Research on the performance of a two-stage transportable vane compressor
[Objective]As a carrier of high technology,gas turbines cover many theoretical disciplines and fields and are the key research content under the cooperation of universities and enterprises.The compressor is one of the three major parts of a gas turbine.Its role is to use the shaft work to continuously provide higher-quality air for the combustion chamber so that the gas turbine can work efficiently,orderly,and stably.The compressor pressure ratio,efficiency,and other related parameters directly affect the operation of the gas turbine.The study of the structure or the internal flow of the compressor aims to make the compressor obtain higher efficiency,higher pressure ratio,and better stability.Compressor stability is the basis to ensure the good performance and normal operation of gas turbines.However,the compressor undergoes unstable phenomena,such as stall and surge,which seriously affect the stability of the whole machine.The adjustable guide vane/stator vane is an effective measure for mitigating surges and preventing the compressor from entering unstable flow.[Methods]This study first mainly tackled the adjustment angle of the inlet guide vane and found that a reasonable adjustment of the inlet guide vane angle could effectively prevent the compressor from entering a surge state.Subsequently,changing the mounting angle of the stator blade was found to have the same effect.In addition,the angle adjustment of the guide vane/stator vane affected the pressure ratio and efficiency of the compressor and changed the overall performance of the compressor.In the deepening of the research on the influence of movable guide vanes on compressor performance,a single-stage movable guide vane was found unable to meet the needs of compressor performance.In this study,the characteristics of a 2.5-stage axial flow compressor were analyzed using experimental and numerical simulation methods when the installation angles of the inlet guide vane and the stator vane were changed simultaneously.A company provided units for the compressor-related experiments.The school completed the simulation work.The simulation results could be optimized by enterprises.The test bench was an integrated compressor test bench.In addition to the performance of the high-precision movable guide vane,this study tested and measured the comprehensive performance and local characteristics of different compressor blades.The design of the data acquisition integrated system can meet the requirements of the real-time accurate observation of the relevant parameters of the test bench.[Results]The regulation rules of the inlet guide vane and primary stator vane of the compressor at 0.6n speed were obtained through numerical simulations.There was a double hump trend between compressor efficiency and blade rotation angle.The rotation angle of the inlet guide vane was+4°,and the rotation angle of the primary stator vane was-4°,which were the best angle regulation laws of the compressor.[Conclusions]In this paper,by changing the installation angle of the inlet guide vane and the primary stator vane step by step,the functional relationship between the adjustment angle and the efficiency of the blade was explored,and the final adjustment law was determined.After changing the inlet guide vane and the primary stator vane,the compressor stability boundary could be moved to the left.This increased the surge margin of the compressor and achieved expanded stability.
NETL
NSTL
万方数据
