The current work presents an experimental parametric study on tangential, supersonic film cooling in the expansion part of a conical nozzle. For simulating rocket-engine-like hot gas conditions, the nozzle is attached to a detonation tube providing hydrogen-oxygen combustion gas at high stagnation pressures and temperatures. The Mach number of the hot gas at the point of injection is about , whereas the coolant is injected at Mach numbers of . Within the presented study the coolant injection conditions, the hot gas conditions, and the coolant gases are varied to determine the influence of different parameters on film cooling behavior. The results indicate that film cooling effectiveness massively depends on the blowing ratio and slot height. Film cooling efficiency is also found to depend on the coolant gas heat capacity, molar mass, and the density and velocity ratio of coolant and hot gas at the point of injection. To compare the experimental data the film cooling efficiencies are calculated using the measured wall heat fluxes and a newly developed, simple approach for the calculation of heat transfer coefficients. For a theoretical investigation of the experimental results the common Goldstein model is extended for axisymmetric flows. Finally, the gained experimental data are correlated by the extended Goldstein model.
Experimental Investigations of Film Cooling in a Conical Nozzle Under Rocket-Engine-Like Flow Conditions
AIAA Journal ; 57 , 3 ; 1172-1183
2019-03-01
Conference paper , Article (Journal)
Electronic Resource
English
British Library Conference Proceedings | 2018
|Secondary gas injection in conical rocket nozzle
Engineering Index Backfile | 1963
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