在近失速条件下运行的跨音速轴流压缩机中的表面粗糙度效应

Prashant B. Godse, Harshal D. Akolekar, A. M. Pradeep
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摘要

表面粗糙度是导致燃气涡轮发动机性能下降的一个主要因素。风扇和压缩机作为发动机气路的首要部件,特别容易受到表面粗糙度的影响。通常在低气压条件下,经过几个运行周期后,碎片的摄入、污垢、灰尘或昆虫残留物的积累是造成叶片表面粗糙的一些主要原因。压缩机转子的流动本身就非常复杂。因此,从部件设计者的角度来看,研究表面粗糙度对性能和流动物理的影响非常重要,尤其是在近气流条件下。在本研究中,我们研究了表面粗糙度对流动物理的影响,如冲击-边界层相互作用、尖端和轮毂流动分离、临界点的形成和变化以及尖端漏孔等现象。对光滑和粗糙的 NASA(美国国家航空航天局)67 号转子叶片进行了近滞流条件下的稳定和非稳定雷诺平均纳维斯托克斯(RANS)计算。据观察,从失速开始到完全失速条件下,在光滑情况下,从90%跨度到叶尖的阻塞从21.7%到59.6%不等;在粗糙情况下,阻塞从40.5%到75.2%不等。这种由涡流破坏和混乱的流动结构造成的严重堵塞导致了全转子失速的发生。
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Surface roughness effects in a transonic axial flow compressor operating at near-stall conditions
Surface roughness is a major contributor to performance degradation in gas turbine engines. The fan and the compressor, as the first components in the engine's air path, are especially vulnerable to the effects of surface roughness. Debris ingestion, accumulation of grime, dust, or insect remnants, typically at low atmospheric conditions, over several cycles of operation are some major causes of surface roughness over the blade surfaces. The flow in compressor rotors is inherently highly complex. From the perspective of the component designers, it is thus important to study the effect of surface roughness on the performance and flow physics, especially at near-stall conditions. In this study, we examine the effect of surface roughness on flow physics such as shock-boundary layer interactions, tip and hub flow separations, the formation and changes in the critical points, and tip leakage vortices amongst other phenomena. Steady and unsteady Reynolds Averaged Navier Stokes (RANS) calculations are conducted at near-stall conditions for smooth and rough NASA (National Aeronautics and Space Administration) rotor 67 blades. Surface streamlines, Q-criterion, and entropy contours aid in analyzing the flow physics qualitatively and quantitatively. It is observed that from the onset of stall, to fully stalled conditions, the blockage varies from 21.7\% to 59.6\% from 90\% span to the tip in the smooth case, and from 40.5\% to 75.2\% in the rough case. This significant blockage, caused by vortex breakdown and chaotic flow structures, leads to the onset of full rotor stall.
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