Self-adjustment jet type comb tooth vapor sealing structure for turbomachine

Abstract

The invention relates to a self-adjustment jet type comb tooth vapor sealing structure for a turbomachine. A support housing is fixed to the internal surface of an air cylinder; comb type sealing teeth are formed between the support housing and a shroud band; a drainage hole is formed in the support housing; convergent nozzles are formed in the comb type sealing teeth; and the drainage hole communicates with the convergent nozzles, a flowing channel of a leaked fluid is formed, and the fluid is subjected to expansion acceleration in the convergent nozzles. According to the self-adjustment jet type comb tooth vapor sealing structure, the drainage hole and the convergent nozzles are formed in and arranged on the support housing fixed to the internal surface of the air cylinder, so that the flow direction of the fluid at a blade tip clearance inlet is changed, the circumferential flow of the fluid is reduced, the spiral flow effect and the gas bearing effect of the fluid are reduced, and the exciting force of the fluid is inhibited. Through the effects of the convergent nozzles, the velocity direction when the fluid flows out is changed to be consistent with the mainflow direction, hence the mixed flow effect of a blade tip clearance outlet can be reduced, an attack angle of the leaked fluid entering an inferior stationary blade is optimized, the mixed flow and attack angle losses are reduced and the stage internal efficiency is improved.

Description

technical field [0001] The invention relates to a sealing structure applied to turbomachinery, in particular to a sealing structure which can effectively suppress fluid excitation in the blade top clearance of the turbomachinery and reduce mixed flow loss. Background technique [0002] my country is the largest developing country, and rational use of energy and improvement of energy utilization efficiency are of special significance to my country's economic development. At present, it is generally accepted at home and abroad that fluid excitation at the blade tip of turbomachinery is one of the key factors affecting the safe, stable and reliable operation of the unit. On the other hand, the mixed flow loss of fluid at the tip of the turbine blade is one of the main factors affecting the efficiency of the unit, and reducing the mixed flow loss can effectively improve the efficiency of the unit. With the development of units towards large capacity and high parameters and the ...

AI Technical Summary

Problems solved by technology

[0004] The above-mentioned technology is effective for suppressing fluid excitation at the blade tip of a turbomachinery, but its effect largely depends on the size of the blade tip clearance, the smaller the blade tip clearance, the better the effect; More auxiliary equipment, the reliability of unit operation is also reduced

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