为了研究某跨音速压气机的流动机理与稳定工作的范围，采用三维雷诺平均Navier-Stokes方程组和Spalart-Allmaras湍流模型进行了定常数值模拟。分别计算了90%、100%和110%设计转速下的全工况，同时着重分析了100%设计转速下的近堵塞点与近失速点和其他转速下的最高效率点。结果表明：设计工况点的等熵效率85.35%、压比1.387、流量4.861 kg/s，与设计指标相比，等熵效率和流量偏差2%以内以及压比偏差5%左右均在允许范围内，说明该计算方法验证压气机的内部流动特性是可靠的；叶片吸力面的低能流体在叶片尾缘汇合形成尾迹、激波造成叶片边界层分离和激波与叶顶间隙的泄露流相互作用形成的二次流是引发流动失稳的主要因素；随着转速的提高，进口马赫数增加，压气机在90%、100%和110%设计转速下最高效率点的等熵效率分别为88.57%、86.76%和82.66%。

In order to study the flow mechanism and stable working range of a transonic compressor,the threedimensional Reynolds average NavierStokes equations and the SpalartAllmaras turbulence model were used to simulate steady state conditions.The full operating conditions at 90%,100% and 110% of the design speed were calculated separately,and the nearblocking point and the nearstall point and the highest efficiency point at other speeds under 100% design speed were also analyzed.The calculation results and analysis show that the isentropic efficiency of the design condition point is 85.35%,the pressure ratio is 1.387,and the flow rate is 4.861 kg/s.Compared with the design index,the isentropic efficiency and the flow deviation are within 2% and the pressure ratio deviation is about 5%.Within the allowable range,the calculation method verifies that the internal flow characteristics of the compressor are reliable; the lowenergy fluid of the suction side of the blade merges to form a wake at the trailing edge of the blade,the shock wave causes the boundary layer separation of the bladeThe secondary flow formed by the flow interaction between the leakage of the shock wave and the tip clearance is the main factor that causes the flow instability; With the increase of rotational speed and the inlet Mach number,the maximum isentropic efficiency of the compressor at 90%,100% and 110% of the designed rotational speed is 88.57%,86.76% and 82.66%,respectively.

V235

国家自然科学基金（21878102）