Component Improvements And Performance Test Of Micro Turbine Engine

Micro turbine engine, with its merits in high power density and thrust-weight ratio, can be used as propulsion system and satisfy the requirements of advanced micro vehicles at low payment. Development of micro turbine engine technique can contribute to the using process of micro turbine engine and enhance our army ability of spy-beating quickly.Based on the simulation and experiment results of MTE-C (16 centimeters), a new integer engine model is built using the software Gasturb. At design and off-design points, the performance of MTE-C is obtained, as well as working line of compressor and turbine at different height. Changing rules of rotate speed to thrust,unit thrust,specific fuel consumption,air flux,pressure ratio of compressor and temperature at combustor's exit are also gained. These all contribute to the next stage of development and experiments of micro turbine engine.Comparison of prototype diffuser performance at different design parameters is also finished in this paper, and design-rules of distribution on the convex are obtained. In order to control the area of flow path, spline interpolation is used in this paper, which improves the design technic of prototype diffuser. Three main design features are summarized as well. With improvement, the total pressure recovery of this new diffuser used in MTE-C can be 0.875, 5.5% higher than the former. At the same time, diffuser degree is increased greatly, pressure ratio raised from 1.14 to 1.23.The influences of meridian-passage and vane angle distribution are researched, and the design cretirion of the vane turbine nozzle is obtained. The numerical simulation of original turbine nozzle is completed, and a vane turbine nozzle is designed to promote the turbine performance. The total pressure recovery of turbine nozzle increases from 0.909 to 0.918 and the quality of nozzle exit is improved obviously. The numerical simulation results of turbine stages with original and modified turbine nozzles show that the performance of turbine with improved vane nozzle promote greatly. The efficiency of turbine stage at design point increases from 70.9% to 84.2%.The performance improvements of MTE-C are predicted with the engine performance simulation model, for the prototype diffuser and modified turbine nozzle respectively. The area of engine nozzle is adjusted for optimal matching of engine parts. It directs the ground test of the micro turbine engine.The ground test of MTE-C is completed and the ration speed reached 85krpm. The air mass is 0.618kg/s, the pressure ratio is 3.45, the engine thrust is 295N, and the specific fuel consumption is 0.0488g/(N·s), at this speed. The ground test of MTE-C with prototype diffuser is completed. At 70000rpm, the air mass and engine thrust increase by 6.5% and 11% respectively, and the specific fuel consumption decreases by 7%. The ground test of MTE-C with modified turbine nozzle is completed. At 69000rpm, the air mass, engine thrust and the specific fuel consumption increase by 4%, 36.8% and 5.1% respectively.