EXPERIMENTAL STUDY ON HEAT TRANSFER OF INTERNAL COOLING COMPOUND PASSAGE
Trailing edge cooling cavities in modem gas turbine blades often have a compound passage which has a partition wall between two cavities. Commonly they are roughened with turbulators such as rib and pin fins to enhance cooling effectiveness in these passages. In this study, the emphasis is located at the thermal performance of the compound cooling passage with different partition wall. To investigate the effects of bleed holes on the heat transfer performance and pressure drop, several holes are drilled along the partition wall. The endwall temperature of the trapezoidal compound passage with suitable ejection holes in the partition wall are performed using Thermochromic liquid crystal and the heat transfer characteristic was analyzed. Four sinusoid-shaped partition walls with different diameter ejection holes are designed to obtained better effectiveness of heat transfer and reasonable resistant coefficient of the cooling passage. Measurements are performed for several different Reynolds numbers varying between 8500～27000. The passage with two-two period sinusoid-shaped partition wall between the two cavities has the optimum heat transfer and resistant characteristic compared with other passages which with the two-period sinusoid-shaped partition wall and the seven-period one.
internal cooling trailing edge partition wall ejection holes
Guo-qiang Xu Li Li Shui-ting Ding Zhi Tao Fei Wei
National Key Lab.On Aero-engines, School of Jet Propulsion, BUAA
国际会议
昆明
英文
318-324
2006-09-18（万方平台首次上网日期，不代表论文的发表时间）