JP2021156266A - Turbine and supercharger - Google Patents

Abstract

To suppress vibrations of a blade body.SOLUTION: A turbine includes an open type turbine wheel 17 that has a plurality of blade bodies 17b provided at intervals in a circumferential direction, a turbine scroll channel that is formed on the outer side in a diametrical direction than the turbine wheel 17, a discharge port that is communicated with the turbine scroll channel through the turbine wheel 17, and a coupling member 33 that couples the blade bodies 17b adjacent to each other, and is connected to a trailing edge R2 side rather than a leading edge R1 in the blade bodies 17b.SELECTED DRAWING: Figure 3

Description

The present disclosure relates to turbines and turbochargers.

As a turbine provided in a turbocharger or the like, there is a turbine provided with an open type (that is, a type in which a side plate covering the impeller is not provided) turbine impeller. In an open turbine impeller, it is highly necessary to suppress the vibration of the blade body. For example, in Patent Document 1, in a radial turbine in which gas flows into a turbine impeller from the outside in the radial direction, the blade thickness (that is, the wall thickness of the blade body) is partially increased in order to suppress vibration of the blade body. The technology to be used is disclosed.

International Publication No. 2014/1288898

However, if the blade thickness is increased, the aerodynamic performance may decrease. Therefore, in a turbine (specifically, a radial turbine or a mixed flow turbine) in which gas flows into the turbine impeller from the outside in the radial direction, it is desired to suppress the vibration of the blade body by a method other than devising the blade thickness distribution. It is rare.

An object of the present disclosure is to provide a turbine and a turbocharger capable of suppressing vibration of a blade body.

In order to solve the above problems, the turbines of the present disclosure include an open turbine impeller having a plurality of blades provided at intervals in the circumferential direction and a turbine formed radially outside the turbine impeller. A connecting member that connects the scroll flow path, the discharge port that communicates with the turbine scroll flow path via the turbine impeller, and the blade bodies that are adjacent to each other, and is connected to the trailing edge side of the leading edge of the blade body. , Equipped with.

The connecting member may be connected radially outward of the trailing edge side of the leading edge of the blade.

At least one of the plurality of blades is connected to the adjacent blades on one side in the circumferential direction by a connecting member with respect to at least one blade, and is connected in the circumferential direction with respect to at least one blade. It does not have to be connected to the blade adjacent to the other side by a connecting member.

The connecting member may be formed between the blades adjacent to each other along a circular arc extending in the circumferential direction passing through the connection position between each of the blades adjacent to each other and the connecting member.

The connecting member is formed between the adjacent blades along a path that passes radially inside the arc extending in the circumferential direction that passes through the connection position between each of the adjacent blades and the connecting member. May be good.

The connecting member may be hollow.

In order to solve the above problems, the supercharger of the present disclosure includes the above turbine.

According to the present disclosure, vibration of the blade body can be suppressed.

FIG. 1 is a schematic cross-sectional view showing a turbocharger according to the first embodiment of the present disclosure. FIG. 2 is a diagram in which the alternate long and short dash line portion of FIG. 1 is extracted. FIG. 3 is a perspective view showing a turbine impeller according to the first embodiment of the present disclosure. FIG. 4 is a top view showing a turbine impeller according to the first embodiment of the present disclosure. FIG. 5 is a cross-sectional view showing a connecting member according to the first embodiment of the present disclosure. FIG. 6 is a top view showing a turbine impeller of the second embodiment of the present disclosure. FIG. 7 is a top view showing a turbine impeller according to a third embodiment of the present disclosure.

An embodiment of the present disclosure will be described below with reference to the accompanying drawings. The dimensions, materials, and other specific numerical values shown in the embodiments are merely examples for facilitating understanding, and the present disclosure is not limited unless otherwise specified. In the present specification and drawings, elements having substantially the same function and configuration are designated by the same reference numerals to omit duplicate description, and elements not directly related to the present disclosure are omitted from the illustration. do.

FIG. 1 is a schematic cross-sectional view showing a turbocharger TC according to the first embodiment of the present disclosure. Hereinafter, the direction of arrow L shown in FIG. 1 will be described as the left side of the turbocharger TC. The arrow R direction shown in FIG. 1 will be described as the right side of the turbocharger TC. As shown in FIG. 1, the supercharger TC includes a supercharger main body 1. The turbocharger main body 1 includes a bearing housing 3, a turbine housing 5, and a compressor housing 7. The turbine housing 5 is connected to the left side of the bearing housing 3 by a fastening mechanism 9. The compressor housing 7 is connected to the right side of the bearing housing 3 by a fastening bolt 11. The turbocharger TC includes a turbine T and a centrifugal compressor C. The turbine T includes a bearing housing 3 and a turbine housing 5. The centrifugal compressor C includes a bearing housing 3 and a compressor housing 7.

A protrusion 3a is provided on the outer peripheral surface of the bearing housing 3. The protrusion 3a is provided on the turbine housing 5 side. The protrusion 3a projects in the radial direction of the bearing housing 3. A protrusion 5a is provided on the outer peripheral surface of the turbine housing 5. The protrusion 5a is provided on the bearing housing 3 side. The protrusion 5a projects in the radial direction of the turbine housing 5. The bearing housing 3 and the turbine housing 5 are band-fastened by the fastening mechanism 9. The fastening mechanism 9 is, for example, a G coupling. The fastening mechanism 9 sandwiches the protrusion 3a and the protrusion 5a.

A bearing hole 3b is formed in the bearing housing 3. The bearing hole 3b penetrates the supercharger TC in the left-right direction. A semi-floating bearing 13 is arranged in the bearing hole 3b. The semi-floating bearing 13 rotatably supports the shaft 15. A turbine impeller 17 is provided at the left end of the shaft 15. The turbine impeller 17 is rotatably housed in the turbine housing 5. A compressor impeller 19 is provided at the right end of the shaft 15. The compressor impeller 19 is rotatably housed in the compressor housing 7. The axial direction of the shaft 15 is the axial direction of the turbocharger TC (that is, the left-right direction). Hereinafter, the axial direction, the radial direction, and the circumferential direction of the turbocharger TC are simply referred to as the axial direction, the radial direction, and the circumferential direction, respectively.

An intake port 21 is formed in the compressor housing 7. The intake port 21 opens on the right side of the turbocharger TC. The intake port 21 is connected to an air cleaner (not shown). The diffuser flow path 23 is formed by the facing surfaces of the bearing housing 3 and the compressor housing 7. The diffuser flow path 23 boosts air. The diffuser flow path 23 is formed in an annular shape. The diffuser flow path 23 communicates with the intake port 21 via the compressor impeller 19 on the inner side in the radial direction.

The compressor housing 7 is provided with a compressor scroll flow path 25. The compressor scroll flow path 25 is formed in an annular shape. The compressor scroll flow path 25 is located, for example, radially outside the diffuser flow path 23. The compressor scroll flow path 25 communicates with the intake port of an engine (not shown) and the diffuser flow path 23. When the compressor impeller 19 rotates, air is taken into the compressor housing 7 from the intake port 21. The intake air is pressurized and accelerated in the process of flowing between the blades of the compressor impeller 19. The pressurized and accelerated air is boosted by the diffuser flow path 23 and the compressor scroll flow path 25. The boosted air is guided to the intake port of the engine.

A discharge port 27 is formed in the turbine housing 5. The discharge port 27 opens on the left side of the turbocharger TC. The discharge port 27 is connected to an exhaust gas purification device (not shown). A communication passage 29 and a turbine scroll flow path 31 are formed in the turbine housing 5. The turbine scroll flow path 31 is formed in an annular shape. The turbine scroll flow path 31 is formed radially outward of the turbine impeller 17. The turbine scroll flow path 31 communicates with a gas inlet (not shown). Exhaust gas discharged from an engine exhaust manifold (not shown) is guided to the gas inlet. The communication passage 29 communicates the turbine scroll flow path 31 and the discharge port 27 via the turbine impeller 17. The exhaust gas guided from the gas inflow port to the turbine scroll flow path 31 is guided to the discharge port 27 via the communication passage 29 and the turbine impeller 17. The exhaust gas guided to the discharge port 27 rotates the turbine impeller 17 in the distribution process.

The rotational force of the turbine impeller 17 is transmitted to the compressor impeller 19 via the shaft 15. When the compressor impeller 19 rotates, the air is boosted as described above. In this way, air is guided to the intake port of the engine.

FIG. 2 is a diagram in which the alternate long and short dash line portion of FIG. 1 is extracted. The turbine impeller 17 is an open type (that is, a type in which a side plate covering the impeller is not provided). The turbine impeller 17 has a hub 17a and a plurality of blade bodies 17b. The hub 17a is connected to the left end of the shaft 15. The outer diameter of the hub 17a becomes smaller toward the left side of the turbocharger TC. A plurality of blades 17b are provided on the outer peripheral surface of the hub 17a. The plurality of blades 17b are provided at intervals in the circumferential direction. Each blade body 17b is formed so as to extend radially outward from the outer peripheral surface of the hub 17a.

The outer peripheral edge of the wing body 17b includes a leading edge R1, a trailing edge R2 and an intermediate edge R3. The leading edge R1 is an edge portion of the blade body 17b on the upstream side in the flow direction of the exhaust gas. The leading edge R1 is an edge portion of the blade body 17b on the turbine scroll flow path 31 side. Exhaust gas from the turbine scroll flow path 31 flows into the leading edge R1. The leading edge R1 is formed on the right end side of the blade body 17b. The leading edge R1 extends in the axial direction. The trailing edge R2 is an edge portion of the blade body 17b on the downstream side in the flow direction of the exhaust gas. The trailing edge R2 is an edge portion of the blade body 17b on the discharge port 27 side. Exhaust gas flows out from the trailing edge R2 toward the discharge port 27. The trailing edge R2 is formed on the left end side of the blade body 17b. The trailing edge R2 extends in the radial direction while twisting in the circumferential direction. The intermediate edge R3 is formed between the leading edge R1 and the trailing edge R2. The intermediate edge portion R3 extends along the shroud portion 29a that defines the communication passage 29 in the turbine housing 5.

As shown by the arrow D1 in FIG. 2, exhaust gas flows into the turbine impeller 17 in the radial direction from the outside in the radial direction. As described above, the turbine T is a so-called radial turbine. The turbine T may be a so-called oblique flow turbine in which exhaust gas flows in from the outside in the radial direction in a direction inclined with respect to the radial direction.

Here, in a radial turbine or a mixed flow turbine in which gas flows into the turbine impeller 17 from the radial outer side, in the main vibration mode of the blade body 17b, the radial outer end E1 of the trailing edge R2 is the antinode of vibration. It becomes. Specifically, in the primary mode, the radial outer end E1 of the trailing edge R2 becomes the antinode of vibration. In the secondary mode, in addition to the end E1, the left end E2 of the leading edge R1 becomes the antinode of vibration. In the turbine T of the present embodiment, the connecting member 33 is provided in order to suppress the vibration of the blade body 17b.

FIG. 3 is a perspective view showing the turbine impeller 17. FIG. 4 is a top view showing the turbine impeller 17. As shown in FIGS. 3 and 4, the turbine impeller 17 is provided with eight blades 17b. The number of blades 17b provided on the turbine impeller 17 may be other than eight. The connecting member 33 connects the blades 17b adjacent to each other. Specifically, the connecting member 33 is an annular member coaxial with the hub 17a. The connecting member 33 is attached to each blade body 17b in a state of penetrating each blade body 17b. For example, the connecting member 33 is attached so that the relative movement with respect to each blade body 17b is restricted by welding or the like. The connecting member 33 may be a separate member from each blade body 17b, or may be integrally formed with each blade body 17b.

The connecting member 33 is connected to the trailing edge R2 side of the leading edge R1 of the blade body 17b. Specifically, the connecting member 33 is connected to a region of the blade body 17b closer to the trailing edge R2 than the leading edge R1 in the flow direction of the exhaust gas. For example, as shown in FIG. 2, the connecting member 33 is connected to a position in the region A1 in the vicinity of the trailing edge R2 on the blade body 17b. 2 to 4 show an example in which the connecting member 33 is connected to the trailing edge R2 side (that is, the downstream side) of the blade body 17b near the center in the radial direction.

As described above, in the turbine T of the present embodiment, the blades 17b adjacent to each other are connected by the connecting member 33. The connecting member 33 is connected to the trailing edge R2 side of the leading edge R1 of the blade body 17b. Thereby, in the main vibration mode of the blade body 17b, the vibration in the vicinity of the end portion E1 which is the antinode of the vibration can be suppressed. Therefore, the vibration of the blade body 17b can be suppressed. Further, since the vibration of the blade body 17b is suppressed by a method other than devising the blade thickness distribution, the deterioration of the aerodynamic performance is also suppressed.

Here, it is preferable that the connecting member 33 is connected to the radial outer side of the trailing edge R2 side of the leading edge R1 of the blade body 17b. Specifically, the connecting member 33 is preferably connected to a region on the trailing edge R2 side (that is, the downstream side) of the blade body 17b that is radially outer of the center position in the radial direction. For example, the connecting member 33 is preferably connected to a position in the radial outer region A2 of the region A1 shown in FIG. Thereby, in the main vibration mode of the blade body 17b, it is possible to suppress the vibration at a position closer to the end portion E1 which is the antinode of the vibration. Therefore, the vibration of the blade body 17b can be suppressed more effectively.

As shown in FIG. 4, the connecting member 33 is provided between the adjacent blades 17b along a circular arc extending in the circumferential direction through the connection position between each of the adjacent blades 17b and the connecting member 33. It is formed. For example, the connecting member 33 is connected to the blade body 17b1 at the connecting position P1. The connecting member 33 is connected to the blade body 17b2 adjacent to the blade body 17b1 at the connection position P2. The connecting member 33 is formed between the blades 17b1 and the blades 17b2 that are adjacent to each other along the arc AR1 extending in the circumferential direction through the connection position P1 and the connection position P2.

As described above, the connecting member 33 is formed in an arc shape along the circumferential direction between the blades 17b adjacent to each other. Therefore, at the connection position between each of the blades 17b adjacent to each other and the connecting member 33, the connecting member 33 is orthogonal to the blade 17b. Specifically, the connection direction of the connecting member 33 to the blade body 17b is a direction orthogonal to the extending direction of the blade body 17b (that is, the circumferential direction of the turbocharger TC). Here, the vibration direction of the blade body 17b is a direction orthogonal to the extending direction of the blade body 17b (that is, the circumferential direction of the turbocharger TC). Therefore, the connection direction of the connecting member 33 with respect to the blade body 17b coincides with the vibration direction of the blade body 17b. Therefore, the vibration of the blade body 17b can be suppressed more effectively.

FIG. 5 is a cross-sectional view showing the connecting member 33. Specifically, FIG. 5 is a diagram showing a cross section taken along the line AA of FIG. As shown in FIG. 5, the connecting member 33 is hollow. The connecting member 33 has a tubular shape extending in the circumferential direction. The wall thickness of the connecting member 33 may be constant as in the example shown in FIG. The wall thickness of the connecting member 33 does not have to be constant. For example, it is realized that the hollow connecting member 33 is formed by laminated modeling using a 3D printer or the like. When the volume of the connecting member 33 is constant, when the connecting member 33 is hollow, bending is performed while suppressing an increase in the weight of the connecting member 33 as compared with the case where the connecting member 33 is solid. It is possible to improve the strength against deformation and the strength against torsional deformation.

The shape of the connecting member 33 is not limited to the examples shown in FIGS. 2 to 5. For example, FIGS. 2 to 5 show an example in which the radial length of the connecting member 33 is longer than the axial length, but the radial length of the connecting member 33 is longer than the axial length. It may be short. The cross-sectional shape of the connecting member 33 may be different from the shape shown in FIG. The connecting member 33 may be solid. The connecting member 33 does not have to have a rotationally symmetric shape.

Hereinafter, as another embodiment in which the configuration of the connecting member 33 is different from that of the turbine impeller 17 of the first embodiment of the present disclosure, the turbine impeller 17A of the second embodiment of the present disclosure and the present disclosure The turbine impeller 17B of the third embodiment will be described.

FIG. 6 is a top view showing the turbine impeller 17A of the second embodiment of the present disclosure. As shown in FIG. 6, the turbine impeller 17A is provided with eight blades 17b, similarly to the turbine impeller 17 described above. That is, the number of regions between the blades 17b adjacent to each other (hereinafter, also referred to as inter-blade regions) is eight. In the turbine impeller 17A, four connecting members 33A are provided in a part of the inter-blade region. The connecting member 33A connects adjacent blades 17b forming an inter-blade region in which the connecting member 33A is provided. In the turbine impeller 17A, the inter-blade region in which the connecting member 33A is provided and the inter-blade region in which the connecting member 33A is not provided are alternately arranged. The connecting member 33A may be a member separate from the blade body 17b, or may be integrally formed with the blade body 17b.

Each blade body 17b is connected to a blade body 17b adjacent to each blade body 17b on one side in the circumferential direction by a connecting member 33A, and a blade adjacent to each blade body 17b on the other side in the circumferential direction. It is not connected to the body 17b by the connecting member 33A. For example, the blade body 17b1 is connected to the blade body 17b2 adjacent to the blade body 17b1 on one side in the circumferential direction (counterclockwise side on the paper surface) by a connecting member 33A, and is connected to the blade body 17b1 on the other side in the circumferential direction. It is not connected to the blade body 17b3 adjacent to (clockwise on the paper) by the connecting member 33A.

If the blade body 17b is connected only to one of the two blade bodies 17b adjacent to the blade body 17b by the connecting member 33A, the effect of suppressing vibration can be obtained. Therefore, by connecting at least one blade body 17b to only one of the two blade bodies 17b adjacent to the blade body 17b by the connecting member 33A, the total volume and the total weight of the connecting member 33A are reduced. Can be made to.

The arrangement of the inter-blade region where the connecting member 33A is provided is not limited to the example shown in FIG. For example, the inter-blade regions where the connecting member 33A is provided may be adjacent to each other in the circumferential direction. The inter-blade regions where the connecting member 33A is not provided may be adjacent to each other in the circumferential direction. However, from the viewpoint of reducing the total volume and total weight of the connecting member 33A, when the number of blades 17b is even, the inter-blade region where the connecting member 33A is provided and the inter-blade region where the connecting member 33A is not provided are located. , It is preferable that they are arranged alternately.

FIG. 7 is a top view showing the turbine impeller 17B of the third embodiment of the present disclosure. As shown in FIG. 7, in the turbine impeller 17B, the connecting member 33B is formed by one or more members in an annular shape surrounding the hub 17a. The connecting member 33B is attached to each blade body 17b in a state of penetrating each blade body 17b, similarly to the turbine impeller 17 described above. The connecting member 33B may be a separate member from each blade body 17b, or may be integrally formed with each blade body 17b.

In FIG. 7, the shape of the connecting member 33 of the turbine impeller 17 described above is shown by a broken line. As described above, in the turbine impeller 17, the connecting member 33 is an arc extending in the circumferential direction between the adjacent blades 17b and passing through the connection position between each of the adjacent blades 17b and the connecting member 33. It is formed along. On the other hand, as shown in FIG. 7, in the turbine impeller 17B, the connecting member 33B passes through the connection position between each of the adjacent blades 17b and the connecting member 33 between the adjacent blades 17b. It is formed along a path that passes radially inside the arc extending in the direction. For example, the connecting member 33B is radially inside (that is, on the hub 17a side) of the arc AR1 extending in the circumferential direction passing through the connecting position P1 and the connecting position P2 between the blades 17b1 and the blades 17b2 adjacent to each other. It is formed along the path that passes through.

As described above, in the turbine impeller 17B, the connecting member 33B is formed between the blade bodies 17b adjacent to each other through the inner side in the radial direction as compared with the case where the connecting member 33B is formed in an arc shape along the circumferential direction. .. Thereby, in the inter-blade region, the connecting member 33B can be brought closer to the rotation axis of the turbine impeller 17B. Therefore, the centrifugal force acting on the connecting member 33B in the inter-blade region can be reduced. Therefore, it is possible to suppress an increase in the volume and weight of the connecting member 33B in order to counter the centrifugal force.

Although the embodiments of the present disclosure have been described above with reference to the accompanying drawings, it goes without saying that the present disclosure is not limited to such embodiments. It is clear to those skilled in the art that various modifications or modifications can be conceived within the scope of the claims, and it is understood that they also naturally belong to the technical scope of the present disclosure. Will be done.

In the above, the example in which the turbine T is mounted on the supercharger TC has been described, but the turbine T may be mounted on a device other than the supercharger TC (for example, a generator or the like).

The embodiments described above may be combined. For example, when the connecting member is omitted in a part of the inter-blade region as in the second embodiment, the trajectory of the connecting member in the inter-blade region may be the same as in the first embodiment, and the third embodiment. It may be the same as the embodiment of.

The present disclosure can be used for turbines and turbochargers.

17 Turbine impeller 17A Turbine impeller 17B Turbine impeller 17b Blade 27 Discharge port 31 Turbine scroll flow path 33 Connecting member 33A Connecting member 33B Connecting member AR1 Arc P1 Connection position P2 Connection position R1 Leading edge R2 Trailing edge R3 Intermediate edge Part T Turbine TC Supercharger

Claims (7)

An open turbine impeller with multiple blades spaced apart in the circumferential direction,
A turbine scroll flow path formed radially outside the turbine impeller, and
A discharge port that communicates with the turbine scroll flow path via the turbine impeller, and
A connecting member that connects the blades adjacent to each other and is connected to the trailing edge side of the leading edge of the blades.
To prepare
Turbine. The connecting member is connected radially outward of the trailing edge side of the leading edge of the wing body.
The turbine according to claim 1. At least one of the plurality of blades is connected to the adjacent blades on one side in the circumferential direction by the connecting member, and the at least one blade is connected to the at least one blade. It is not connected to the blades adjacent to each other on the other side in the circumferential direction by the connecting member.
The turbine according to claim 1 or 2. The connecting member is formed between the adjacent blades along a circular arc extending in the circumferential direction through the connection position between each of the adjacent blades and the connecting member.
The turbine according to any one of claims 1 to 3. The connecting member is formed between the adjacent blades along a path that passes radially inside the arc extending in the circumferential direction through the connection position between each of the adjacent blades and the connecting member. Is formed,
The turbine according to any one of claims 1 to 3. The connecting member is hollow.
The turbine according to any one of claims 1 to 5. A supercharger including the turbine according to any one of claims 1 to 6.

Images