JP2006504021A - Turbocharger with variable nozzle device - Google Patents

Abstract

The turbocharger comprises a wing region formed between a nozzle element (21) and a floating insert (17) supported on the exhaust housing (7), the floating insert (17) being a biasing member (43) is pressed against the wing (27) arranged in the wing area. This configuration improves turbine efficiency and avoids the risk of blade sticking to a significant degree.

Description

  The present invention relates to a turbocharger including a variable nozzle device for adjusting a flow rate of exhaust gas that drives a turbine.

  In a turbocharger including a turbine that drives a compressor impeller and the like, it is necessary to control the flow rate of exhaust gas that drives the turbine in order to achieve different operating conditions. Such control is possible by arranging a plurality of blades in a circle between the nozzle ring and the turbocharger exhaust housing. These blades form a plurality of nozzle passages, and the throat area of the nozzle passages can be varied by arranging the blades in a pivotable manner.

  The document WO 01/96713 A1 discloses a turbocharger device comprising a wing region formed between a nozzle ring and a ring member that is slidable in the axial direction with respect to the wing.

  It is an object of the present invention to provide an improved turbocharger device.

According to one aspect of the invention, the above object is achieved by a turbocharger as defined in claim 1. Preferred embodiments of this turbocharger are described in the dependent claims.
According to the technical solution as defined in claim 1, the turbocharger comprises a nozzle element and a floating insert supported axially slidably on an exhaust housing or turbine housing in the nozzle. It has wings inserted between them. With this arrangement, the gap between the turbine housing and the nozzle element is closed under any operating conditions in order to avoid the risk of blade sticking and at the same time increase the overall turbine efficiency of the turbocharger and improve its regulation. Can be kept.

  In this turbocharger, the floating insertion portion can be pressed against the blades in the nozzle by the pressure difference between the exhaust gas inlet and the nozzle and / or the biasing member supported on the exhaust housing. As the urging member, a recess formed in the gas outlet or a spring washer disposed in the side plate of the turbine housing can be used.

  Alternatively, the urging member can be inserted into a recessed portion formed in the floating insertion portion. In this case, the floating insert is preferably made of sheet metal and has a C-shaped cross section with the opening facing the turbine housing.

  In a turbocharger structure in which the floating insert is configured to be pressed against the blade by the pressure difference between the exhaust gas inlet and the nozzle within the nozzle, the space or recess formed between the insert and the turbine housing is Preferably, the cutout portion of the insertion portion communicates with the exhaust gas inlet of the exhaust housing.

  For mounting the variable nozzle device, its nozzle element carrying a mechanism for pivoting the blades is preferably clamped between a stepped portion of the inner peripheral surface of the turbine and a disk-shaped member supported on the central housing. Yes. In another construction of the turbocharger, the nozzle ring is abutted against the turbine housing by a spacer element, which also acts as a guiding means through the floating insert and thereby guides the movement of the floating insert. .

  A spacer element is placed on the nozzle ring that restricts the movement of the insert towards the wing so that the wing can pivot without pressure during the initial stage of turbocharger operation. In addition, a piston ring can be provided between the floating insert and the gas outlet portion of the turbine housing.

  In the following, further technical solutions of the object of the present invention will be described in detail with reference to the accompanying drawings.

  FIG. 1 shows a part of a turbocharger comprising a central housing 1 that supports a shaft 3. A turbine impeller 5 is mounted on the shaft 3 so as to extend through an exhaust housing or a turbine housing 7 attached to a flange member 9 of the central housing 1 by mounting bolts not specifically shown in FIG. ing.

  As shown in FIG. 1, the exhaust housing 7 forms a generally spiral chamber 11 for receiving exhaust gas from an internal combustion engine. Exhaust gas is fed from a spiral spiral chamber 11 through an annular blade region forming a nozzle 13 to a turbine side plate 15 that forms part of the turbine housing and surrounds the turbine impeller 5. The nozzle 13 is formed between an annular insert 17 supported on the first outlet portion 19 of the turbine housing and the nozzle ring 21. The nozzle ring 21 is fitted inside the second flange portion of the turbine housing, and the turbine housing is attached to the central housing 1 by this nozzle ring. The flange portion of the turbine housing has an opening with a step inside, and this opening engages with the nozzle ring 21 so that the nozzle ring is arranged in the axial direction of the turbocharger. Press toward the elastic disk side plate 23 supported on the central housing 1.

  A plurality of blades specifically shown in FIG. 2 are attached to the nozzle ring 21, which extends through the nozzle 13 and forms a plurality of nozzle passages between itself. The blade 27 is coupled to a blade pin rotatably supported in the nozzle ring, and a blade arm 29 specifically shown in FIG. 3 is attached to the end of each blade pin facing the central housing 1. In the blade arm 29, the length of the blade pin slidable in the axial direction in the nozzle ring exceeds the thickness of the nozzle ring 21, thereby allowing the blade 27 to move slightly in the axial direction back and forth in the nozzle. As such, it is preferably attached to the wing pin by welding. The end of the wing arm 29 is received by a groove formed on the inner peripheral surface of the harmony ring 31. The harmony ring 31 is supported by its inner peripheral surface on at least three rollers 33 that are spaced apart from each other in the circumferential direction, and the rollers are radially inward of the harmony ring in each hole of the nozzle ring 21. It is rotatably attached to a dowel 35 attached to the. The roller 33 includes an outer peripheral groove that receives the inner peripheral surface of the harmony ring 31.

  In the embodiment shown in FIG. 1, the diver 35 is fixed to the holes of the flange member 9 and the nozzle ring 21 at both ends thereof to prevent the nozzle ring from rotating. However, rotation prevention can be achieved by another means in which all the dowels are fixed only in the nozzle ring holes, or by extending only one dowel into both the flange member and the nozzle ring and the remaining dowels in the nozzle ring holes. It can also be achieved by extending only into the. In all of these mounting variations, the gibber is a roller that can rotate and slide axially on the diver to follow the rotation and / or axial strain of the harmonic ring with minimal friction or resistance. Acts as a radial support for

  In order to operate the conditioning ring, an operating system not specifically shown in the figure is used. As such a system, for example, the bell crank system described in US Pat. No. 4,804,316 can be used.

  The annular insertion portion 17 is provided with at least one dowel pin 37 slidably received in a corresponding hole of the exhaust housing 7 at the outer peripheral portion thereof. An annular recess for accommodating the piston ring 39 is formed on the inner peripheral surface of the annular insertion portion 17. An annular recess 41 is provided in the exhaust housing on the radially inner side of the hole that accommodates the dowel pin 37, and the recess accommodates an elastic spring washer 43, whereby the annular insert 17 is disposed on the side surface of the wing 27. As a result, the wing is sandwiched between the nozzle ring 21 and the ring-shaped insertion portion with a moderately balanced pressure. In this way, the spacing of the contact portions between the wing and the nozzle ring and between the wing and the annular insert can be reduced, and at the same time these surfaces can be elastically contacted so that these contact surfaces This minimizes the risk of wing sticking.

  The thickness of the insertion ring 17 can be dimensioned such that a small gap remains between the insertion ring and the outlet portion 19 of the turbine housing in order for the annular recess 41 to communicate with the spiral chamber 11. By using this communication, and preferably the piston ring 39 as a seal between the recess 41 and the nozzle 13, during operation of the turbocharger, the pressure in the annular recess 41 is controlled by the movement in the nozzle 13. Higher than the typical flow pressure, and as a result, the pressure differential creates an additional force that pushes the insert 17 toward the blade forming the nozzle passage.

  In the second embodiment of the turbocharger shown in FIGS. 3 and 4, a spacer element 145 is disposed that extends between the nozzle ring 121 and the first gas output portion 119 of the turbine housing 107. The spacer element 145 serves as a shaft support for the nozzle ring 121 that is pressed against the first portion 119 of the turbine housing 107 by the elastic disk side plate 123.

  An annular insert according to one of the embodiments shown in FIGS. 7a-9b can be used in the turbocharger of the second embodiment. In these embodiments, a radial cutout 149 is provided around the annular insert, thereby slidably engaging the insert 117 with the spacer element 145 to prevent rotation.

  As shown in FIGS. 8 a and 8 b, the annular insertion portion 117 has an axial notch portion 147 that provides communication between the annular recess 141 and the spiral chamber 111 on the side facing the gas outlet portion 119 of the exhaust housing 7. Is provided. This communication causes the pressure between the insert and the turbine housing to be higher than the dynamic flow pressure inside the nozzle 113, resulting in the additional pressure pushing the insert 117 toward the blades forming the nozzle passage. Produces the power of

  In the second embodiment, the spacer element 145 extends so that both ends thereof enter the turbine housing 107 and the nozzle ring 121, and thus are fixed in the same manner as the retaining pin 26 used in the first embodiment shown in FIG. 2. There is no need to provide an element.

  The third embodiment of the turbocharger according to the present invention shown in FIG. 6 mainly uses the sleeve spacer 245 penetrated by the bolt 251 in place of the former spacer element 145 in FIG. Different from the second embodiment shown. The sleeve spacer 245 allows a very flat elastic spring washer (not shown in FIG. 6) to be placed in the space between the annular insert 217 and the gas outlet portion 219 of the exhaust housing 207. The axial length is longer than the sum of the axial thickness of the wing 227 and the axial thickness of the annular insertion portion 217.

In this embodiment, the same variation of the annular insert shown in FIGS. 7a-9b can be used as well.
In the turbocharger according to the fourth embodiment shown in FIG. 10, the annular insertion portion 317 has an L-shaped cross section, and the cross section cooperates with the gas outlet portion 319 of the turbine housing to provide the elastic spring washer 343. Except for forming the circumferential space 341 to be accommodated, it is substantially the same as the turbocharger shown in FIG. The piston ring 339 used in the fourth embodiment is housed in a recess formed in a portion of the turbine housing that faces the inner peripheral surface of the insertion ring 317.

  According to the above description, the essential advantage of the present invention is that the outer wall of the nozzle can be constituted by a relatively small independent element, which itself integrates the swirl chamber and the outlet side plate surrounding the turbine. In addition to being independently replaceable, the turbine housing is also adjustable flexibly toward the blades, thus providing a limited clearance for the blades, and the blades become stuck and impair movement Is avoided.

  FIG. 12 shows a turbocharger according to the fifth embodiment. In this embodiment, the floating insert is indicated by reference numeral 517. The floating insert 517 is in the form of a side plate with a flange 518. The flange 518 is inserted between the exhaust housing 507 and the central housing 51. At least one hole is formed in the flange 518 in alignment with a corresponding hole in the central housing 51. A retaining pin 537 is threaded through both holes, thereby preventing the floating insert 517 from rotating relative to the central housing 51 and the exhaust housing 507.

  The flange 518 is fitted into an inner recess 541 formed in the exhaust housing 507. The axial width of the flange 518 is smaller than the axial width of the inner recess 541 so that the spring member 543 can also be accommodated in the recess 541. The spring member 543 pushes the floating insertion portion 517 in the axial direction toward the wing 527.

  The floating insertion portion 517 is formed integrally with a wall 516 that contacts the wing 527. Therefore, the blade 527 is sandwiched between the floating insertion portion 517 and the nozzle ring 521 in a floating manner by the spring member 543 in order to maintain a constant nozzle width.

  Such a structure not only floats between the central housing 51 and the exhaust housing 507 but also includes a nozzle ring 521 and a floating insert 517 that are axially movable for the purpose of floating relative to each other. A variable nozzle device is provided that incorporates, thereby making it possible to widen the nozzle and thus more effectively avoid sticking and restraining of the wing 527.

This embodiment advantageously facilitates guiding the floating insert 517 in the axial direction and reduces its components.
The fifth embodiment can be modified as follows.

  Such a floating configuration variation of the variable nozzle device can use the central housing design described above, where the central housing has an inner recess and the floating insert 517 is in the recess. Are accommodated so as to be movable in the axial direction.

The retaining pin 537 can also be attached to the exhaust housing.
Instead of the retaining pin 537, another fixing means can be provided. For example, the inner recess of the exhaust housing can have an irregular internal shape that matches the profile of the floating insert so as to prevent the floating insert from rotating relative to the exhaust housing.

  The spring member 543 can be eliminated. In this case, an elastic disk side plate similar to the elastic disk side plates 23 and 123 of the above-described embodiment is used to press the wing 527 to the floating insertion portion 517 via the nozzle ring 521.

1 is a partial cross-sectional view of an exhaust gas turbocharger according to a first embodiment of the present invention. It is an expanded sectional view of the turbocharger shown in FIG. It is a fragmentary sectional view of the exhaust-gas turbocharger by the 2nd Embodiment of this invention. It is an expanded sectional view of the structure of the floating insertion part in 2nd Embodiment shown in FIG. FIG. 5a is a front view of an elastic spring washer used in each of the embodiments shown in FIGS. FIG. 5b is a side view of the elastic spring washer used in each of the embodiments shown in FIGS. It is a fragmentary sectional view of the exhaust-gas turbocharger by the 3rd Embodiment of this invention. FIG. 7a is a front view of a first embodiment of a floating insert used in a turbocharger according to the present invention. FIG. 7b is a cross-sectional view of a first embodiment of a floating insert used in a turbocharger according to the present invention. FIG. 8a is a cross-sectional view of a second embodiment of a floating insert used in a turbocharger according to the present invention. FIG. 8b is a front view of a second embodiment of a floating insert used in a turbocharger according to the present invention. FIG. 9a is a cross-sectional view of a third embodiment of a floating insert used in a turbocharger according to the present invention. FIG. 9b is a front view of a third embodiment of a floating insert used in a turbocharger according to the present invention. It is sectional drawing of 4th Embodiment of the turbocharger by this invention. FIG. 11a is a front view of the floating insert used in the fourth embodiment of the turbocharger shown in FIG. FIG. 11b is a cross-sectional view of the floating insert used in the fourth embodiment of the turbocharger shown in FIG. It is sectional drawing of 5th Embodiment of the turbocharger by this invention.

Claims (13)

  An exhaust housing (7, 107, 207, 307, 507) and a variable nozzle device comprising wings (27, 127, 227, 327, 527), said wings having nozzle elements (21, 121, 221, 321, 521) and a floating insertion portion (17, 117, 217, 317, 517) supported slidably in the axial direction with respect to the exhaust housing (7, 107, 207, 307, 507) Turbocharger inserted between and.   The turbocharger according to claim 1, wherein the floating insert is pressed against the blades (27, 127, 227, 327) in the blade region by a pressure difference between an exhaust gas inlet and a nozzle.   The turbocharger according to claim 1 or 2, wherein the floating insertion portion is pressed against the wing (27, 127, 227, 327, 527) by a biasing member (43, 143, 343, 543).   A spring washer (43, 143) in which the urging member is disposed in a recess (41, 141) formed in a gas outlet side plate portion (19, 119) of the exhaust housing (7, 107, 207, 307, 507). The turbocharger according to claim 3, wherein   The turbocharger device according to claim 3, wherein the urging member is a spring washer arranged in a recess (341) formed in the floating insertion portion (317).   The floating insertion portion (317) is formed of sheet metal and has a C-shaped cross section, and the floating insertion portion together with the exhaust housing (7, 107, 207, 307) defines the recess (341). The turbocharger device according to claim 5.   The turbocharger device according to any one of claims 4 to 6, wherein the recess (41, 141, 341) communicates with the exhaust gas inlet of the exhaust housing (7, 107, 207, 307).   A disk shape in which the nozzle element (21) is supported on the step portion (25) of the inner peripheral surface of the exhaust housing (7, 107, 207, 307) and the central housing (1) of the turbocharger. The turbocharger device according to one of claims 3 to 7, wherein the turbocharger device is clamped between the members.   The nozzle ring (21, 121) is connected to the exhaust housing (7, 107, 207) by a first spacer element (145, 245, 345) passing through the floating insert (17, 117, 217, 317, 517). , 307, 507). The turbocharger device according to one of claims 3 to 7.   The floating insertion portion (17) is brought into contact with the second spacer element (45) by the biasing member, and the second spacer element (45) is supported on the nozzle ring (21). The turbocharger device according to any one of the preceding claims.   A piston ring (39, 139, 339) is provided between the floating insert and the gas outlet side plate portion (19, 119, 319) of the exhaust housing (7, 107, 207, 307). The turbocharger apparatus as described in any one of Claims.   The turbocharger according to claim 11, wherein the piston ring (39, 139, 339) is received in an annular recess of either the floating insert or the exhaust housing (7, 107, 207, 307). apparatus. The floating insert (517) having a flange (518) floatingly inserted between the exhaust housing (507) and a central housing (51) of the turbocharger;
Fixing means (537) for preventing the floating insert (517) from rotating relative to the central housing (51) and the exhaust housing (507);
The turbocharger device according to claim 1, comprising a spring member (543) for pressing the floating insert (517) against the wing (527).

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