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The cooling performance of three-row compound angle holes on the suction surface of a rotating turbine blade

Propulsion and Power Research 2021年第1期10卷 23-36页

作者： Zhiyu Zhou Haiwang Li Gang Xie Shuangzhi Xia Jianjun Zhou National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics School of Energy and Power EngineeringBeihang UniversityBeijing100191China Beihang University Beijing100191China New Era Engineering Consulting Co. LtdBeijing100088China Shenyang Aeroengine Research Institute Aero Engine Corporation of ChinaShenyang110015China

Experiments were carried out to study the effects of compound angle,hole arrangement,and blowing ratio on the film cooling performance of multiple rows of holes on the suction surface of a turbine *** turbine worked at rotational speed of 600 rpm corresponding to the rotational Reynolds number of 5.36*** rows of cylindrical holes arranged in line or in stagger were drilled on the rotor blade suction surface at the streamwise location of 12.4%,17.8%,and 23.2%,*** compound angles,with the same streamwise angle of 45but different lateral deflection angles of 45,0,and45,were stud*** film cooling effectiveness was obtained using pressure sensitive paint(PSP)technique with average blowing ratios varied from 0.5 to *** results showed that the application of compound angle changes the jet direction in the near-hole region and makes the film spread *** with the film cooling without compound angle,using positive and negative compound angle can improve overall average film cooling effectiveness by about 20%and 25%,*** effects of the secondary flow also can be weakened.A stagger film trajectory arrangement can achieve more uniform film coverage with higher overall film cooling *** film trajectory arrangement of a positive compound angle injection is determined by the combined effect of hole arrangement and blowing ***,the film trajectory arrangement of a negative compound angle injection is almost the same as the hole arrangement and nearly does not change with the blowing ratio.

关键词： Film cooling Turbine blade suction surface Compound angle Hole arrangement Blowing ratio

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跨音涡轮叶栅吸力面气膜/激波交互作用的数值研究

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风机技术 2022年第6期64卷 40-47页

作者：黄康陈帝云李世峰时培杰马护生 Aerospace Technology Institute China Aerodynamics Research and Development Center

The interaction between the cooling film on the suction surface of the transonic turbine cascade and the shock wave in the passage is analyzed by numerical calculation *** effects of cooling pressure and incident angle on the shock wave shape and the film cooling efficiency under the action of shock wave are *** results show that with the increase of exit Mach number,the incident position of the left shock wave at the trailing edge of the cascade moves backward relative to the leading edge of the adjacent cascade,and the shock wave intensity increases;there is a temperature jump behind the temperature peak at the exit Mach number of 1.05 and 1.2,the main reason is that with the increase of shock wave intensity,the interaction between shock wave and boundary layer intensifies,and the boundary layer appears local separation,in the separation region,the mixing of high-temperature mainstream and boundary layer flow intensifies,which makes the temperature in the separation region of suction surface increase;the results show that different cooling gas injection positions have great influence on the shock wave shape in the channel,and the cooling area of the wall is smaller than that before and after the shock wave,which is mainly due to the reduction of the film coverage area under the impact of the incident shock wave,after the impact zone of shock wave,the cooling film is compressed by the main stream and attached to the wall again,resulting in the discontinuous film coverage at the shock wave incident point;the film cooling efficiency decreases significantly with the increase of cooling flow angle from 25°to 35°and changes little with the increase of cooling flow angle from 35°to 45°;the cooling efficiency does not increase infinitely with the increase of blowing ratio,when the blowing ratio is greater than a certain value,the influence of blowing ratio on cooling efficiency gradually decreases.

关键词： Transonic Turbine suction surface Film Cooling Shock Wave

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