ROTARY DEVICE

Abstract

The rotary device T1 has an impeller 3, a first housing 6, a second housing 5, an annular flow path 62 positioned radially outside the impeller 3, a plurality of vanes V arranged in the annular flow path 62, an annular plate 52 positioned between the plurality of vanes V and the second housing 5 and supporting the plurality of vanes V, the plurality of vanes V being fixed to the annular plate 52, the annular plate 52 having a positioning surface 54a facing radially inwards and contacting the second housing 5 from a radially outer side, and an elastic body 55 arranged between the annular plate 52 and the second housing 5 and pressing the annular plate 52 and the plurality of vanes V in the axial direction.wherein the positioning surface 54a is located radially inside the elastic body 55 or is located in the same position as a radially inner end of the elastic body 55 in a radial direction.

Description

Technical field

[0001] The present disclosure relates to a rotating device. The present application claims the effect of the priority based on Japanese patent application No. 2023-143955, which was filed on September 5, 2023, and the contents of which are incorporated herein by reference. Technical background

[0002] A rotating device, such as a turbine, can have a plurality of vanes arranged radially outside an impeller. These vanes can be fixed to a ring plate. For example, patent literature 1 discloses a turbine device with a plurality of guide vanes arranged radially outside a turbine impeller. The guide vanes are fixed to a support ring. The support ring contacts a cylindrical centering surface that extends radially inward from a turbine housing. List of patent literature

[0003] Patent Literature 1: JP 2022-161035 A Summary Technical Problem

[0004] For example, high-temperature exhaust gas is fed to a turbine. The annular plate can be subjected to thermal deformation due to the heat from the exhaust gas. If the annular plate thermally deforms, a gap can form between the annular plate and a housing, potentially allowing exhaust gas to escape through the gap to the rear of the impeller. This leads to a reduction in turbine power.

[0005] The present disclosure relates to the provision of a rotating device that can reduce gas leakage. Solution to the problem

[0006] A rotary device according to one aspect of the present disclosure has a shaft, an impeller provided at one end of the shaft, a first housing accommodating the impeller, a second housing connected to the first housing and accommodating a bearing rotatably supporting the shaft, an annular flow path formed between the first housing and the second housing and positioned radially outside the impeller, a plurality of vanes arranged along a circumferential direction in the annular flow path, an annular plate arranged between the plurality of vanes and the second housing and supporting the plurality of vanes, the plurality of vanes being fixed to the annular plate, the annular plate having a positioning surface facing radially inward and contacting the second housing from a radially outer side, and an elastic body.which is arranged between the ring plate and the second housing and which presses the ring plate and the plurality of wings in an axial direction, wherein the positioning surface is located radially inside the elastic body or is located in the same position as a radially inner end of the elastic body in a radial direction.

[0007] The rotating device can have a screw flow path formed in the first housing and positioned radially outside the annular flow path, and a radially outer edge of one of the plurality of vanes can be positioned on a line segment connecting a tongue of the screw flow path and an axis of the impeller, viewed in the axial direction.

[0008] The ring plate can have one component of components protrusion and groove that engages with the protrusion, and one of the first housing and the second housing can have the other component of the components protrusion and groove.

[0009] The elastic body can touch the ring plate at a position radially outside of the radially inner edges of the plurality of wings. Advantageous effects of the invention

[0010] According to the present disclosure, gas leakage can be reduced. Brief description of the drawings Fig. Figure 1 is a schematic cross-sectional view of a turbocharger with a turbine according to a first embodiment. Fig. Figure 2 is a schematic enlarged cross-sectional view of area A in Fig. 1. Fig. Figure 3 is a schematic cross-sectional view along a line III-III in Fig. 1. Fig. Figure 4 is a schematic enlarged cross-sectional view of the turbocharger with a turbine according to a second embodiment. Description of exemplary implementations

[0011] Exemplary embodiments of the present disclosure are described in detail below with reference to the accompanying drawings. Specific dimensions, materials, and numerical values ​​described in the exemplary embodiments are merely examples for better understanding and do not limit the present disclosure unless otherwise specified. In this description and the drawings, duplicate explanations for elements that have essentially the same functions and designs have been omitted by assigning the same reference numeral. Furthermore, elements that do not directly relate to the present disclosure have been omitted from the figures.

[0012] Fig. Figure 1 is a schematic cross-sectional view of a turbocharger 100 with a turbine T1 according to a first embodiment. The turbine T1 according to the present embodiment is applied to the turbocharger 100. In another embodiment, the turbine T1 can be applied to equipment that is different from the turbocharger 100, or it can be a freestanding unit. The turbocharger 100 has a housing 1, a shaft 2, a turbine impeller 3, and a compressor impeller 4.

[0013] As will be described later, the turbine impeller 3 and the compressor impeller 4 rotate integrally with the shaft 2. Therefore, an axis of the turbine impeller 3 and an axis of the compressor impeller 4 are identical to an axis of the shaft 2. In the present disclosure, an axial direction, a radial direction, and a circumferential direction of the shaft 2, the turbine impeller 3, and the compressor impeller 4 may simply be referred to as the "axial direction," the "radial direction," and the "circumferential direction," respectively, unless otherwise indicated. Furthermore, in the present disclosure, the axes of the shaft 2, the turbine impeller 3, and the compressor impeller 4 may simply be referred to as the "axis," unless otherwise indicated.

[0014] The housing 1 comprises a bearing housing (second housing) 5, a turbine housing (first housing) 6, and a compressor housing 7. In the axial direction, one end of the bearing housing 5 is connected to the turbine housing 6 by a fastening device, such as a G-coupling. In the axial direction, the other end of the bearing housing 5 is connected to the compressor housing 7 by a fastening device, such as a bolt.

[0015] The bearing housing 5 has a bearing bore 51. The bearing bore 51 extends axially within the bearing housing 5. The bearing bore 51 accommodates a bearing B. The bearing B rotatably supports the shaft 2. In the present embodiment, a pair of rolling bearings is used as the bearing B. In another embodiment, other radial bearings, such as a fully floating bearing or a semi-floating bearing, can be used as the bearing B.

[0016] The turbine impeller 3 is located at one end of the shaft 2 in the axial direction. The turbine impeller 3 rotates integrally with the shaft 2. The turbine housing 6 accommodates the turbine impeller 3 in a rotatable manner. The compressor impeller 4 is located at a second end of the shaft 2, opposite to the first end in the axial direction. The compressor impeller 4 rotates integrally with the shaft 2. The compressor housing 7 accommodates the compressor impeller 4 in a rotatable manner.

[0017] The compressor housing 7 has an inlet 71 at one end opposite the bearing housing 5 in the axial direction. The inlet 71 is connected to an air filter (not shown).

[0018] The bearing housing 5 and the compressor housing 7 have a diffuser flow path 72 between them. The diffuser flow path 72 has an annular shape. The diffuser flow path 72 is positioned radially outside the compressor impeller 4. The diffuser flow path 72 is fluidly connected to the inlet 71 via the compressor impeller 4.

[0019] The compressor housing 7 has a compressor screw flow path 73. The compressor screw flow path 73 is positioned radially outside the diffuser flow path 72. The compressor screw flow path 73 is connected to the diffuser flow path 72. Furthermore, the compressor screw flow path 73 is fluidly connected to an intake port of a machine (not shown).

[0020] When the compressor impeller 4 rotates, air is drawn into the compressor housing 7 through the inlet 71. The air is accelerated and pressurized by centrifugal force as it passes through the compressor impeller 4. The air is further pressurized as it passes through the diffuser flow path 72 and the compressor screw flow path 73. The pressurized air exits through an outlet port (not shown) and is directed to the machine's intake port. In the turbocharger 100, a component comprising the compressor impeller 4 and the compressor housing 7 functions as a centrifugal compressor C.

[0021] The turbine housing 6 has an outlet 61 at one end opposite the bearing housing 5 in the axial direction. The outlet 61 is connected to an exhaust gas cleaning device (not shown).

[0022] The bearing housing 5 and the turbine housing 6 have a connecting flow path (annular flow path) 62 between them. The connecting flow path 62 has an annular shape. The connecting flow path 62 is positioned radially outside the turbine impeller 3. The connecting flow path 62 is fluidly connected to the outlet 61 via the turbine impeller 3. A plurality of vanes V are arranged in the connecting flow path 62. The plurality of vanes V are arranged along the circumferential direction in a region radially outside the turbine impeller 3. The vanes V will be described in detail later.

[0023] The turbine housing 6 has a turbine screw flow path 63. The turbine screw flow path 63 is positioned radially outside the connecting flow path 62. The turbine screw flow path 63 is connected to the connecting flow path 62. Furthermore, the turbine screw flow path 63 is fluidically connected to a gas inlet opening (not shown). The gas inlet opening receives exhaust gas that is discharged from an exhaust manifold of a machine (not shown).

[0024] The exhaust gas is directed from the gas inlet opening to the turbine screw flow path 63 and is further directed through the connecting flow path 62 and the turbine impeller 3 to the outlet 61. As the exhaust gas passes through the turbine impeller 3, the turbine impeller 3 is rotated. A rotational force from the turbine impeller 3 is transmitted to the compressor impeller 4 via the shaft 2. As the compressor impeller 4 rotates, air is pressurized as described above. The pressurized air is directed to the intake port of the machine. In the turbocharger 100, a component comprising the turbine impeller 3 and the turbine housing 6 functions as the turbine T1.

[0025] Next, the wings V will be described.

[0026] Fig. Figure 2 is a schematic enlarged cross-sectional view of area A in Fig. 1. The turbine T1 has a ring plate 52. In the present embodiment, the ring plate 52 further comprises a first ring plate 53 and a second ring plate 54. The turbine T1 also has an elastic body 55. The bearing housing 5 has a mounting groove 56 for accommodating the first ring plate 53, the second ring plate 54, and the elastic body 55. The mounting groove 56 has a substantially annular shape.

[0027] In the present embodiment, the plurality of vanes V are supported by the first ring plate 53. The first ring plate 53 is arranged axially between the plurality of vanes V and the bearing housing 5. In other words, the first ring plate 53 is arranged axially between the connecting flow path 62 and the bearing housing 5. The first ring plate 53 defines a portion of the connecting flow path 62. The first ring plate 53 has an annular shape around the axis.

[0028] The vanes V are fixed to an end face 53a of the first ring plate 53. The end face 53a faces the connecting flow path 62 in the axial direction. In other words, the vanes V do not move or rotate relative to the first ring plate 53. In the present disclosure, the vane V can also be referred to as a fixed vane. For example, the vanes V can be formed monolithically with the first ring plate 53. Alternatively, the vanes V can be formed separately from the first ring plate 53 and connected to the first ring plate 53 by welding, bolting, or the like.

[0029] Fig. Figure 3 is a schematic cross-sectional view along a line III-III in Fig. 1. Fig. Figure 3 shows a cross-sectional view from the axial direction. For better understanding, only the turbine housing 6, the first ring plate 53 and the blades V are shown. Fig. Figure 3 shows that in the present embodiment, the first ring plate 53 has a projection 57. For example, the projection 57 extends radially outward from an outer circumferential surface 53b of the first ring plate 53. In the present embodiment, the turbine housing 6 has a groove 64. The projection 57 is inserted into the groove 64. The engagement between the projection 57 and the groove 64 prevents rotation of the first ring plate 53 relative to the turbine housing 6 and positions the first ring plate 53 and the plurality of vanes V in the circumferential direction. In another embodiment, the turbine housing 6 may have a projection, and the first ring plate 53 may have a groove that engages with the projection.

[0030] The turbine casing 6 has a tongue 65. In the present disclosure, the “tongue” refers to a circumferential end of a wall that radially separates the turbine screw flow path 63 and the connecting flow path 62. In the present embodiment, a leading edge (radially outer edge) LE of one of the plurality of blades V, namely blade Vb, is positioned on a line segment LS connecting the tongue 65 and the axis X. In the present disclosure, the leading edge LE refers to an upstream end of blade V. In the present embodiment, the remaining blades V are arranged circumferentially and uniformly with respect to blade Vb. In the present disclosure, blade Vb can also be referred to as a reference blade.

[0031] With reference to Fig. In Figure 2, the second ring plate 54 is arranged between the first ring plate 53 and the bearing housing 5. In the present disclosure, the second ring plate 54 can also be referred to as a "heat shield plate". The second ring plate 54 has an annular shape around the axis. For example, the second ring plate 54 is designed to contact an inner circumferential surface 53c and an end surface 53d of the first ring plate 53. The end surface 53d is positioned opposite the end surface 53a, which supports the wings V.

[0032] The bearing housing 5 has a surface 56a that faces radially outwards. In the present embodiment, the surface 56a has a cylindrical shape. The surface 56a defines the mounting groove 56 in the radial direction.

[0033] An inner circumferential surface 54a of the second ring plate 54 contacts the surface 56a of the bearing housing 5. Specifically, the inner circumferential surface 54a faces radially inward and contacts the surface 56a from a radially outer side. For example, the inner circumferential surface 54a has a cylindrical shape. For example, the surface 56a is press-fitted into the inner circumferential surface 54a. In this way, the plurality of vanes V, the first ring plate 53, and the second ring plate 54 are positioned radially. In the present disclosure, the inner circumferential surface 54a of the second ring plate 54 can also be referred to as a "positioning surface".

[0034] The elastic body 55 is arranged axially between the second ring plate 54 and the bearing housing 5. The elastic body 55 presses the ring plate 52 and the plurality of vanes V towards the turbine housing 6 in the axial direction. In the present embodiment, the elastic body 55 is, for example, a disc spring. In another embodiment, the elastic body 55 can be other elastic bodies, such as a plurality of coil springs.

[0035] The elastic body 55 contacts the ring plate 52 at a position radially outside the trailing edges (radially inner edges) TE of the plurality of wings V. Specifically, in the present embodiment, an outer circumferential edge of the elastic body 55 contacts the second ring plate 54. Consequently, the diameter of the outer circumferential edge of the elastic body 55 is larger than the diameter of a circle passing through the trailing edges TE of the plurality of wings V. In the present embodiment, an inner circumferential edge of the elastic body 55 contacts the bearing housing 5.

[0036] The elastic body 55 is positioned radially outside a contact position between the second ring plate 54 and the bearing housing 5, i.e., radially outside the inner surface 54a of the second ring plate 54 and the surface 56a of the bearing housing 5. In other words, the inner surface (positioning surface) 54a of the second ring plate 54 is positioned radially inside the elastic body 55.

[0037] As described above, the exhaust gas from the machine flows through the connecting flow path 62. The annular plate 52 is exposed to the exhaust gas. If the exhaust gas reaches a high temperature, the annular plate 52 can thermally deform. Thermal deformation in the radially outer part is greater than in the radially inner part. Consequently, if the positioning of the annular plate 52 is carried out on its radially outer part, a gap is easily formed between the annular plate 52 and the bearing housing 5 or the turbine housing 6. In this case, the exhaust gas easily escapes from the gap into the mounting groove 56 and further to the rear of the turbine impeller 3. This leads to a reduction in the power output of the turbine T1.

[0038] In contrast, in the turbine T1 of the present embodiment, the positioning of the ring plate 52 is made at its radially inner part, specifically at the inner circumferential surface 54a of the second ring plate 54. Consequently, a gap between the ring plate 52 and the bearing housing 5 is less likely to form. In this case, the escape of exhaust gas can be reduced.

[0039] The turbine T1 of the present embodiment, described above, has the shaft 2, the turbine impeller 3, which is provided at one end of the shaft 2, the turbine housing 6, which accommodates the turbine impeller 3, the bearing housing 5, which is connected to the turbine housing 6 and which accommodates the bearing B, which rotatably supports the shaft 2, the connecting flow path 62, which is formed between the turbine housing 6 and the bearing housing 5 and which is positioned radially outside the turbine impeller 3, the plurality of vanes V, which are arranged along the circumferential direction in the connecting flow path 62, the ring plate 52, which is arranged between the plurality of vanes V and the bearing housing 5 and which supports the plurality of vanes V, wherein the plurality of vanes V are fixed to the ring plate 52, wherein the ring plate 52 has the positioning surface 54a,which faces radially inwards and contacts the bearing housing 5 from its radially outer side, and the elastic body 55, which is arranged between the ring plate 52 and the bearing housing 5 and which presses the ring plate 52 and the plurality of vanes V in the axial direction, wherein the positioning surface 54a is located radially inside the elastic body 55. As described above, according to such a design, the positioning of the ring plate 52 is effected by the positioning surface 54a, which is located radially inside the elastic body 55. Thus, the formation of a gap between the ring plate 52 and the bearing housing 5 is less likely. As a consequence, the escape of exhaust gas can be reduced.

[0040] Furthermore, the turbine T1 has the turbine screw flow path 63, which is formed in the turbine housing 6 and is positioned radially outside the connecting flow path 62. The leading edge LE of one of the plurality of vanes V, namely vane Vb, is positioned on the line segment LS that connects the tongue 65 of the turbine screw flow path 63 and the axis X of the turbine impeller 3, viewed in the axial direction.

[0041] Furthermore, in turbine T1, the ring plate 52 has the projection 57, and the turbine housing 6 has the groove 64, which engages with the projection 57. According to this design, rotation of the ring plate 52 is prevented by a simple construction.

[0042] Furthermore, in turbine T1, the elastic body 55 contacts the ring plate 52 at the position radially outside the trailing edges TE of the plurality of vanes V. According to such a design, the vanes V are pressed firmly against the turbine housing 6.

[0043] Next, another example of implementation will be described.

[0044] Fig. Figure 4 is a schematic enlarged cross-sectional view of the turbocharger 100 with a turbine T2 according to a second embodiment. Turbine T2 differs from turbine T1 of the first embodiment in that the ring plate 52 has only the first ring plate 53 and not the second ring plate 54. Furthermore, the mounting groove 56 is reduced in both the radial and axial directions. Specifically, the surface 56a of the bearing housing 5 is moved radially outwards. With regard to other configurations, turbine T2 can be the same as turbine T1.

[0045] In the present embodiment, the inner circumferential surface 53c of the first ring plate 53 is used to position the plurality of vanes V and the first ring plate 53. Specifically, in the present embodiment, the inner circumferential surface 53c of the first ring plate 53 contacts the surface 56a of the bearing housing 5. The inner circumferential surface 53c faces radially inward and contacts the surface 56a from a radially outer side. For example, the inner circumferential surface 53c has a cylindrical shape. For example, the surface 56a is press-fitted into the inner circumferential surface 53c. In this way, the plurality of vanes V and the first ring plate 53 are positioned in the radial direction. In the present disclosure, the inner circumferential surface 53c of the first ring plate 53 can also be referred to as the "positioning surface".

[0046] In the present embodiment, the outer circumferential edge of the elastic body 55 contacts the first ring plate 53. In the present embodiment, the inner circumferential edge of the elastic body 55 contacts the bearing housing 5. In the present embodiment, the inner circumferential edge of the elastic body 55 is spaced apart from the surface 56a of the bearing housing 5.

[0047] The turbine T2 described above has effects that are the same or similar to those of the turbine T1 according to the first embodiment.

[0048] Although the embodiments of the present disclosure have been described above with reference to the accompanying drawings, the present disclosure is not limited thereto. It is obvious that a person skilled in the art can devise various examples of variations or modifications within the scope of the claims, which are also to be understood as belonging to the technical scope of the present disclosure.

[0049] For example, in the preceding embodiment, the present invention is applied to the vanes (nozzle vanes) V arranged in the connecting flow path 62 of the turbine T1. In another embodiment, the present invention can be applied to diffuser vanes (not shown) arranged in the diffuser flow path 72 of the centrifugal compressor C.

[0050] Furthermore, in the preceding embodiment, for example, the projection 57 extends radially outwards from the outer circumferential surface 53b of the first ring plate 53. In another embodiment, the projection 57 can extend radially inwards from the inner circumferential surface of the first ring plate 53 or the second ring plate 54, and the groove 64 can be provided in a corresponding position on the bearing housing 5.

[0051] Furthermore, in the preceding embodiments, for example, the positioning surfaces 54a and 53c are positioned radially inside the elastic body 55. For example, in the second embodiment of Fig. 4 the inner circumferential edge of the elastic body 55 touches the surface 56a of the bearing housing 5, and the positioning surface 53c can be located in the same position as the inner circumferential edge of the elastic body 55 in the radial direction. Reference symbol list 2nd wave 3 Turbine wheel 5 bearing housings (second housing) 6 turbine housings (first housing) 52 ring plate 53c Inner circumferential area (positioning area) 54a Inner circumferential area (positioning area) 55 elastic body 57 lead 62 Connecting flow path (ring-shaped flow path) 63 Turbine screw flow path 64 Nut 65 Tongue B Storage LE leading margin (radial outer margin) LS line segment T1 Turbine (rotating device) T2 Turbine (rotary device) TE lagging edge (radial inner edge) V-wing X-axis QUOTES INCLUDED IN THE DESCRIPTION

[0000] This list of documents cited by the applicant was automatically generated and is included solely for the reader's convenience. The list is not part of the German patent or utility model application. The DPMA accepts no liability for any errors or omissions. Cited patent literature

[0000] JP 2023-143955

[0001] JP 2022-161035 A

[0003]

Claims

[1] Rotating device with: a wave; a wheel that is provided at one end of the shaft; a first housing that accommodates the impeller; a second housing connected to the first housing, which accommodates a bearing that rotatably supports the shaft; a ring-shaped flow path formed between the first housing and the second housing and positioned radially outside of the impeller; a multitude of wings arranged along a circumferential direction in the annular flow path; a ring plate positioned between the plurality of wings and the second housing, supporting the plurality of wings, the plurality of wings being fixed to the ring plate, the ring plate having a positioning surface facing radially inward and contacting the second housing from a radially outer side; and an elastic body arranged between the ring plate and the second housing, which presses the ring plate and the plurality of wings in the axial direction, wherein the positioning surface is located radially inside the elastic body or is located in the same position as a radially inner end of the elastic body in a radial direction. [2] Rotating device according to claim 1, further comprising: a snail flow path formed in the first housing and positioned radially outside the annular flow path, wherein a radially outer edge of one of the plurality of wings is positioned on a line segment connecting a tongue of the screw flow path and an axis of the impeller, viewed in the axial direction. [3] Rotating device according to claim 1 or 2, wherein the ring plate has a component consisting of the components projection and groove, which engages with the projection, and one of the first housings and the second housing, the other component has the protrusion and groove. [4] Rotating device according to claim 1 or 2, wherein the elastic body contacts the ring plate at a position radially outside of radially inner edges of the plurality of wings. [5] Rotating device according to claim 3, wherein the elastic body contacts the ring plate at a position radially outside of radially inner edges of the plurality of wings.

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