SEALING APPARATUS FOR GAS TURBINE, GAS TURBINE, AND AIRCRAFT ENGINE

• US 20180073378A1
• Filed: 12/22/2015
• Published: 03/15/2018
• 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
• Granted Patent: US 10,641,118 B2
• Time in Patent Office: 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

In a sealing apparatus for a gas turbine, a gas turbine, and an aircraft engine: a first sealing portion provided 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 communicating, via an opening, with a disc cavity between the turbine blade and the turbine vane are provided. Accordingly, improvement in gas turbine efficiency is aimed for, by reduction of entrance of combustion gas into a turbine body being enabled with a small amount of purge air.

Claims

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

a sealing portion that is provided 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 which communicates, via an opening, with a disc cavity provided between the turbine blade and the turbine vane.

2. The sealing apparatus for the gas turbine according to claim 1, wherein the closed space portion is arranged at an inner side of the inner shroud in a radial direction.

3. The sealing apparatus for the gas turbine according to claim 2, wherein the sealing portion has a first sealing portion that is formed by arranging the platform more inward in the radial direction than the inner shroud with a predetermined gap from the inner shroud, and the opening is provided facing the first sealing portion in a turbine axial direction.

4. The sealing apparatus for the gas turbine according to claim 2, wherein the sealing portion has:

a first sealing portion formed by arranging the platform more inward in the radial direction than the inner shroud with a predetermined gap from the inner shroud; and

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

5. The sealing apparatus for the gas turbine according to claim 2, wherein the sealing portion has:

a first sealing portion formed by arranging the platform more inward in the radial direction than the inner shroud with a predetermined gap from the inner shroud; and

a second sealing portion provided more inward in the radial direction than the first sealing portion, wherein the opening is provided between the first sealing portion and the second sealing portion in the radial direction.

6. The sealing apparatus for the gas turbine according to claim 2, wherein the sealing portion has:

a first sealing portion formed by arranging the platform more inward in the radial direction than the inner shroud with a predetermined gap from the inner shroud; and

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

a first opening that is provided facing the first sealing portion in a turbine axial direction; and

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

7. The sealing apparatus for the gas turbine according to claim 6, wherein the closed space portion has:

a first closed space portion that is positioned at an outer side in the radial direction; and

a second closed space portion that is positioned at an inner side in the radial direction, wherein the first opening is provided in the first closed space portion, and the second opening is provided in the second closed space portion.

8. The sealing apparatus for the gas turbine according to claim 1, wherein the closed space portion is arranged at an inner side of the platform in the radial direction.

9. The sealing apparatus for the gas turbine according to claim 8, wherein the sealing portion is formed by extending a sealing fin more inward in the radial direction than the inner shroud with a predetermined gap from the inner shroud, and extending the sealing fin from the platform side, the closed space portion is provided more inward in the radial direction than the sealing fin, and the opening is provided in the sealing fin.

10. The sealing apparatus for the gas turbine according to claim 8, wherein the closed space portion is provided by a front sealing plate and a rear sealing plate in an axial direction at an inner side of the platform in the radial direction, and the opening is provided in the rear sealing plate.

11. The sealing apparatus for the gas turbine according to claim 1, wherein the closed space portion is provided along a circumferential direction.

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

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

the sealing apparatus for the gas turbine according to claim 1 is provided in the turbine.

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

the sealing apparatus for the gas turbine according to claim 1 is provided in the turbine.