Another Look at the Practical and Theoretical Limits of an Expander Cycle, LOX/H2 Engine

Abstract

Advances in materials and increases in turbopump efficiencies necessitate another look at the theoretical and practical limits for growth in chamber pressure and thrust in a liquid rocket expander cycle engine. The basic equations for turbopump power and heat flux rate out of the cooling jacket are examined to determine the theoretical limits for chamber pressure using an expander cycle. Turbopump efficiencies and operating speed limits for a LOX/H2 expander engine are explored to determine practical limits as applied to the chamber pressure.

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Document Details

Document Type
Technical Report
Publication Date
Jun 16, 1999
Accession Number
ADA409900

Entities

People

  • A. E. Krach
  • A. M. Sutton

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Chambers
  • Combustion
  • Combustion Chambers
  • Energy
  • Engines
  • Equations
  • Flow Rate
  • Heat Exchangers
  • Heat Flux
  • Heat Transfer
  • Heat Transfer Coefficients
  • Hot Gases
  • Mass Flow
  • Materials
  • Military Research

Readers

  • Life Cycle Cost Analysis
  • Rocket Propulsion.
  • Thermal Physics or Thermal Science.