WO2011152454A1

WO2011152454A1 - Stator vane-type turbocharger

Info

Publication number: WO2011152454A1
Application number: PCT/JP2011/062598
Authority: WO
Inventors: 石井　幹人
Original assignee: 株式会社Ihi
Priority date: 2010-06-01
Filing date: 2011-06-01
Publication date: 2011-12-08
Also published as: JPWO2011152454A1

Abstract

Provided is a stator vane-type turbocharger wherein a stator vane (15) is provided in a passage (9) between a bearing housing (1) as a first member and a turbine housing (4) as a second member. The stator vane is comprised of a movable member (11) which can move forward or backward against the front surface of a first member or a second member, opposite to the movable member, and a vane body (15) secured to the front surface of the movable member, or secured to the front surface of the first member or the second member, opposite to the movable member. Furthermore, a pushing means (16) provided on the back surface of the movable member pushes the movable member so that the tip of the vane body is pressure-bonded to the front surface of the first member or the second member, opposite to the movable member, or the front surface of the movable member, by. Thus, the side clearance of the stator vane in the stator vane-type turbocharger can be removed.

Description

Fixed-wing turbocharger

The present invention relates to a fixed-wing turbocharger in which the rectification effect by a fixed blade is enhanced with a simple configuration.
This application claims priority based on Japanese Patent Application No. 2010-126009 filed in Japan on June 1, 2010, the contents of which are incorporated herein by reference.

2. Description of the Related Art Conventionally, internal combustion engines for automobiles or the like are known that have a turbocharger to improve output. A turbocharger includes a turbine scroll into which exhaust gas from an internal combustion engine is fed, a turbine impeller that rotates when exhaust (fluid) in the turbine scroll is supplied through a passage, and a compressor that rotates integrally with the turbine impeller. An impeller and a compressor scroll as a diffuser to which air (fluid) from the compressor impeller is supplied through a passage, and forcibly supply pressurized air from the compressor scroll to the combustion chamber of the internal combustion engine .

The turbocharger may be provided with a blade body for rectifying the flow of fluid in one or both of the passage through which the exhaust on the turbine side flows and the passage through which the air on the compressor side flows.

The blade body provided in the turbine side passage will be described below. The turbine scroll formed in the turbine housing increases the flow velocity and feeds the exhaust gas sent to the turbine impeller uniformly from the periphery of the turbine impeller by the blades to improve the efficiency of the turbine. The blade body includes a fixed blade that fixes the blade body to one of the facing surfaces of the turbine housing and the bearing housing, and a shaft provided in each blade body between the facing surfaces of the turbine housing and the bearing housing. There are known variable wing bodies that are arranged so that the angles of the wing bodies can be changed simultaneously by rotating them simultaneously by a link mechanism or the like.

Here, since the fixed blade has a fixed exhaust inflow angle, the flow velocity of the exhaust gas cannot be changed according to the rotational speed of the internal combustion engine. The flow rate of the exhaust can be changed by changing the inflow angle. On the other hand, the fixed wing has a relatively simple configuration, whereas the variable wing body is movable, so that the configuration is complicated.

Furthermore, as described above, there is a problem that a gap called a blade side clearance is generated in the blade body provided between the opposed surfaces of the turbine housing and the bearing housing. That is, even if the clearance between the turbine housing or the bearing housing facing the blade body is designed with zero clearance, the turbine housing and the bearing housing having a complicated shape may be thermally deformed unevenly during operation, and the blade body and the blade Since the deformation due to the difference in thermal expansion due to the difference in material from the housing to which the body is fixed occurs, the actual clearance cannot be zero. Here, in order to make the variable wing body movable, it is necessary to provide a constant side clearance on both sides of the wing body, and in the fixed wing, a side clearance is generated only on one side of the wing body.

Also, in the blade body provided in the above-described compressor-side passage, the temperature is lower than that of the turbine, but side clearance similarly occurs.

As prior art document information of this type of turbocharger related to the present invention, for example, there is an example provided with both a fixed wing and a variable wing (see Patent Document 1). Further, in the variable wing body in which the wing body is rotatably held between the rear exhaust introduction wall and the front exhaust introduction wall, the rear exhaust is introduced between the shaft of each wing body and the bearing housing. There is an example in which a pressing means for pressing the wall side to displace the wing body to the rear exhaust introduction wall side is provided to reduce the side clearance between the rear exhaust introduction wall side and the wing body (see Patent Document 2). .

JP 2007-192124 A JP 2009-144546 A

However, in the turbocharger as described above, even if the axial height dimension of the blade body is manufactured with high accuracy so that the side clearance of the blade body provided in the turbine-side passage becomes zero clearance, The side clearance cannot be set to zero clearance at the assembly stage. Therefore, the exhaust from the turbine scroll leaks through the side clearance of the blade provided in the passage on the turbine side. This leaking exhaust gas not only contributes to the action of increasing the exhaust gas flow rate by the blades, but also disturbs the exhaust gas led to the turbine impeller, thereby greatly reducing the turbine efficiency. Therefore, if the side clearance of the blade body provided in the passage on the turbine side can be set to zero clearance, the turbine efficiency can be greatly increased, which is very effective.

Also, even in the blade body provided in the above-mentioned compressor side passage, even if the blade body is manufactured with high dimensional accuracy so as to achieve zero clearance, it cannot be made zero clearance at the stage of assembly. Therefore, air from the compressor impeller leaks through the side clearance. This leaking air not only contributes to the pressure boosting effect by the diffuser, but also causes turbulence in the air guided to the compressor scroll, thereby reducing the diffuser function. Therefore, if the side clearance of the blade body provided in the compressor-side passage can be set to zero clearance, the diffuser function can be enhanced, which is very effective.

The present invention has been made in view of such circumstances, and an object of the present invention is to provide a fixed wing turbocharger in which the rectification effect by the fixed wing is enhanced by a simple configuration.

In the present invention, a passage between the bearing housing and the turbine housing and a passage between the bearing housing and the compressor are formed by the first member and the second member facing each other, and at least one of the passages includes a fixed blade. Related to fixed-wing turbochargers.
In this fixed wing type turbocharger, the fixed wing is disposed between the front surfaces of the first member or the second member facing each other so as to be movable in the front-rear direction, and the wing body fixed to the front surface of the movable member. And a pressing means that presses the movable member so as to press the tip of the wing body against the front surface of the first member or the second member facing the movable member. It has.
Alternatively, in this fixed wing type turbocharger, the fixed wing is disposed so as to be movable in the front-rear direction between the front surfaces of the first member or the second member facing each other, and the first member or the second member. A wing body fixed to the front surface of the movable member, and pressing the movable member against the front surface of the movable member so as to press the tip of the wing body against the front surface of the movable member. Means.

In the above fixed wing type turbocharger, it is preferable that the pressing means is a disc spring that seals leakage of fluid to the back side of the movable member.

In the fixed wing turbocharger, it is preferable that the movable member is a heat shield plate provided on the front surface of the bearing housing so as to face the turbine housing.

According to the fixed-wing turbocharger of the present invention, the movable member provided to be movable in the front-rear direction with respect to the front surface of the first member or the second member forming the passage, and the blade fixed to the front surface of the movable member A fixed wing is constituted by a body, or a wing body fixed to the front surface of the first member or the second member facing the movable member. Then, the pressing means provided on the back surface of the movable member is movable so that the tip of the wing body is pressed against the front surface of the first member or the second member facing the movable member or the front surface of the movable member. Press the member. As a result, the side clearance of the fixed wing can be set to zero clearance. Therefore, one or both of the improvement of the turbine efficiency and the improvement of the diffuser function by the fixed wing can be achieved and the turbocharging efficiency of the turbocharger can be increased.

Also, even if the nozzle side clearance changes due to thermal deformation of the housing or thermal expansion difference between the housing and the stationary blade during hot operation due to turbocharger operation, zero clearance is achieved by the movement of the stationary blade following in the longitudinal direction. Has the effect of always holding. Therefore, in the past, the dimensional accuracy of the height of the fixed wing was increased in order to ensure the zero clearance, but in the present invention, the zero clearance was easily achieved without paying attention to the dimensional accuracy of the height of the fixed wing. Can be achieved.

If the pressing means is formed of a disc spring, it is possible to prevent the problem of exhaust leakage to the back side of the movable member at the same time.

Since the movable member also serves as a heat shield, heat transfer from the movable member to the bearing housing can be suppressed.

It is a cutaway side view showing an example of the fixed wing type turbocharger of the present invention provided with fixed wings in the passage on the turbine side. It is a front view which shows an example of the disk spring which is a press means. It is an AA direction arrow line view of FIG. 2A. It is sectional drawing which shows an example of the disk spring which is a press means, and its installation condition. FIG. 4 is a cut side view showing another example of the fixed wing turbocharger shown in FIG. 1. It is detailed sectional drawing of the wave washer and seal ring with which FIG. 3A is equipped. It is a cutaway side view showing an example of the fixed wing type turbocharger of the present invention provided with fixed wings in the passage on the compressor side. It is a cutting side view showing an example of the fixed wing type turbocharger of the present invention.

Hereinafter, embodiments of the present invention will be described with reference to the drawings.

FIG. 1 is a cut-away side view showing an example of a fixed-wing turbocharger according to the present invention provided with fixed blades in a passage on the turbine side. This figure includes a fixed vane 15 on the bearing housing 1 (first member) side in a passage 9 formed between the opposed front surfaces of the bearing housing 1 (first member) and the turbine housing 4 (second member). Shows the case.

1, a turbine impeller 3 is fixed to one end of a rotating shaft 2 that is rotatably supported by a bearing housing 1. Further, the front surface of the bearing housing 1 facing the turbine housing 4 (the left side surface in FIG. 1; hereinafter, sometimes referred to as “opposite front surface”) is opposed to the bearing housing 1 of the turbine housing 4. A positioning step 4a provided on the front surface (the right side surface in FIG. 1; hereinafter may be abbreviated as “opposing front surface”) is aligned with a positioning pin 5 provided on the opposing front surface of the bearing housing 1 in the circumferential direction (rotation direction). The bearing housing 1 and the turbine housing 4 are assembled together by tightening the fastening ring 6 provided on the outer periphery with the fastening bolt 7.

A turbine scroll 8 is formed in the turbine housing 4, and exhaust (fluid) from the turbine scroll 8 is circumferentially outwardly passed to the turbine impeller 3 via a passage 9 between the bearing housing 1 and the opposed front surface of the turbine housing 4. Derived from. A compressor impeller 25 shown in FIG. 4 is provided at the other end of the rotary shaft 2, and a compressor housing 26 forming a compressor scroll 27 is provided on the outer periphery of the compressor impeller 25. The bearing housing 1 and the compressor housing 26 is integrally assembled by forming a passage 28 between the opposed front surfaces.

An annular fitting groove 10 is formed on the front face of the bearing housing 1 (first member), and the fitting groove 10 has an annular protrusion 12 protruding from the rear surface of the outer periphery of the ring-shaped movable member 11. Thus, the movable member 11 can be moved in the front-rear direction. Furthermore, the movement of the movable member 11 in the circumferential direction is restricted by matching the concave portion 13 formed in the annular protrusion 12 with the positioning pin 5.

The base end of the wing body 14 is fixed to the front surface of the movable member 11, and the tip end of the wing body 14 is opposed to the opposite front surface of the turbine housing 4. The movable member 11 and the wing body 14 constitute a fixed wing 15.

Between the back surface of the movable member 11 (the right side surface in FIG. 1) and the opposed front surface of the bearing housing 1, the movable member 11 is attached so that the tip of the blade 14 of the movable member 11 is crimped to the opposed front surface of the turbine housing 4. A pressing means 16 for pressing forward (leftward in the figure) is provided. The pressing means 16 presses the movable member 11 and presses the tip of the blade body 14 against the opposed front surface of the turbine housing 4, so that the side clearance between the blade body 14 and the opposed front surface of the turbine housing 4 is made substantially zero. Can do.

As the pressing means 16, FIGS. 1, 2 </ b> A, and 2 </ b> B show a case where a conical disc spring 17 with a head cut off is provided. The disc spring 17 may have a ring shape as shown in FIG. 2A, or a part of the ring may be cut off as indicated by a virtual line. By using such a disc spring 17, one end of the disc spring 17 abuts on the back surface of the movable member 11 along the circumferential direction, and the other end of the disc spring 17 extends along the circumferential direction of the bearing housing 1. Abuts against the front face. As a result, the gap between the movable member 11 and the bearing housing 1 is sealed with a disc spring 17 to prevent the problem that the exhaust (fluid) from the turbine scroll 8 leaks to the bearing housing 1 side through the back surface of the movable member 11. be able to.

More specifically, in the example of FIG. 1, the outer peripheral end of one end of the disc spring 17 abuts the back surface of the movable member 11 along the circumferential direction, and the inner peripheral side of the other end of the disc spring 17. Is in contact with the opposed front surface of the bearing housing 1 along its circumferential direction.
In this case, for example, as shown in FIG. 2C, the bearing housing 1 among the one end of the disc spring 17, the portion (a peripheral end) 17 a that contacts the back surface of the movable member 11, and the other end of the disc spring 17. It is desirable that the portions (inner peripheral end portions) 17b that are in contact with the opposite front surface are chamfered and have an arc-shaped cross section. By chamfering these

portions

17a and 17b, when the

portions

17a and 17b are brought into contact with the opposed front surfaces of the movable member 11 and the bearing housing 1 as shown in FIG. The contact area between the bearing housing 1 and the bearing housing 1 increases. As a result, the disc spring 17, the movable member 11, and the bearing housing 1 can be reliably brought into line contact along the circumferential direction, and the sealing performance of the disc spring 17 is improved.

As the pressing means, in addition to the disc spring 17, a wave washer, a coil spring, or the like can be used. When a wave washer, a coil spring, or the like is used, a sealing material such as an O-ring or a C-ring is provided to prevent exhaust from leaking to the bearing housing 1 through the back surface of the movable member 11.

Further, when a member having elasticity in the front-rear direction, such as a disc spring 17, is used as the pressing means 16, the force by which the pressing means 16 presses the movable member 11 can be arbitrarily set by adjusting the elasticity. it can. Further, since the pressing means 16 is not affected by the flow rate of the exhaust gas sent from the turbine scroll to the turbine impeller, the pressing means 16 presses the movable member 11 with a constant force regardless of the flow rate of the exhaust gas from the turbine scroll. can do.

Furthermore, since a space 18 for arranging the pressing means 16 is formed on the back surface of the movable member 11, the movable member 11 can also serve as a heat shield.

Next, the operation of the above embodiment will be described.
In the fixed wing turbocharger of FIG. 1, the annular protrusion 12 of the movable member 11 in a state in which the disc spring 17 is disposed on the back surface of the movable member 11 is fitted into the fitting groove 10 provided on the front surface of the bearing housing 1. Further, at this time, the movable member 11 is arranged so that the concave portion 13 formed in the annular protuberance 12 matches the positioning pin 5 and positioning in the circumferential direction (rotation direction) is performed. Further, after the turbine housing 4 is arranged and positioned in the circumferential direction so that the positioning step portion 4 a on the front surface of the turbine housing 4 matches the positioning pin 5, the fastening ring 6 provided on the outer periphery is connected with the fastening bolt 7. By tightening, the bearing housing 1 and the turbine housing 4 are assembled together.

By this assembly, the disc spring 17 disposed on the back surface of the movable member 11 is compressed and deformed, whereby the fixed blade 15 is sandwiched between the bearing housing 1 and the turbine housing 4.

At this time, the movable member 11 is always pushed to the turbine housing 4 side by the disc spring 17, and as a result, the tip of the blade body 14 is always crimped to the opposed front surface of the turbine housing 4, so the side clearance of the blade body 14 is eliminated. Zero clearance can be achieved. As a result, the problem of exhaust (fluid) leakage from the side clearance can be prevented, and the turbine efficiency can be greatly increased.

Further, as described above, when the pressing means 16 is formed by the disc spring 17, the disc spring 17 contacts the movable member 11 and the bearing housing 1 along the circumferential direction thereof, and the movable member 11 and the bearing housing are arranged. 1 is sealed. As a result, the problem of exhaust leaking to the back side of the movable member 11 can be prevented at the same time. Moreover, since the movable member 11 also serves as a heat shield, heat transfer from the movable member 11 to the bearing housing 1 can be suppressed.

FIG. 3A is a cut side view showing another example of the fixed-wing turbocharger shown in FIG. In this example, a fixed blade 15 is provided on the turbine housing 4 (second member) side in a passage 9 formed between opposed front surfaces of the bearing housing 1 (first member) and the turbine housing 4 (second member). Shows the case.

That is, the opposed front surface of the turbine housing 4 (second member) corresponding to the turbine impeller 3 and the passage 9 is constituted by a movable member 19, and the movable member 19 is moved back and forth along an annular guide portion 20 provided in the turbine housing 4. It is arranged to be movable in the direction.

The base end of the wing body 21 is fixed to the front surface of the movable member 19, and the distal end of the wing body 21 is opposed to the opposite front surface of the bearing housing 1, and the fixed wing 15 is configured by the movable member 19 and the wing body 21. Has been.

Further, the movable member 19 is placed between the rear surface of the movable member 19 and the step portion 22 formed in the turbine housing 4 so that the tip of the blade body 21 of the movable member 19 is pressure-bonded to the opposed front surface of the bearing housing 1. A pressing means 16 for pressing backward (rightward in the figure) is provided. The pressing means 16 in FIG. 3A shows a case where a wave washer 23 as shown in FIG. 3B is provided. Since the wave washer 23 has a low sealing capability, a piston ring-shaped seal ring 24 is provided between the outer periphery of the pressing means 16 and the annular guide portion 20. In addition to the wave washer 23, the pressing means 16 may use a disc spring 17 as shown in FIGS. 2A and 2B or a combination of a coil spring and a seal ring 24.

3A and 3B, the wave washer 23 disposed on the back surface of the movable member 19 is incorporated in a compressed and deformed state, and the movable member 19 is always pushed toward the bearing housing 1 by the wave washer 23. Become. For this reason, the tip of the wing body 21 is always crimped to the opposed front surface of the bearing housing 1, so that the side clearance of the wing body 21 can be eliminated. As a result, the problem of exhaust (fluid) leakage from the side clearance can be prevented, and the turbine efficiency can be greatly increased.

FIG. 4 is a cut-away side view showing an example of the fixed-wing turbocharger of the present invention provided with fixed blades in the passage on the compressor side. In the figure, 25 is a compressor impeller that is supported by the bearing housing 1 and rotates integrally with the

turbine invera

3, 26 is a compressor housing formed so as to surround the

turbine invera

25, and 27 is a compressor scroll provided in the compressor housing 26. Show. In this example, in the passage 28 formed between the opposed front surfaces of the bearing housing 1 (first member) and the compressor housing 26 (second member), the fixed blades 29 are provided on the bearing housing 1 (first member) side. I have.

That is, an annular groove 30 is formed at a position corresponding to the passage 28 at the outlet of the compressor impeller 26 on the front surface facing the bearing housing 1 (first member), and the wing body 32 is provided in the groove 30 on the front surface on the passage 28 side. The fixed wing 29 is configured by fitting the ring member 31 movably back and forth. Further, a pressing means 16 including a disc spring 17 and the like is disposed between the back surface of the ring member 31 (left side surface in FIG. 4) and the bottom surface of the groove portion 30. The pressing means 16 presses the ring member 31 rearward (rightward in the drawing) to press the tip of the blade body 32 against the front surface of the compressor housing 26, so that the space between the blade body 32 and the front surface of the compressor housing 26 is Zero clearance can be achieved by eliminating side clearance. Therefore, the problem of air (fluid) leakage due to the side clearance can be prevented. Here, the pressing means 16 may be a wave washer 23 or a coil spring in addition to the disc spring 17. Moreover, you may use together the press means 16 and the seal ring 24 for sealing performance provision.

Note that the fixed-wing turbocharger of the present invention is not limited to the above-described embodiments, and it is needless to say that various modifications can be made without departing from the gist of the present invention.
For example, in the embodiment of FIG. 1, the base end of the wing body 14 is fixed to the front surface of the movable member 11 provided on the opposite front surface of the bearing housing 1 to form the fixed wing 15, and the tip end of the wing body 14 is the turbine housing. 4 is provided with a pressing means 16 for pressing the movable member 11 forward so as to be crimped to the front surface of the opposite side. However, the blades 14 are fixed to the front surface of the movable member 11 provided on the front surface of the bearing housing 1 by the pressing means 16 that fixes the tip of the blade body 14 to the front surface of the turbine housing 4 and presses the movable member 11 forward. The base end of the body 14 may be crimped.

3A and 3B, the base end of the blade body 21 is fixed to the front surface of the movable member 19 provided on the front surface of the turbine housing 4 to form the fixed blade 15, and the tip of the blade body 21 is A pressing means 16 that presses the movable member 19 backward is provided so as to be crimped to the opposed front surface of the bearing housing 1. However, the blades 14 are fixed to the front surface of the bearing housing 1 by the pressing means 16 that fixes the tip of the blade body 14 to the front surface of the bearing housing 1 and presses the movable member 19 backward. The base end of the body 14 may be crimped.

In the embodiment of FIG. 4, the fixed wing 29 is configured by fixing the base end of the wing body 32 to the front surface of the movable member 31 provided on the opposed front surface of the bearing housing 1 (first member). However, the movable member provided on the opposed front surface of the bearing housing 1 by the action of the pressing means 16 that fixes the tip of the blade body 32 to the opposed front surface of the compressor housing 26 (second member) and presses the movable member 31 rearward. The proximal end of the wing body 32 may be crimped to the front surface of the blade 31.

Further, in the embodiment of FIG. 1, the positioning member 5 is provided on the front surface of the bearing housing 1, and the positioning member 5 and the concave portion 13 provided in the annular protrusion 12 of the movable member 11 are made to coincide with each other. Is restricted from moving in the circumferential direction.
However, for example, as shown in FIG. 5, a concave portion (key groove) 40 is provided on the front face of the bearing housing 1, and the concave portion 40 and the convex portion (key) 41 provided on the movable member 11 are matched to each other to move the bearing housing 1. The movement of the member 11 in the circumferential direction may be restricted.

In the embodiment of FIG. 1, the fitting groove 10 is provided radially outward from the space 18 of the bearing housing 1, but the fitting groove 10 is provided radially inward of the bearing housing 1 from the space 18. May be provided.

According to the present invention, the side clearance of the fixed wing in the fixed wing turbocharger can be set to zero clearance. Therefore, one or both of the improvement of the turbine efficiency by the fixed blade and the improvement of the diffuser function can be achieved, and the supercharging efficiency of the turbocharger can be increased.

DESCRIPTION OF SYMBOLS 1 Bearing housing (1st member) 4, Turbine housing (2nd member), 9 channel | path, 11 movable member, 14 wing body, 15 fixed wing | blade, 16 pressing means, 17 disc spring (pressing means), 19 movable member, 21 Wing body, 26 compressor housing (second member), 28 passages, 29 fixed wings

Claims

A fixed blade having a passage between the bearing housing and the turbine housing and a passage between the bearing housing and the compressor formed by the first member and the second member facing each other, and having a fixed blade in at least one of the passages A turbocharger,
The fixed wing is composed of a movable member arranged to be movable in the front-rear direction between the front surfaces of the first member or the second member facing each other, and a wing body fixed to the front surface of the movable member. A fixed wing type turbocharger comprising, on the back surface of the member, pressing means for pressing the movable member so as to press the tip of the wing body against the front surface of the first member or the second member facing the movable member.
A fixed blade having a passage between the bearing housing and the turbine housing and a passage between the bearing housing and the compressor formed by the first member and the second member facing each other, and having a fixed blade in at least one of the passages A turbocharger,
The fixed wing is disposed between a front surface of the first member or the second member facing each other so as to be movable in the front-rear direction, and the front surface of the first member or the second member facing the movable member. A fixed wing tart comprising a fixed wing body, and provided with pressing means for pressing the movable member on the back surface of the movable member so as to press the tip of the wing body against the front surface of the movable member. Bochaja.
The fixed-wing turbocharger according to claim 1, wherein the pressing means is a disc spring that seals leakage of fluid to the back side of the movable member.
3. The fixed wing turbocharger according to claim 2, wherein the pressing means is a disc spring that seals leakage of fluid to the back side of the movable member.
The fixed-wing turbocharger according to claim 1, 2, 3, or 4, wherein the movable member provided on the front surface of the bearing housing facing the turbine housing is a heat shield.