垂直于叶片弦线方向喷气对转子稳定性的影响研究

以NASA Rotor37为研究对象,采用数值模拟的方法进行叶顶喷气对转子稳定性的影响研究。研究表明,在叶顶垂直于叶片弦线方向喷气可以达到扩稳效果,其扩稳机理在于通过喷口喷射出的高速射流把叶顶泄漏流吹向转子吸力面,减弱了叶顶泄漏流对主流的影响,使得转子叶顶堵塞区域减小,改善了叶顶区域的流通状况,从而得到扩稳效果。在喷气流量对转子稳定性的研究中,喷气流量越大,对增强稳定性越有利。在所选取的1%,1.5%和2%三种喷气流量水平下,2%的喷气流量可以使转子的流量裕度提高4.24%,综合裕度改进量提高5.16%。此外,不同喷气流量对转子的流场影响不同,随着喷气流量的增大,除了可以降低叶顶前缘负荷外,还可以通过将激波位置推向下游,从而有利于减弱流动分离,对转子稳定性的提升更为有利。

Effects of Injection Perpendicular to Blade Chord on Stability of Rotor

NASA Rotor37 was used as the research object and the effects of injection on rotor stability were studied by numerical simulation. The research shows that the injection can achieve the stability effect when injection is perpendicular to the chord of the blade. The mechanism of enhancing stability is that the high-speed jet through the nozzle blows the tip leakage flow to the suction surface of the rotor, which weakens the leakage flow at the tip of the blade. The rotor tip blockage area is reduced, and the flow condition of the tip area is improved, thereby achieving the enhancing stability. In the study of the injection flow to the stability of rotor, as the injection flow rate becomes larger, the stability is enhanced. Among the selected 1%, 1.5% and 2% three injection flow levels, 2% of the injection flow can increase the rotor flow margin by 4.24% and the stall margin improvement by 5.16%. In addition, different injection flow has different effects on the flow field of the rotor. In addition to reducing the tip load of the blade leading edge, it can also reduce flow separation of the blade by pushing the shock wave position downstream. It is more advantageous to improve the stability of the rotor.