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Turbine disc cavity sealing structure of gas turbine

A technology of sealing structure and gas turbine, which is applied in the direction of gas turbine devices, mechanical equipment, engine components, etc. It can solve the problems of easy wear, poor sealing, complex structure, etc., and achieve the effect of simple sealing structure, reduced damage, and simplified structure

Active Publication Date: 2021-04-06
HANGZHOU TURBINE POWER GRP
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Aiming at various problems such as complex structure, easy wear, and poor sealing performance of the gas turbine disk cavity sealing structure in the prior art, it is necessary to find a gas turbine disk cavity sealing structure that makes the structure simple and easy to operate while ensuring the sealing performance , while achieving the purpose of avoiding structural wear and reducing costs

Method used

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  • Turbine disc cavity sealing structure of gas turbine
  • Turbine disc cavity sealing structure of gas turbine
  • Turbine disc cavity sealing structure of gas turbine

Examples

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Embodiment 1

[0034] figure 1 It is a schematic diagram of a sealing structure in the prior art, including a vane 1, an interstage sealing ring 3, a honeycomb seal 6, a sealing tooth 12, a wheel seal extending wing 13, a sealing plate 8, a wheel 9, a single tooth seal 10 and The extended end 14 of the wheel disc; wherein, the single-tooth seal is a single-tooth-shaped sealing fitting.

[0035] The honeycomb seal 6 is located on the lower surface of the interstage sealing ring 3 ; the sealing teeth are located on the upper surface of the disc seal extension wing 13 . In addition, the wheel disc 9 extends outward to form a wheel disc sealing extension end 13 . The interstage sealing ring 3 , the sealing plate 8 and the stationary vane 1 cooperate to form the interstage sealing ring air supply cavity 2 . The single-tooth seal 10 is located on the interstage sealing ring 3, and cooperates with the extended end 14 of the wheel disc to realize sealing.

[0036] The disc 9, the sealing plate 8,...

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Abstract

The invention provides a turbine disc cavity sealing structure of a gas turbine, and relates to the technical field of gas turbines. The sealing structure comprises a stationary blade (1), an interstage sealing ring (3), a honeycomb seal (6), a wheel disc (9), a wheel disc sealing extending wing (13), a stationary blade inner shroud ring (24), a stationary blade inner shroud ring extending end (15), a vent hole (16), a spring component (17), a T-shaped groove (18), an axial limiting bolt (20) and an axial limiting groove (21); and the vent hole (16) is located inside the stationary blade inner shroud ring extending end (15) and penetrates through the stationary blade inner shroud ring extending end (15). The sealing structure is simple and easy to operate, abrasions of the honeycomb seal can be avoided, then the cost is reduced, meanwhile, the sealing air circulation path is simplified, and the operation safety is improved.

Description

technical field [0001] The invention relates to the technical field of gas turbines, in particular to a gas turbine disk cavity sealing 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 method is to introduce cooling air to cool the wheel disc. The cooling air is generally supplied from the air supply cavity at the outer periphery of the stator vane. After the gas flows through the inner channel of the stator vane, it enters the inner shroud of the stator vane and the interstage seal. The air supply chamber composed of the ring, finally cools the upstream and downstream discs respectively after passing through the upper and downstream sealing teeth, and finally, the gas after cooling the discs will flow into the main flow through the dynami...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/28F01D9/02F01D11/00
CPCF02C7/28F01D9/02F01D11/00F01D11/003
Inventor 蓝吉兵张发生张伟赵旭洋李柳明赵鸿琛隋永枫辛小鹏
Owner HANGZHOU TURBINE POWER GRP
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