畸变强度对压气机气动性能影响研究

Study on the Influence of Distortion Intensity on the Aerodynamic Performance of Compressor

以Stage 35为研究对象,采用商业软件ANSYS CFX开展进气总压畸变对压气机性能影响的数值模拟研究。在70%叶高处安装插板式畸变模拟器,改变插板位置,得到3种不同畸变度的进气总压畸变。计算结果表明:当插板与动叶的距离分别为42,32和22 cm时,压气机压比分别下降了3.45%、3.66%和4.51%;效率则依次降低了5.10%、5.12%和6.95%;稳定裕度降低了25%、26.11%和26.62%。总压畸变会显著影响压气机内部流动,改变动叶进气角,导致动叶尾缘分离区域增大,尾迹损失增大;进口总压畸变度越大,压气机总压比下降越多,整机绝热效率越低,稳定工作裕度越小。

Taking Stage35 as the research object, the commercial software ANSYS CFX was used to numerically simulate the influence of the total pressure distortion of air intake on the aerodynamic performance of the compressor.In the calculation, a plug-in plate distortion simulator was installed at 70% of the blade height, and the position of the plug-in plate was changed to obtain three kinds of total pressure distortions of air intake with different distortion degrees.The calculation results show that when the distance is 42 cm, 32 cm and 22 cm between the plug-in plate and rotor blade, the pressure ratios of compressor were decreased by 3.45%,3.66% and 4.51% respectively;the efficiencies were decreased by 5.10%,5.12% and 6.95% respectively;the stability margins were reduced by 25%,26.11% and 26.62%.This means total pressure distortion will significantly affect the internal flow of the compressor, the inlet flow angle of rotor blade changes, leading to an increase in the separation area of the trailing edge of the rotor blade and an increase in wake loss.The greater the degree of inlet total pressure distortion is, the more the total pressure ratio of the compressor decreases, the lower the adiabatic efficiency of the whole machine is, and the smaller the margin for stable operation is.