Accession Number:
AD0870534
Title:
Altitude Developmental Testing of the J-2S Rocket Engine in Rocket Development Test Cell (J-4) (Tests J-4-1902-13 through J4-1902-15)
Descriptive Note:
Final rept.
Corporate Author:
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
Personal Author(s):
Report Date:
1970-06-01
Pagination or Media Count:
110.0
Abstract:
Seven firings of the J-2S rocket engine SN J-112-1C were conducted. The major objectives of these test periods were 1 to determine a method of increasing fuel turbine inlet temperature in order to prevent turbine icing and attain stable high thrust idle-mode operation, and 2 to demonstrate post-main-stage transition to low thrust idle model. Changes in injector mixture ratio during high thrust idle-mode operation from 1.55 to 2.02 increased inlet temperature, in general, from 85 to 190 deg F for the fuel turbine, and from 45 to 95 deg F for the oxidizer turbine. Stable high thrust idle-mode operation was attained on five firings which had fuel turbine inlet temperatures above 160 deg F. Satisfactory transition to post-main-stage low thrust idle mode was accomplished.
Descriptors:
- *LIQUID PROPELLANT ROCKET ENGINES
- ALTITUDE
- ALTITUDE CHAMBERS
- CAPTIVE TESTS
- COMBUSTION CHAMBERS
- CRYOGENIC PROPELLANTS
- DUCT INLETS
- FUEL INJECTION
- FUEL INJECTORS
- HIGH ALTITUDE
- HYDROGEN
- ICE PREVENTION
- INTERIOR BALLISTICS
- LAUNCH VEHICLES
- LIQUEFIED GASES
- LIQUID ROCKET FUELS
- LIQUID ROCKET OXIDIZERS
- OXYGEN
- PERFORMANCE(ENGINEERING)
- PROPELLANT CONTROL
- SIMULATION
- TEMPERATURE CONTROL
- THROTTLING
- THRUST
- TURBINES
- TURBOPUMPS
Subject Categories:
- Liquid Propellant Rocket Engines