TS-82 Influence of Endwall Phenomena on Leading Edge Ejection(Session C-10 Turbine Cooling 2)
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概要
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A leading edge cooling configuration is investigated numerically by application of a 3-D conjugate fluid flow and heat transfer solver, CHT-Flow. The cooling configuration is an axial turbine blade cascade with leading edge ejection through two rows of cooling holes (showerhead ejection). The rows are located in the vicinity of the stagnation line, one row is on the suction side, the other row is on the pressure side. Each row consists of 20 cooling holes. The cooling fluid is ejected streamwise. This configuration has been investigated experimentally by other authors and the results have been documented as a test case for numerical calculations of ejection flow phenomena. The numerical domain consists of the internal cooling fluid supply (plenum), the ejection holes and the complete external flow field of the turbine vane including one passage endwall. The numerical investigations focus on the development of secondary flow phenomena induced by the endwall boundary layer and their influence on the aerothermal mixing process in the cooling jets at the leading edge. Within a secondary flow analysis it can be shown that complex vortex systems which are formed in the cooling fluid jets are heavily influenced by the development of several secondary flow phenomena. In particular, the horseshoe vortex has a significant influence on the cooling jets near the endwall. The impact of the passage vortex leads to cooling fluid displacement on the suction side and pressure side. The results of an aerothermal calculation show an intensified mixing process of the hot gas and the cooling fluid in the cooling jets near the endwall and a significant cooling jet displacement.
- 社団法人日本ガスタービン学会の論文
- 1999-11-14
著者
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Bohn Dieter
Institute of Steam and Gasturbine, Aachen University
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Bohn Dieter
Institute Of Steam And Gas Turbines Aachen University Of Technology
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Kusterer Karsten
Institute Of Steam And Gas Turbines Aachen University Of Technology
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