Turbine test bed of aero-engine under high altitude and low Reynolds number, simulation method and application

Abstract

The invention provides a simulation method and application of an aero-engine turbine test system under a high-altitude low Reynolds number. The method comprises the steps that input conditions such as performance design points and limit boundaries of an aero-engine air inlet system are obtained through arrangement, and design points and limit boundaries of an exhaust system under the high-altitude low Reynolds number working environment are obtained through analysis; obtaining injection coefficients of active flow and passive flow of the ejector according to the design principle of the ejector; preliminary design parameters of the exhaust system are obtained through numerical simulation; the preliminary design parameters are repeatedly optimized according to limiting conditions, and finally the exhaust contour is determined; due to the fact that an air inlet system and the pressure and flow ranges required by active flow and passive flow of an ejector are different, a pressure reducing valve needs to be selected based on the design standard of a pressure reducing valve for compressed air JISB3372-1982, and finally the opening degree of the pressure reducing valve and the longest test time under the working condition are determined. According to the turbine test system simulation method provided by the invention, rapid design and shaping of the test system can be realized, so that the test process is simpler, more convenient and more accurate.

Description

technical field [0001] The invention relates to the field of aero-engine testing, and discloses an aero-engine turbine test bed at high altitude and low Reynolds number, a simulation method and an application. Background technique [0002] Aeroengines work at high altitudes most of the time. The pressure P at high altitudes is about 28% of atmospheric pressure at an altitude of 10,000 meters, which leads to a decrease in air density ρ. According to the formula of Reynolds number (where U represents the motion velocity, μ represents the dynamic viscosity, and l represents the characteristic size), it can be seen that when flying at high altitude, it is under the condition of low Reynolds number relative to the ground, so when testing on the ground, in order to meet the real high-altitude environment and Under various extreme conditions, it is necessary to ensure a drop pressure ratio similar to the real situation, as well as a relatively wide drop pressure ratio range at low...

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Problems solved by technology

[0005] The purpose of the present invention is to provide a simulation method and application of an aero-engine turbine test system at high altitude and low Reynold

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