Seal device for turbine, turbine, and thin plate for seal device

Patent metadata

Field	Value
Publication number	US-10731499-B2
Application number	US-201515551383-A
Country	US
Kind code	B2
Filing date	Dec 22, 2015
Priority date	Feb 20, 2015
Publication date	Aug 4, 2020
Grant date	Aug 4, 2020

Abstract

A seal device for a turbine is disposed around a rotor so as to separate a high-pressure space and a low-pressure space and includes: a plurality of thin plates arranged along an outer peripheral surface of the rotor. Each of the thin plates has a thin-plate tip surface facing the outer peripheral surface of the rotor; a first side plate disposed so as to face the high-pressure space and covering outer peripheral regions of first side surfaces; and a second side plate disposed so as to face the low-pressure space and covering outer peripheral regions of second side surfaces. The first side surface of each of the thin plates is covered with the first side plate in a region extending further to an inner side, in a radial direction of the rotor, than a region of the second side surface covered with the second side plate.

First claim

The invention claimed is:

1. A seal device for a turbine disposed around a rotor so as to separate a high-pressure space and a low-pressure space, the seal device comprising:
a plurality of thin plates arranged in a multilayer fashion along an outer peripheral surface of the rotor, each of the thin plates having a thin-plate tip surface facing the outer peripheral surface of the rotor;
a first side plate disposed so as to face the high-pressure space and covering outer peripheral regions of first side surfaces, on a side of the high-pressure space, of the plurality of thin plates; and
a second side plate disposed so as to face the low-pressure space and covering outer peripheral regions of second side surfaces, on a side of the low-pressure space, of the plurality of thin plates,
wherein the first side surface of each of the thin plates is covered with the first side plate in a region extending further to an inner side, in a radial direction of the rotor, than a region of the second side surface covered with the second side plate, and
wherein the thin plates arranged in the multilayer fashion along the outer peripheral surface of the rotor have the same shape in which:
a radial-directional position of the thin-plate tip surface of each of the thin plates has a distribution that the side of the high-pressure space is farther away from the outer peripheral surface of the rotor than the side of the low-pressure space in at least a partial range of the thin-plate tip surface in an axial direction of the rotor, and the radial-directional position of the thin-plate tip surface at an axial-directional position closest to the high-pressure space is positioned radially inward with respect to an inner peripheral edge of the first side plate; and
the thin-plate tip surface includes an inclined surface such that the side of the high-pressure space is farther away from the outer peripheral surface of the rotor than the side of the low-pressure space, in the axial direction of the rotor.

2. The seal device for a turbine according to claim 1 , wherein a distance between the thin-plate tip surface and the outer peripheral surface of the rotor decreases from the side of the high-pressure space toward the side of the low-pressure space in the axial direction of the rotor.

3. The seal device for a turbine according to claim 1 , further comprising a retainer configured to hold a side of a root portion of the plurality of thin plates,
wherein the first side plate and the second side plate are supported by the retainer while being nipped between the retainer and a corresponding one of both side surfaces of the plurality of thin plates.

4. The seal device for a turbine according to claim 1 , wherein a tip portion of each of the plurality of thin plates is configured to deform and distort during rotation of the rotor so that an end portion on the side of the high-pressure space is disposed downstream of an end portion on the side of the low-pressure space with respect to a rotational direction of the rotor, and
wherein the thin plates are configured to contact with each other on the side of the low-pressure space due to the distortion.

5. A turbine, comprising:
a rotor having a turbine blade; and
the seal device for a turbine according to claim 1 disposed around the rotor so as to separate an annular space around the rotor into a high-pressure space and a low-pressure space.

6. A thin plate for the seal device for a turbine according to claim 1 .

7. The seal device for a turbine according to claim 1 , wherein the inclined surface of the thin-plate tip surface of each thin plate extends along an entire width of the tip surface.

8. A seal device for a turbine disposed around a rotor so as to separate a high-pressure space and a low-pressure space, the seal device comprising:
a plurality of thin plates arranged along an outer peripheral surface of the rotor, each of the thin plates having a thin-plate tip surface facing the outer peripheral surface of the rotor;
a first side plate disposed so as to face the high-pressure space and covering outer peripheral regions of first side surfaces, on a side of the high-pressure space, of the plurality of thin plates; and
a second side plate disposed so as to face the low-pressure space and covering outer peripheral regions of second side surfaces, on a side of the low-pressure space, of the plurality of thin plates,
wherein the first side surface of each of the thin plates is covered with the first side plate in a region extending further to an inner side, in a radial direction of the rotor, than a region of the second side surface covered with the second side plate, and
wherein the thin plates arranged along the outer peripheral surface of the rotor have the same shape in which
a radial-directional position of the thin-plate tip surface of each of the thin plates has a distribution that the side of the high-pressure space is farther away from the outer peripheral surface of the rotor than the side of the low-pressure space in at least a partial range of the thin-plate tip surface in an axial direction of the rotor, and the radial-directional position of the thin-plate tip surface at an axial-directional position closest to the high-pressure space is positioned radially inward with respect to an inner peripheral edge of the first side plate,
wherein the thin-plate tip surface includes a step such that the side of the high-pressure space is farther away from the outer peripheral surface of the rotor than the side of the low-pressure space, in the axial direction of the rotor, and
the step of the thin-plate tip surface is disposed closer to the low-pressure space than a midpoint of the thin plate with respect to a width direction of the thin plate.

9. The seal device for a turbine according to claim 8 , further comprising a retainer configured to hold a side of a root portion of the plurality of thin plates,
wherein the first side plate and the second side plate are supported by the retainer while being nipped between the retainer and a corresponding one of both side surfaces of the plurality of thin plates.

10. A turbine, comprising:
a rotor having a turbine blade; and
the seal device for a turbine according to claim 8 disposed around the rotor so as to separate an annular space around the rotor into a high-pressure space and a low-pressure space.

11. A seal device for a turbine disposed around a rotor so as to separate a high-pressure space and a low-pressure space, the seal device comprising:
a plurality of thin plates arranged in a multilayer fashion along an outer peripheral surface of the rotor, each of the thin plates having a thin-plate tip surface facing the outer peripheral surface of the rotor;
a first side plate disposed so as to face the high-pressure space and covering outer peripheral regions of first side surfaces, on a side of the high-pressure space, of the plurality of thin plates; and
a second side plate disposed so as to face the low-pressure space and covering outer peripheral regions of second side surfaces, on a side of the low-pressure space, of the plurality of thin plates,
wherein the first side surface of each of the thin plates is covered with the first side plate in a region extending further to an inner side, in a radial direction of the rotor, than a region of the second side surface covered with the second side plate, and
wherein the thin plates arranged in the multilayer fashion along the outer peripheral surface of the rotor have the same shape in which:
a radial-directional position of the thin-plate tip surface of each of the thin plates has a distribution such that the side of the high-pressure space is farther away fr

Assignees

• Mitsubishi Hitachi Power Sys

Inventors

• Yoshida Azumi
• Uehara Hidekazu
• Oyama Hiroharu
• Ozaki Kohei
• Hamada Katsuhisa
• Sugishita Hideaki
• NISHIKAWA Toyoharu
• Kuwamura Yoshihiro
• Hatano Kohei
• Matsuyama Keisuke

Classifications

• F01D11/001 Primary

  for sealing space between stator blade and rotor · CPC title

• F16J15/4472

  with axial path · CPC title

• F16J15/3292

  Lamellar structures · CPC title

• F05D2240/59

  Lamellar seals · CPC title

• F05D2250/131

  polygonal · CPC title