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Approximate Nonlinear Modeling of Aircraft Engine surge margin Based on Equilibrium Manifold Expansion

Chinese Journal of Aeronautics 2012年第5期25卷 663-674页

作者： LIU Xiaofeng ZHAO Lei School of Transportation Science and Engineering Beihang UniversityBeijing 100191China

Stable operation of aircraft engine compressions is constrained by rotating surge. In this paper, an approximate nonlinear surge margin model of aircraft engine compression system by using equilibrium manifold is presented. Firstly, this paper gives an overview of the current state of modeling aerodynamic flow instabilities in engine compressors. Secondly, the expansion form of equilibrium manifold is introduced, and the choosing scheduling variable method is discussed. Then, this paper also gives the identification procedure of modeling the approximate nonlinear model. Finally, the modeling and simulations with high pressure （liP） compressor surge margin of the aircraft engine show that this real-time model has the same accuracy with the thermody- namic model, but has simpler structure and shorter computation time.

关键词： aircraft engine surge margin system identification equilibrium manifold scheduling variable perpendicular expan-sion

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Design of a high-performance centrifugal compressor with new surge margin improvement technique for high speed turbomachinery

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Propulsion and Power Research 2018年第1期7卷 19-29页

作者： Sagar Pakle Kyle Jiang School of Engineering University of BirminghamEdgbastonBirmingham B152TTUnited Kingdom

This paper presents the design of a centrifugal compressor for high-speed *** main focus of the research is to develop a centrifugal compressor with improved aerodynamic *** a meridional frame has a significant effect on overall performance of the compressor,special attention has been paid to the end wall *** shroud profile is design with bezier curve and hub profile with circular arc *** blade angle distribution has been arranged in a manner that it merges with single value at impeller *** rake angle is positive at leading edge and negative at trailing edge with identical ***,three-dimensional straight line element approach has been used for this design for better *** verification of the aerodynamic performance has been carried out using CFD software with consideration of a single blade passage and vaneless *** result has been compared with matching size aftermarket compressor stage gas stand *** compressor stage with Trim 55 provides 34%increase in choke flow at 210000 RPM as compared to gas stand data with 87%peak stage efficiency at 110000 *** addition,new surge margin improvement technique has been proposed by means of diffuser *** technique provides an average of 16%improvement in surge margin compared to standard diffuser stage with 55 trim compressor *** mechanical integrity has been validated at maximum RPM with the aluminum alloy 2014-T6 as a fabrication material.

关键词： Centrifugal compressor Aerodynamic performance surge margin Blade angles Stress analysis Computational fluid dynamics

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