CONVECTIVE HEAT TRANSFER IN ROCKET ENGINES. PART 4. HEAT TRANSFER IN THE COMBUSTION CHAMBER.

Abstract

A boundary layer method previously developed for predicting the heat transfer to rocket nozzles is extended to the prediction of heat transfer rates inside the rocket combustion chamber. The important factor is shown to be the available enthalpy of the partly burned gases in the free stream. A mixing theory is presented which enables the rate of increase of available enthalpy to be calculated. The theory has been applied to some 524 experimental measurements, made over a range of propellent combinations and injector designs, and an overall rms deviation of approximately 15% is obtained. The effects of injector patterns on circumferential heat transfer rates and of combustion instability are also considered. (Author)

Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1969
Accession Number
AD0709307

Entities

People

  • R. C. Parkinson

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Chambers
  • Combustion
  • Combustion Chambers
  • Engines
  • Enthalpy
  • Free Stream
  • Gas Turbine Nozzles
  • Heat Transfer
  • Heat Transfer Devices
  • Injectors
  • Nozzles
  • Rocket Engines
  • Rocket Nozzles
  • Rockets

Fields of Study

  • Physics

Readers

  • Combustion science or combustion engineering.
  • Fluid Dynamics.
  • Rocket Propulsion.