Numerical Study of a Transpiration Cooled Rocket Nozzle

Abstract

This study proved that transpiration cooling provides a better cooling scheme than regenerative cooling for long operating duration, liquid-fueled rocket engine nozzles. This proof was made on the basis of maximum wall temperature. This study compared transpiration cooling to regenerative cooling in the throat region of the Space Shuttle Main Engine Main Combustion Chamber. The study also analyzed the effects of porosity, solid thermal conductivity, and porous sphere size on a porous wall made of packed spheres. The transpiration cooled nozzle operated 35% cooler than a regeneratively cooled nozzle, but the temperature gradient at the hot gas surface was 72 times greater than the regeneratively cooled nozzle.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1995
Accession Number
ADA303221

Entities

People

  • Jay A. Landis

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Combustion
  • Combustion Chambers
  • Energy Transfer
  • Engineering
  • Fluids
  • Gas Turbine Nozzles
  • Heat Transfer
  • Hot Gases
  • Porous Materials
  • Regenerative Cooling
  • Rocket Engines
  • Space Shuttles
  • Temperature Gradients
  • Thermal Conductivity
  • Thermodynamic Properties

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster