TY - JOUR
AU1 - Kumar, A.
AU2 - Pisharady, J.
AU3 - Shine, S.
AB - 
Experimental and numerical investigations are carried out to analyze the effect of coolant injector configuration on overall film cooling performance in a divergent section of a rocket nozzle. Two different injector orientations are investigated: (1) shaped slots with a divergence angle of 15° (semi-divergent injector) (2) fully divergent slot (fully divergent injector). A 2-dimensional, axis-symmetric, multispecies computational model using finite volume formulation has been developed and validated against the experimental data. The experiments provided a consistent set of measurements for cooling effectiveness for different blowing ratios ranging from 3.7 to 6. Results show that the semi divergent configuration leads to higher effectiveness compared to fully divergent slot at all blowing ratios. The spatially averaged effectiveness results show that the difference between the two configurations is significant at higher blowing ratios. The increase in effectiveness was around 2 % at BR = 3.7 whereas it was around 12 % in the case of BR = 6. Numerical results show the presence of secondary flow recirculation zones near the jet exit for both the injectors. An additional recirculation zone present in the case of fully divergent injector caused an increase in mixing of the coolant and mainstream, and a reduction in film cooling performance.
TI - Effect of injector configuration in rocket nozzle film cooling
JF - Heat and Mass Transfer
DO - 10.1007/s00231-015-1590-7
DA - 2015-05-21
UR - https://www.deepdyve.com/lp/springer-journals/effect-of-injector-configuration-in-rocket-nozzle-film-cooling-OkZ5xRTpOQ
SP - 727
EP - 739
VL - 52
IS - 4
DP - DeepDyve
ER -