Combustor Modelling.
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 fuel/air ratio) these results give confidence that his modelling technique can be applied at all normal operating conditions. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1974
- Accession Number
- AD0784906
Entities
People
- I. Poll
- J. Swithenbank
- M. W. Vincent
- R. Payne
Organizations
- University of Sheffield