U.S. patent application number 14/724162 was filed with the patent office on 2015-09-17 for sealing device for turbocharger.
This patent application is currently assigned to IHI Corporation. The applicant listed for this patent is IHI Corporation. Invention is credited to Yoshimitsu MATSUYAMA.
Application Number | 20150260288 14/724162 |
Document ID | / |
Family ID | 44319069 |
Filed Date | 2015-09-17 |
United States Patent
Application |
20150260288 |
Kind Code |
A1 |
MATSUYAMA; Yoshimitsu |
September 17, 2015 |
SEALING DEVICE FOR TURBOCHARGER
Abstract
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.
Inventors: |
MATSUYAMA; Yoshimitsu;
(Tokyo, JP) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
IHI Corporation |
Tokyo |
|
JP |
|
|
Assignee: |
IHI Corporation
Tokyo
JP
|
Family ID: |
44319069 |
Appl. No.: |
14/724162 |
Filed: |
May 28, 2015 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
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13517487 |
Jun 20, 2012 |
9074687 |
|
|
PCT/JP2011/000429 |
Jan 27, 2011 |
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14724162 |
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Current U.S.
Class: |
415/110 |
Current CPC
Class: |
F02B 37/00 20130101;
F02B 37/24 20130101; F16J 15/0887 20130101 |
International
Class: |
F16J 15/08 20060101
F16J015/08; F02B 37/00 20060101 F02B037/00 |
Foreign Application Data
Date |
Code |
Application Number |
Jan 29, 2010 |
JP |
2010-018597 |
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.
Description
CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] 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 FIELD
[0002] The present invention relates to a sealing device for a
turbocharger.
BACKGROUND ART
[0003] FIG. 1 shows a conventional sealing device for a variable
geometry turbocharger. The turbocharger comprises turbine and
compressor housings 1 and 2 integrally assembled via a bearing
housing 3 with fastening bolts 3a and 3b, turbine and compressor
impellers 4 and 5 in the housings 1 and 2 being coupled together
with a turbine shaft 7 rotatably supported in the bearing housing 3
by a bearing 6.
[0004] As shown in FIG. 2 which is an enlarged view of a portion II
in FIG. 1, the bearing housing 3 has, on its side adjacent to the
turbine housing 1, an exhaust nozzle 10 (shroud) with a plurality
of radial vanes 9 arranged circumferentially equidistantly between
turbine- and bearing-housing-side exhaust introducing walls 9a and
9b for guidance of fluid (exhaust gas) introduced in a scroll
passage 8 of the housing 1 to the turbine impeller 4, the exhaust
nozzle 10 being sandwiched by the turbine and bearing housings 1
and 3 and fixed with the fastening bolt 3a in FIG. 1.
[0005] In FIG. 2, reference numerals 10a and 10b denote vane shafts
extending through the turbine- and bearing-housing-side exhaust
introducing walls 9a and 9b of the exhaust nozzle 10 to rotatably
support the vanes 9, the respective vanes 9 being supported on
opposite sides thereof by the vane shafts 10a and 10b.
Alternatively, the vanes 9 may be supported on the opposite sides
thereof with the turbine-housing-side vane shafts 10a being short
shafts not extending through the exhaust introducing walls 9a but
embedded in bearing-housing-side side surfaces of the walls 9a.
Alternatively, without the turbine-housing-side vane shafts 10a,
the vanes 9 may be supported in a cantilever manner only by the
vane shafts 10b extending through the bearing-housing-side exhaust
introducing wall 9b.
[0006] In FIG. 1, reference numeral 11 denotes a positioning pin
used in assembling of the exhaust nozzle 10; 12, a scroll passage
in the compressor housing 2; and 13a, 13b, 13c and 13d, a link
mechanism for adjusting an opening degree of the vanes 9 via the
vane shafts 10b.
[0007] 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.
[0008] 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.
[0009] 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.
[0010] Thus, it has been conventionally proposed as shown in FIG. 2
that an annular groove 18 is formed on an outer periphery of the
extension 17 of the exhaust nozzle 10, and sealing piston rings 19
and 20 generally used for a piston of an engine are fitted into the
groove 18 to provide a sealing device, so that outer peripheries of
the piston rings 19 and 20 are brought into close contact with an
inner periphery of the shoulder 16 due to resilience of the rings
19 and 20. Thus, the gas leakage from the gaps 15 and 15' is
prevented and any thermal deformation is absorbed.
[0011] General state-of-art relevant to the sealing device for the
turbocharger shown in FIGS. 1 and 2 is disclosed, for example, in
Patent Literature 1.
CITATION LIST
Patent Literature
[0012] [Patent Literature 1] JP2006-125588A
SUMMARY OF INVENTION
Technical Problems
[0013] 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 FIG. 3 and cannot be formed as
continuous ring and, therefore, even if the positions of the closed
gaps 21 in the two rings 19 and 20 are shifted from each other, the
gas is allowed to leak through the closed gaps 21.
[0014] 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.
[0015] 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 Problems
[0016] The 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:
[0017] 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
[0018] 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.
[0019] According to the above means, the following operation can be
acquired.
[0020] 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.
[0021] 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,
[0022] 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,
[0023] 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.
[0024] 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,
[0025] 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,
[0026] 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.
[0027] 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,
[0028] said fitted/fixed portion comprising an inner annular
portion extending along the annular wall of said shoulder,
[0029] 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 Invention
[0030] A 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.
BRIEF DESCRIPTION OF DRAWINGS
[0031] FIG. 1 is an sectional side elevation of a conventional
sealing device for a turbocharger;
[0032] FIG. 2 is an enlarged view of a portion II in FIG. 1;
[0033] FIG. 3 is a plain view of a conventional sealing piston
ring;
[0034] FIG. 4 is an enlarged sectional side elevation of a relevant
portion showing a first embodiment of a sealing device for a
turbocharger of the invention;
[0035] FIG. 5 is an overall sectional view of a seal body in FIG.
4;
[0036] FIG. 6 is an overall plain view of the seal body in FIG. 4,
corresponding to an arrow view taken along VI-VI in FIG. 5;
[0037] FIG. 7 is an enlarged view of a portion VII in FIG. 4;
[0038] FIG. 8 is an enlarged sectional side elevation of a relevant
portion showing a second embodiment of a sealing device for a
turbocharger of the invention;
[0039] FIG. 9 is an enlarged view of a portion IX in FIG. 8;
[0040] FIG. 10 is a sectional side elevation showing a modification
of the second embodiment of the sealing device for a turbocharger
of the invention, corresponding to a portion IX in FIG. 8; and
[0041] FIG. 11 is an enlarged sectional side elevation of a
relevant portion showing a third embodiment of a sealing device for
a turbocharger of the invention.
DESCRIPTION OF EMBODIMENTS
[0042] Embodiments of the invention will be described with
reference to the accompanying drawings.
[0043] FIGS. 4 to 7 show a first embodiment of a sealing device for
a turbocharger of the invention in which parts similar to those in
FIGS. 1 and 2 are represented by the same reference numerals. The
sealing device comprises a seal body 24 formed annularly as shown
in FIGS. 5 and 6 to have an 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 of an exhaust nozzle 10 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. The fitted/fixed
portion 25 of the seal body 24 is formed with slipout preventive
means 29 for prevention of the fitted/fixed portion 25 from
slipping out of the shoulder 22.
[0044] In the first embodiment, the shoulder 22 comprises, as shown
in FIG. 4, an annular wall 22a orthogonal to an axis of a turbine
impeller 4 and a cylindrical wall 22b orthogonal to the annular
wall 22a and about the axis of the turbine impeller 4. The
fitted/fixed portion 25 of the seal body 24 comprises an inner
annular portion 25a extending along the annular wall 22a of the
shoulder 22 and an inner cylindrical portion 25b extending from an
inner peripheral end of the inner annular portion 25a along the
cylindrical wall 22b of the shoulder 22 toward the
turbine-housing-side exhaust introducing wall 9a. The slipout
preventive means 29 is provided by tapering the inner cylindrical
portion 25b of the fitted/fixed portion 25 into a shape with an
open end reduced in diameter as indicated by an imaginary line in
FIG. 4 and shown in FIG. 5.
[0045] 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.
[0046] 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 .theta. 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 .theta. is effective to an angle of the order of
10 degrees.
[0047] In FIG. 4, reference numeral 28 denotes a convex between the
portions 27a and 27b so as to avoid a corner of the outer
peripheral end surface 23' of the exhaust introducing wall 9a.
[0048] 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.
[0049] An operation of the first embodiment will be described.
[0050] 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.
[0051] 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 FIG. 4 and shown in
FIG. 5, so that a corner of the open end of the inner cylindrical
portion 25b bites into the cylindrical wall 22b as a result of a
wedge effect as shown in FIG. 7 and the fitting state after
press-fitting becomes stronger, thereby reliably preventing the
fitted/fixed portion 25 from slipping out of or being displaced on
the shoulder 22.
[0052] 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 FIG. 1, the turbine-housing-side exhaust introducing wall 9a of
the exhaust nozzle 10 faces the clearance facing portion 27 of the
seal body 24 with the clearance S.
[0053] 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.
[0054] 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.
[0055] 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.
[0056] FIGS. 8 and 9 show a second embodiment of the sealing device
for the turbocharger according to the invention in which parts
similar to those in FIGS. 4-7 are represented by the same reference
numerals. The second embodiment, which has a basic configuration
similar to that in the first embodiment shown in FIGS. 4-7, is
characteristic in that, as shown in FIGS. 8 and 9, a protrusion 30
is formed on an outer periphery of the cylindrical wall 22b
adjacent to an open end of the cylindrical wall 22b of the shoulder
22 to engage with an open end of the inner cylindrical portion 25b
of the fitted/fixed portion 25, thereby providing the slipout
preventive means 29 which prevents the fitted/fixed portion 25 from
slipping out of the shoulder 22.
[0057] 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.
[0058] 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 FIG. 4 for smooth fitting of the seal body 24
to the shoulder 22.
[0059] An operation of the second embodiment will be described.
[0060] 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.
[0061] 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 FIGS. 8 and
9, the fitted/fixed portion 25 can be reliably prevented from
slipping out of or being displaced in the shoulder 22 after
press-fitting.
[0062] 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 FIG. 1, the turbine-housing-side exhaust introducing wall 9a of
the exhaust nozzle 10 faces the clearance facing portion 27 of the
seal body 24 with the clearance S as is the case with the first
embodiment shown in FIG. 4. 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 sealing 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. When the turbocharger is operated, a
pressure due to the fluid in the scroll passage 8 acts on the seal
body 24 and the greater fluid passing resistance in the clearance S
makes difficult 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.
[0063] In the second embodiment shown in FIGS. 8 and 9, as is the
case with the first embodiment shown in FIGS. 4 to 7, the gap 15
between the turbine housing and the exhaust nozzle 10 can be
reliably closed with the simple structure to improve the
sealability.
[0064] In the second embodiment shown in FIGS. 8 and 9, in addition
to forming the protrusion 30 engaging with the open end of the
inner cylindrical portion 25b of the fitted/fixed portion 25 as the
slipout preventive means 29 on the outer peripheral surface of the
cylindrical wall 22b of the shoulder 22 adjacent to the open end
thereof, it is needless to say that the open end of the inner
cylindrical portion 25b of the fitted/fixed portion 25 may be
formed into a tapered shape with a reduced diameter as indicated by
the imaginary line in FIG. 4 and shown in FIG. 5 as is the case
with the first embodiment.
[0065] In the second embodiment shown in FIGS. 8 and 9, the
protrusion 30 acting as the slipout preventive means 29 may have an
edge adjacent to the inner cylindrical portion 25b in the form of a
tapered surface 30a with a gradually reduced outer diameter as
shown in FIG. 10, which enables the tapered surface 30a to allow
more or less displacement in position of the open end of the inner
cylindrical portion 25b axially of the turbine impeller 4 due to
any deviation in dimension accuracy of the seal body 24. In this
case, a corner of the open end of the inner cylindrical portion 25b
bites into the tapered surface 30a as a result of the wedge effect,
so that the effect of slipping-out prevention and the sealability
become effective without concern for inhibition.
[0066] FIG. 11 shows a third embodiment of a sealing device for a
turbocharger of the invention in which parts similar to those in
FIGS. 4 to 7 are represented by the same reference numerals. The
third embodiment, which has the basic configuration similar to that
in the first embodiments shown in FIGS. 4 to 7, is characteristic
in that, as shown in FIG. 11, the fitted/fixed portion 25 comprises
the inner annular portion 25a extending along the annular wall 22a
of the shoulder 22. The slipout preventive means 29 preventing the
fitted/fixed portion 25 from slipping out of the shoulder 22 is
provided by a groove 31 formed on the outer periphery of the
cylindrical wall 22b of the shoulder 22 adjacent to the annular
wall 22a of the shoulder 22, an inner peripheral end of the inner
annular portion 25a of the fitted/fixed portion 25 being fitted
into the groove 31.
[0067] 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.
[0068] An operation of the third embodiment will be described.
[0069] 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.
[0070] 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 FIG. 11, so that the fitted/fixed portion 25 can be
reliably prevented from slipping out of or being displaced in the
shoulder 22 after press-fitting.
[0071] 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 FIG. 1, the turbine-housing-side exhaust introducing wall 9a of
the exhaust nozzle 10 faces the clearance facing portion 27 of the
seal body 24 with the clearance S as is the case with the first and
second embodiments shown in FIGS. 4 and 8, respectively. 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 sealing 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. When the turbocharger is operated, a pressure due to the fluid
in the scroll passage 8 acts on the seal body 24 and the greater
fluid passing resistance in the clearance S makes difficult 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.
[0072] In the third embodiment shown in FIG. 11, as is the case
with the first and second embodiments shown in FIGS. 4-7 and 8-9,
respectively, the gap 15 between the turbine housing and the
exhaust nozzle 10 can be reliably closed with the simple structure
to improve the sealability.
[0073] 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
[0074] 1 turbine housing [0075] 4 turbine impeller [0076] 8 scroll
passage [0077] 9a turbine-housing-side exhaust introducing wall
[0078] 10 exhaust nozzle [0079] 15 gap [0080] 22 shoulder [0081]
22a annular wall [0082] 22b cylindrical wall [0083] 23 outer
periphery [0084] 24 seal body [0085] 25 fitted/fixed portion [0086]
25a inner annular portion [0087] 25b inner cylindrical portion
[0088] 26 frustoconical portion [0089] 27 clearance facing portion
[0090] 29 slipout preventive means [0091] 30 protrusion [0092] 30a
tapered surface [0093] 31 groove [0094] S clearance [0095] .theta.
inclination angle
* * * * *