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In this study, the lock-in phenomenon of Tip Clearance Flow(TCF) instabilities and their relationship to blade vibration are investigated numerically on an axial transonic rotor with a large tip clearance. The capabilities of simulating instability flow and lock-in phenomenon are verified on a transonic rotor and a NACA0012 airfoil by comparing with the test data, respectively.The lock-in phenomenon is first numerically confirmed that may occur to TCF instabilities when its frequency is close to... 相似文献
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Experimental and numerical study of tip injection in a subsonic axial flow compressor 总被引:2,自引:0,他引:2
Parametric study of tip injection was implemented experimentally on a subsonic axial flow compressor to understand the underlying flow mechanisms of stability improvement of the compressor with discrete tip injection.Injector throat height varied from 2 to 6 times the height of rotor tip clearance,and circumferential coverage percentage ranged from 8.3% to 25% of the annulus.Static pressure fluctuations over the rotor tip were measured with fast-response pressure transducers.Whole-passage time-accurate simulations were also carried out to help us understand the flow details.The combinations of tip injection with traditional casing treatments were experi mentally studied to generate an engineering-acceptable method of compressor stall control.The results indicate that the maximum stability improvement is achieved when injectors are choked despite their different sizes.The effect of circumferential coverage percentage on compressor stabil ity depends on the value of injector throat height for un-choked injectors,and vice versa.Tip blockage in the blade passage is greatly reduced by the choked injectors,which is the primary reason for stability enhancement.The accomplishment of blockage diminishment is maintained in the circumferential direction with the unsteady effect of tip injection,which manifests as a hysteresis between the recovery of tip blockage and the recovery of tip leakage vortex.The unsteady effect is primarily responsible for the effectiveness of tip injection with a partial circumferential coverage.Tip injection cannot enhance the stability of the rotor with axial slots significantly,but it can improve the stabil ity of the rotor with circumferential grooves further.The combined structure of tip injection with circumferential grooves is an alternative for engineering application. 相似文献
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变体翼梢小翼的减阻机理数值模拟 总被引:1,自引:0,他引:1
总结了对翼梢小翼减阻效果影响最大的几何参数,在此基础上采用数值模拟方法研究了这些几何参数的最佳变化范围,为变体翼梢小翼设计提供理论依据.并从气动性能、气动载荷分布和翼尖涡的角度探讨了变体翼梢小翼相对传统翼梢小翼的优缺点.结果表明:在飞机的起飞阶段,变体翼梢小翼的减阻效率比传统翼梢小翼高2.2%,同时将翼尖涡强度降低了15%,有利于提高飞机的燃油效率和机场空域安全;但也会增大机翼的翼根弯矩,因此必须权衡变体翼梢小翼带来的气动收益与结构强度不利因素. 相似文献
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Effect of tip geometry and tip clearance on aerodynamic performance of a linear compressor cascade 总被引:2,自引:0,他引:2
The tip leakage flow between a blade and a casing wall has a strong impact on compressor pressure rise capability, efficiency, and stability. Consequently, there is a strong motivation to look for means to minimize its impact on performance. This paper presents the potential of passive tip leakage flow control to increase the aerodynamic performance of highly loaded compressor blades. Experimental investigations on a linear compressor cascade equipped with blade winglets mounted to the blade tips have been carried out. Results for a variation of the tip clearance and the winglet geometry are presented. Current results indicate that the use of proper tip winglets in a compressor cascade can positively affect the local aerodynamic field by weakening the tip leakage vortex. Results also show that the suction-side winglets are aerodynamically superior to the pressure-side or combined winglets. The suction-side winglets are capable of reducing the exit total pressure loss associated with the tip leakage flow and the passage secondary flow to a significant degree. 相似文献
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基于涡格法的近程无人机气动优化与风洞实验验证 总被引:1,自引:0,他引:1
针对低雷诺数的近程无人机,利用涡格法(VLM)对无人机气动特性进行了加装翼尖小翼优化设计,并通过风洞实验进行了验证。首先给出了翼尖小翼的几何参数并分析其对全机气动特性的影响,其次利用涡格法对小翼进行气动建模和优选,针对无人机巡航状态给出了小翼优化结果,最后利用风洞实验对优化前后的无人机进行了吹风实验对比验证,实验结果表明,涡格法和风洞实验结果在线性段相符,涡格法能够较准确地描述和预测翼尖小翼特性,加装翼尖小翼后的无人机巡航状态升阻比提高12%,全机滚转阻尼加大,偏航阻尼变化很小。 相似文献