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在对实验室对转压气机进行定常数值模拟的基础上,开展了对转压气机旋转失速机理的初步研究.研究结果表明:①该对转压气机在近失速工况存在突尖波型失速初始扰动;②在近失速点转子2中间隙泄漏涡在三维空间上迅速发展,导致转子2流道严重堵塞,引起压气机内部失稳;③由于转子2叶片排存在较大的气动负荷,其叶顶间隙泄漏涡的发展情况很大程度上决定着对转压气机的稳定性.
On the basis of the constant numerical simulation of the rotary compressor in the laboratory, a preliminary study on the mechanism of rotary stall of the rotary compressor was carried out. The results show that: (1) There is a sudden spike-type stall in the near-stall condition Initial turbulence. At the near stall point, the leakage vortex in the rotor 2 rapidly develops in the three-dimensional space, resulting in a serious blockage of the flow passage in the rotor 2, causing the internal instability of the compressor. (3) Since there are large aerodynamic loads in the rotor blade row, The development of tip vortex leakage vortex largely determines the stability of rotary compressor.