Gas turbine interstage sealing ring structure

A technology of interstage seals and gas turbines, which is applied in the direction of gas turbine devices, mechanical equipment, engine components, etc., can solve the problems of unit performance degradation, circumferential speed difference, air flow temperature rise, etc., to improve unit efficiency, reduce speed difference, The effect of dosage reduction

Active Publication Date: 2020-11-20
浙江燃创透平机械有限公司
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  • Application Information

AI Technical Summary

Problems solved by technology

[0008] 1. Due to the circumferential speed difference between the airflow and the rotating surface, the frictional resistance will increase the temperature of the airflow, resulting in the need to consume more cooling air when the cooling requirements of the wheel are the same, and the increase in the amount of cooling air will degrades unit performance

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  • Gas turbine interstage sealing ring structure
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  • Gas turbine interstage sealing ring structure

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Embodiment 1

[0042] The present invention provides a gas turbine interstage seal ring structure, including an interstage seal ring 9:

[0043] The inner wall of the radial air supply hole 6 of the interstage seal ring 9 has a tangential angle structure, and the tangential angle β is greater than 0° and less than or equal to 60°, so that the airflow has a pre-rotation after passing through the radial air supply hole 6 . The larger the tangential angle, the more pre-rotation of the airflow, the greater the circumferential velocity of the resulting airflow, the smaller the relative velocity between the airflow and the rotor, and the smaller the temperature rise of the airflow due to frictional resistance. The amount of air-conditioning is also small.

[0044] The radial air supply hole 6 of the interstage seal ring 9 can also be provided with a detachable part 15 with a tangential angle on the inner wall to realize pre-rotation after the air flow passes through the radial air supply hole 6. T...

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Abstract

The invention provides a gas turbine interstage sealing ring structure, and belongs to the field of mechanical structure design. According to the gas turbine interstage sealing ring structure, the airinlet angle is increased in radial air supply holes in an interstage sealing ring. According to the gas turbine interstage sealing ring structure, a tangential angle structure is arranged in the radial hole of the interstage sealing ring, and the pre-rotation of airflow passing through the radial hole is increased, so that the circumferential speed difference between the airflow and the rotor surface is reduced, the temperature rise caused by the frictional resistance after the air flows through the rotor surface is weakened, and the use amount of cooling air is reduced under the same wheel disc cooling requirement. According to the gas turbine interstage sealing ring structure, on the premise that it is guaranteed that an original flow path structure is basically unchanged, optimizationis achieved, part machining is easy, installation is convenient, and the maintenance cost is low.

Description

technical field [0001] The invention relates to the field of mechanical structure design, in particular to a gas turbine interstage sealing ring structure. Background technique [0002] In a gas turbine, the working temperature of the rotor disk is relatively high. If the temperature is not controlled, the excessively high temperature will lead to a decrease in strength, which will affect the safe operation of the unit. The usual way to cool down the rotor disk is to introduce cooling air. The cooling air is generally supplied from the air supply chamber at the outer belt of the stator blade. After the gas flows through the inner passage of the stator blade, it enters the inner shroud of the stator blade and the interstage seal ring. The formed air supply chamber finally cools the upstream wheel disc and the downstream wheel disc respectively after the upstream seal and the downstream seal. Finally, the gas after cooling the wheel disc will flow into the main flow through th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/28F02C7/18F01D11/00F01D25/12
CPCF01D11/003F01D25/12F02C7/18F02C7/28
Inventor 张发生许运宾张宏伟戴斌臧鹏张伟周灵敏隋永枫蓝吉兵赵鸿琛
Owner 浙江燃创透平机械有限公司
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