THE RESEARCH ON THE AERODYNAMIC LOSS OF GAS TURBINE WITH COOLANT INJECTION
Detailed Experiment and numerical simulations were performed to research the mechanics of the total pressure loss at the three-dimensional turbine flow field with coolant injection from a single row of holes on the suction or pressure side of the blades. The total,pressure loss coefficient based on the cascade outlet dynamic pressure was used to assess the aerodynamic characteristics. Good agreement between analysis based on the experimental data and the results of numerical simulation for the fluid injection showed that the value of mass flow rate of injection was the most important factor affecting the aerodynamic performance. When the injection angle was 30 degree, the large amount of fluid injection could reduce total pressure loss coefficient evidently. This obviously was due to the momentum in boundary layer supplied by the injected fluid.When the value of injection was little, the loss coefficient had a phase of rising and reducing again as the increasing value of fluid injection for suction side injection. The essential reason for this phenomenon was also the boundary layer profiles changed by the injected fluid.
Zhang Man Qiao Weiyang Zeng Jun Sun Dawei
School of Engine and Energy, Northwestern Polytechnical University Xian, 710072 P.R.China Gas Turbine Establishment Chengdu, 610500 P.R.China
国际会议
昆明
英文
277-282
2006-09-18（万方平台首次上网日期，不代表论文的发表时间）