Development and Test of an Advanced Expander Combustor

Abstract

This paper discusses development and test of an advanced expander combustion chamber for a 50,000 pound (222.4 kN) thrust Upper Stage Expander Cycle Engine. The chamber is 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 Propulsion Technology (IHPRPT) program. The Advanced Expander Combustor is designed to provide increased heat pick-up to the coolant and improved system thrust to weight, increased specific impulse, and increased reliability. These benefits will be accomplished and demonstrated through design, development, and test of this high heat flux, compact thrust chamber capable of supporting a chamber pressure of 1375 psia (97 kg/sq cm in an expander cycle configuration.

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Document Details

Document Type
Technical Report
Publication Date
Jun 24, 1999
Accession Number
ADA408493

Entities

People

  • A. Minick
  • S. Fentress
  • S. Peery
  • T. Jennings

Organizations

  • Pratt & Whitney

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Aluminum Oxides
  • Combustion
  • Combustion Chambers
  • Combustors
  • Copper Alloys
  • Energy
  • Fabrication
  • Heat Transfer
  • Liquid Oxygen
  • Manufacturing
  • Materials
  • Rocket Engines
  • Rocket Propulsion
  • Test Facilities
  • Thrust Chambers

Fields of Study

  • Physics

Readers

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

Technology Areas

  • Space
  • Space - Hall-Effect Thruster