Applications of Model Reduction Techniques in Aerospace Combustors

In this paper we consider some practical applications of model reduction methods in unstable gas turbine and rocket combustion. We explore a set of promising methods for reducing computational burden in large scale LES calculations of unsteady turbulent combustion, as well as define scenarios in which model reduction can be advantageous. Three combustors will be considered here, that have been well documented in recent times. Reduction of the time taken to perform parametric unsteady simulations of a given geometry will be discussed first. Next, we will present our experiences in the use of reduced models as surrogate representations of fuel injectors, and demonstrate multi-injector simulations in which reduced basis models inter-operate with one another and with full numerical computations. This paper will be an empirical exploration of these ideas, while the formal mathematical implications will be discussed in a separate paper.