JP5082991B2 - Turbocharger - Google Patents

Description

  The present invention relates to a supercharger.

  With the exhaust gas and environmental issues of automobiles being highlighted worldwide, the use of turbochargers is essential to comply with emissions regulations, reduce fuel consumption, and improve performance, including the passenger car class small diesel engine market. Accordingly, variable capacity turbochargers that can improve performance in a wide range from a low speed to a high speed range are attracting attention.

A conventional variable capacity supercharger 100 will be described with reference to FIG.
The variable displacement supercharger 100 includes a nozzle vane (nozzle blade) 129 that changes in a gas flow path 125 formed between the turbine impeller 115 and the turbine housing 121, and a part of the gas flow path 125 of the turbine housing 121. A variable capacity device 127 having a nozzle support ring (mounting portion) 133 that is provided along the inner wall surface 121a of the projecting portion 121A of the turbine housing 121 and that rotatably supports the nozzle vane 129 on the surface 133a. ing.

The nozzle support ring 133 is connected to the other end 139 </ b> B side of the support member 139 and supported by the housing 103 via the support member 139.
As shown in FIG. 12, the support member 139 is formed of a thin plate-like material in an annular shape, and has one end 139 </ b> A side serving as an outer peripheral end and the other end 139 </ b> B serving as an inner peripheral end. The 139A side is sandwiched and fixed between the bearing housing 117 and the turbine housing 121 so as to be orthogonal to the rotation center axis CL1.

  The exhaust gas emitted from the engine of the automobile through the scroll passage 123 and the gas passage 125 in the variable capacity supercharger 100 is supplied to the turbine impeller 115, and the turbine impeller 115 rotates, so that the rotary shaft member 9 is rotated. The compressor impeller 13 is rotated via the compressor to compress the air.

The gas after rotationally driving the turbine impeller 115 is discharged from a gas outlet (not shown) formed at the center of the turbine housing 121 (the center located on the opposite side of the bearing housing 117). (For example, refer to Patent Document 1).
JP 2006-125588 A

  However, in the conventional variable displacement supercharger 100, the deformation and movement of the housing 103 in the radial direction and the axial direction are restricted on the one end 139A side of the support member 139. Therefore, when the nozzle support ring 133 is thermally expanded, the support member 139 is displaced with respect to the bearing housing 117 and the turbine housing 121 around the one end 139A, and the nozzle vane 129 does not rotate or is difficult to rotate. There is a problem that the nozzle support ring 133 may come into contact with the nozzle vane 129 or may be twisted.

  In addition, with the displacement of the support member 139, the gap S1 increases and the working gas leaks outside through the gap S1, and there is a problem that a predetermined flow rate cannot be supplied to the turbine impeller 115.

  The present invention has been made in view of the above circumstances, and can suppress the leakage of the working gas flowing through the inside to the outside, and can stably operate the variable capacity device and maintain a stable output. The purpose is to provide a supercharger capable of

The turbocharger according to the present invention employs the following means in order to solve the above problems.
The present invention is provided along a nozzle blade that is variable in a gas flow path formed between a turbine impeller and a turbine housing, and an inner wall surface of the turbine housing that forms a part of the gas flow path. A turbocharger comprising a variable capacity device having a mounting portion for rotatably supporting the nozzle blade on a surface, the turbocharger having one end side and the other end side, between the bearing housing and the turbine housing The turbine housing, comprising: a support portion that is disposed on the one end side and supports the attachment portion on the other end side; and a biasing portion that presses the one end side of the support portion against the bearing housing or the turbine housing. And the attachment portion are slidably in contact with each other in the direction of expanding the gas flow path.

In the present invention, since one end side of the support portion is pressed via the biasing portion with respect to the bearing housing and the turbine housing, the biasing portion is elastically deformed, so that one end side of the support portion is Relative movement with respect to the turbine housing is possible. Therefore, even if the support member is thermally expanded and deformed with respect to the bearing housing and the turbine housing, it can be suitably absorbed by the balance with the urging force of the urging portion.
At this time, since the turbine housing and the mounting portion are slidably in contact with each other in the direction of expanding the gas flow path, the turbine housing and the mounting portion can be deformed or displaced relative to the turbine housing. It is possible to suppress the attachment portion from being separated from the housing and to secure a sufficient gas flow path.

  In the turbocharger according to the present invention, a first facing surface that faces the mounting portion adjacent to the inner wall surface is provided in the turbine housing, and the first facing surface that faces the turbine housing is adjacent to the surface. Two opposing surfaces are provided in the mounting portion, and a first tangential plane in contact with the first opposing surface and a second tangential plane in contact with the second opposing surface are upstream of the gas flow path with respect to the inner wall surface. It intersects in the direction which becomes an acute angle.

  In the present invention, when the turbine housing and the mounting portion are thermally expanded and deformed with each other, the gas flow path is relatively moved without causing the mounting portion to protrude relatively into the gas flow path from the inner wall surface of the turbine housing. The mounting portion can be moved in the direction of spreading. Therefore, the flow of the working gas in the gas flow path can be maintained in a smooth state.

  The supercharger according to the present invention is characterized in that the first facing surface and the second facing surface are in line contact.

  According to the present invention, when the turbine housing and the mounting portion are thermally expanded, the sliding resistance between the first facing surface and the second facing surface can be more suitably suppressed.

  The supercharger according to the present invention is characterized in that the urging portion is an elastic body.

  According to the present invention, the movement or deformation of the support portion can be suitably absorbed by the elastic deformation of the urging portion.

  ADVANTAGE OF THE INVENTION According to this invention, while being able to suppress the leakage to the exterior of the working gas which distribute | circulates an inside, a variable capacity apparatus can be operated stably and the stable output can be maintained.

Hereinafter, an embodiment of a supercharger according to the present invention will be described with reference to FIGS. 1 to 6.
The variable capacity supercharger 1 includes a housing 3, a centrifugal compressor 5 is provided on one end side of the housing 3, and a centrifugal turbine 7 is provided on the other end side.

  A rotating shaft member 9 is provided between the turbine 7 and the compressor 5 via a fluid bearing 11 so as to be rotatable with respect to the housing 3. A compressor impeller 13 constituting the compressor 5 is integrally fixed to one end of the rotating shaft member 9, and a turbine impeller 15 constituting the turbine 7 is fixed to the other end of the rotating shaft member 9. Are integrally fixed.

  The housing 3 includes a bearing housing 17 that supports the rotating shaft member 9, a compressor housing 19 that surrounds the compressor impeller 13 and is provided integrally with the bearing housing 17 on the compressor impeller 13 side, and a turbine impeller that surrounds the turbine impeller 15. And a turbine housing 21 provided integrally with the bearing housing 17 on the 15 side.

  The turbine housing 21 is provided with a scroll passage 23 provided with a gas inlet (not shown) at one end. An annular gas passage is provided between the turbine housing 21 and the turbine impeller 15 at the inner periphery of the scroll passage 23. 125 is formed. The turbine housing 21 is provided with a protruding portion 21A that protrudes along the inner wall surface 21a of the turbine housing 21 that forms the gas flow path 25.

A multi-vane nozzle type variable capacity device 27 is provided on the annular gas flow path 25 on the tip side (the side opposite to the compressor 5) of the turbine impeller 15.
As shown in FIG. 2 (II-II sectional view of FIG. 1), the multi-vane nozzle type variable capacity device 27 is constituted by a plurality of nozzle vanes 29 arranged on the circumference of the annular gas flow path 25. And the annular nozzle support ring 33 that rotatably supports each nozzle vane 29 with a central axis parallel to the rotation center axis CL1 of the rotation shaft member 9 as a rotation center.

  The nozzle vane 29 is also rotatably supported by an annular shroud 35 provided between the turbine impeller 15 and the turbine housing 21 at a predetermined interval from the nozzle support ring 33. The gas flow path 125 is formed between the nozzle support ring 33 and the shroud 35.

The nozzle vane 29 is rotated, for example, between a posture shown by a solid line and a posture shown by a broken line in FIG. 2 via a vane nozzle drive mechanism 37 configured by a slide joint method or the like.
In addition, when each nozzle vane 29 exists in the attitude | position shown as a continuous line in FIG. 2, the width W1 of the gas flow path in the vane nozzle 31 is the narrowest, and when each nozzle vane 29 exists in the attitude | position shown as a broken line in FIG. The width W3 of the gas flow path in FIG. That is, by rotating each nozzle vane 29 in the same direction, the size of the flow path of the vane nozzle 31 is changed, and the flow rate of the gas supplied to the turbine 107 (turbine impeller 15) is changed.

The nozzle support ring 33 is formed in a ring shape with a predetermined sheet thickness, and the surface 33a forms a gas flow path 125 together with the inner wall surface 21a of the protruding portion 21A. The nozzle support ring 33 has an outer diameter slightly larger than the inner diameter of the scroll passage 23 and an inner diameter slightly larger than the outer diameter of the turbine impeller 15.
Furthermore, the nozzle support ring 33 is installed in the vicinity of the turbine impeller 15 on the back side (compressor 5 side) of the turbine impeller 15 so that the center axis coincides with the rotation center axis CL1 of the rotary shaft member 9.

  As shown in FIGS. 1 to 3, the variable displacement supercharger 1 includes a nozzle vane (nozzle blade) 29 that is variable in a gas flow path 25 formed between the turbine impeller 15 and the turbine housing 21, and a turbine. A nozzle support ring (mounting portion) 33 provided along the inner wall surface 21a of the protruding portion 21A of the turbine housing 21 that forms a part of the gas flow path 25 of the housing 21 and rotatably supporting the nozzle vane 29 on the surface 33a. And a variable capacitance device 27 having

  The nozzle support ring 33 is positioned with respect to the turbine housing 21 such that the inner wall surface 21a of the protruding portion 21A of the turbine housing 21 and the surface 33a of the nozzle support ring 33 are substantially on the same plane. The surface 33 a of the nozzle support ring 33 also forms part of the gas flow path 25.

  A first facing surface 21 b is provided on the turbine housing 21 adjacent to the inner wall surface 21 a of the projecting portion 21 </ b> A of the turbine housing 21, and a second facing surface 33 b is adjacent to the surface 33 a of the nozzle support ring 33. It is provided on the outer peripheral end face.

The first opposed surface 21b and the second opposed surface 33b are configured such that the first tangential plane P1 in contact with the first opposed surface 21b and the second tangential plane P2 in contact with the second opposed surface 33b are gas flow paths 25 with respect to the inner wall surface 21a. Is formed so as to intersect at an acute angle on the upstream side.
That is, when the angle at which the first tangent plane P1 and the second tangent plane P2 intersect with the inner wall surface 21a is θ1, the first facing surface 21b and the second facing surface are crossed at 0 <θ1 <90 degrees. 33b is in surface contact so as to be slidable in the direction of expanding the gas flow path 25.
For example, as shown in FIG. 4, this inclination may be 90 degrees or less even if θ2> θ1.

One end 39A side of the support member (support portion) 39 is disposed between the bearing housing 17 and the turbine housing 21 so as to be orthogonal to the rotation center axis CL1. The bearing housing 17 and the turbine housing 21 are fixed in contact with each other in the direction of the rotation center axis CL1 in the vicinity of the one end 39A (see FIGS. 3 and 11).
The one end 39A is not coupled (fixed) to the turbine housing 21 or the bearing housing 17 and moves in the axial direction or the radial direction (against the elastic force or frictional force of the wave washer 41 described later). It is provided as possible. In the illustrated example, one end 39 </ b> A is in contact with the inner surface of the turbine housing 21.
The one end 39A may not be brought into contact with the turbine housing 21 in the radial direction. That is, as shown in FIG. 3, a gap may be formed between the one end 39 </ b> A and the inner surface of the turbine housing 21. In this way, when the nozzle support ring 33 and the support member 39 are thermally expanded in the radial direction as will be described later, the one end 39A is likely to move (expand) in the radial direction. Thereby, deformation (inclination and twisting) of the nozzle support ring 33 and the support member 39 can be prevented.

Between the bearing housing 17 and the turbine housing 21, a wave washer (biasing part) 41 that presses the one end 39 A of the support member 39 against the bearing housing 17 or the turbine housing 21 is arranged together with the one end 39 A of the support member 39. Has been. In the illustrated example, the wave washer 41 is provided between the one end 39 </ b> A and the bearing housing 17. Further, it is not coupled (fixed) to the bearing housing 17 and is held by being sandwiched between the one end 39 </ b> A and the bearing housing 17.
The wave washer 41 is made of metal or the like with heat resistance, and is formed such that wave-shaped irregularities are repeated in the circumferential direction on a flat washer-like member as shown in FIG. The unevenness is formed to be uneven with respect to the direction in which the wave washer 41 is sandwiched.
The width of the wave washer 41 and the number and size of the irregularities can be changed as appropriate. For example, the wave washer 41 may have a width of about 2 mm and the number of irregularities of about two. Further, the one end 39A and the wave washer 41 may be slidable in the radial direction without being coupled (fixed). In this way, when the nozzle support ring 33 and the support member 39 are thermally expanded in the radial direction as will be described later, the one end 39A is likely to move (expand) in the radial direction. Therefore, deformation (tilt and twist) of the nozzle support ring 33 and the support member 39 can be effectively suppressed.

Next, the operation of the variable capacity supercharger 1 according to this embodiment will be described.
During operation of the variable displacement supercharger 1, exhaust gas from the engine is supplied to the turbine impeller 15 through the scroll passage 23 and the gas passage 25, and the turbine impeller 15 is rotating.
At this time, the turbine housing 21 and the nozzle support ring 33 are also heated and thermally expanded.

  Here, the first opposed surface 21b and the second opposed surface 33b are in surface contact with the gas flow path 25 in a state where both are inclined at an angle θ. Therefore, the nozzle support ring 33 tends to be deformed and moved relative to the turbine housing 21 in the direction of widening the channel width of the gas channel 25 as shown in FIG.

  As the nozzle support ring 33 is deformed and moved in the radial direction and the axial direction, the support member 39 is pressed and the load is concentrated on the one end 39A. At this time, since one end 39A of the support member 39 is pressed by the wave washer 41, the load is relieved by the elastic deformation of the wave washer 41, and the deformation of the support member 39 is restricted.

  Thus, the contact state between the projecting portion 21A and the nozzle support ring 33 is maintained without excessive contact or separation between the first facing surface 21b and the second facing surface 33b, and the gas flow path 25 and the outside are blocked. State is maintained.

  According to the variable capacity supercharger 1, the one end 39 </ b> A side of the support member 39 is pressed against the bearing housing 17 and the turbine housing 21 via the wave washer 41. On the other hand, the one end 39A side of the support member 39 can be relatively moved. Therefore, even if the support member 39 is thermally expanded and deformed with respect to the bearing housing 17 and the turbine housing 21, it can be suitably absorbed by the balance with the urging force of the wave washer 41.

  At this time, since the turbine housing 21 and the nozzle support ring 33 are slidably in contact with each other, even if the nozzle support ring 33 is relatively deformed or displaced with respect to the turbine housing 21, It is possible to prevent the nozzle support ring 33 from separating and to secure a sufficient gas flow path 25. Therefore, leakage of the working gas flowing through the inside can be suppressed and the variable capacity device 27 can be stably operated, and a stable output can be maintained.

  In particular, the first tangent plane P1 of the first facing surface 21b and the second tangent plane P2 of the second facing surface 33b intersect the inner wall surface 21a upstream of the gas flow path at θ1. For this reason, when the turbine housing 21 and the nozzle support ring 33 are thermally expanded and deformed, the nozzle support ring 33 is restricted from projecting into the gas flow path 25 relative to the inner wall surface 21a of the turbine housing 21. Thus, the gas flow path 25 can be moved in a relatively widening direction. Therefore, the flow of the working gas in the gas flow path 25 can be maintained in a smooth state.

  The technical scope of the present invention is not limited to the above embodiment, and various modifications can be made without departing from the spirit of the present invention.

For example, as shown in FIG. 7, the first opposing surface 51b of the protruding portion 51A and the second opposing surface 53b of the nozzle support ring 53 are formed as curved surfaces that are convex toward each other, or as shown in FIG. In addition, only the first facing surface 55b of the protruding portion 55A may be formed in a curved surface that is convex on the side facing the second facing surface 33b.
Further, only the second facing surface may be formed as a curved surface convex toward the first facing surface. In this case, the first facing surface and the second facing can be brought into line contact, and the contact state between the two can be suitably maintained while changing the line contact position.
Therefore, sliding resistance can be further reduced while maintaining sealing performance.

  Further, as shown in FIGS. 9 and 10, even if the projecting portion 59A and the nozzle support ring 61 are formed in a gear shape and the first opposed surface 59b and the second opposed surface 61b are opposed to each other, the concave and convex portions are fitted. Good.

Further, the support member 39 and the wave washer 41 as the urging portion are separate members. However, the present invention is not limited to this, and as shown in FIG. 11, one end 63A of the support member 63 is orthogonal to the rotation center axis CL1. It is good also as arrange | positioning between the turbine housing 21 and the bearing housing 17 in the state bent by angle (theta) 3 used as an acute angle with respect to the direction L2 to perform.
In this case, a deformation margin S of the one end 63A of the support member 63 is formed between the one end 63A of the support member 63 and the turbine housing 21 and the bearing housing 17. Therefore, during thermal expansion, the one end 63A of the support member 63 can be elastically deformed between the deformation margins S to absorb the thermal expansion.

  In addition, the urging part is not limited to the wave washer, and can be applied as long as it can be urged (such as an elastic body), but the wave washer has excellent heat resistance, ease of manufacture, It can be used suitably.

It is a schematic structure figure showing a variable capacity type supercharger concerning one embodiment of the present invention. It is a figure (II-II section of Drawing 1) showing a variable capacity device. It is a figure (III expansion of FIG. 1) which shows the connection part vicinity of a turbine housing and a variable capacity apparatus. It is a figure which shows the other example of the connection part of a turbine housing and a variable capacity apparatus. It is a perspective view of a wave washer. It is explanatory drawing which shows the state which the thermal displacement of the variable capacity | capacitance supercharger which concerns on one Embodiment of this invention. It is a figure which shows the other example of the connection part of a turbine housing and a variable capacity apparatus. It is a figure which shows the other example of the connection part of a turbine housing and a variable capacity apparatus. It is a figure which shows the other example of the connection part of a turbine housing and a variable capacity apparatus. It is a figure (IV arrow view of FIG. 9) which shows the other example of the connection part of a turbine housing and a variable capacity apparatus. It is a figure which shows the other example of a support part. It is a figure which shows the principal part of the conventional variable capacity | capacitance supercharger.

Explanation of symbols

  DESCRIPTION OF SYMBOLS 1 ... Variable capacity type | mold supercharger (supercharger), 15 ... Turbine impeller, 17 ... Bearing housing, 21 ... Turbine housing, 21A, 51A, 53A, 55A, 59A ... Projection part, 21a ... Inner wall surface, 21b, 51b , 55b, 59b ... first facing surface, 25 ... gas flow path, 27 ... variable capacity device, 29 ... nozzle vane (nozzle blade), 33, 53, 61 ... nozzle support ring (mounting part), 33a ... surface, 33b, 53b, 61b ... second opposing surface, 39, 63 ... support member, 39A ... one end, 39B ... other end, 41 ... wave washer (biasing part), P1 ... first tangential plane, P2 ... second tangential plane

Claims (2)

A nozzle blade that is variable in a gas flow path formed between the turbine impeller and the turbine housing, and an inner wall surface of the turbine housing that forms a part of the gas flow path, and the nozzle on the surface A turbocharger comprising a variable capacity device having a mounting portion for rotatably supporting a wing,
A support portion having one end side and the other end side, the one end side being disposed between a bearing housing and the turbine housing, and supporting the attachment portion on the other end side;
An urging portion that presses the one end side of the support portion against the bearing housing or the turbine housing;
With
A first facing surface that is adjacent to the inner wall surface and faces the mounting portion is provided in the turbine housing,
A second facing surface facing the turbine housing adjacent to the surface is provided on the mounting portion;
A first tangential plane in contact with the first opposed surface and a second tangential plane in contact with the second opposed surface intersect with each other in a direction that forms an acute angle upstream of the gas flow path with respect to the inner wall surface;
The supercharger, wherein the first facing surface and the second facing surface are in line contact . The supercharger according to claim 1, wherein the urging portion is an elastic body .

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