Accession Number : ADA265708


Title :   Orbital Transfer Vehicle Oxygen Turbopump Technology. Volume 3. Hot Oxygen Testing


Descriptive Note : Final rept. 17 Jul-31 Dec 89,


Corporate Author : AEROJET PROPULSION DIV SACRAMENTO CA


Personal Author(s) : Urke, Robert L


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a265708.pdf


Report Date : May 1992


Pagination or Media Count : 94


Abstract : This report covers the work done in preparation for a liquid oxygen rocket engine turbopump test utilizing high pressure hot oxygen gas for the turbine drive. The turbopump (TPA) is designed to operate with 400 deg F oxygen turbine drive gas. The goal of this test program was to demonstrate the successful operation of the TPA under simulated engine conditions including the hot oxygen turbine drive. This testing follows a highly successful series of tests pumping liquid oxygen with gaseous nitrogen as the turbine drive gas. That testing included starting of the TPA with no assist to the hydrostatic bearing. The bearing start entailed a rubbing start unfit the pump generated enough pressure to support the bearing. The articulating, self-centering hydrostatic bearing exhibited no bearing load or stability problems. The TPA was refurbished for the hot gas drive tests and facility work was begun, but unfortunately funding cuts prohibited the actual testing.... Oxygen turbopump, Hydrostatic bearings, Expander cycle engine, Cryogenic propellant pumping, Hot oxygen gas turbine drive.


Descriptors :   *LIQUID OXYGEN , *ROCKET ENGINES , *TURBOPUMPS , BEARINGS , CRYOGENIC PROPELLANTS , CYCLES , ENGINES , GAS TURBINES , HIGH PRESSURE , HYDROSTATICS , OXYGEN , PROPELLANTS , PUMPS , STABILITY , TEST AND EVALUATION , TURBINES


Subject Categories : Pumps, Filters, Pipes, Tubing, Fittings & Vlvs
      Rocket Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE