US-20260125985-A1 - TURBINE AND MANUFACTURING METHOD OF TURBINE

US20260125985A1US 20260125985 A1US20260125985 A1US 20260125985A1US-20260125985-A1

Abstract

A turbine includes: a turbine blade wheel; a plurality of nozzle vanes arranged apart from each other in a circumferential direction of the turbine blade wheel on a radially outer side of the turbine blade wheel, the plurality of nozzle vanes provided in a freely rotatable manner about a rotation shaft in an axial direction of the turbine blade wheel; an annular member extending in the circumferential direction and freely rotatably provided in conjunction with the plurality of nozzle vanes; and an engagement portion including a pair of sliding surfaces provided on the annular member and facing each other in the circumferential direction, a driving member rotatably driven by an actuator and slidably engaged with the pair of sliding surfaces, the engagement portion having a thickness thicker than a thickness of a peripheral portion of the annular member.

Inventors

Xianpeng REN
Kenta KAWAMITSU
Kotomichi KITAJIMA

Assignees

IHI CORPORATION

Dates

Publication Date: 20260507
Application Date: 20251222
Priority Date: 20231010

Claims (12)

1 . A turbine comprising: a turbine blade wheel; a plurality of nozzle vanes arranged apart from each other in a circumferential direction of the turbine blade wheel on a radially outer side of the turbine blade wheel, the plurality of nozzle vanes provided in a freely rotatable manner about a rotation shaft in an axial direction of the turbine blade wheel; an annular member extending in the circumferential direction and freely rotatably provided in conjunction with the plurality of nozzle vanes; and an engagement portion including a pair of sliding surfaces provided on the annular member and facing each other in the circumferential direction, a driving member rotatably driven by an actuator being slidably engaged with the pair of sliding surfaces, the engagement portion having a thickness thicker than a thickness of a peripheral portion of the annular member.
2 . The turbine according to claim 1 , wherein the annular member includes a main body corresponds to a portion of the annular member excluding the engagement portion, is separate from the engagement portion, and extends in the circumferential direction, and the engagement portion is joined to the main body via at least one welding portion.
3 . The turbine according to claim 2 , wherein the main body includes a recessed portion recessed from a peripheral surface of the main body, a width in the circumferential direction of the recessed portion decreasing as the recessed portion is closer to a bottom, and the engagement portion is joined to side surfaces of the recessed portion on both sides in the circumferential direction via the welding portion.
4 . The turbine according to claim 3 , wherein the engagement portion includes a first engagement portion joined to a first side surface of the recessed portion in the circumferential direction via the welding portion and a second engagement portion joined to a second side surface of the recessed portion in the circumferential direction via the welding portion, the second engagement portion separated from the first engagement portion in the circumferential direction, and the pair of sliding surfaces includes a first facing surface of the first engagement portion, the first facing surface facing the second engagement portion and a second facing surface of the second engagement portion, the second facing surface facing the first engagement portion.
5 . The turbine according to claim 4 , wherein a first gap is formed between the bottom and the first engagement portion, and a second gap is formed between the bottom and the second engagement portion.
6 . The turbine according to claim 5 , wherein a first groove recessed in a direction away from the bottom is formed on a side of the second engagement portion in a portion of the first engagement portion facing the bottom, and a second groove recessed in a direction away from the bottom is provided on a side of the first engagement portion in a portion of the second engagement portion facing the bottom.
7 . A manufacturing method of a turbine, the method comprising the steps of: preparing a turbine blade wheel; arranging a plurality of nozzle vanes apart from each other in a circumferential direction of the turbine blade wheel on a radially outer side of the turbine blade wheel and providing the plurality of nozzle vanes in a freely rotatable manner about a rotation shaft in an axial direction of the turbine blade wheel; providing an annular member extending in the circumferential direction in a freely rotatable manner in conjunction with the plurality of nozzle vanes; and providing an engagement portion to the annular member, the engagement portion including a pair of sliding surfaces facing each other in the circumferential direction, a driving member rotatably driven by an actuator being slidably engaged with the pair of sliding surfaces, the engagement portion having a thickness thicker than a thickness of a peripheral portion of the annular member.
8 . The manufacturing method of a turbine according to claim 7 , wherein the step of providing the engagement portion to the annular member includes the steps of: preparing a main body corresponding to a portion of the annular member excluding the engagement portion, the main body being a separate body from the engagement portion and extending in the circumferential direction; and joining the engagement portion to the main body by welding.
9 . The manufacturing method of a turbine according to claim 8 , wherein the step of preparing the main body includes the step of forming a recessed portion in such a manner as to be recessed from a peripheral surface of the main body, the recessed portion in which a width in the circumferential direction decreases as the recessed portion is closer to a bottom, and the step of joining the engagement portion to the main body includes the step of joining the engagement portion to side surfaces of the recessed portion on both sides in the circumferential direction by welding.
10 . The manufacturing method of a turbine according to claim 9 , wherein the step of joining the engagement portion to the main body includes the steps of: joining a thick member having a thickness thicker than a thickness of the main body to side surfaces of the recessed portion on both sides in the circumferential direction by welding; and forming, as the engagement portion, by cutting the thick member, a first engagement portion joined to a first side surface of the recessed portion in the circumferential direction by welding and a second engagement portion joined to a second side surface of the recessed portion in the circumferential direction by welding and separated from the first engagement portion in the circumferential direction, and forming, as the pair of sliding surfaces, a first facing surface of the first engagement portion facing the second engagement portion and a second facing surface of the second engagement portion facing the first engagement portion.
11 . The manufacturing method of a turbine according to claim 10 , wherein the step of joining the engagement portion to the main body includes the step of: joining the thick member to each of the side surfaces of the recessed portion on both sides in the circumferential direction by welding such that a first gap is formed between the bottom and the first engagement portion and a second gap is formed between the bottom and the second engagement portion.
12 . The manufacturing method of a turbine according to claim 11 , wherein the step of joining the engagement portion to the main body includes the step of: cutting the thick member such that a first groove recessed in a direction away from the bottom is formed on a side of the second engagement portion in a portion of the first engagement portion facing the bottom and that a second groove recessed in a direction away from the bottom is provided on a side of the first engagement portion in a portion of the second engagement portion facing the bottom.

Description

CROSS REFERENCE TO RELATED APPLICATIONS This application is a continuation application of International Application No. PCT/JP2024/021641, filed on June 14, 2024, which claims priority to Japanese Patent Application No. 2023-175446, filed on October 10, 2023, the entire contents of which are incorporated by reference herein. DESCRIPTION BACKGROUND ART TECHNICAL FIELD The present disclosure relates to a turbine and a manufacturing method of a turbine. The present application claims the benefit of priority based on Japanese Patent Application No. 2023-175446 filed on October 10, 2023, the content of which is incorporated herein. Related Art In turbines used for a turbocharger or the like, there are cases where a nozzle vane for adjusting the flow velocity of exhaust gas is provided. For example, as disclosed in Patent Literature 1, a plurality of nozzle vanes are arranged apart from each other in the circumferential direction of a turbine blade wheel on a radially outer side of the turbine blade wheel. With each nozzle vane rotating, a cross-sectional area of a flow path formed between nozzle vanes adjacent to each other changes. As a result, the flow velocity of the exhaust gas flowing between the nozzle vanes adjacent to each other changes. Citation List Patent Literature Patent Literature 1: JP 2004-116313 A SUMMARY Technical Problem Each nozzle vane rotates in conjunction with an annular member rotated by an actuator. The annular member is provided with an engagement portion including a pair of sliding surfaces. A driving member rotatably driven by an actuator is slidably engaged with a pair of sliding surfaces of the engagement portion. As the driving member slides, wear of the engagement portion or the driving member occurs. The object of the present disclosure is to provide a turbine and a manufacturing method of a turbine capable of suppressing wear. Solution to Problem In order to solve the above problem, a turbine of the present disclosure includes: a turbine blade wheel; a plurality of nozzle vanes arranged apart from each other in a circumferential direction of the turbine blade wheel on a radially outer side of the turbine blade wheel, the plurality of nozzle vanes provided in a freely rotatable manner about a rotation shaft in an axial direction of the turbine blade wheel; an annular member extending in the circumferential direction and freely rotatably provided in conjunction with the plurality of nozzle vanes; and an engagement portion including a pair of sliding surfaces provided on the annular member and facing each other in the circumferential direction, a driving member rotatably driven by an actuator and slidably engaged with the pair of sliding surfaces, the engagement portion having a thickness thicker than a thickness of a peripheral portion of the annular member. The annular member may include a main body corresponds to a portion of the annular member excluding the engagement portion, is separate from the engagement portion, and extends in the circumferential direction, and the engagement portion may be joined to the main body via at least one welding portion. The main body may include a recessed portion recessed from a peripheral surface of the main body, a width in the circumferential direction of the recessed portion decreasing as the recessed portion is closer to a bottom, and the engagement portion may be joined to side surfaces of the recessed portion on both sides in the circumferential direction via the welding portion. The engagement portion may include a first engagement portion joined to a first side surface of the recessed portion in the circumferential direction via the welding portion and a second engagement portion joined to a second side surface of the recessed portion in the circumferential direction via the welding portion, the second engagement portion separated from the first engagement portion in the circumferential direction, and the pair of sliding surfaces may include a first facing surface of the first engagement portion, the first facing surface facing the second engagement portion, and a second facing surface of the second engagement portion, the second facing surface facing the first engagement portion. A first gap may be formed between the bottom and the first engagement portion, and a second gap may be formed between the bottom and the second engagement portion. A first groove recessed in a direction away from the bottom may be formed on a side of the second engagement portion in a portion of the first engagement portion facing the bottom, and a second groove may be provided in a direction away from the bottom on a side of the first engagement portion in a portion of the second engagement portion facing the bottom. In order to solve the above problems, a manufacturing method of a turbine according to the present disclosure includes the steps of: preparing a turbine blade wheel; arranging a plurality of nozzle vanes apart from each other in a circumferenti