SEALING DEVICE FOR TURBOCHARGER
A seal body 24 is formed annularly to have a fitted/fixed portion 25 airtightly fitted and fixed to a shoulder 22 in a turbine housing 1 formed facing a scroll passage 8 and have a clearance facing portion 27 facing an outer periphery of a turbine-housing-side exhaust introducing wall 9a with a clearance S, the clearance facing portion 27 being caused to be pressed against the exhaust introducing wall 9a due to a difference in fluid pressure between the clearance S and the scroll passage 8. Slipout preventive means 29 is formed on the fitted/fixed portion 25 of the seal body 24 for preventing the fitted/fixed portion 25 from slipping out of the shoulder 22.
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This application is a division of filed Jun. 20, 2012, the entire contents of which is incorporated herein by reference. U.S. application Ser. No. 13/517,487 is a National Stage of Application No. PCT/JP11/000429 filed Jan. 27, 2011 and claims the benefit of priority from prior Japanese Application No. 2010-018597 filed Jan. 29, 2010.
TECHNICAL FIELDThe present invention relates to a sealing device for a turbocharger.
BACKGROUND ARTAs shown in
In
In
The turbine housing 1 providing the scroll passage 8 is formed with a nozzle facing portion 14 which faces the turbine-housing-side exhaust introducing wall 9a of the exhaust nozzle 10, an annular gap 15 being formed between the nozzle 10 and the nozzle facing portion 14 to extend radially and open to the scroll passage 8. The exhaust introducing wall 9a constituting the exhaust nozzle 10 has an inner end extending as an extension 17 along the turbine impeller 4 toward a shoulder 16 formed on an inner periphery of the nozzle facing portion 14, which brings about a gap 15′ between the extension 17 and the shoulder 16 opening to the inner periphery of the portion 14 and communicating with the gap 15.
The gaps 15 and 15′ are inherently unnecessary, but are provided for countermeasure to, for example, any thermal deformation of the turbine housing 1 between hot and cold states and any dispersion in accuracy between parts to be assembled.
However, when the gaps 15 and 15′ are present, the gas in the scroll passage 8 may disadvantageously leak through the gaps 15 and 15′ from the higher to the lower pressure side, and the gas leakage substantially varies the performance of the turbocharger on a lower velocity side, leading to a problem such as unstable engine performance.
Thus, it has been conventionally proposed as shown in
General state-of-art relevant to the sealing device for the turbocharger shown in
- [Patent Literature 1] JP2006-125588A
However, even if the sealing piston rings 19 and 20 are disposed in the gap 15′ for prevention of the gas leakage as described above, the prevention of the gas leakage is limited. Specifically, each of the sealing piston rings 19 and 20 must have a closed gap 21 as shown in
Moreover, even if the inner periphery of the shoulder 16 of the nozzle facing portion 14 is machined with higher circularity, any slight deviation in circularity of the sealing piston rings 19 and 20 makes the rings 19 and 20 unable to closely contact the inner periphery of the nozzle facing portion 14 with uniform pressure, leading to leakage of the gas through the outer peripheries of the rings 19 and 20.
The invention was conceived in view of the above and has its object to provide a sealing device for a turbocharger capable of reliably closing a gap between a turbine housing and an exhaust nozzle with a simple structure to improve sealability.
Means for Solving the ProblemsThe invention provides a sealing device for a turbocharger having a gap between a turbine housing with a scroll passage and a turbine-housing-side exhaust introducing wall of an exhaust nozzle, comprising:
a seal body annularly formed to have a fitted/fixed portion airtightly fitted and fixed to a shoulder in the turbine housing formed facing the scroll passage and have a clearance facing portion facing an outer periphery of said turbine-housing-side exhaust introducing wall with a clearance, said clearance facing portion being caused to be pressed against the turbine-housing-side exhaust introducing wall due to a difference in fluid pressure between the clearance and the scroll passage, and
slipout preventive means formed on at least either of the shoulder and the fitted/fixed portion of the seal body for preventing the fitted/fixed portion from slipping out of the shoulder.
According to the above means, the following operation can be acquired.
On the one hand, the fitted/fixed portion of the seal body airtightly fitted and fixed to the shoulder formed facing the scroll passage of the turbine housing ensures the sealing in this area, and the slipout preventive means formed at least either of the shoulder and the fitted/fixed portion of the seal body can prevent the fitted/fixed portion from slipping out of the shoulder. On the other hand, with the clearance facing portion on the outer-peripheral-end side facing an outer periphery of the turbine-housing-side exhaust introducing wall with a clearance, when the turbocharger is operated, a difference in fluid pressure between the clearance and the scroll passage deforms the seal body to cause the clearance facing portion to be pressed against the outer periphery of the turbine-housing-side exhaust introducing wall, thereby closing the clearance S. Thus, the automatic sealing by the clearance facing portion is achieved to effectively seal the gap.
In said sealing device for the turbocharger, said shoulder may comprise an annular wall orthogonal to an axis of a turbine impeller and a cylindrical wall orthogonal to said annular wall and about the axis of said turbine impeller,
said fitted/fixed portion comprising an inner annular portion extending along the annular wall of said shoulder and an inner cylindrical portion extending from an inner peripheral end of said inner annular portion along the cylindrical wall of said shoulder toward the turbine-housing-side exhaust introducing wall,
said slipout preventive means being provided by tapering the inner cylindrical portion of said fitted/fixed portion into a shape with an open end reduced in diameter.
In said sealing device for the turbocharger, said shoulder may comprise an annular wall orthogonal to an axis of a turbine impeller and a cylindrical wall orthogonal to said annular wall and about the axis of said turbine impeller,
said fitted/fixed portion comprising an inner annular portion extending along the annular wall of said shoulder and an inner cylindrical portion extended from an inner peripheral end of said inner annular portion along the cylindrical wall of said shoulder toward the turbine-housing-side exhaust introducing wall,
said slipout preventive means being provided by forming a protrusion on an outer periphery of the cylindrical wall of said shoulder adjacent to an open end thereof which engages with an open end of the inner cylindrical portion of said fitted/fixed portion.
In said sealing device for the turbocharger, said shoulder may comprise an annular wall orthogonal to an axis of a turbine impeller and a cylindrical wall orthogonal to said annular wall and about the axis of said turbine impeller,
said fitted/fixed portion comprising an inner annular portion extending along the annular wall of said shoulder,
said slipout preventive means being provided by forming a groove on an outer periphery of the cylindrical wall of said shoulder adjacent to the annular wall thereof into which an open end of the inner annular portion of said fitted/fixed portion is fitted.
Advantageous Effect of InventionA sealing device for a turbocharger of the invention can achieve an excellent effect that the gap between the turbine housing and the exhaust nozzle can be reliably closed with a simple structure to improve the sealability.
Embodiments of the invention will be described with reference to the accompanying drawings.
In the first embodiment, the shoulder 22 comprises, as shown in
The inner annular portion 25a of the seal body 24 has an outer peripheral end formed with a frustoconical portion 26 extending outward, away from the annular wall 22a and toward the exhaust introducing wall 9a. The clearance facing portion 27 comprises an outer annular portion 27a extending outward from an outer peripheral end of the frustoconical portion 26 along the exhaust introducing wall 9a and an outer cylindrical portion 27b extending from an outer circumferential end of the outer annular portion 27a along an outer peripheral end surface 23′ of the exhaust introducing wall 9a. In the first embodiment, the clearance S is disposed between the clearance facing portion 27 and the exhaust introducing wall 9a; otherwise, with no clearance S disposed for the portion 27, a fluid pressure of the scroll passage 8 applied on the portions 26 and 27 would directly act via the seal body 24 on the exhaust introducing wall 9a of the exhaust nozzle 10 due to lack of a deformation margin of the seal body 24, whereby the exhaust nozzle 10 may be deformed. In order to prevent such deformation, the seal body 24 is formed with the clearance facing portion 27 facing the outer periphery of the turbine-housing-side exhaust introducing wall 9a of the exhaust nozzle 10 with the clearance S.
The inner cylindrical portion 25b of the fitted/fixed portion 25 is preliminarily formed with a base end away from an open end thereof and having a bore diameter airtightly fittable with the cylindrical wall 22b of the shoulder 22; the seal body 24 is airtightly fitted and fixed by press fitting the fitted/fixed portion 25 to the shoulder 22. An inclination angle θ formed by the tapered inner cylindrical portion 25b may be less than 30 degrees in consideration of the airtight fitting thereof into the cylindrical wall 22b of the shoulder 22; preferably, the inclination angle θ is effective to an angle of the order of 10 degrees.
In
The cylindrical wall 22b of the shoulder 22 has an open end with a convergent tapered surface 22c for smooth fitting of the seal body 24 to the shoulder 22.
An operation of the first embodiment will be described.
The fitted/fixed portion 25 of the seal body 24 is preliminarily airtightly fitted and fixed by press fitting the same to the shoulder 22 in the turbine housing 1 formed facing the scroll passage 8. The inner cylindrical portion 25b of the seal body 24, which is preliminarily formed to have the base end away from the open end of the seal body and having a bore diameter airtightly fittable to the cylindrical wall 22b of the shoulder 22, is airtightly fixed to the cylindrical wall 22b.
Moreover, the inner cylindrical portion 25b of the fitted/fixed portion 25 has the open end formed as slipout preventive means 29 into the tapered shape with the reduced diameter as indicated by the imaginary line in
With the seal body 24 being fixed to the shoulder 22 of the turbine housing 1, when the turbine and bearing housings 1 and 3 are assembled and fixed to sandwich the exhaust nozzle 10 as shown in
The fitted/fixed portion 25 on the inner peripheral end side of the seal body 24, which is airtightly fitted to the shoulder 22, ensures the seal in this area.
On the other hand, the clearance facing portion 27 on the outer peripheral end side faces the outer periphery 23 of the exhaust introducing wall 9a with the clearance S. However, when the turbocharger is operated, a fluid pressure acts on the seal body 24 due to the fluid in the scroll passage 8 and a greater fluid passing resistance in the clearance S makes difficult the passing of fluid in the clearance S to lower a pressure in this portion than the pressure in the scroll passage 8, so that the seal body 24 is deformed to cause the clearance facing portion 27 to be pressed against the outer periphery 23 of the exhaust introducing wall 9a, thereby closing the clearance S. Thus, automatic sealing by the clearance facing portion 27 is achieved to effectively seal the gap 15. Moreover, the formation of the clearance facing portion 27 on the seal body 24 facing the outer periphery of the exhaust introducing wall 9a of the exhaust nozzle 10 with the clearance S ensures a deflection margin of the seal body 24 when the fluid pressure of the scroll passage 8 acts on the frustoconical portion 26 and the clearance facing portion 27 to thereby reduce a force directly acting via the seal body 24 on and trying to deform the exhaust introducing wall 9a of the exhaust nozzle 10, which is much effective for prevention of the deformation of the exhaust nozzle 10.
Thus, the gap 15 between the turbine housing and the exhaust nozzle 10 can be reliably closed with the simple structure to improve the sealability.
The inner cylindrical portion 25b of the seal body 24 is preliminarily formed to have a bore diameter airtightly fittable to the cylindrical wall 22b of the shoulder 22.
The open end of the cylindrical wall 22b of the shoulder 22 with the protrusion 30 as the slipout preventive means 29 is formed with a convergent tapered surface 22c as is the case with the first embodiment shown in
An operation of the second embodiment will be described.
The fitted/fixed portion 25 of the seal body 24 is preliminarily fitted and fixed by press fitting the same to the shoulder 22 in the turbine housing 1 formed facing the scroll passage 8 such that the inner cylindrical portion 25b is displaced beyond the protrusion 30 acting as the slipout preventive means 29. Since the inner cylindrical portion 25b of the seal body 24 is preliminarily formed to have a bore diameter airtightly fittable to the cylindrical wall 22b of the shoulder 22, the inner cylindrical portion 25b is airtightly fitted and fixed to the cylindrical wall 22b after the inner cylindrical portion 25b is displaced beyond the protrusion 30 acting as the slipout preventive means 29.
Moreover, the open end of the inner cylindrical portion 25b of the fitted/fixed portion 25 is engaged with the protrusion 30 acting as the slipout preventive means 29 as shown in
With the seal body 24 being fixed to the shoulder 22 of the turbine housing 1, when the turbine and bearing housings 1 and 3 are assembled and fixed to sandwich the exhaust nozzle 10 as shown in
In the second embodiment shown in
In the second embodiment shown in
In the second embodiment shown in
The inner peripheral end of the inner annular portion 25a of the seal body 24 is preliminarily formed to have a bore diameter airtightly fittable into the groove 31 formed as the slipout preventive means 29 on the cylindrical wall 22b of the shoulder 22.
An operation of the third embodiment will be described.
The fitted/fixed portion 25 of the seal body 24 is preliminarily fitted and fixed by press fitting the same into the shoulder 22 in the turbine housing 1 formed facing the scroll passage 8 such that the inner peripheral end of the inner annular portion 25a is fitted into the groove 31 acting as the slipout preventive means 29. Since the inner peripheral end of the inner annular portion 25a of the seal body 24 is preliminarily formed to have the bore diameter airtightly fittable into the recessed groove 31 as the slipout preventive means 29 on the cylindrical wall 22b of the shoulder 22, the inner annular portion 25a is airtightly fixed to the cylindrical wall 22b while closely contacting the annular wall 22a.
Moreover, the inner peripheral end of the inner annular portion 25a of the fitted/fixed portion 25 is fitted into the recessed groove 31 acting as the slipout preventive means 29 as shown in
With the seal body 24 being fixed to the shoulder 22 of the turbine housing 1, when the turbine and bearing housings 1 and 3 are assembled and fixed to sandwich the exhaust nozzle 10 as shown in
In the third embodiment shown in
It is to be understood that a sealing device for a turbocharger according to the invention is not limited to the above embodiments and that various changes and modifications may be made without departing from the scope of the invention.
REFERENCE SIGNS LIST
- 1 turbine housing
- 4 turbine impeller
- 8 scroll passage
- 9a turbine-housing-side exhaust introducing wall
- 10 exhaust nozzle
- 15 gap
- 22 shoulder
- 22a annular wall
- 22b cylindrical wall
- 23 outer periphery
- 24 seal body
- 25 fitted/fixed portion
- 25a inner annular portion
- 25b inner cylindrical portion
- 26 frustoconical portion
- 27 clearance facing portion
- 29 slipout preventive means
- 30 protrusion
- 30a tapered surface
- 31 groove
- S clearance
- θ inclination angle
Claims
1. A sealing device for a turbocharger having a gap between a turbine housing with a scroll passage and a turbine-housing-side exhaust introducing wall of an exhaust nozzle, comprising:
- a seal body annularly formed to have a fitted/fixed portion fitted to a shoulder in the turbine housing formed facing the scroll passage and have a clearance facing portion facing an outer periphery of said turbine-housing-side exhaust introducing wall with a clearance, and
- slipout preventive means formed on at least either of the shoulder and the fitted/fixed portion of the seal body for preventing the fitted/fixed portion from slipping out of the shoulder.
2. The sealing device for the turbocharger as claimed in claim 1 wherein said shoulder comprises an annular wall orthogonal to an axis of a turbine impeller and a cylindrical wall orthogonal to said annular wall and about the axis of said turbine impeller,
- said fitted/fixed portion comprising an inner annular portion extending along the annular wall of said shoulder and an inner cylindrical portion extending from an inner peripheral end of said inner annular portion along the cylindrical wall of said shoulder toward the turbine-housing-side exhaust introducing wall,
- said slipout preventive means being provided by tapering the inner cylindrical portion of said fitted/fixed portion into a shape with an open end reduced in diameter.
3. The sealing device for the turbocharger as claimed in claim 1 wherein said shoulder comprises an annular wall orthogonal to an axis of a turbine impeller and a cylindrical wall orthogonal to said annular wall and about the axis of said turbine impeller,
- said fitted/fixed portion comprising an inner annular portion extending along the annular wall of said shoulder and an inner cylindrical portion extended from an inner peripheral end of said inner annular portion along the cylindrical wall of said shoulder toward the turbine-housing-side exhaust introducing wall,
- said slipout preventive means being provided by forming a protrusion on an outer periphery of the cylindrical wall of said shoulder adjacent to an open end thereof which engages with an open end of the inner cylindrical portion of said fitted/fixed portion.
4. The sealing device for the turbocharger as claimed in claim 1 wherein said shoulder comprises an annular wall orthogonal to an axis of a turbine impeller and a cylindrical wall orthogonal to said annular wall and about the axis of said turbine impeller,
- said fitted/fixed portion comprising an inner annular portion extending along the annular wall of said shoulder,
- said slipout preventive means being provided by forming a groove on an outer periphery of the cylindrical wall of said shoulder adjacent to the annular wall thereof into which an open end of the inner annular portion of said fitted/fixed portion is fitted.
Type: Application
Filed: May 28, 2015
Publication Date: Sep 17, 2015
Applicant: IHI Corporation (Tokyo)
Inventor: Yoshimitsu MATSUYAMA (Tokyo)
Application Number: 14/724,162