Study On Mechanism And Law Of The Effect Of High Temperature Steam Ingestion On Aerodynamic Stability Of Compressor

Steam ejection is one of the main ways in which a carrier aircraft can take off.Due to problems such as the structure of the steam catapult,high-temperature steam leakage occurs during the take-off of the aircraft,which degrades the performance and stability of the engine.The aerodynamic stability of the engine is mainly determined by the compressor.In order to study the influence of high temperature steam ingestion on the aerodynamic stability of axial compressor,in this paper,the CFX software is used to simulate the transonic rotor Rotor37 and the two-stage low-speed axial compressor,and a test plan is developed for the two-stage low-speed axial compressor.Through the steady and unsteady simulation of the single-passage transonic rotor,the effects of high temperature steam mass fraction,temperature rise rate and temperature rise on the aerodynamic stability of axial compressors were studied.Results show that: with the ingestion of high-temperature steam,the stable boundary of the compressor moves toward the direction of increasing flow.The greater the steam mass fraction,the greater the impact on the stable boundary;the temperature rise rate has no effect on the aerodynamic performance of the compressor.The greater the temperature rise,the greater the impact on the stable boundary;with the ingestion of high-temperature steam,the average density of the gas at the inlet of the compressor is affected,and the shock position in the passage moving forward,the loss increases,causing the stall to occur in advance.Through the steady and unsteady simulation of the annulus transonic rotor,the influence of high temperature steam distribution on the aerodynamic stability of the transonic rotor is studied.Results show that when the steam quantity is the same,the non-dimensional stable operating range of the rotor becomes larger with the increase of the high-temperature steam ingestion area at different speeds.The effect of the steam distribution on the rotor is more pronounced at low rotational speeds.Through unsteady analysis,it is found that when the high-temperature steam is partially ingested,the shock position in these blade passages is moved forward,the shock intensity is increased,the shock wave and tip leakage flow in the passage have strong interference,and the mixing of the mainstream and the leakage flow moves forward.Through the steady simulation of the annulus two-stage low-speed axial compressor,the effects of high-temperature steam mass fraction and steam distribution on the aerodynamic stability of the two-stage low-speed axial compressor are studied.Results show that the steam ingestion will make the stable boundary of the low-speed axial compressor move in the direction of increasing flow rate,the dimensionless stability range is reduced.However,the larger the steam ingestion area,the smaller the stability range,which is contrary to the calculation results of the transonic axial flow compressor.According to the analysis of the flow field,the reason for this trend is that in the low-speed compressor,as the steam ingestion area increases,the flow conditions in the affected area are improved,but the change is not obvious.However,the flow conditions in the large-area passages are not ideal,which plays a leading role in compressor stall.For the transonic compressor,due to the existence of complex structures such as shock waves,when the steam ingestion area is small,the flow conditions are bad,and as the area increases,the flow conditions are better improved.In addition,when the steam ingestion area is the same,as the steam quantity increases,the stable boundary line of the compressor moves toward the flow increasing direction,that is,the higher the mass fraction of the high-temperature steam,the more adverse effects of the high-temperature steam on the two-stage low-speed axial compressor.