Sealing apparatus for gas turbine, gas turbine, and aircraft engine

• US 10,641,118 B2
• Filed: 12/22/2015
• Issued: 05/05/2020
• Est. Priority Date: 03/06/2015
• Status: Active Grant

• Current Assignee: Mitsubishi Heavy Industries, Ltd.
• Original Assignee: Mitsubishi Heavy Industries, Ltd.
• Inventors: Ikeda, Kazufumi, Kitagawa, Hitoshi, Araki, Masato, Okabe, Yoshiyuki
• Primary Examiner(s): Sutherland, Steven M
• Assistant Examiner(s): Chabreyrie, Rodolphe Andre
• Application Number:
  US15/554,572
• Publication Number:
  US 20180073378A1
• Time in Patent Office: 1,596 Days
• CPC Class Codes: F01D 11/001 for sealing space between stator blade and rotor
• CPC Class Codes: F01D 25/04 Antivibration arrangements
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: F05D 2240/35 Combustors or associated equipment
• CPC Class Codes: F16J 15/064 the packing combining the sealing function with other functions
• CPC Class Codes: F16J 15/08 with exclusively metal packing
• CPC Class Codes: F16J 15/447 Labyrinth packings
• CPC Class Codes: F16J 15/54 Other sealings for rotating shafts

Abstract

A sealing apparatus includes a sealing portion configured to be positioned between a platform of a turbine blade and an inner shroud of a turbine vane of a turbine, and an acoustic damper having a closed space portion which is configured to communicate, via an opening, with a disc cavity configured to be positioned between the turbine blade and the turbine vane.

Claims

1. A sealing apparatus for a gas turbine, the sealing apparatus comprising:

a sealing portion positioned between a platform of a turbine blade and an inner shroud of a turbine vane; and

an acoustic damper that has a closed space portion to communicate, via an opening, with a disc cavity positioned between the turbine blade and the to vane, wherein;

the closed space portion is at least partially defined by a buffer plate;

the buffer plate has

a plate main body at least partially extending in a radial direction and a partition portion at least partially extending parallel to the plate main body;

the plate main body defines an upstream side of the closed space portion;

the partition portion defines a downstream side of the closed space portion;

the plate main body contacts a sealing ring retaining ring of the inner shroud of the turbine vane; and

the partition portion contacts a projection protruding inward in the radial direction from an inner surface of the inner shroud of the turbine vane.

2. The sealing apparatus according to claim 1, wherein:

the sealing portion has a first sealing portion defined by the platform of the turbine blade being more inward in the radial direction than the inner shroud of the turbine vane with a gap from the inner shroud of the turbine vane; and

the opening faces the first sealing portion in a turbine axial direction.

3. The sealing apparatus according to claim 1, wherein the sealing portion has:

a first sealing portion defined by the platform of the turbine blade being more inward in the radial direction than the inner shroud of the turbine vane with a gap from the inner shroud of the turbine vane; and

a second sealing portion which is more inward in the radial direction than the first sealing portion, and wherein the opening is defined at an outer side of the second sealing portion in the radial direction.

4. The sealing apparatus according to claim 1, wherein the sealing portion has:

a first sealing portion defined by the platform of the turbine blade being more inward in the radial direction than the inner shroud of the turbine vane with a gap from the inner shroud of the turbine vane and a second sealing portion which is more inward in the radial direction than the first sealing portion, and wherein the opening is defined between the first sealing portion and the second sealing portion in the radial direction.

5. The sealing apparatus according to claim 1, wherein the sealing portion has:

a first sealing portion defined by the platform of the turbine blade being more inward in the radial direction than the inner shroud of the turbine vane with a gap from the inner shroud of the turbine vane; and

a second sealing portion which is more inward in the radial direction than the first sealing portion, and wherein the opening has;

a first opening that faces the first sealing portion in a turbine axial direction; and

a second opening defined at an outer side of the second sealing portion in the radial direction.

6. The sealing apparatus according to claim 5, wherein the closed space portion has:

a first closed space portion; and

a second closed space portion,

wherein;

the second closed space portion is more inward in the radial direction than the first closed space portion;

the first opening is defined in the first closed space portion; and

the second opening is defined in the second closed space portion.

10. The sealing apparatus according to claim 1, wherein the closed space portion is defined along a circumferential direction.

11. The sealing apparatus for the gas turbine according to claim 10, wherein the closed space portion is plurally divided in the circumferential direction by a partition plate.

12. A gas turbine having a compressor, a combustor, and a turbine, wherein

the sealing apparatus according to claim 1 is in the turbine.

13. An aircraft engine having a compressor, a combustor, and a turbine, wherein

the sealing apparatus according to claim 1 is in the turbine.

7. A sealing apparatus for a gas turbine, the sealing apparatus comprising:

a sealing portion positioned between a platform of a turbine blade and an inner shroud of a turbine vane; and

an acoustic damper that has a closed space portion to communicate, via an opening, with a disc cavity positioned between the turbine blade and the turbine vane, wherein;

the closed space portion is positioned at an inner side of the platform of the turbine blade in a radial direction, the closed space portion is defined by a sealing plate, a buffer plate, and a sealing fin;

the sealing fin extends from the sealing plate;

a first end of the buffer plate adjoins the sealing plate;

a second end of the buffer plate adjoins the sealing fin; and

the opening is defined in the sealing fin.

8. The sealing apparatus according to claim 7, wherein the sealing fin extends more inward in the radial direction than the inner shroud of the turbine vane with a gap from the inner shroud of the turbine vane, the sealing fin extends from a platform side, and the closed space portion is more inward in the radial direction than the sealing fin.

9. A sealing apparatus for a gas turbine, the sealing apparatus comprising:

a sealing portion positioned between a platform of a turbine blade and an inner shroud of a turbine vane; and

an acoustic damper that has a closed space portion to communicate, via an opening, with a disc cavity positioned between the turbine blade and the turbine vane, wherein;

the closed space portion is at least partially defined by a front sealing plate and a rear sealing plate in an axial direction and is positioned at an inner side of the platform of the turbine blade in a radial direction;

the rear sealing plate extends in the radial direction,

a first end of the rear sealing plate adjoins the platform of the turbine blade and a second end of the rear sealing plate is mechanically coupled to a turbine disc;

a sealing fin extends from the rear sealing plate downstream in the axial direction;

and the opening is defined in the rear sealing plate and is outward in the radial direction from the sealing fin.