Complex distortion generator for testing stability of compressor

Abstract

The invention discloses a complex distortion generator for testing the stability of a compressor. The complex distortion generator comprises a steady-state total pressure distortion generator and a rotational flow distortion generator which are arranged in a compressor casing along the length direction, and is characterized in that the steady-state total pressure distortion generator generates different ranges of steady-state circumferential total pressure distortion through controlling distributed nozzles, and adjusts the air injection speed of the nozzles to change the steady-state total pressure distortion intensity; the rotational flow distortion generator adjusts the rotational flow distortion form through changing the angle of a rotational flow adjustment plate in a switching section of a rotational flow generator, generates three kinds of rotational flow distortion such as same-direction single vortex, opposite-direction single vortex and pair vortex, and can change the rotational flow distortion intensity through adjusting the pressure of an air pump and the openness of an electromagnetic valve. The complex distortion generator is simple in structure and convenient to operate, can generate individual steady-state total pressure distortion or rotational flow distortion at an inlet of the compressor conveniently, can also generate steady-state total pressure and rotational flow combined distortion, facilitates to carry out tests on influences imposed on the stability of the compressor by different forms of complex distortion, and is stable and reliable in operation.

Description

technical field [0001] The invention relates to a test device for evaluating the aerodynamic stability of a compressor, which belongs to the technical field of impeller machinery. Background technique [0002] In order to realize the next-generation high-stealth fighter and stealth unmanned reconnaissance aircraft, it is necessary to adopt a large-offset S-curved inlet. The SR-72 hypersonic unmanned reconnaissance aircraft, which is being developed by Lockheed Martin of the United States, has a one-hour global strike capability, and its inlet is also a large offset S-curve. The large-offset S-bend inlet will produce three situations: steady-state total pressure distortion, swirl flow distortion, and combination distortion of swirl flow and steady-state total pressure at the engine inlet, which will adversely affect engine performance and stability, and even threaten flight. Safety. Therefore, it is necessary to focus on and solve this problem. As the compression part of t...

AI Technical Summary

Problems solved by technology

It may be that considering the complexity of the combined distortion of swirling flow and steady-state total pressure, no special distortion generator has been develope

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