DIFFUSER AUXILIARY EJECTOR DEVELOPMENT FOR THE DESIGN OF THE J-3 LEM DESCENT EXHAUST SYSTEM

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Abstract
A four-phase investigation was conducted to select a rocket engine diffuser auxiliary ejector configuration. The configuration was required to maintain test cell pressure sufficiently low to keep the rocket engine nozzle flowing full at 10% of full power while operating against an exit pressure of approximately 1.50 psia. The investigation was in support of the LEM Descent test program scheduled for the J-3 test cell. The annular-type auxiliary ejector was selected because of its superior performance over the centerbody- type ejector. A successful model rocket engine throttling demonstration to 10% of full power was made with the annular-type auxiliary ejector. An ejector second throat (having a contraction area ratio of 0.62) was used to increase the limiting diffuser exit pressure. Pressure distribution through the J-3 model ducting was obtained at various exhaust header pressures.

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