端壁合成射流激励参数变化对跨声速轴流压气机性能的影响

Effects of the Endwall Synthetic Jet Excitation Parameters on Performance of Transonic Axial Flow Compressor

为了提升高负荷轴流压气机的气动性能,提出了一种在端壁上施加合成射流的主动流动控制方法。以跨声速轴流压气机NASA Rotor35为研究对象,在固定端壁激励于叶顶堵塞核心位置的基础上,数值模拟了3个激励频率和3个射流峰值速度对该压气机气动性能的影响,获得了端壁合成射流激励参数的影响规律。计算结果表明:激励频率对压气机的近失速流量影响不大,但对总压比和等熵效率有较大影响,并且存在一个激励频率的阈值,只有当激励频率大于该阈值时,才能使得总压比和等熵效率高于原型压气机。射流峰值速度对压气机性能的影响不如激励频率,在超过激励频率阈值的端壁合成射流作用下,即使射流峰值速度较小,压气机也能获得比原型压气机更高的流量裕度、总压比和等熵效率,而且随着射流峰值速度的增大,压气机的性能还可以进一步提高。

To improve the aerodynamic performance of high-load axial compressor,an active flow control method with synthetic jet applied on the endwall was proposed.A transonic axial flow compressor NASA Rotor35 was taken as the research object.On the basis of fixed endwall excitation at the core of blade tip blockage,the influences of three excitation frequencies and three jet peak velocities on the aerodynamic performance of the compressor were numerically simulated,and the influencing rules of the endwall synthetic jet excitation parameters were obtained.The results show that the excitation frequency has little influence on the near stall flow of the compressor,but has great influence on the total pressure ratio and isentropic efficiency.It is also found that there is a threshold of excitation frequency,and only when the excitation frequency is greater than the threshold,can the total pressure ratio and isentropic efficiency be higher than those of the prototype compressor.The effect of jet peak velocity on the performance of compressor is inferior to the excitation frequency.Under the action of the endwall synthetic jet exceeding the excitation frequency threshold,the compressor can obtain higher flow margin,total pressure ratio and isentropic efficiency than the prototype compressor even if the peak velocity of the jet is small,and the performance of the compressor can be further improved with the increase of the jet peak velocity.