Accession Number:

ADA303221

Title:

Numerical Study of a Transpiration Cooled Rocket Nozzle

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1995-12-01

Pagination or Media Count:

92.0

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.

Subject Categories:

  • Thermodynamics
  • Liquid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE