An improved compressor performance prediction model. IMechE Conference Proceedings CP 1987-6, paper C279/87, 1987. Off-design prediction of compressor blade losses. The use of boundary layer techniques to calculate the blockage from the annulus wall boundary layer in a compressor. Von Karman Institute for Fluid Dynamics, Lecture Series 1985-05, 1985. Effect of tip clearance flow on compressor stability and engine performance. A study of spike and modal stall phenomena in a low-speed axial compressor. Endwall effects at two tip clearances in a multi-stage axial flow compressor with controlled diffusion blading. The effect of hub leakage flow on two high speed axial flow compressor rotors. ASME paper 95-GT-461 to 464, 1995, to be published in J. Boundary layer development in axial compressors and turbines: Parts 1 to 4. Compressor Aerodynamics, 1989 ( Longman). Gas Turbines Power (April, 1985) Comparison of Controlled Diffusion Airfoils With Conventional NACA 65 Airfoils Developed for Stator Blade Application in a Multistage Axial Compressor. Keywords Key wordscompressor, aerodynamics, design, computational fluid dynamics (CFD), secondary flows, endwall flows, boundary layers, tip clearance flow, rotors, stators, stall, surge, reactionĬlosure to “Discussions of ‘Axial Compressor Stator Aerodynamics’” (1985, ASME J.
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