When the cloud is at the end, the surge margin is running out. In addition, under various distortion indexes, at 5 o'clock, the surge margin loss is the smallest, and the remaining speed is relatively larger, which indicates that the low-pressure compressor has strong anti-distortion ability at the design speed. Surge margins under various imported distorted flow fields at the time of Wuyi The upper and lower boundary upper bounds of the aircraft design are the distortion characteristics of various states obtained by the wind tunnel test of the inlet port model and the inlet distortion of a low pressure compressor. The test results were determined after compatibility analysis.

Since the low-pressure compressor inlet distortion test only simulates the steady-state distortion force and does not simulate the average turbulence degree, the influence of the average turbulence degree on the surge margin of the low-pressure compressor should also be considered when determining the upper boundary. The results of the inlet tunnel test show that under normal conditions, the average turbulence of the total pressure pulsation at the inlet of the inlet is about 01. For this reason, the average surge margin of the low pressure compressor is set aside. Turbulence. The margin to be subtracted from the total surge margin is taken into account in terms of manufacturing tolerances and the effects of long-term aging on the compressor surge margin.

In this way, under the stable operating state of the engine, a total of the low pressure compressor surge margin is required, and the remaining surge margin can be used to resist the steady flow field distortion of the inlet port. At a small angle of attack, the normal regulation of the inlet is far from the upper and lower boundaries, and there is sufficient margin. However, when the angle of attack of the inlet is the angle of attack of the aircraft, the number of Mach above is adjusted. The law is relatively close to the lower boundary, and the inlet passage is prone to occur.

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