Four firings of the rocketdyne J-2 rocket engine were conducted in Test Cell J-4 of the Large Rocket Facility. These firings were accomplished during test period J4-1801-07 at pressure altitudes ranging from 89,000 to 106,000 ft at engine start. The objectives of the test included the evaluation of the effect of start tank energy on the oxidizer pump spin speed and the effect of thrust chamber temperature on the fuel pump high level stall margin. Firing 07A was conducted with 12 experimental oxidizer pump primary seal drain tubes attached to the engine. The accumulated firing duration for this test period was 66.5 sec. (Author)
Altitude Developmental Testing of the J-2 Rocket Engine in Propulsion Engine Test Cell (J-4) (Test J4-1801-07)
1968
101 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Liquid propellant rocket engines , Captive tests , Combustion chambers , Fuel injectors , Turbopumps , Instrumentation , Liquid rocket oxidizers , Guided missile silos , Test facilities , Fuel systems , Pressure , Velocity , Performance(Engineering) , Gas generating systems , Fluid flow , Valves , J-2 engines , Saturn launch vehicles