Structure for improving stability of stationary blade of gas turbine

Abstract

The invention relates to a structure for improving the stability of a stationary blade of a gas turbine. The structure comprises the stationary blade and a rotating inner cylindrical surface, the stationary blade is a guide blade or a diffuser blade or a swirler blade, and the inner ring fluid of the stationary blade is in direct contact with the rotating inner cylindrical surface, so that the fluid vortex in the boundary layer of the inner ring of the stationary blade is subjected to suction, the vortices are enhanced, the volume is reduced, the influence of the vortices on downstream can bereduced, and fluid enters an axial-flow type gas compressor or a blade pump or the gas turbine through the guide blades and then leaves through an outlet diffuser.

Description

technical field [0001] The invention relates to an axial flow compressor, a vane pump and a gas turbine, in particular to a premix burner of the gas turbine. Background technique [0002] In axial flow compressors, vane pumps, gas turbines and other equipment, the interaction between the fluid in the vane and the rotating inner cylinder or inner cone has not yet been determined, nor has it become a standard design. The domestic 4000 horsepower Long March 2 gas turbine locomotive was originally designed to install the inner shroud of the compressor vane. The surge phenomenon was basically eliminated after the inner shroud was removed during the trial production process. At present, the MHI Mitsubishi Heavy Industries 400MW gas turbine M701F intermediate compressor stator vane with a large installed capacity The inner ring of the diffuser is installed with an inner shroud. Such as figure 1 , 2, 3 show that in the traditional structure, the fluid diffuses and flows in the inn...

AI Technical Summary

Problems solved by technology

like figure 1 , 2, 3 show that in the traditional structure, the fluid diffuses and flows in the inner ring of the guide vane 5 or the outlet diffuser 9, and the separated vortices in the boundary layer of the inner ring are affected by the annular (circumferential) pressure gradient, tangential ( Radial) Viscous force continuous "rubbing" movement causes the strength and volume of the vortex to increase, and a channel vortex across the slot of the stator blade may be formed in the inner ring of the closed stator vane, resulting in enhanced backflow after the vane

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