Project Title:

A New Unsteady Mixing Model to Predict NOx Production During Rapid Mixing in a Dual

01.01-9500
900831
A New Unsteady Mixing Model to Predict NOx Production During Rapid Mixing in a Dual

Abstract:

Stage Combustor
An advanced gas turbine engine to power supersonic transport aircraft is currently
under study. In addition to high combustion efficiency requirements, environmental
concerns have placed stringent restrictions on the pollutant emissions from these
engines. A combustor design with the potential for minimizing pollutants such as
NOx emissions is undergoing experimental evaluation. A major technical issue in the
design of this combustor is how to rapidly mix the hot fuel-rich primary zone product
with the secondary diluent air to obtain a fuel-lean mixture for combustion in the
secondary stage. Numerical predictions using steady-state methods cannot account
for the unsteady phenomena in the mixing region. Therefore, this project is addressing
a novel unsteady mixing model that can be used to evaluate mixing and combustion,
including NO production within the mixing region,  This model will be developed to
be used in conjunction with steady-state prediction methods and thus will have the
potential for providing an improved engineering design analysis tool. The capability
of this model will be demonstrated in Phase I with the eventual objective of coupling
the model to a steady-state solver in Phase II.
The model of unsteady mixing in realistic gas turbine combustors can be utilized
for a variety of design and analysis work both by the government and by the engine
manufacturing industry.
NOx production, rapid mixing, linear eddy, combustion, turbulent mixing, finite-rate
kinetics, entrainment, molecular diffusion