AN EXPERIMENTAL INVESTIGATION OF NOZZLE COOLING FOR A SMALL ROCKET ENGINE

Abstract

An investigation was made to determine experimentally the effect of film-cooling a rocket engine nozzle with a reactant gas. Coolant quantities, injection velocities and angles, and axial injection location were varied to determine the conditions under which adequate film cooling could be achieved. Five basic coolant configurations consisting of three De Laval type nozzles and three coolant chamber liners provided coolant injection at the nozzle entrance and/or near the nozzle throat. Decreasing the injection velocity resulted in increased wall temperature reductions so that critical areas of the nozzle could be adequately film cooled.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1963
Accession Number
AD0419544

Entities

People

  • Donald J. Alser

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Combustion
  • Combustion Chambers
  • Combustion Products
  • Energy
  • Engineers
  • Gas Turbine Nozzles
  • Geometry
  • Heat Transfer
  • Heat Transfer Coefficients
  • Jet Propulsion
  • Lepidoptera
  • Measurement
  • Plastic Explosives
  • Rocket Engines
  • Temperature Gradients
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.