Publication Date:
2019-07-13
Description:
A model is formulated for estimating the performance and chamber heat transfer in rocket injectors/chambers operating with gaseous H2-O2 propellants. The model quantifies the combustion performance and chamber heat flux for variables such as chamber length, element type, element area ratio, impingement angle, thrust/element, mixture ratio, moment ratio, element spacing, and physical size. Design equations are given and curves are plotted for evaluation of combustion performance in injectors comprised of F-O-F triplet, premix, coaxial and swirl coaxial element types. Curve plots and equations are also included for estimation of the chamber wall heat fluxes generated by these element types.
Keywords:
PROPULSION SYSTEMS
Type:
AIAA PAPER 73-1242
,
Propulsion Conference; Nov 05, 1973 - Nov 07, 1973; Las Vegas, NV; US
Format:
text
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