Sealing structure between turbine rotor disk and interstage disk

Patent metadata

Field	Value
Publication number	US-2020386110-A1
Application number	US-202015931812-A
Country	US
Kind code	A1
Filing date	May 14, 2020
Priority date	Jun 5, 2019
Publication date	Dec 10, 2020
Grant date	—

Abstract

A sealing structure for a gas turbine includes a turbine rotor disk, a turbine blade coupled the turbine rotor disk, and an interstage disk interposed between adjacent turbine rotor disks. The turbine blade includes a blade circumferential surface protruding axially and extending in a circumferential direction of the turbine rotor disk and mutually engaging with a disk circumferential surface formed circumferentially on the turbine rotor disk. The interstage disk includes a rim portion and a groove formed in the rim portion. A plurality of static ring seals are mounted in the groove, each static ring seal facing toward the blade circumferential surface and the disk circumferential surface. The static ring are configured such that an outer circumferential surface of all the static ring seals contact the blade circumferential surface and the outer circumferential surface of at least one of the static ring seals does not contact the disk circumferential surface.

First claim

What is claimed is:

1 . A sealing structure for a gas turbine including a plurality of turbine rotor disks, the sealing structure comprising:
a turbine rotor disk of the plurality turbine rotor disks; a turbine blade fastened to a coupling slot formed in a circumferential surface of the turbine rotor disk, the turbine blade including
a root having a shape corresponding to the coupling slot,
a platform positioned radially outward from the root part,
a blade extending from the platform part, and
a blade circumferential surface that is formed on a radially inner side of the platform and protrudes in an axial direction, the blade circumferential surface extending in a circumferential direction of the turbine rotor disk and mutually engaging with a disk circumferential surface formed circumferentially on the turbine rotor disk;
an interstage disk interposed between adjacent turbine rotor disks of the plurality of turbine rotor disks, the interstage disk including a rim portion extending radially outward and a groove formed in the rim portion; and a plurality of static ring seals mounted in the groove of the interstage disk, each static ring seal having an outer circumferential surface facing toward the blade circumferential surface and the disk circumferential surface, the plurality of static ring configured such that the outer circumferential surface of all of the plurality of static ring seals contact the blade circumferential surface and such that the outer circumferential surface of at least one of the plurality of static ring seals does not contact the disk circumferential surface.

2 . The sealing structure according to claim 1 ,
wherein the plurality of static ring seals are arranged in the axial direction from the turbine blade and include an outermost static ring seal with respect to the turbine blade, and wherein the at least one of the plurality of static ring seals that does not contact the disk circumferential surface includes the outermost static ring seal.

3 . The sealing structure according to claim 2 , wherein each static ring seal consists of a plurality of ring segments.

4 . The sealing structure according to claim 3 ,
wherein each of the plurality of ring segments includes a separation hole, and wherein the rim portion of the interstage disk includes a radially outer edge in which a separation slot is formed and configured to expose the separation hole of a ring segment of the outermost static ring seal.

5 . The sealing structure according to claim 4 ,
wherein the plurality of ring segments of one of the plurality of static ring seals are mounted to be staggered in the axial direction with respect to the plurality of ring segments of an adjacent static ring seal of the plurality of static ring seals, and wherein the separation slots include at least two separation slots configured to expose the separating holes of the staggered ring segments.

6 . The sealing structure according to claim 3 , wherein each of the plurality of ring segments includes a radially inner edge in which an anti-rotation slot is formed, the anti-rotation slot receiving an anti-rotation pin provided in the groove.

7 . The sealing structure according to claim 6 ,
wherein the plurality of ring segments of one of the plurality of static ring seals are mounted to be staggered with respect to the plurality of ring segments of an adjacent static ring seal of the plurality of static ring seals, and wherein the anti-rotation slots of the plurality of ring segments are respectively formed at positions where the anti-rotation pin is received simultaneously by the anti-rotation slots of the plurality of ring segments.

8 . The sealing structure according to claim 1 ,
wherein the plurality of static ring seals are arranged in the axial direction from the turbine blade and include an outermost static ring seal with respect to the turbine blade, wherein each of the plurality of static ring seals has an equal thickness in the axial direction, and wherein the disk circumferential surface is not in contact with only the outermost static ring seal.

9 . The sealing structure according to claim 1 ,
wherein the rim portion of the interstage disk includes an opposing pair of rim portions respectively extending in opposite directions toward each of the adjacent turbine rotor disks, and wherein the blade circumferential surface and the disk circumferential surface are formed on opposite sides of the interstage disk.

10 . The sealing structure according to claim 1 , wherein the blade circumferential surface is formed such that a radially outer portion of the root protrudes in the axial direction.

11 . The sealing structure according to claim 10 , wherein the blade circumferential surface includes a curved surface respectively formed on axially opposite sides of the turbine blade.

12 . The sealing structure according to claim 11 ,
wherein the disk circumferential surface includes a curved surface respectively formed on axially opposite sides of the turbine rotor disk, and wherein the curved surface of the disk circumferential surface corresponds to the curved surface of the blade circumferential surface, such that the curved surfaces of the disk circumferential surface and the blade circumferential surface are mutually engaged with each other.

13 . The sealing structure according to claim 1 ,
wherein the plurality of ring segments of one of the plurality of static ring seals are mounted to be staggered in the axial direction with respect to the plurality of ring segments of an adjacent static ring seal of the plurality of static ring seals, wherein each of the staggered ring segments includes a separation hole and a radially inner edge in which an anti-rotation slot is formed, wherein the rim portion of the interstage disk includes a radially outer edge in which at least two separation slots are formed and configured to expose corresponding separation holes of the staggered ring segments, and wherein the groove is provided with a single anti-rotation pin configured to be simultaneously captured by the anti-rotation slots of the staggered ring segments.

14 . A method of replacing the plurality of static ring seals in a sealing structure for a gas turbine including a plurality of turbine rotor disks and an interstage disk interposed between adjacent turbine rotor disks of the plurality of turbine rotor disks, the method comprising:
firstly separating a turbine blade from a turbine rotor disk of the plurality of turbine rotor disks; secondly separating, after the firstly separating, a ring segment of an outermost static ring seal of the plurality of static ring seals arranged in an axial direction from the turbine blade, the outermost static ring seal disposed farthest from the turbine blade and exposed in a radial direction; and thirdly separating, after the secondly separating, a ring segment of a next-outermost static ring seal of the plurality of static ring seals that is accessible by being exposed in the radial direction.

15 . The method according to claim 14 , further comprising repeating the thirdly separating until all of the plurality of static ring seals are separated.

16 . The method according to claim 14 , wherein the separation of the ring segments of the secondly separating and the thirdly separating is performed by accessing a separation hole formed in each ring segment through a separation slot formed in a radially outer edge of a rim portion of the interstage disk.

17 . The method according to claim 14 , further comprising sequent

Assignees

• Doosan Heavy Ind & Construction Co Ltd

Inventors

• Jung Sung Chul
• Shemyatovskiy Victor

Classifications

• F01D11/006 Primary

  Sealing the gap between rotor blades or blades and rotor · CPC title

• F01D5/3015

  with side plates · CPC title

• F05D2240/55

  Seals · CPC title

• F05D2240/59

  Lamellar seals · CPC title

• F01D5/082

  on the side of the rotor disc · CPC title