Accession Number:

AD0784906

Title:

Combustor Modelling.

Descriptive Note:

Final rept.,

Corporate Author:

SHEFFIELD UNIV (ENGLAND)

Report Date:

1974-03-01

Pagination or Media Count:

16.0

Abstract:

A modelling procedure is presented for the prediction of gas turbine combustor performance. The individual processes of fuel-spray evaporation, homogeneous turbulent mixing, and chemical reaction are combined by means of a partially stirred chemical reactor sequence representing the internal mean flow pattern derived from the geometry of a given combustor. Subsequent tests on the combustor showed satisfactory agreement between experimental and theoretical combustion extinction limits over a wide range of combustor loading. Since the reactor sequence depends on the geometry and is, for example, independent of fuelair ratio these results give confidence that his modelling technique can be applied at all normal operating conditions. Author

Subject Categories:

  • Combustion and Ignition
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE