Design and Test Results of an Advanced Liquid Hydrogen Turbopump

Abstract

This paper discusses the design, the test facility, and the test results of an Advanced Liquid Hydrogen Turbopump for a 30,000 pound (22,679 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 lb m/sec (7.3 kg/sec.) of liquid hydrogen at 4600 psia (323.4 kg/sq cm).

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jun 15, 1999
Accession Number
ADA404890

Entities

People

  • A. Minick
  • G. Crease
  • Jaeheung Park
  • R. Lyda

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Biomedical
  • Sensors
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Axial Loads
  • Computational Fluid Dynamics
  • Contracts
  • Control Systems
  • Films
  • Flow Rate
  • Fluid Dynamics
  • Fluid Mechanics
  • Instrumentation
  • Liquid Hydrogen
  • Liquid Oxygen
  • Measurement
  • Military Research
  • Pressure Regulators
  • Test Facilities

Readers

  • Internal Combustion Engine (ICE) Technology.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster