Laser Ignition of Oxygen-Hydrocarbon Fuels in Rocket Engines

The article examines the main results of the studies of implementing laser ignition in rocket engines operating on oxygen-hydrocarbon fuels. It defines requirements to laser ignition systems and operating ranges of combustion chambers with regard to the pressure, composition and consumption of the fuel mixture to provide stable ignition in ignition devices, thrusters as well as model and full-scale combustion chambers. Spark ignition by optical breakdown in the area with favourable characteristics for the initiation of combustion is used as an ignition method. Laser radiation is focused either in the fuel mixture or near the metal surface. Based on the test results, the feasibility of laser ignition on small-size combustion chambers, with the volume of several cubic centimetres, as well as cruise engines using small-size lasers installed directly on these chambers is shown. The data obtained is used for developing recommendations for testing laser ignition on large-size combustion chambers of rocket engines.

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