Design and Development of an Advanced Liquid Hydrogen Turbopump

Abstract

This paper discusses design and development of an Advanced Liquid Hydrogen Turbopump for a 50,000 pound (22,6?9 kg) 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).

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1998
Accession Number
ADA406213

Entities

People

  • A. Minick
  • S. Peery

Organizations

  • Pratt & Whitney

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Assembly
  • Computational Fluid Dynamics
  • Engines
  • Films
  • Fluid Dynamics
  • Frequency
  • Heat Transfer
  • Liquid Hydrogen
  • Liquid Oxygen
  • Manufacturing
  • Materials
  • Military Research
  • Modal Analysis
  • Resonant Frequency
  • Turbines

Readers

  • Combustion and Flow Dynamics.
  • Internal Combustion Engine (ICE) Technology.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster