Parallel computation of the flow- and acoustic fields in a gas turbine combustion chamber

Abstract

The chapter presents a parallel solver that is based on domain decomposition and equation decomposition. The primary objective of the chapter is to evaluate the performance of the solver. The solver is used to evaluate the aero-acoustic field in a model gas turbine burner geometry. A parallel solver of a splitting approach for computational aero acoustics (CAA) is also presented in the chapter. The solver is based on a hybrid approach, where the flow field and acoustic fields are computed as separate but coupled processes. The large eddy simulation (LES)-based flow solver is parallelized using a domain decomposition approach. The performance of the solver is evaluated and good parallel performance is obtained. The acoustical solver utilizes the LES data for computing the acoustical sources. The combined solver is successfully applied for the computation of the aero-acoustic field in a model gas turbine combustion chamber.