J-GLOBAL ID:201110033878674452   Research Resource code:5000002710 Update date:Jan. 11, 2005

High Pressure LOX Turbopump Test Facility

Owning Organization:
Contact: SHIMURA Takashi
Resource classification: Experience equipment, Facilities, etc
Research area  (1): Fluidics
Purpose: Tests of Lox Turbopumps for Large-Sized
High Pressure Rocket Engines.
Performance: Thrust Maximum 1000kN
Tank Capacity 1.5MPa,10m3
Flowrate 0.2m3(Maximum)
Outlet Pressure 33MPa(Maximum)
Gas Generator LOX. GH2
Turbine Driver Gas 16kg/s (Maximum)
Turbine Inlet Pressure
24MPa (Maximum)
Built: 1985
Research field : Rocket Engine Turbopumps<br>
User environment and conditions:
Test Models
User procedures and method:
-Procedure of Use
Inquire details from the Program Support Division

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