Inlet stage blade assemblies for compressors and axial flow compressors incorporating same

Abstract

The invention discloses an inlet-stage blade assembly for a compressor and an axial-flow compressor containing the same. The inlet-stage blade assembly includes an inlet guide vane and a first-stage moving blade, and the inlet guide vane has the largest trailing edge metal angle. The position is the first position, and the relative blade height T at the first position satisfies 0.8≤T≤0.9; The airfoil section at the second position of T has a second chord length, and the first chord length is 3%~10% longer than the second chord length; between the second position and the tip of the first-stage moving blade, the first chord length The forward or backward sweep of the stacking axis of the first-stage rotor blade shall not exceed 1% of the absolute blade height of the first-stage rotor blade. Adopting the above structure can improve the stall margin of the blade tip of the first-stage moving blade, and make the radial deformation of the leading edge and the trailing edge of the first-stage moving blade more coordinated when the first-stage moving blade changes from a static state to a running state.

Description

technical field [0001] The invention relates to an inlet-stage blade assembly for a compressor and an axial compressor comprising the same. Background technique [0002] Inlet guide vanes are a common component in compressor components for aero-engines, gas turbines, and ground-based axial flow compressors. The inlet guide vane is the first row of stator blades at the compressor inlet. Its function is usually to deflect the axial flow, so that it has a certain tangential component velocity, and the direction of the tangential component velocity is the same as the rotor rotation direction. In this way, the incoming Mach number of the first-stage moving blades (rotor blades) will be lower than that without guide vanes, so the loss is smaller and the efficiency is higher. In addition, the inlet guide vane is usually designed to be adjustable, and its installation angle will be changed as the operating conditions of the compressor change, so as to keep the first-stage rotor bla...

AI Technical Summary

Problems solved by technology

[0006] The technical problem to be solved by the present invention is how to improve the working capacity of the blade tip of the first-stage moving blade of the compressor, improve its stall margin, and at the same time avoid the occurrence of strong radial deformation imbalance between the leading edge and the trailing edge Defects, providing an inlet-stage blade assembly for a compressor and an axial flow compressor including the same

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