Turbo machine

Patent metadata

Field	Value
Publication number	US-2020200033-A1
Application number	US-201816620096-A
Country	US
Kind code	A1
Filing date	Jul 9, 2018
Priority date	Jul 10, 2017
Publication date	Jun 25, 2020
Grant date	—

Abstract

A turbo machine includes a casing in which fluid flows; turbine blades arranged side by side in a circumferential direction with respect to a rotational shaft rotatably provided in the casing; a ring segment forming an inner surface of the casing; a seal fin provided as an extension at a tip end part of each turbine blade and facing the ring segment; and a seal member through which the turbo machine faces the seal fin, the seal member having a first inner surface that accepts contact of the seal fin. The ring segment has a second inner surface incrementally enlarging toward a downstream side in an axial direction of the rotational shaft. The first and second inner surfaces are connected with each other without a step between the inner surfaces on the downstream side of the first inner surface in the axial direction.

First claim

1 . A turbo machine comprising:
a casing in which fluid flows; a plurality of turbine blades arranged side by side in a circumferential direction with respect to a rotational shaft rotatably provided in the casing; a ring segment forming an inner surface of the casing; a seal fin provided as an extension at a tip end part of each turbine blade and facing the ring segment; and a seal member through which the turbo machine faces the seal fin, the seal member having a first inner surface that accepts contact of the seal fin, the seal member being provided on a radial-direction inner surface of the ring segment, wherein the ring segment has a second inner surface incrementally enlarging toward a downstream side in an axial direction of the rotational shaft, the second inner surface being a different rigid body from the seal member, the first inner surface is configured such that there is no step in the axial direction between an upstream surface of the seal member that faces toward an upstream side in the axial direction of the rotational shaft and a downstream surface of the seal member that faces toward the downstream side in the axial direction of the rotational shaft, and a radial-direction inner surface of the seal member is parallel to the rotational shaft, and the first inner surface and the second inner surface are connected with each other without a step between the inner surfaces on the downstream side of the first inner surface in the axial direction.

2 . A turbo machine comprising:
a casing in which fluid flows; a plurality of turbine blades arranged side by side in a circumferential direction with respect to a rotational shaft rotatably provided in the casing; a ring segment forming an inner surface of the casing; a seal fin provided as an extension at a tip end part of each turbine blade and facing the ring segment; and a seal member through which the turbo machine faces the seal fin, the seal member having a first inner surface that accepts contact of the seal fin, the seal member being provided on a radial-direction inner surface of the ring segment, wherein the ring segment has a second inner surface incrementally enlarging toward a downstream side in an axial direction of the rotational shaft, the second inner surface being a different rigid body from the seal member, the first inner surface is configured such that there is no step in the axial direction between an upstream surface of the seal member that faces toward an upstream side in the axial direction of the rotational shaft and a downstream surface of the seal member that faces toward the downstream side in the axial direction of the rotational shaft, and a radial-direction inner surface of the seal member is parallel to the rotational shaft, the first inner surface and the second inner surface are connected with each other on the downstream side in the axial direction of the first inner surface with a step such that the first inner surface protrudes on an inner side with respect to the second inner surface in a radial direction, the step being smaller than a thickness of the seal member, and the upstream surface of the seal member that faces toward the upstream side in the axial direction of the rotational shaft protrudes from the inner surface of the ring segment, a step between the protruded upstream surface and the inner surface of the ring segment being smaller than the thickness of the seal member.

3 . A turbo machine comprising:
a casing in which fluid flows; a plurality of turbine blades arranged side by side in a circumferential direction to a rotational shaft rotatably provided in the casing; a ring segment forming an inner surface of the casing; and a seal fin provided as an extension at a tip end part of each turbine blade and facing the ring segment; and a seal member facing the seal fin as an extension at the tip end part of each turbine blade at a last stage and having a first inner surface that accepts contact of the seal fin, the seal member being provided on a radial-direction inner surface of the ring segment, wherein the ring segment has a second inner surface having an inner diameter incrementally increasing toward a downstream side in an axial direction of the rotational shaft, the second inner surface being a different rigid body from the seal member, the first inner surface is configured such that there is no step in the axial direction between an upstream surface of the seal member that faces toward an upstream side in the axial direction of the rotational shaft and a downstream surface of the seal member that faces toward the downstream side in the axial direction of the rotational shaft, and a radial-direction inner surface of the seal member is parallel to the rotational shaft, the first inner surface and the second inner surface are connected with each other on the downstream side in the axial direction of the first inner surface with a step such that the first inner surface protrudes on an inner side with respect to the second inner surface in a radial direction, and the upstream surface of the seal member that faces toward the upstream side in the axial direction of the rotational shaft protrudes from the inner surface of the ring segment, a step between the protruded upstream surface and the inner surface of the ring segment being smaller than the thickness of the seal member.

4 . (canceled)

5 . The turbo machine according to claim 3 , wherein the first inner surface and the second inner surface connected with the first inner surface on the downstream side in the axial direction have no step discontinuous in the axial direction except for the protrusion of the seal member.

6 . The turbo machine according to claim 3 , wherein the amount of the protrusion of the seal member is larger than a depth to which shaving by the seal fin is expected and smaller than twice of the depth.

7 . The turbo machine according to claim 3 , wherein the second inner surface is integrated with the ring segment.

8 . The turbo machine according to claim 3 , wherein the second inner surface is provided separately from the ring segment.

9 . The turbo machine according to claim 1 , wherein the upstream surface of the seal member that faces toward the upstream side in the axial direction of the rotational shaft protrudes from the inner surface of the ring segment.

10 . The turbo machine according to claim 1 , wherein the second inner surface is integrated with the ring segment.

11 . The turbo machine according to claim 1 , wherein the second inner surface is provided separately from the ring segment.

12 . The turbo machine according to claim 2 , wherein the first inner surface and the second inner surface connected with the first inner surface on the downstream side in the axial direction have no step discontinuous in the axial direction except for the protrusion of the seal member.

13 . The turbo machine according to claim 2 , wherein the amount of the protrusion of the seal member is larger than a depth to which shaving by the seal fin is expected and smaller than twice of the depth.

14 . The turbo machine according to claim 2 , wherein the second inner surface is integrated with the ring segment.

15 . The turbo machine according to claim 2 , wherein the second inner surface is provided separately from the ring segment.

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Kitagawa Hitoshi
• Fujimura Daigo

Classifications

• F05D2240/11

  Shroud seal segments · CPC title

• F01D11/127 Primary

  with a deformable or crushable structure, e.g. honeycomb · CPC title

• F05D2250/70

  Shape · CPC title

• F05D2250/10

  Two-dimensional · CPC title

• F05D2240/55

  Seals · CPC title