Modeling And Performance Research Of The Turbine Engine

Small medium tactical UAV’s(unmanned aerial vehicle),small tactical missiles and target drones, which are respectively used for the scout of land and sea areas in the air, for attacks against warships or tanks and for performance estimates of weapon systems, play a very important role in modern wars. IT has a higher demand for propulsion systems, as the arduous war mission of weapon systems Thus, a mini-jet engine, which features simply design, compact structure, reduced mass, small size and low cost, is proved to be a prior propulsion system for short-short-range tactical UAV’s. The method of computing steady-state characteristic can achieve a higher accurate level, which can provide the engine performance at design point and characteristics of the altitude, the velocity, the throttling and the environment for aircraft overall designers to work on aircraft/engine integrated design whereas the mathematical model of engines obtained from the characteristic compute help designers to carry on a simulation of control systems, what’s more, the compute of steady-state characteristic of a engine id the base of improving engine performance and provides reasons of fault diagnosis Consequently, the compute and research of engine performance is a major procedure in the development of a jet engine.Targeted on issues that there is no mathematical model and engine performance in every operating condition cannot be obtained, the compute and research of a jet engine is presented in this article, Based on the method of American 7901 program, a Newton-like method based on Broyden theory, which is actually a non-linear equation of flux of nozzle throat and combustor outlet.In consideration of the issue that there are no part characteristics of the compressor, turbine and combustor of the engine, a adapted model of part performance characteristic is added, into which a weight function and a series of coupling factors are introduced, that is used to correction is that by changing coupling factors to minimize the value of the weight function, part characteristics and the mathematical model of the engine is corrected to the realistic condition. Then, variations of the realistic part characteristics(compressor, combustor and turbine) on steady-state work curve are predicted according to engine experimental data. On the basis of this method, more accurate characteristics of the engine altitude, velocity, environment and throttling are acquired.The technical indexes and parameters achieved in this research are as followed.The variations of part characteristics on the steady-state work curve are predicted(0~0.8mach), environment, throttling are acquired What’s more, the deviation is less than 5% by using the engine’s performance computing program, compared with the experiment data of the engine altitude and velocity characteristics.By adding the adapted model of part performance characteristic, the major problem that there are no part performance characteristics is settled and the steady-state performance model of the engine is obtained along with the satisfaction provided for aircraft overall presented in this article works with broad application value and provides a solution for study of the mathematical model of engines without part performance characteristics.