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pressure Measurement on Suction Surface of a Single Vane Using pressure-sensitive paint

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Chinese Journal of Aeronautics 2009年第2期22卷 138-144页

作者：周强刘波高丽敏陈柳生史淼西北工业大学动力与能源学院

Global pressure distribution on the suction surface of a single vane in a transonic cascade wind tunnel is measured with the help of intensity-based pressure-sensitive paint (PSP) technique using a type of temperature-insensitive fluorescent paint and a self-made measurement system. This measurement is conducted at the outlet of the cascade wind tunnel at the Mach numbers 0.3 and 0.4, attack angle about –20°, ambient pressure 95.4 kPa and temperature 15 °C. The vane under study owns a large camber angle of ...

关键词： turbomachinery pressure measurement pressure-sensitive paint pressure distribution cascade wind tunnel suction surface of vane image registration

pressure field measurements on large-scale propeller blades using pressure-sensitive paint

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Acta Mechanica Sinica 2022年第2期38卷 35-45,I0001页

作者： Chunhua Wei Lingrui Jiao Fan Tong Zhengwu Chen Yingzheng Liu Di Peng China Aerodynamic Research and Development Center Mianyang 621000China Key Lab of Education Ministry for Power Machinery and Engineering School of Mechanical EngineeringShanghai Jiao Tong UniversityShanghai 200240China Gas Turbine Research Institute Shanghai Jiao Tong UniversityShanghai 200240China

pressure-sensitive paint(PSP)is a global pressure measurement *** with pressure transducers,PSP has significant advantages such as high spatial resolution and a lack of contact when applied to fast-rotating ***,due to the limitations of other pressure measurement techniques,the validation of PSP measurements on fast-rotating blades is generally *** this work,a comprehensive study including PSP measurement,force balance measurement,and simulation was conducted on a 1 m-diameter propeller at the China Aerodynamic Research and Development ***,our computational fluid dynamics(CFD)code was validated by comparing the calculated aerodynamic thrust with the results from force balance ***,the pressure distributions on the propeller blade obtained by PSP were carefully compared with the CFD results under different working *** results of PSP measurements,force balance measurements,and CFD showed good agreement,and the PSP measurement errors were estimated to be less than 5% of the dynamic pressure at the blade ***,the variations in pressure distribution under different rotating speeds and free-stream velocities were discussed.

关键词： pressure-sensitive paint pressure distribution Propeller blade

Improved Turbine Vane Endwall Film Cooling by Using Sand-Dune-Inspired Design

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Journal of Thermal Science 2022年第3期31卷 958-973页

作者： ZHOU Wenwu SHAO Hongyi QENAWY Mohamed PENG Di HU Hui LIU Yingzheng Key Lab of Education Ministry for Power Machinery and Engineering School of Mechanical EngineeringShanghai Jiao Tong UniversityShanghai200240China Gas Turbine Research Institute Shanghai Jiao Tong UniversityShanghai200240China Department of Aerospace Engineering Iowa State UniversityAmesIA50011USA

As continuous of the previous sand-dune-inspired design,the Barchan-Dune-Shaped Injection Compound(BDSIC)’s film cooling performance at the endwall region was further investigated both experimentally and *** the public 777-shaped hole was served as a baseline,the BDSIC’s endwall effectiveness was assessed at various blowing *** were performed in a single-passage transonic wind tunnel using pressure-sensitive paint(PSP)*** dioxide was used as coolant with density ratio of DR=*** purge slot’s blowing ratio was fixed at M=0.3,but the coolant holes were adjusted within M=0.5–*** measured experimental results indicate that the film distribution at the endwall is strongly affected by the passage flow *** BDSIC holes demonstrate much higher film effectiveness than the 777-shaped holes for all blowing ratios,~30%enhancement for regionally averaged effectiveness at M=1.0 and~26%at M=*** shown by the numerical results,the existence of BDSIC reduced the coolant penetration effect at a higher blowing *** was deflected and its momentum increased in the streamwise direction,therefore providing more robust film coverage over the endwall *** anti-counter-rotating vortex pair induced by the BDSIC further stabilized the coolant film and increased the coolant spreading downstream.

关键词： endwall film cooling pressure-sensitive paint Barchan dune 777-shaped hole counter-rotating vortex

Experimental Study on the Film Cooling Characteristics of Three Complex Tip Structures

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Journal of Thermal Science 2023年第4期32卷 1378-1392页

作者： LIN Juqiang LI Haiwang YOU Ruquan LIU Runzhou TAO Zhi LIU Song School of Energy and Power Engineering Beihang UniversityBeijing100191China Research Institute for Aero-Engines Beihang UniversityBeijing100191China National Key Laboratory of Science and Technology on Aero Engines Aero-thermodynamics Beijing100191China AECC Sichuan Gas Turbine Establishment Sichuan610500China

The turbine blades of aircrafts must be properly cooled to prevent engine ***,to investigate the influence of the tip structure on the film cooling effect,pressure-sensitive paint test technology was used to determine the adiabatic film cooling effectiveness in this *** experiment was completed in a cascade comprising three straight *** effects of the blowing ratio,density ratio,tip clearance,and tip structure on film cooling efficiency were *** experimental results demonstrated that,as the blowing ratio increased,the film coverage area and film cooling efficiency increased under most experimental ***,the film cooling efficiency was found to initially increase,and subsequently decrease,as the blowing ratio *** respective influences of the density ratio and tip clearance on the film cooling efficiency were found to be *** density ratio experiments revealed that a high-density ratio can result in better film coverage than the low-density-ratio *** tip clearance experimental results indicated that a small tip clearance promotes an increase in film cooling efficiency;this is because the small tip clearance negatively affects the main stream leakage flow,which can reduce the film coverage *** the conditions of the Base case 2 configuration,a blowing ratio of 2.1,and a tip clearance of 0.6%h,the average film cooling efficiency of the blade tip was *** the three blade tip structures applied in this study,Base case 2 demonstrated higher film cooling efficiency than the other two blade tip structures under the conditions of the same blowing ratio,tip clearance,and density ratio.

关键词： film cooling tip structure pressure-sensitive paint leakage flow