Accession Number : AD0478353


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


Descriptive Note : Technical rept.


Corporate Author : ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN


Personal Author(s) : Hale, J W


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/478353.pdf


Report Date : Feb 1966


Pagination or Media Count : 83


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.


Descriptors :   *LIQUID PROPELLANT ROCKET ENGINES , *ROCKET NOZZLES , *TEST FACILITIES , ALTITUDE CHAMBERS , CONTROLLABLE THRUST ROCKET ENGINES , DESCENT , DIFFUSERS , EXHAUST SYSTEMS , LUNAR CRAFT , MATHEMATICAL MODELS , MODEL TESTS , ROCKET PROPULSION


Subject Categories : Test Facilities, Equipment and Methods
      Liquid Propellant Rocket Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE