Laser Ignition of Hydrocarbon Rocket Engine Combustion Chambers

Development of electro-optically controlled, rapidly multiplexed laser induced plasma to ignite one or more preburner or main-chambers, synchronize multiple chamber firings, and dampen impending combustion instabilities is proposed. CFDRC has teamed with Los Alamos National Laboratory (LANL) to measure laser energy and multiplexing requirements, Q-switching specifications, beam quality, and focal point locations of laser ignition in a GOx/CH4 combustion chamber. Phase I evaluation will include: 1. Demonstration of a prototype rapid-multiplexed laser initiator; 2. Analytical and experimental characterization of a single element GOx/CH4 laser ignition process using corroborating transient CFD and CCD camera photography; and 3. Assessment of commercial grade solid state lasers, and optics/windows followed by mechanical layout of a laser ignition system in an Air Force selected LOx/CH4 RBCC combustion system installation. Comparisons of the CFD simulation and CCD camera photography will generate breakthrough insights into the GOx/CH4 ignition process. With consulting from WASK Engineering, CFDRC will focus on supporting laser-based LOx/CH4 combustion chamber ignition at one or more engine system manufacturers (i.e. Boeing, Aerojet or P&W) during Phase II.