There exists inlet-engine match conflict between high and low speeds for a non-adjustable bump inlet.A scheme of using a bistable bump surface at the throat region of the inlet is proposed to adjust the throat area.Th...There exists inlet-engine match conflict between high and low speeds for a non-adjustable bump inlet.A scheme of using a bistable bump surface at the throat region of the inlet is proposed to adjust the throat area.The FEM model of the bistable surface is established with hinged constraint,and the bistability condition and structural transition process are investigated in detail.Moreover,the effects of loading method,loading position and structural parameters on critical driving force,input energy and structural strain are studied.Finally,the influences of an elastic boundary condition on the structural bistability are discussed.The results show that the bistability of the adjustable bump surface requires a certain boundary constraint and geometric parameter combination,and that there are local and overall snap-through phenomena during transition which are related to the loading position and structural parameters.Therefore,suitable loading position and structural material could reduce input energy and meet the demand of structural strain.展开更多
The air intake-compression systems of modern aircraft usually use the aero-engine intake and fan/compressor as the main components.Inlet-engine compatibility has always been the key to the stable and safe operation of...The air intake-compression systems of modern aircraft usually use the aero-engine intake and fan/compressor as the main components.Inlet-engine compatibility has always been the key to the stable and safe operation of the propulsion system,including the influence of inlet distortion on the compressor performance and stall margin.Since 1950,theoretical models and experiments on the flow stability and inlet distortion of axial compressors have been released.After the 1990s,numerical methods became important tools.In the 21st century,the new trends of aircraft propulsion system/inlet integration,blended wing body,and stealth capability led to a new direction for the inlet-engine flow matching problem.This review aims to combine the development of both the inlet and the axial compressor components,and provides an overview of the research history,latest progress,and prospects of compressor inlet distortion in inlet-engine compatibility problems.Analytical or numerical models,experiments,and simulations related to inlet distortion problems are summarized.展开更多
基金supported by the National Natural Science Foundation of China(Nos.11172128,51475228)the Specialized Research Fund for the Doctoral Program of Higher Education of China (No.20123218110001)+1 种基金the Research Fund of State Key Laboratory of Mechanics and Control of Mechanics Structures (Nanjing University of Aeronautics and Astronautics)(No.0515G01)the Priority Academic Program Development of Jiangsu Higher Education Institutions and the Funding of Jiangsu Innovation Program for Graduate Education(the Fundamental Research Funds for the Central Universities)(No.CXZZ12_ 0139)
文摘There exists inlet-engine match conflict between high and low speeds for a non-adjustable bump inlet.A scheme of using a bistable bump surface at the throat region of the inlet is proposed to adjust the throat area.The FEM model of the bistable surface is established with hinged constraint,and the bistability condition and structural transition process are investigated in detail.Moreover,the effects of loading method,loading position and structural parameters on critical driving force,input energy and structural strain are studied.Finally,the influences of an elastic boundary condition on the structural bistability are discussed.The results show that the bistability of the adjustable bump surface requires a certain boundary constraint and geometric parameter combination,and that there are local and overall snap-through phenomena during transition which are related to the loading position and structural parameters.Therefore,suitable loading position and structural material could reduce input energy and meet the demand of structural strain.
基金supported by National Natural Science Foundation of China(52306036)Science Center for Gas Turbine Project(P2022-A-II-002-001,P2022-C-II-003-001)supported by the Key Laboratory of Pre-Research Management Centre(No.6142702200101).
文摘The air intake-compression systems of modern aircraft usually use the aero-engine intake and fan/compressor as the main components.Inlet-engine compatibility has always been the key to the stable and safe operation of the propulsion system,including the influence of inlet distortion on the compressor performance and stall margin.Since 1950,theoretical models and experiments on the flow stability and inlet distortion of axial compressors have been released.After the 1990s,numerical methods became important tools.In the 21st century,the new trends of aircraft propulsion system/inlet integration,blended wing body,and stealth capability led to a new direction for the inlet-engine flow matching problem.This review aims to combine the development of both the inlet and the axial compressor components,and provides an overview of the research history,latest progress,and prospects of compressor inlet distortion in inlet-engine compatibility problems.Analytical or numerical models,experiments,and simulations related to inlet distortion problems are summarized.
