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Experimental Investigation of Film Cooling Efficiency on Turbine Blade Leading Edge

Author: DuLiMei
Tutor: LiShaoHua
School: Tohoku Electric Power University
Course: Thermal Power Engineering
Keywords: Leading edge of the blade Film cooling effectiveness Experimental study Numerical Simulation Blowing ratio Reynolds number
CLC: TK473
Type: Master's thesis
Year: 2011
Downloads: 82
Quote: 0
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Abstract


Imported high operating temperatures of modern gas turbine design , sophisticated cooling techniques must be used to maintain normal operation , the highest , the heat transfer rate of the blade leading edge region in the entire blade area . Therefore , in order to study in detail the heat transfer characteristics of the leading edge of the gas film cooling of gas turbine blades , using a combination of experimental and numerical calculation method of the blade leading edge film cooling results very important guiding significance for engineering design . Order to study the leading edge of the gas film cooling heat transfer characteristics of gas turbine blades , blade test platform visualization , experimental studies on the cooling efficiency of the blade leading edge region , mainly to study the different hair than , and different from the mainstream Reynolds number blade before changes in the cooling efficiency of the edge region . Experimental results show that : - the holes near the cooling efficiency with the blowing ratio increases and reduces the cooling efficiency of the downstream of the film cooling holes with the blowing ratio increases ; generated and the highest cooling efficiency in the suction surface , the lowest gas film the cooling efficiency of the pressure surface . Different Reynolds number on the suction side of the cooling efficiency ; blade leading edge , low blowing ratio , Reynolds number has little effect on the cooling efficiency of the high blowing ratio , the higher hole near the cooling efficiency . FLUENT software , Realizable k-ε model with three exhaust film cooling holes numerical study of the heat transfer characteristics of the leading edge of the blade . The location of the three rows of holes are two rows of holes in the suction side , another row of holes in the pressure surface . This paper analyzes the difference between the three rows of holes on the suction and pressure surfaces of the cooling efficiency and heat transfer coefficient , and different hair than under the gas film cooling efficiency and heat transfer coefficient distribution . The results show that : immediately in the suction and pressure surface holes downstream of the cooling efficiency are higher , but the cooling efficiency of the suction surface is higher than the pressure surface cooling efficiency ; hole near the film cooling efficiency With the blowing ratio increase will be reduced , but will increase in the downstream region ; high blowing ratio leads to a high Nusselt number ( Nu ) , and farther downstream of the Nusselt number change is more pronounced than the holes near the region ; Finally, the comparison of the experimental results and the numerical results obtained in good agreement with the experimental results and the numerical results .

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CLC: > Industrial Technology > Energy and Power Engineering > Internal combustion engine > Gas turbine ( gas turbine ) > Structure
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