͓7͔ Takeishi, K., Aoki, S., Sato, T., and Tsukagoshi, K., 1992, ``Film Cooling on a Gas Turbine Rotor Blade,'' ASME J. Turbomach., 114, pp. 828 - 834.TAKEISHI K;AOKI S;SATO T;.Film cooling on a gas turbine rotor blade.Journal of Turbomachinery.1992.828-834...
Heat transfer measurements with film cooling have been made on a gas turbine rotor profile in a cascade at engine representative operating conditions. The blade temperature was varied independently to investigate the scaling of heat transfer coefficient, and a superposition model was found to correlate...
The stator–rotor–stator test section is housed in a closed loop wind tunnel that allows for the performance of transient heat transfer tests. Measurements of the heat transfer coefficient and film cooling effectiveness are done on the blade tip using liquid crystal thermography. These measurements...
Film cooling of jet engine components A jet engine component, such as an aircraft gas turbine engine rotor blade or a scramjet engine fuel injector. The component has a wall portion including a first surface exposable to a cooler, higher static pressure fluid and a second su... CP Lee,N ...
In order to explore the influence of the unsteady stator wake on the cooling effectiveness of the rotor blade under real situation, the film cooling of moving turbine blades, with preceding stationary vanes, was investigated numerically, and the influence of the unsteady interaction between the ...
This project experimentally investigates the heat transfer phenomena on the rotor blade platform of gas turbines. Designers often rely on experimental data gathered from non-rotating models to provide cooling designs on rotating platform... A Suryanarayanan,SP Mhetras,MT Schobeiri,... 被引量: 21...
JE Sargison,SM Guo,MLG Oldfield,... - 《Journal of Turbomachinery》 被引量: 230发表: 2001年 Film Cooling Effectiveness Distributions on a Turbine Blade Cascade Platform With Stator-Rotor Purge and Discrete Film Hole Flows An experimental investigation has been completed to obtain detailed film co...
PurposeNumerical simulations were carried out for two cooling schemes, a circular hole and a louver cooling scheme, at the leading edge of a rotor blade in a complete turbine stage. Design/methodology/approachTwo holes were positioned at the leading edge of a rotating blade, one on the pressure...
We analyze the efficiency of cooling shroud platforms under combined shroud cooling together with conventional jet air flow cooling from above and organization of barrier cooling out of inner blade cavity.会议名称: Herald of the Samara State Aerospace University. Series: Problems and Perspectives of ...
The effect of relative position of two rows of film holes on film cooling performance was experimentally and numerically investigated on each side (suction side and pressure side) of rotating blade leading edge. The film cooling performance was measured by pressure sensitive paint and phase-locked ...