TY - GEN
T1 - Transonic film-cooling investigations
T2 - ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1996
AU - Wittig, S.
AU - Schulz, A.
AU - Gritsch, M.
AU - Thole, K. A.
N1 - Publisher Copyright:
Copyright © 1998 by ASME.
PY - 1996
Y1 - 1996
N2 - The emphasis of the present study is to understand the effects of various flowfield and geometrical parameters in the nearfield region of a scaled-up film-cooling hole on a flat test plate. The effect of these different parameters on adiabatic wall effectivenesses, heat transfer coefficients, discharge coefficients and the near-hole velocity field will be addressed. The geometrical parameters of concern include several angles of inclination and rotation of a cylindrical film-cooling hole and two different hole shapes - A fanshaped hole and a laidback fanshaped hole. The fluid dynamic parameters include both the internal and external Mach number as well as the mainstream-to-coolant ratios of total temperature, velocity, mass flux, and momentum flux. In particular, the interaction of a film-cooling jet being injected into a transonic mainstream will be studied. This paper includes a detailed description of the test rig design as well as the measuring techniques. Firstly, tests revealing the operability of the test rig will be discussed. Finally, an outlook of the comprehensive experimental and numerical program will be given.
AB - The emphasis of the present study is to understand the effects of various flowfield and geometrical parameters in the nearfield region of a scaled-up film-cooling hole on a flat test plate. The effect of these different parameters on adiabatic wall effectivenesses, heat transfer coefficients, discharge coefficients and the near-hole velocity field will be addressed. The geometrical parameters of concern include several angles of inclination and rotation of a cylindrical film-cooling hole and two different hole shapes - A fanshaped hole and a laidback fanshaped hole. The fluid dynamic parameters include both the internal and external Mach number as well as the mainstream-to-coolant ratios of total temperature, velocity, mass flux, and momentum flux. In particular, the interaction of a film-cooling jet being injected into a transonic mainstream will be studied. This paper includes a detailed description of the test rig design as well as the measuring techniques. Firstly, tests revealing the operability of the test rig will be discussed. Finally, an outlook of the comprehensive experimental and numerical program will be given.
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U2 - 10.1115/96-GT-222
DO - 10.1115/96-GT-222
M3 - Conference contribution
AN - SCOPUS:84923884749
T3 - ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1996
BT - Heat Transfer; Electric Power; Industrial and Cogeneration
PB - Web Portal ASME (American Society of Mechanical Engineers)
Y2 - 10 June 1996 through 13 June 1996
ER -