schematic diagram of the structure of a V-band clamp.

(3) FIG. 3A is an enlarged cross-sectional view showing a turbine-housing side flange portion 6 and a bearing-housing side flange portion 18 before being gripped by a gripping unit 20 of the turbocharger 100 (100A) according to an embodiment.

(4) FIG. 3B is an enlarged cross-sectional view showing a turbine-housing side flange portion 6 and a bearing-housing side flange portion 18 after being gripped by a gripping unit 20 of the turbocharger 100 (100A) according to an embodiment.

(5) FIG. 4 is an enlarged cross-sectional view of a part of a turbocharger 100 (100B) according to an embodiment.

(6) FIG. 5 is an enlarged cross-sectional view of a part of a turbocharger 100 (100C) according to an embodiment.

(7) FIG. 6 is an enlarged cross-sectional view of a part of a turbocharger 100 (100D) according to an embodiment.

(8) FIG. 7 is an enlarged cross-sectional view of a part of a turbocharger 100 (100E) according to an embodiment.

(9) FIG. 8 is an enlarged cross-sectional view of a part of a turbocharger 100 (100F) according to an embodiment.

(10) FIG. 9 is an enlarged cross-sectional view of a part of a turbocharger 100 (100G) according to an embodiment.

(11) FIG. 10 is an enlarged cross-sectional view of a part of a turbocharger 100 (100H) according to an embodiment.

(12) FIG. 11 is an enlarged cross-sectional view of a part of the turbocharger 100 (100B) shown in FIG. 4.

(13) FIG. 12 is an enlarged cross-sectional view of a part of the turbocharger 100 (100C) shown in FIG. 5.

(14) FIG. 13 is an enlarged cross-sectional view of a part of the turbocharger 100 (100H) shown in FIG. 10.

DETAILED DESCRIPTION

(15) Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It is intended, however, that unless particularly identified, dimensions, materials, shapes, relative positions and the like of components described in the embodiments shall be interpreted as illustrative only and not intended to limit the scope of the present invention.

(16) For instance, an expression of relative or absolute arrangement such as in a direction, along a direction, parallel, orthogonal, centered, concentric and coaxial shall not be construed as indicating only the arrangement in a strict literal sense, but also includes a state where the arrangement is relatively displaced by a tolerance, or by an angle or a distance whereby it is possible to achieve the same function.

(17) For instance, an expression of an equal state such as same equal and uniform shall not be construed as indicating only the state in which the feature is strictly equal, but also includes a state in which there is a tolerance or a difference that can still achieve the same function.

(18) Further, for instance, an expression of a shape such as a rectangular shape or a cylindrical shape shall not be construed as only the geometrically strict shape, but also includes a shape with unevenness or chamfered corners within the range in which the same effect can be achieved.

(19) On the other hand, an expression such as comprise, include, have, contain and constitute are not intended to be exclusive of other components.

(20) FIG. 1 is a schematic cross-sectional view of a turbocharger 100 according to an embodiment of the present invention, taken along the rotational axis of the turbocharger 100.

(21) As shown in FIG. 1, the turbocharger 100 includes a turbine rotor 2, a turbine housing 4 which accommodates the turbine rotor 2, a compressor impeller 10 coupled to the turbine rotor 2 via a shaft 8, a compressor housing 12 which accommodates the compressor impeller 10. The turbine housing 4 has a turbine-housing side flange portion 6 on the radially outer side of the turbine housing 4.

(22) Further, the turbocharger 100 includes a bearing device 14 supporting the shaft 8 rotatably, and a bearing housing 16 which accommodates the bearing device 14. The bearing housing 16 has a bearing-housing side flange portion 18 facing the turbine-housing side flange portion 6, disposed on the radially outer side of the bearing housing 16. Further, the turbocharger 100 includes a gripping unit 20 which holds together the turbine-housing side flange portion 6 and the bearing-housing side flange portion 18 to couple the turbine housing 4 and the bearing housing 16.

(23) Further, the turbocharger 100 includes a back plate 24 having an annular shape, disposed along the back surface 26 of the turbine rotor 2, between the turbine rotor 2 and the bearing housing 16, as a heat shield plate for suppressing heat transmission toward the bearing device 14 from high-temperature exhaust gas that flows through the turbine housing 4. The back plate 24 is held between the turbine housing 4 and the bearing housing 16.

(24) The turbocharger 100 is configured to rotary-drive the turbine rotor 2 with exhaust gas of an engine (not shown), compress air through rotation of the compressor impeller 10 provided coaxially with the turbine rotor 2, and supply the compressed air to the engine.

(25) The gripping unit 20 may be a V-band clamp (V coupling) shown in FIG. 2, for instance. FIG. 2 is a schematic diagram of the structure of a V-band clamp. The V band clamp fastens the turbine-housing side flange portion 6 (see FIG. 1) and the bearing-housing side flange portion (see FIG. 1) by connecting first end portions of a pair of clamp pieces 52, 54 formed into a semi-arc shape with a link 56 and tightly fastening the second end portions of the clamp pieces 52, 54 with a bolt 58, while the end portions of the clamp pieces 52, 54 are matched in position. That is, the V band clamp is configured to hold the turbine-housing side flange portion 6 and the bearing-housing side flange portion 18 together, as a result of applying a surface pressure toward the center axis O over the entire circumferential direction of the V band clamp (clamp pieces 52, 54) by tightly fastening the bolt 58 as disclosed above. Further, the bearing housing 16 and the compressor housing 12 are coupled by a bolt (not shown).

(26) FIG. 3A is an enlarged view of the turbine-housing side flange portion 6 and the bearing-housing side flange portion 18 before being gripped by the gripping unit 20 in the turbocharger 100 (100A) according to an embodiment. FIG. 3B is an enlarged view of the turbine-housing side flange portion 6 and the bearing-housing side flange portion 18 after being gripped by the gripping unit 20 in the turbocharger 100 (100A) according to an embodiment.

(27) Hereinafter, unless otherwise stated, the axial direction of the turbine rotor 2 is merely referred to as axial direction, the radial direction of the turbine rotor 2 is merely referred to as radial direction, and the circumferential direction of the turbine rotor 2 is merely referred to as circumferential direction.

(28) In an embodiment, as shown in FIG. 3A, a gap g is disposed between the turbine-housing side flange portion 6 and the bearing-housing side flange portion 18 when not being gripped by the gripping unit 20. Further, as shown in FIGS. 3A and 3B, the gripping unit 20 grips the turbine-housing side flange portion 6 and the bearing-housing side flange portion 18 so as to elastically deform the turbine-housing side flange portion 6 toward the bearing-housing side flange portion 18 in the axial direction and elastically deform the bearing-housing side flange portion 18 toward the turbine-housing side flange portion 6 in the axial direction.

(29) Accordingly, the gripping unit 20 generates an elastic force in a direction to separate the turbine-housing side flange portion 6 and the bearing-housing side flange portion 18 from each other, as a reaction force against the gripping force by the gripping unit 20, on each of the turbine housing 4 and the bearing housing 16. In other words, the gripping unit 20 generates an elastic force in a direction away from the bearing-housing side flange portion 18 in the axial direction as the reaction force on the turbine housing 4, and generates an elastic force in a direction away from the turbine-housing side flange portion 6 as the reaction force on the bearing-housing side flange portion 18.

(30) With the above configuration, even if the gripping unit thermally expands during transient operation of the engine, the turbine-housing side flange portion 6 and the bearing-housing side flange portion 18 follow the thermal expansion of the gripping unit 20 due to the elastic forces. Thus, it is possible to maintain a situation where the gripping unit 20 grips and holds the turbine-housing side flange portion 6 and the bearing-housing side flange portion 18, and suppress occurrence of loosening in coupling of the turbine housing 4 and the bearing housing 16.

(31) In an embodiment, as shown in FIGS. 3A and 3B, the gripping unit 20 may be configured to make the turbine-housing side flange portion 6 and the bearing-housing side flange portion 18 contact with each other at least when the turbocharger 100 (100A) is at full load, by elastically deforming the turbine-housing side flange portion 6 toward the bearing-housing side flange portion 18 in the axial direction, and elastically deforming the bearing-housing side flange portion 18 toward the turbine-housing side flange portion 6 in the axial direction.

(32) With the above configuration, when the turbocharger 100 (100A) is at full load, the contact part 22 between the turbine-housing side flange portion 6 and the bearing-housing side flange portion 18 serves as a heat transmission path from the turbine housing 4 to the bearing housing 16. Accordingly, by providing a heat transmission path from the turbine housing 4 to the bearing housing 16 on the radially outer side so as to be away from the bearing device 14, it is possible to improve the turbocharger performance.

(33) FIG. 4 is an enlarged cross-sectional view of a part of a turbocharger 100 (100B) according to an embodiment. FIG. 5 is an enlarged cross-sectional view of a part of a turbocharger 100 (100C) according to an embodiment. FIG. 6 is an enlarged cross-sectional view of a part of a turbocharger 100 (100D) according to an embodiment. FIG. 7 is an enlarged cross-sectional view of a part of a turbocharger 100 (100E) according to an embodiment. FIG. 8 is an enlarged cross-sectional view of a part of a turbocharger 100 (100F) according to an embodiment. FIG. 9 is an enlarged cross-sectional view of a part of a turbocharger 100 (100G) according to an embodiment. FIG. 10 is an enlarged cross-sectional view of a part of a turbocharger 100 (100H) according to an embodiment.

(34) In FIGS. 4 to 10, the dotted line represents a virtual center line of the plate thickness of the back plate 24 in the natural state of the back plate 24 (not elastically deformed).

(35) In some embodiments, as shown in FIGS. 4 to 10 for instance, at least a part of the back plate 24 is held between the turbine housing 4 and the bearing housing 16 in an elastically deformed state. The back plate 24 functions as a biasing member (plate spring member) that biases the turbine housing 4 and the bearing housing 16 so as to apply, to each the turbine housing 4 and the bearing housing 16, an elastic forces in a direction to separate the turbine-housing side flange portion 6 and the bearing-housing side flange portion 18 away from each other in the axial direction, while the gripping unit 20 grips and holds the turbine housing 4 and the bearing housing 16.

(36) With the above configuration, even if the gripping unit 20 thermally expands during transient operation of the engine, the turbine-housing side flange portion 6 and the bearing-housing side flange portion 18 follow the thermal expansion of the gripping unit 20 due to above the elastic force of the back plate 24. Thus, it is possible to maintain a situation where the gripping unit 20 grips and holds the turbine-housing side flange portion 6 and the bearing-housing side flange portion 18, and suppress occurrence of loosening in coupling of the turbine housing 4 and the bearing housing 16.

(37) In some embodiments, as shown in FIG. 4, the turbine housing 4 supports a radially outer portion 28 of the back plate 24 in the axial direction from the side of the turbine rotor 2 against the elastic force of the back plate 24. The bearing housing 16 supports a radially inner portion 30 of the back plate 24 in the axial direction from the side opposite to the turbine rotor 2 against the elastic force of the back plate 24. In the illustrative embodiment shown in FIG. 4, the back plate 24 has a cylindrical plate spring shape. In the depicted embodiment, the back plate 24 includes a protruding curved portion 32 curved so as to protrude toward the turbine rotor 2, in a cross section along the axial direction. The radially outer portion 28 of the back plate 24 extends linearly from the protruding curved portion 32 outward in the radial direction, and the radially inner portion 30 extends linearly from the protruding curved portion 32 inward in the radial direction. The turbine housing 4 includes an annular protruding portion 34 protruding inward in the radial direction. The annular protruding portion 34 supports the radially outer portion 28 of the back plate 24 against the elastic force.

(38) With the above configuration, the turbine housing 4 receives an elastic force toward the turbine rotor 2 in the axial direction from the radially outer portion 28 of the back plate 24 (elastic force in a direction to separate the turbine-housing side flange portion 6 from the bearing-housing side flange portion 18) while the turbine housing 4 and the bearing housing 16 are coupled by the gripping unit 20, and the bearing housing 16 receives an elastic force opposite to the turbine rotor 2 in the axial direction from the radially inner portion 30 of the back plate 24 (elastic force in a direction to separate the bearing-housing side flange portion 18 from the turbine-housing side flange portion 6). Thus, it is possible to suppress occurrence of loosening in the coupling of the turbine housing 4 and the bearing housing 16, by utilizing the elastic force of the entire back plate 24.

(39) In some embodiments, as shown in FIGS. 5 to 10, the turbine housing 4 supports the radially outer portion 28 of the back plate 24 in the axial direction from the side of the turbine rotor 2 against the elastic force, and the bearing housing 16 supports the radially outer portion 28 of the back plate 24 in the axial direction from the side opposite to the turbine rotor 2 against the elastic force. In the embodiment shown in FIGS. 5 to 8, the radially outer portion 28 of the back plate 24 has a cylindrical plate spring shape, and an inner peripheral edge 25 of the back plate 24 is a free end separated from the bearing housing 16.

(40) In the embodiment shown in FIGS. 5 to 10, the turbine housing 4 receives an elastic force toward the turbine rotor 2 in the axial direction from the radially outer portion 28 of the back plate 24 (elastic force in a direction to separate the turbine-housing side flange portion 6 from the bearing-housing side flange portion 18) while the turbine housing 4 and the bearing housing 16 are coupled by the gripping unit 20, and the bearing housing 16 receives an elastic force opposite to the turbine rotor 2 in the axial direction from the radially outer portion 28 of the back plate 24 (elastic force in a direction to separate the bearing-housing side flange portion 18 from the turbine-housing side flange portion 6). Thus, it is possible to enhance the design flexibility of the radially inner portion 30 of the back plate 24, while suppressing occurrence of loosening in coupling between the turbine housing 4 and the bearing housing 16 by utilizing an elastic force of the radially outer portion 28 of the back plate 24.

(41) In some embodiments, the cross-sectional shape along the axial direction at the radially outer portion 28 of the back plate 24 may have a V shape as shown in FIG. 5, a C shape as shown in FIG. 6, a rectangular U-shape as shown in FIG. 7, or an oblique line shape that intersects with the axial direction as shown in FIG. 8.

(42) With the above configuration, it is possible to utilize the elastic force of the back plate to suppress occurrence of loosening in the coupling between the turbine housing 4 and the bearing housing 16, while forming the radially outer portion 28 of the back plate 24 into a simple shape.

(43) In some embodiments, as shown in FIGS. 5 to 7, the opening portion 36 of the V shape (see FIG. 5), the opening portion 36 of the C shape (see FIG. 6), or the opening portion 36 of the rectangular U shape (see FIG. 7) is open toward the inner side with respect to the radial direction of the turbine rotor.

(44) With the above configuration, it is possible to utilize the elastic force of the back plate to suppress occurrence of loosening in the coupling between the turbine housing 4 and the bearing housing 16, while forming the back plate 24 into a simple shape.

(45) In some embodiments, as shown in FIG. 9, the radially outer portion 28 of the back plate 24 is elastically deformed in the axial direction toward the turbine rotor 2, and the turbine housing 4 supports the back plate 24 at a position closer to the radially inner side from a position where the radially outer portion 28 is supported by the bearing housing 16.

(46) In the illustrative embodiment shown in FIG. 9, the back plate 24 includes, in a cross section along the axial direction, a first linear portion 38 extending in the radial direction along a back surface 26 of the turbine rotor 2, a second linear portion 40 extending opposite to the turbine rotor 2 along the axial direction from the radially inner end of the first linear portion 38, and a third linear portion 42 extending opposite to the turbine rotor 2 along the axial direction from the radially outer end of the first linear portion 38. The radially outer portion 28 extends linearly outward in the radial direction from an end portion of the third linear portion 42 that is opposite to the turbine rotor 2. The second linear portion 40 may be in contact with the bearing housing 16 on the radially inner side as shown in the drawing, or may be separated from the bearing housing 16.

(47) Also with the above configuration, it is possible to utilize the elastic force of the back plate to suppress occurrence of loosening in the coupling between the turbine housing 4 and the bearing housing 16, while forming the back plate 24 into a simple shape.

(48) In some embodiments, as shown in FIG. 10 for instance, the radially outer portion 28 of the back plate 24 is elastically deformed in the axial direction opposite to the turbine rotor 2, and the turbine housing 4 supports the back plate 24 at a position closer to the radially outer side from a position where the radially outer portion 28 is supported by the bearing housing 16.

(49) Also in the embodiment shown in FIG. 10, the back plate 24 includes, in a cross section along the axial direction, a first linear portion 38 extending in the radial direction along the back surface 26 of the turbine rotor 2, a second linear portion 40 extending opposite to the turbine rotor 2 along the axial direction from the radially inner end of the first linear portion 38, and a third linear portion 42 extending opposite to the turbine rotor 2 along the axial direction from the radially outer end of the first linear portion 38. The radially outer portion 28 extends linearly outward in the radial direction from an end portion of the third linear portion 42 that is opposite to the turbine rotor 2. The second linear portion 40 may be in contact with the bearing housing 16 on the radially inner side as shown in the drawing, or may be separated from the bearing housing 16.

(50) Also with the above configuration, it is possible to utilize the elastic force of the back plate to suppress occurrence of loosening in the coupling between the turbine housing 4 and the bearing housing 16, while forming the back plate 24 into a simple shape.

(51) FIG. 11 is an enlarged cross-sectional view of a part of the turbocharger 100 (100B) shown in FIG. 4. FIG. 12 is an enlarged cross-sectional view of a part of the turbocharger 100 (100C) shown in FIG. 5. FIG. 13 is an enlarged cross-sectional view of a part of the turbocharger 100 (100H) shown in FIG. 10.

(52) In some embodiments, as shown in FIGS. 11 to 13 for instance, the back plate 24 is configured to satisfy an expression dfdi<01, where is a step in the axial direction between a back-plate side first supported portion 44 of the back plate 24 supported on the turbine housing 4, and a back-plate side second supported portion 46 of the back plate 24 supported on the bearing housing 16, 0 is the step in the natural state of the back plate 24, 1 is an initial step in the initial state after the back plate 24 is mounted, d is a distance in the axial direction between a turbine-housing side support portion 48 of the turbine housing 4 supporting the back-plate side first supported portion 44 and a bearing-housing side support portion 50 of the bearing housing 16 supporting the back-plate side second supported portion 46, di is the distance d in the initial state, and df is the distance d at the time when the turbocharger 100 is at full load. That is, the back plate 24 is configured such that the difference (dfdi) between the distance df and the distance di is smaller than the difference (02) between the step 0 and the step 1.

(53) Herein, the initial state refers to a state where the back plate 24 is disposed between the turbine housing 4 and the bearing housing 16, the turbine housing 4 and the bearing housing 16 are coupled by the gripping unit 20, and the turbocharger 100 is not yet started for the first time.

(54) With the above configuration, even if the distance between the turbine-housing side support portion 48 and the bearing-housing side support portion 50 is increased from the initial state corresponding to the above difference (dfdi) due to thermal expansion of the turbine housing 4 and the bearing housing 16 when the turbocharger 100 is at full load, the back-plate side first supported portion 44 follows the turbine-housing side support portion 48 and the back-plate side second supported portion 46 follows the bearing-housing side support portion 50, due to the elastic force of the back plate 24. Thus, it is possible to utilize the elastic force of the back plate to suppress occurrence of loosening in the coupling between the turbine housing 4 and the bearing housing 16, over the period from the standing time to the full-load time of the turbocharger 100.

(55) In some embodiments, as shown in FIGS. 4 to 10, while the turbine housing 4 and the bearing housing 16 are coupled by the gripping unit 20, the turbine-housing side flange portion 6 and the bearing-housing side flange portion 18 are in contact in the initial state after the back plate 24 is mounted.

(56) With the above configuration, in the initial state after the back plate 24 is mounted, the turbine-housing side flange portion 6 and the bearing-housing side flange portion 18 are in contact regardless of the dimension variation of the plate thickness or the like of the back plate, which facilitates management of the gripping force of the gripping unit 20 to grip the turbine-housing side flange portion 6 and the bearing-housing side flange portion 18 (if the gripping unit 20 is the above described V band clamp, management of the fastening force of the bolt 58). In other words, it is possible to stabilize the coupling state between the turbine housing 4 and the bearing housing 16.

(57) Embodiments of the present invention were described in detail above, but the present invention is not limited thereto, and various amendments and modifications may be implemented.

(58) For instance, the configuration of the gripping unit 20, the turbine-housing side flange portion 6, and the bearing-housing side flange portion 18 described with reference to FIGS. 3A and 3B can be also applied to the turbocharger 100 (100B to 100H) shown in FIGS. 4 to 10.

(59) Further, while the back plate 24 of the turbocharger 100 (100B, 100C, 100H) described above with reference to FIGS. 11 to 13 for instance is configured to satisfy dfdi<01, the back plate 24 of the above described turbocharger 100 (100D to 100G) may be also configured to satisfy dfdi<01.

DESCRIPTION OF REFERENCE NUMERALS

(60) 2 Turbine rotor 4 Turbine housing 6 Turbine-housing side flange portion 8 Shaft 10 Compressor impeller 12 Compressor housing 14 Bearing device 16 Bearing housing 18 Bearing-housing side flange portion 20 Gripping unit 22 Contact part 24 Back plate 25 Inner peripheral edge 26 Back surface 28 Radially outer portion 30 Radially inner portion 32 Protruding curved portion 34 Annular protruding portion 36 Opening portion 38 First linear portion 40 Second linear portion 42 Third linear portion 44 First supported portion 46 Second supported portion 48 Turbine-housing side support portion 50 Bearing-housing side support portion 52, 54 Clamp piece 56 Link 58 Bolt 100 Turbocharger O Center axis d, df Distance g Gap