CN-116608011-B - Gas seal assembly structure of turbine blade and gas turbine

Abstract

The invention relates to a gas seal assembly structure of turbine blades and a gas turbine. The turbine blade comprises a turbine blade body comprising a blade profile, a platform and a blade root, a turbine rotor disk having the blade root mounted thereon, an air seal plate mounted between the platform and one side of the turbine rotor disk for sealing cooling channels formed in the blade root and the platform, and a plug inserted through the turbine rotor disk for supporting the air seal plate and fixing it to the turbine rotor disk, wherein the turbine rotor disk has a mounting groove for inserting the radially inner end of the air seal plate, and the air seal plate has an axial shoulder supported by a step portion of the mounting groove in the radial direction.

Inventors

• JIANG ZHOUHENG
• Yuri Goroshchak
• Alexis Corepin

Assignees

• 斗山恒能有限公司

Dates

Publication Date

20260508

Application Date

20230213

Priority Date

20220215

Claims (17)

1. 1. A gas seal assembly structure of turbine blade is characterized in that, Comprising the following steps: a turbine blade comprising a blade profile portion, a platform portion, and a blade root portion; A turbine rotor disk having a root portion of the turbine blade mounted thereon; A gas seal plate mounted between the platform and a side of the turbine rotor disk for sealing cooling channels formed in the blade root and the platform, A bolt inserted through the turbine rotor disk to support the air seal plate and fix the air seal plate to the turbine rotor disk; The turbine rotor disk has a mounting groove into which the radially inner end portion of the air seal plate is inserted, The air seal plate is provided with a shaft shoulder supported by the step part of the mounting groove in the radial direction, An inclined surface is formed on the shoulder portion, the inclined surface is formed so as to be smaller in thickness toward the inner end portion in the radial direction, the lower end portion has a thickness smaller than the thickness of the body plate on the upper surface of the shoulder portion, The bevel gear further comprises a chamfer part which is formed at the other side corner of the shaft shoulder part, and an outer side corner which meets the inclined surface on the upper surface of the shaft shoulder part is formed at an angle of 40-50 degrees.
2. 2. A gas seal assembly structure for a turbine blade according to claim 1, The turbine rotor disk includes: a mounting rib extending in a radial direction on one side in an axial direction and forming the mounting groove with the turbine rotor disk; and a through hole formed through the mounting rib and into which the plug is inserted.
3. 3. A gas seal assembly structure for a turbine blade according to claim 2, wherein The air seal plate includes a pin groove formed at a radially inner end position of the through hole corresponding to the mounting rib.
4. 4. A gas seal assembly structure for a turbine blade according to claim 3, The pin grooves are formed in a semicircular shape.
5. 5. A gas seal assembly structure for a turbine blade according to claim 2, The gas seal plate further comprises: An arc groove is formed at an inner corner between the shaft shoulder and the body plate in order to prevent stress concentration.
6. 6. A gas seal assembly structure for a turbine blade according to claim 5, The turbine rotor disk includes: an arc groove formed at a recessed corner of the installation groove step portion; And the chamfer part is formed at the protruding corner part of the mounting groove step part.
7. 7. A gas seal assembly structure for a turbine blade according to claim 1, The bolt includes: a body portion having a cylindrical shape; the head part is integrally formed on one side of the body part in a manner of having an outer diameter larger than that of the body part.
8. 8. A gas seal assembly structure for a turbine blade according to claim 3, And a holder for holding the plug together with the plug by inserting the plug into the through hole of the mounting rib so as to prevent the plug from falling off.
9. 9. A gas seal assembly structure for a turbine blade according to claim 8, The bolt includes: a body portion having a cylindrical shape; a head part integrally formed on one side of the body part in a manner of having an outer diameter larger than that of the body part; and a cutting part formed at the lower parts of the body part and the head part for tightly attaching the fixer.
10. 10. A gas seal assembly structure for a turbine blade according to claim 9, The plug further includes a groove portion continuing from the cutting portion and formed in a stepped shape on the head portion to allow the holder to be abutted.
11. 11. A gas seal assembly structure for a turbine blade according to claim 10, A through hole of the turbine rotor disk is provided with a head receiving hole which is formed at one side and has an inner diameter larger than that of the through hole to receive the head of the bolt.
12. 12. A gas seal assembly structure for a turbine blade according to claim 11, The fixer is formed by bending a rectangular plate and comprises: a horizontal portion which is plastically deformed and bent; a level difference part which is connected with the horizontal part in a level difference way; and a vertical portion vertically bent at the step portion.
13. 13. A gas seal assembly structure for a turbine blade according to claim 12, The fastener is inserted into the through hole of the mounting rib, and after the plug is inserted, a bent portion formed by bending a part of the horizontal portion supports the head of the plug.
14. 14. A gas seal assembly structure for a turbine blade according to claim 13, The bent portion is arranged inside the head accommodating hole after being bent.
15. 15. A gas turbine is characterized in that, Comprising the following steps: the compressor sucks external air and compresses the air; A combustion chamber for mixing fuel with air compressed by the compressor and burning the mixed fuel, A turbine rotated by the gas discharged from the combustion chamber; the turbine comprises: a turbine blade comprising a blade profile portion, a platform portion, and a blade root portion; A turbine rotor disk having a root portion of the turbine blade mounted thereon; A gas seal plate mounted between the platform and a side of the turbine rotor disk for sealing cooling channels formed in the blade root and the platform, A bolt inserted through the turbine rotor disk to support the air seal plate and fix the air seal plate to the turbine rotor disk; The turbine rotor disk has a mounting groove into which the radially inner end portion of the air seal plate is inserted, The air seal plate is provided with a shaft shoulder supported by the step part of the mounting groove in the radial direction, An inclined surface is formed on the shoulder portion, the inclined surface is formed so as to be smaller in thickness toward the inner end portion in the radial direction, the lower end portion has a thickness smaller than the thickness of the body plate on the upper surface of the shoulder portion, The bevel gear further comprises a chamfer part which is formed at the other side corner of the shaft shoulder part, and an outer side corner which meets the inclined surface on the upper surface of the shaft shoulder part is formed at an angle of 40-50 degrees.
16. 16. The gas turbine as claimed in claim 15, wherein, The turbine rotor disk comprises a mounting rib, a through hole, a bolt and a bolt, wherein the mounting rib extends in the radial direction on one side of the axial direction and forms a mounting groove with the turbine rotor disk; The air seal plate includes a pin groove formed at a radially inner end position of the through hole corresponding to the mounting rib.
17. 17. The gas turbine as claimed in claim 16, wherein, The gas seal plate further includes an arc groove formed at an inner corner between the shaft shoulder portion and the body plate in order to prevent stress concentration; the turbine rotor disk further comprises an arc-shaped groove formed at a concave corner of the mounting groove step portion, and a chamfer portion formed at a convex corner of the mounting groove step portion.

Description

Gas seal assembly structure of turbine blade and gas turbine Technical Field The invention discloses a gas seal assembly structure of a turbine blade and a gas turbine comprising the same. Background The turbine is a mechanical device for obtaining a rotational force by using a flow of a compressible fluid such as steam and gas with an impact force or a reverse force, and mainly includes a steam turbine using steam, a gas turbine using high-temperature gas, and the like. The gas turbine mainly comprises a gas compressor, a combustion chamber and a turbine. The compressor is provided with an air inlet for introducing air, and a plurality of compressor stator blades and compressor blades are arranged in the compressor shell in a crossed mode. The combustion chamber supplies fuel to the compressed air compressed by the compressor and is ignited by the combustion device to generate high-temperature and high-pressure fuel gas. The turbine has a plurality of turbine stator blades and turbine blades disposed in a turbine housing in a crossing manner. Further, a rotor is disposed through the center of the compressor, the combustion chamber, the turbine, and the exhaust chamber. Both ends of the rotor are supported by bearings to rotate. Further, a plurality of disks are fixed to the rotor to connect the respective blades, and a drive shaft of a generator or the like is connected to an end portion on the exhaust chamber side. The gas turbine has no reciprocating mechanism such as a piston of a four-stroke internal combustion engine, does not have a piston-cylinder mutual friction portion and thus causes little consumption of lubricating oil, thereby greatly reducing the amplitude of one of reciprocating motion characteristics and further enabling high-speed motion. The operation of the gas turbine is briefly described below. The air compressed by the compressor and the fuel are mixed and combusted to generate high-temperature fuel gas, and the generated fuel gas is injected to the turbine side. The injected fuel gas generates a rotational force when passing through the turbine stator blades and turbine vanes, thereby driving the rotor to rotate. A cool air flow path for supplying cooling air from the turbine rotor disk to the turbine blades may be formed inside the root portion of the turbine blades. In order to form and seal the cool air flow path, the blade root of the turbine blade and the two axial side surfaces of the rotor disk can be closely combined with air sealing plates. The prior art uses bolts or the like to secure the gas seal plate to the root of the turbine blade. However, the head of the bolt protrudes from the air seal plate and causes windage loss due to friction with the gas at high speed rotation (windage loss). Further, the centrifugal force generated by the weight of the bolts after being assembled to the blade root is large, and may cause an increase in stress at the blade root. Prior art literature Patent literature Published patent application No. 10-2020-0020415 Disclosure of Invention Technical problem The invention aims to provide an air seal assembly structure of a turbine blade and a gas turbine comprising the same, wherein the lower end part of an air seal plate is fixed on a turbine rotor disk, a part of a fixing piece protruding out of the air seal plate and the rotor disk is cleaned, so that windage loss caused by gas friction is reduced, the load applied to the root part of the blade is greatly reduced, the structural stability of the blade is improved, the stress concentration of the turbine rotor disk and the air seal plate is greatly reduced, and the assembly is easy. Technical proposal for solving the technical problems The air seal assembly structure of the turbine blade comprises a turbine blade, a turbine rotor disk, an air seal plate, a bolt and a mounting groove, wherein the turbine blade comprises a blade profile part, a platform part and a blade root part, the blade root part of the turbine blade is mounted on the turbine blade, the air seal plate is mounted between the platform part and one side part of the turbine rotor disk and seals cooling flow paths formed in the blade root part and the inside of the platform part, the bolt is inserted through the air seal plate to support the turbine rotor disk and fix the air seal plate to the turbine rotor disk, the turbine rotor disk is provided with the mounting groove for inserting the inner end part of the air seal plate in the radial direction, and the air seal plate is provided with a shaft shoulder supported by the step part of the mounting groove in the radial direction. The turbine rotor disk may include a mounting rib extending in a radial direction on one side in an axial direction to form a mounting groove with the turbine rotor disk, and a through hole penetrating the mounting rib and allowing insertion of a plug. The air sealing plate may include pin grooves formed at radially inner end positions of the through ho