HEAT TRANSFER THRU UNBOUNDED CERAMIC LINERS AND WALLS OF THE COMBUSTION CHAMBER,

Abstract

Heat transfer through unbonded ceramic liners and walls of the combustion chamber of a ram-jet has been computed by a simplified method for calculating both static and flight conditions. The procedure for calculation is presented and computations are made considering zirconium silicate (ZrSiO4) as a refractory liner. A combination insulator (1/16-inch asbestos plus 1/4-inch ZrSiO4) was found to offer definite advantages for practical application.

Document Details

Document Type
Technical Report
Publication Date
Oct 02, 1947
Accession Number
AD0659109

Entities

People

  • W. J. Bennet

Organizations

  • General Dynamics

Tags

DTIC Thesaurus Topics

  • Asbestos
  • Chambers
  • Chemical Reactions
  • Combustion
  • Combustion Chambers
  • Computations
  • Cooperation
  • Dielectrics
  • Engines
  • Exothermic Reactions
  • Heat Engines
  • Heat Transfer
  • Heat Transfer Devices
  • Ignition
  • Internal Combustion Engines
  • Silicates

Fields of Study

  • Physics

Readers

  • Calculus or Mathematical Analysis
  • Combustion and Flow Dynamics.
  • Surface Engineering/Surface Coating Technology.

Technology Areas

  • Microelectronics