Linear analysis of jet-engine core noise based upon high-fidelity combustor and turbine simulations

As further reductions in aircraft engine noise are realized, the relative importance of engine core noise increases. In this study, a computational framework for examining in- direct core noise is proposed, consisting of a representative engine flow-path containing a model gas turbine combustor, a single-stage turbine, a converging nozzle, and free-field radiation. Combined high-fidelity and lower-order simulation techniques are used for each component of the modeled engine. Preliminary, uncoupled results from the combustor and turbine are presented as well as the nozzle-flow simulations. Particular attention is paid to the verification and performance of a linearized Euler solver for predicting the subsonic heated jet flow as well as its far-field acoustic radiation. Two relevant verification tests are shown as well as the nozzle’s response to time-harmonic excitations in both the presence and absence of the mean jet flow over a range of Strouhal numbers. Future work will in- clude coupling the simulations and a more detailed analysis of the mechanisms of core-noise generation and propagation.