Evaluation of temperature profile of a cryogenic engine igniter body during engine operation and coasting phase prior to engine restart

Combustion of propellants (liquid oxygen and liquid hydrogen) in the combustion chamber is initiated by an igniter cartridge using a pyrogenic ignition source in cryogenic engines of ISRO. In order to launch multiple satellites in different orbits in a single mission, it is required to re-start the engine. The evaluation of the thermal profile of the igniter is necessary to simulate the thermal environment of the igniter at the time of re-start. The evaluation of the thermal profile of two options of ignition device configured for engine re-start is studied. Transient heat transfer models were generated for two options considered. The model was validated using measured data of ground test for a typical cryogenic engine. The transient heat transfer environment of the igniter during engine operation and coasting phase was simulated. The thermal environment for qualification of the igniter for both the options was evaluated from the simulation results.