The Stability Analysis of Gas Turbine Ompression System
|School||Harbin Engineering University|
|Keywords||Compression system Gas turbine Injection flow Dual-rotor Intercooling Stability|
The situation of blade boundary layer separation of compressor in the process ofpressuriser is the reason which lead to surge and rotating stall. The research of effect tostability of gas turbine by compressor is great important. Model and simulate different formsof gas turbine compression stability is the main content of this article. The main assignment ofthis thesis would be mentioned below:First of all, the paper was studied start-up of basic principle and unstable state for gasturbine, and based on the Moore–Greitzer model，a mathematical model of start-up system forcompression of gas turbine with the form of deflation and injection was built, use this modelto study starting process of unstable state, and the relationship between stability of system andjet flow.Secondly, it is in this context that started on a study about dual-rotor compression systemoperation mode and unstability effect. A steady-state for dual-rotor compression system ofgas turbine based on Moore-Greitzer model was established, and analyse how to affectstability boundary by rotational distortion, inherent frequency, reciprocal time-lag parameterof blade passage and pressure over according to this model.Finally, to study basic principle effect of cooler to dual-rotor compression, the paper wastaken plate-fin heat exchanger as the cooler. Based on the Moore-Greitzer model, atwo-dimentional intercooled dual-rotor compression system model was developed to predictstall transient. Using the mathematical model to calculate and analyse the effect of intercooledsystem for high and low pressure compressor, calculations have been presented that thecoefficient of heat transfer, volume inertia, flow resistance and the dimensions had an effecton the post stall transient behavior.