论文部分内容阅读
为了分析叶尖间隙对压气机气动阻尼的影响,基于相位延迟边界条件,建立了跨声速转子的气动阻尼计算模型,研究叶尖间隙对其流场及气动阻尼的影响。计算该转子在设计间隙条件下的气动性能、叶片模态以及颤振边界,和实验数据吻合较好,比较不同叶尖间隙(1.6%,3.2%,5.0%叶尖弦长)的转子气动性能,发现间隙增加使转子效率和压比均有显著的下降;对叶片表面非定常压力研究表明,叶片非定常压力对叶片振动的响应具有强三维特性,同时叶片间相位角(IBPA)和叶尖间隙流对其有显著的影响,由于叶尖间隙增加使叶尖流动的影响加强,导致叶尖区域由于振动造成的一阶谐波压力幅值相对减小,大间隙趋于恶化压力面的稳定性而对吸力面的影响在不同的叶片间相位角时不同;对于气动阻尼,在不同的叶片间相位角区域,叶尖间隙对其影响有显著的差异,甚至会产生截然相反的规律,特别是在设计状态,对于该转子,大间隙提高了叶片最不稳定状态的气动阻尼。
In order to analyze the influence of tip clearance on the aerodynamic damping of the compressor, the aerodynamic damping model of the transonic rotor is established based on the phase delay boundary conditions, and the influence of tip clearance on its flow field and aerodynamic damping is studied. The aerodynamic performance, blade mode and flutter boundary of the rotor under the designed clearance condition are calculated, which are in good agreement with the experimental data. The aerodynamic performance of the rotor with different tip clearances (1.6%, 3.2% and 5.0% The results show that the unsteady pressure on the blade surface has a strong three-dimensional response to blade vibration, and at the same time the phase angle between blades (IBPA) and blade tip As the tip clearance increases, the influence of tip flow is strengthened. As a result, the amplitude of the first-order harmonic pressure in the tip region is relatively reduced, and the large clearance tends to deteriorate the stability of the pressure surface While the influence on the suction side is different at different interphase phase angles. For aerodynamic damping, there are significant differences in the influence of tip clearance on different interphase phase angles and may even have opposite laws, especially In the design state, for this rotor, the large clearance increases the aerodynamic damping of the most unstable state of the blade.