Liquid rocket engine combustion stabilization devices, NASA SPACE VEHICLE DESIGN CRITERIA (Chemical)

NASA/SP-8113, Liquid rocket engine combustion stabilization devices, NASA SPACE VEHICLE DESIGN CRITERIA (Chemical), NASA (Washington, DC, United States), November,1974, pp. 127, Format(s): PDF 8241k

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Combustion instability, which results from a coupling of the combustion process and the fluid dynamics of the engine system, was investigated. The design of devices which reduce coupling (combustion chamber baffles) and devices which increase damping (acoustic absorbers) are described. Included in the discussion are design criteria and recommended practices, structural and mechanical design, thermal control, baffle geometry, baffle/engine interactions, acoustic damping analysis, and absorber configurations.

Keywords:	propellants and fuels, combustion stability, liquid propellant rocket engines, propellant combustion, absorbers (equipment), baffles, combustion chambers, design analysis, temperature control, thrust vector control
CASI Document ID Number:	75N28247
Subjects:	Astronautics: Spacecraft Propulsion And Power: Rocket Engines, Nozzles And Thrust Chambers
ID Code:	162
Deposited On:	23 May 2002