EVAPORATION AND COMBUSTION OF A SINGLE-COMPONENT FUEL IN A CHAMBER OF A LIQUID ROCKET ENGINE ZHRD

Abstract

An evaporation and combustion theory of a singlecomponent liquid fuel in a ZhRD chamber was developed, which permits certain conclusions on the effect of spraying parameters as well as the physical properties of fuels and combustion products on the chamber and its characteristics. By decreasing the size of the drops, the combustion zone length in ZhRD chamber decreases. When the evaporation rate of very fine sprays becomes greater than the mass velocity because of microdiffusional turbulene combustion, the theory does not apply. With an increase of the liquid-fuel ass flow and heat conductivity of gases, the evaporation and combustion rates rise, but with the growth of gases' heat capacity and viscosity and the elevation of the fuel s density, the evaporation and combustion rates decrease. The calculated zone length for the evaporation and combustion of drops of a single-component or a previously intermixed liquid fuel is close t the length of a ZhRD chamber. (Author)

Document Details

Document Type
Technical Report
Publication Date
Aug 28, 1961
Accession Number
AD0264509

Entities

People

  • S.m. Il'yashenko

Organizations

  • National Air and Space Intelligence Center

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Burning Rate
  • Combustion
  • Combustion Products
  • Conductivity
  • Evaporation
  • Heat Capacity
  • Heat Energy
  • Mechanical Properties
  • Physical Properties
  • Rocket Engines
  • Thermal Conductivity
  • Viscosity

Fields of Study

  • Physics

Readers

  • Internal Combustion Engine (ICE) Technology.
  • Petroleum Engineering
  • Surface Engineering/Surface Coating Technology.