Orbital transfer vehicle oxygen turbopump technology. Volume 1: Design, fabrication, and hydrostatic bearing testing. Final Report

Technical Report · Sat Dec 01 00:00:00 EST 1990

OSTI ID:5682327

Buckmann, P S; Hayden, W R; Lorenc, S A; Sabiers, R L; Shimp, N R

The design, fabrication, and initial testing of a rocket engine turbopump (TPA) for the delivery of high pressure liquid oxygen using hot oxygen for the turbine drive fluid are described. This TPA is basic to the dual expander engine which uses both oxygen and hydrogen as working fluids. Separate tasks addressed the key issue of materials for this TPA. All materials selections emphasized compatibility with hot oxygen. The OX TPA design uses a two-stage centrifugal pump driven by a single-stage axial turbine on a common shaft. The design includes ports for three shaft displacement/speed sensors, various temperature measurements, and accelerometers.

• Research Organization: GenCorp, Sacramento, CA (United States)
• OSTI ID: 5682327
• Report Number(s): N-91-19174; NASA-CR-185175; NAS-1.26:185175; AEROJET-2459-54-2-VOL-1; CNN: NAS3-23772
• Country of Publication: United States
• Language: English

Related Subjects

71 CLASSICAL AND QUANTUM MECHANICS
GENERAL PHYSICS
CRYOPUMPS
DESIGN
LIQUEFIED GASES
PUMP TURBINES
ACCELEROMETERS
BALL BEARINGS
CENTRIFUGAL PUMPS
HYDROGEN
HYDROSTATICS
OXYGEN
SHAFTS
WORKING FLUIDS
BEARINGS
ELEMENTS
EQUIPMENT
FLUIDS
HYDRAULIC TURBINES
LABORATORY EQUIPMENT
MACHINE PARTS
MACHINERY
MEASURING INSTRUMENTS
NONMETALS
PUMPS
TURBINES
TURBOMACHINERY
VACUUM PUMPS
420201* - Engineering- Cryogenic Equipment & Devices