This paper discusses design and development of an Advanced Liquid Hydrogen Turbopump for a 50,000 pound thrust Upper Stage Expander Cycle Engine being developed by Pratt & Whitney Liquid Space Propulsion under contract for the United States Air Force Research Laboratory (AFRL) to support the Integrated High Payoff Rocket Technology (IHPRPT) program. The Advanced Liquid Hydrogen Turbopump is designed to provide improved system thrust to weight, decreased hardware/support costs, and increased reliability. These benefits will be accomplished and demonstrated through design, development, and test of this high speed, high efficiency, two stage hydrogen turbopump capable of supplying 16 lbm/sec (7.3 kg/sec.) of liquid hydrogen at 4600 psia (323.4 kg/ sq cm).
Design and Development of an Advanced Liquid Hydrogen Turbopump
1998
13 pages
Report
No indication
English
Rocket Engines & Motors , Manufacturing, Planning, Processing & Control , Liquid propellant rocket engines , Turbopumps , Cost analysis , Reliability , Weight , Liquid rocket fuels , Liquid hydrogen , Thrust , Space propulsion , Upper stage expander cycle engines , Ihprpt(Integrated high payoff rocket propulsion technology)
Advanced liquid oxygen turbopump design and development
AIAA | 2000
|ADVANCED LIQUID OXYGEN TURBOPUMP DESIGN AND DEVELOPMENT
British Library Conference Proceedings | 2000
|Testing of an advanced liquid hydrogen turbopump
AIAA | 2000
|Testing of an Advanced Liquid Hydrogen Turbopump
NTIS | 2000
|