Study On Flow And Heat Transfer Performance Of Turbulent Jet On Blade Cascade

Enhancing the temperature of gas turbine's inlet is one of the key technology to improve the efficiency of the gas turbine, and the requirement the blade bearing the high temperature is much higher than before. As a result, investigating on flow and heat transfer performance of blade's film cooling possesses is important to protect the blade effectively and design the gas turbine.The paper adopted the experimental and numerical simulation method to study the blade cascade's flow and heat transfer performance of turbulent jet. A large wind tunnel of low speed wind is designed and built. IFA300 hot film anemometer is applied to measure the flowing field of the single row jet hole and analyze its flow performance. Basing on SIMPLE algorithm and discretizing the control equation in finite volume method, standard k-εturbulence model is applied, to numerical simulate film cooling in different jet rate, different angle of incidence and different jet hole position. The effective factors to jet hole's temperature is also analyzed.The results shows that the foot section of suction surface flow field format wake region. The jet makes the wake region close to jet hole and the wake region become thickener and the wake vortex become bigger. Between 0.4~0.6, when jet rate equal to 2.0 the cooling efficiency is best; among 45 degree, 60 degree and 90 degree angle of incidence, the 90 degree's cooling efficiency is minimum. Comparing the 45 degree and 60 degree's angle of incidence the cooling efficiency, the former elevated earlier and decline afterward; Comparing the 3D and 4.5D hole distance, when hole distance is 3D,the suction surface between the centre plane along the mainstream a preferable cold film is formatted. Comparing the different hole position effective to the cooling efficiency in same condition, the most closely to the anterior border of blade hole's efficiency is worst.