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KR-102962356-B1 - A centering device for centering a turbine housing, a turbo system including a centering device, and a method for centering a turbine housing.

KR102962356B1KR 102962356 B1KR102962356 B1KR 102962356B1KR-102962356-B1

Abstract

A centering device (10) for centering a turbine housing (40) with respect to the center axis (33) of a radial turbine of a turbo system is described. The centering device (10) comprises a ring-shaped body (11) having an outer diameter (D1) and an inner diameter (D2), wherein the ratio of D1/D2 is ≤ 2. Additionally, the centering device (10) comprises two or more centering elements (16) provided on the side (12) of the ring-shaped body (11) to engage with each complementary centering element (21) provided on the bearing housing (20). The two or more centering elements (16) are configured to allow radial thermal expansion of the ring-shaped body (11) during the engagement of the two or more centering elements (16) and each complementary centering element (21). Furthermore, a method for centering the turbine housing as well as the turbo system including such a centering device is described.

Inventors

  • 바카 안드레아
  • 리히너 마티아스
  • 헤르텔 안트예

Assignees

  • 액셀러론 스위츠랜드 엘티디

Dates

Publication Date
20260511
Application Date
20201202
Priority Date
20191206

Claims (15)

  1. A centering device (10) for centering a turbine housing (40) with respect to the center axis (33) of a radial turbine of a turbo system, and - A ring-shaped body (11) having an outer diameter (D1) and an inner diameter (D2), wherein the ratio of D1/D2 is ≤2; and - Includes two or more centering elements (16) provided on the side (12) of the ring-shaped body (11) to be coupled with each complementary centering element (21) provided on the bearing housing (20), and the two or more centering elements (16) are configured to allow radial thermal expansion of the ring-shaped body (11) during the coupling of the two or more centering elements (16) and each complementary centering element (21), and The centering device (10) is connected to the nozzle ring of the radial turbine, and To guide the relative movement of two or more centering elements (16) with respect to each complementary centering element (21) during thermal expansion of a ring-shaped body, the two or more centering elements (16) have a first planar guide surface (17) and each complementary centering element (21) has a complementary second planar guide surface (18). A centering device (10), wherein two or more centering elements (16) are at least one of a notch and a cam, and each complementary centering element (21) is at least one of a cam and a notch.
  2. A centering device (10) according to claim 1, wherein the opposing surfaces of one or more first planar guide surfaces (17) among two or more centering elements (16) are parallel or inclined with respect to each other, and the opposing surfaces of one or more complementary second planar guide surfaces (18) among each complementary centering element (21) are parallel or inclined with respect to each other.
  3. In paragraph 1 or 2, the centering device (10) is connected to a nozzle ring through at least one of a welded connection, a soldered connection, and one or more fasteners.
  4. In paragraph 1 or 2, the centering device (10) is an integral part of the nozzle ring.
  5. A centering device (10) according to claim 1 or 2, wherein two or more centering elements (16) are cams, and at least one of the cams includes a receiving portion (19) for receiving a fixed element (51) of a heat sheet (50).
  6. A centering device (10) according to claim 1 or 2, wherein two or more guide elements (16) are spaced equally in the circumferential direction around a central opening (14), or two or more guide elements (16) are spaced irregularly in the circumferential direction around a central opening (14).
  7. It is a turbo system, and - Bearing housing (20); - Turbine housing (40) of a radial turbine; - A shaft (34) that extends along the central axis (33), is mounted within a bearing housing (20), and has a turbine wheel (30) arranged thereon, - An exhaust gas inlet passage (41) formed within a turbine housing (40) upstream of a turbine wheel (30), and - Includes a centering device (10) according to paragraph 1, A bearing housing (20) comprises two or more centering elements (16) of a centering device (10) and a centering element (21) that is complementary to each of the two or more centering elements (16) and each of the centering elements (21) is combined with a turbo system.
  8. In claim 7, the centering device (10) is connected to the nozzle ring through at least one of a welded connection, a soldered connection, and one or more fasteners, or the centering device (10) is an integral part of the nozzle ring, in a turbo system.
  9. In claim 8, the nozzle ring is made of a material having the same coefficient of thermal expansion as the material of the centering device (10), in a turbo system.
  10. In claim 7, the centering device (10) is arranged between the bearing housing (20) and the turbine housing (40), and the centering device (10) is arranged and configured such that heat from the exhaust gas is transferred to the centering device (10) during the operation of the turbo system and the heat flow rate from the exhaust gas to the centering device is a continuous function.
  11. A turbo system according to claim 7, further comprising a heat sheet (50) having a fixed element (51) arranged within the receiving portion (19) of the cam of the centering device (10) according to claim 1.
  12. A method of centering the turbine housing (40) with respect to the central axis (33) of the radial turbine of the turbo system, and - A step of transferring heat from the exhaust gas to a centering device (10) according to claim 1 or 2, and - A method comprising the step of centering a turbine housing through the thermal expansion of a centering device (10).
  13. In paragraph 12, the step of transferring heat from the exhaust gas to the centering device includes the step of providing a heat flow rate from the exhaust gas to the centering device, wherein the heat flow rate is a continuous function.
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Description

A centering device for centering a turbine housing, a turbo system including a centering device, and a method for centering a turbine housing. Embodiments of the present disclosure relate to a central device for centering a turbine housing. Additionally, embodiments of the present disclosure relate to a turbo system, e.g., a turbocharger or a turbo compound, having a centering device as described in the present disclosure. Furthermore, embodiments of the present disclosure relate to a method for centering a turbine housing, particularly by using a centering device as described herein. A typical turbo system is a turbocharger or a turbo compound. Today, exhaust gas turbochargers are widely used to increase the performance of internal combustion engines. An exhaust gas turbocharger typically features a turbine within the exhaust pipe of the internal combustion engine and a compressor upstream of the engine. The exhaust gas from the internal combustion engine is expanded within the turbine. The resulting work is transferred to the compressor via a shaft, and the compressor compresses the air supplied to the internal combustion engine. By utilizing the energy from the exhaust gas to compress the air supplied to the combustion process in the internal combustion engine, the combustion process and efficiency of the internal combustion engine can be optimized. A turbo compound engine is a reciprocating engine that employs a turbine to recover energy from the exhaust gas. Instead of using that energy to drive the turbocharger, the energy is sent to the output shaft to increase the total power delivered by the engine. Typically, a turbo system, e.g., a turbocharger or turbo compound, comprises a turbine, particularly a radial turbine, housed within a turbine housing. The turbine housing must be centered with respect to the central axis of the radial turbine. Typically, the centering of the turbine housing is performed, for example, by hot gas centering over a thermal shield or nozzle ring provided between the turbine housing and the bearing housing. Conventional thermal centering methods have the problem that equally rapid heat transfer from the exhaust gas to the thermal centering element, e.g., the thermal shield, cannot be guaranteed, and consequently, a larger clearance is required between the turbine wheel and the turbine casing under transient operating conditions. However, a larger clearance between the turbine wheel and the turbine casing has an adverse effect on turbine efficiency. In order to enable a detailed understanding of the features described above of the present disclosure, a more specific description of the present disclosure, briefly summarized above, may be provided with reference to the embodiments. The accompanying drawings relate to embodiments of the present disclosure and are described below. FIG. 1 shows a cross-sectional view of a part of a turbo system having a thermal shield for centering a turbine housing and a radial turbine according to the prior art. FIG. 2 illustrates a schematic isometric view of a centering device according to an embodiment described herein. FIG. 3 illustrates a schematic isometric view of a bearing housing including a centering element complementary to a centering element of a centering device according to an embodiment described herein. FIG. 4 illustrates a cross-section of a part of a turbo system having a radial turbine including a centering device according to an embodiment described herein. We will now refer to various embodiments in detail, and one or more examples of these embodiments are illustrated in each figure. Each example is provided for illustrative purposes only and is not intended to be limiting. For example, features illustrated or described as part of one embodiment may be used in any other embodiment or in combination with any other embodiment to yield additional embodiments. It is intended that the present disclosure includes such modifications and variations. In the following description of the drawings, the same reference numerals refer to the same or similar components. Generally, only differences between individual embodiments are described. Unless otherwise specified, the description of a part or aspect in one embodiment may also apply to a corresponding part or aspect in another embodiment. FIG. 1 illustrates a cross-sectional view of a turbo system (100) having a radial turbine (35) and a thermal shield (62) for centering a turbine housing (40) according to the prior art. The radial turbine (35) comprises a shaft (34) provided with a turbine wheel (30) having rotor blades (31) mounted within a turbine housing (40) and a bearing housing (20). Additionally, FIG. 1 illustrates a nozzle ring (61) and a thermal shield (62) arranged between the turbine housing (40) and the bearing housing (20). According to the prior art, high-temperature gas centering of the turbine housing is performed through the thermal shield, as exemplarily illustrated