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Performance Predictions of Liquid Fuel Ramjet Combustor

M. SRINIVASA RAO, R. VIVEK, DARSHAN KUMAR TRIVEDI, SUNITA DEVI JENA

Abstract


rotating parts. Free stream air is compressed in the intake due to ram effect and allowed into a combustion chamber, where fuel is mixed and combustion takes place. Hot gases, after combustion are exhausted through a convergent-divergent nozzle, generating thrust. Liquid Ramjet (LFRJ) combustor is presently being developed at DRDL, Hyderabad. In order to establish ignition and flame stability of the ramjet combustor, initial design of combustor with four circular intakes is realized and tested. Using the experimental data, CFD analysis was carried out and found that the results obtained from the CFD analysis are in good agreement with that of the experimental values. Various designs of LFRJ combustors are analyses using CFD and the best with 90% C* efficiency is recommended. Proof hardware is realized and tested in connect pipe mode. The engine has been static tested maximum for a duration of 40 seconds wherein stable combustion and flame holding is observed. The combustion efficiency is around 90%. A number of static tests were conducted simulating Sea Level, 5km and 10 km altitude conditions and the flame holder has sustained combustion for these altitude conditions.

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