TY - GEN
T1 - Investigation of the mechanisms of jet-engine core noise using large-eddy simulation
AU - O’Brien, Jeff
AU - Kim, Jeonglae
AU - Ihme, Matthias
N1 - Funding Information:
The authors acknowledge the following award for providing computing and visualization resources that have contributed to the research results reported within this paper: MRI-R2: Acquisition of a Hybrid CPU/GPU and Visualization Cluster for Multidisciplinary Studies in Transport Physics with Uncertainty Quantification. This award is funded under the American Recovery and Reinvestment Act of 2009 (Public Law 111-5). Additional computing resources are provided by the Argonne National Laboratory through the ASCR Leadership Computing Challenge. The first author acknowledges the Stanford Graduate Fellowship program for continued support of this work. The authors are grateful to Prof. Sanjiva Lele for useful discussions. The authors also thank Dr. James Bridges at the NASA Glenn Research Center for sharing the PIV and acoustic measurement data for validation.
Publisher Copyright:
© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA . All rights reserved.
PY - 2016
Y1 - 2016
N2 - As further reductions in aircraft engine noise are realized, the relative importance of reducing engine core noise increases. In this work, a representative engine flow path is studied to examine the mechanisms by which direct and indirect core noise propagate through the engine and affect the farfield noise emerging from the exhaust. The flowpath consists of a model gas turbine combustor, a single-stage turbine, a converging nozzle, a near field jet, and far-field acoustic radiation. A combination of high-fidelity and low-order simulation techniques are used to represent the development and propagation of disturbances through the flowpath. Particular detail is provided for a direct noise calculation of the combustion chamber, as well as an LES calculation of the nozzle and its associated near-field jet. A simple one-way coupling procedure is employed for propagating disturbances from one stage of the calculation to the next, and early results showing the increase in farfield jet noise due to upstream core noise effects are presented. Future work will include higher fidelity representations of the turbine stage, a more refined approach to the coupling procedure, and attempts to distinguish the effects of direct and indirect core noise on the farfield acoustic radiation.
AB - As further reductions in aircraft engine noise are realized, the relative importance of reducing engine core noise increases. In this work, a representative engine flow path is studied to examine the mechanisms by which direct and indirect core noise propagate through the engine and affect the farfield noise emerging from the exhaust. The flowpath consists of a model gas turbine combustor, a single-stage turbine, a converging nozzle, a near field jet, and far-field acoustic radiation. A combination of high-fidelity and low-order simulation techniques are used to represent the development and propagation of disturbances through the flowpath. Particular detail is provided for a direct noise calculation of the combustion chamber, as well as an LES calculation of the nozzle and its associated near-field jet. A simple one-way coupling procedure is employed for propagating disturbances from one stage of the calculation to the next, and early results showing the increase in farfield jet noise due to upstream core noise effects are presented. Future work will include higher fidelity representations of the turbine stage, a more refined approach to the coupling procedure, and attempts to distinguish the effects of direct and indirect core noise on the farfield acoustic radiation.
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U2 - 10.2514/6.2016-0761
DO - 10.2514/6.2016-0761
M3 - Conference contribution
AN - SCOPUS:85007557092
SN - 9781624103933
T3 - 54th AIAA Aerospace Sciences Meeting
BT - 54th AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 54th AIAA Aerospace Sciences Meeting, 2016
Y2 - 4 January 2016 through 8 January 2016
ER -