Inlet Flow Temperature Distortion Aviation Engine Performance

Performance, reliability and stability are the basic requirements for an well-designed aero-engine. High stability means that aero-engine should be of sufficient available aerodynamic stability margin to deal with stagnation pressure distortion and stagnation temperature distortion encountered by aero-engines during their flight envelops. Among kinds of influence factors reducing aerodynamic stability margin of aero-engines, the stagnation pressure distortion and stagnation temperature distortion usually play the critical role.Less research about stagnation temperature distortion as well as its impact on aero-engine stability has been carried out at present and meanwhile the key technologies in this field have also been kept secretive against China in other countries. Aiming at the influence of stagnation temperature distortion on aero-engine aerodynamic stability, the author of this paper, under the support of the project of aero-engine aerodynamic research which belongs to the plan of Aviation Propulsion Technology Demonstration, have obtained several achievements such as the deep research about the influence principle of temperature distortion on engine stability, further development of physical and mathematic models describing this influence, and, based on the above research efforts, development of the simulation software.Combined with the current research conditions and the author's personal job, the main contents of this paper involve:First of all, stagnation temperature distortion at the aero-engine inlet is described and the principle research about influence of temperature distortion on compressor and aero-engine is carried out. In the meantime, some important parameters which are used to describe the distorted temperature field in quantity are given and further, the relation between these technical parameters and the change in aerodynamic stability of an aero-engine is analyzed.Secondly, the transfer model of temperature distortion along the flow path of engine has been further developed and the key points of distortion transfer and calculation of critical distortion index were paid more attention and have been solved well. These research contents involve several aspects like the control equations of compressor components, boundary conditions, calculation and analysis methods. Besides, a sample calculation about the effect of temperature distortion upon a certain aero-engine has also been completed.Finally, the comparison between test results and simulation data is done and the numerical simulation method given in this paper is demonstrated to be reasonable and feasible.The comparison between simulation and test indicates that the simulation software established in this paper is of good suitability to the engineering application.