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

Jeff O’Brien, Jeonglae Kim, Matthias Ihme

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

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.

Original languageEnglish (US)
Title of host publication53rd AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103438
DOIs
StatePublished - Jan 1 2015
Externally publishedYes
Event53rd AIAA Aerospace Sciences Meeting, 2015 - Kissimmee, United States
Duration: Jan 5 2015Jan 9 2015

Other

Other53rd AIAA Aerospace Sciences Meeting, 2015
CountryUnited States
CityKissimmee
Period1/5/151/9/15

Fingerprint

Jet engines
Combustors
Nozzles
Turbines
Engines
Radiation
Strouhal number
Aircraft engines
Flow simulation
Acoustic fields
Gas turbines

ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

O’Brien, J., Kim, J., & Ihme, M. (2015). Linear analysis of jet-engine core noise based upon high-fidelity combustor and turbine simulations. In 53rd AIAA Aerospace Sciences Meeting [AIAA 2015-1004] American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2015-1004

Linear analysis of jet-engine core noise based upon high-fidelity combustor and turbine simulations. / O’Brien, Jeff; Kim, Jeonglae; Ihme, Matthias.

53rd AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA, 2015. AIAA 2015-1004.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

O’Brien, J, Kim, J & Ihme, M 2015, Linear analysis of jet-engine core noise based upon high-fidelity combustor and turbine simulations. in 53rd AIAA Aerospace Sciences Meeting., AIAA 2015-1004, American Institute of Aeronautics and Astronautics Inc, AIAA, 53rd AIAA Aerospace Sciences Meeting, 2015, Kissimmee, United States, 1/5/15. https://doi.org/10.2514/6.2015-1004
O’Brien J, Kim J, Ihme M. Linear analysis of jet-engine core noise based upon high-fidelity combustor and turbine simulations. In 53rd AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA. 2015. AIAA 2015-1004 https://doi.org/10.2514/6.2015-1004
O’Brien, Jeff ; Kim, Jeonglae ; Ihme, Matthias. / Linear analysis of jet-engine core noise based upon high-fidelity combustor and turbine simulations. 53rd AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA, 2015.
@inproceedings{459fa734b7a145a996b451c90a32fce6,
title = "Linear analysis of jet-engine core noise based upon high-fidelity combustor and turbine simulations",
abstract = "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.",
author = "Jeff O’Brien and Jeonglae Kim and Matthias Ihme",
year = "2015",
month = "1",
day = "1",
doi = "10.2514/6.2015-1004",
language = "English (US)",
isbn = "9781624103438",
booktitle = "53rd AIAA Aerospace Sciences Meeting",
publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",

}

TY - GEN

T1 - Linear analysis of jet-engine core noise based upon high-fidelity combustor and turbine simulations

AU - O’Brien, Jeff

AU - Kim, Jeonglae

AU - Ihme, Matthias

PY - 2015/1/1

Y1 - 2015/1/1

N2 - 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.

AB - 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.

UR - http://www.scopus.com/inward/record.url?scp=84980315238&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84980315238&partnerID=8YFLogxK

U2 - 10.2514/6.2015-1004

DO - 10.2514/6.2015-1004

M3 - Conference contribution

AN - SCOPUS:84980315238

SN - 9781624103438

BT - 53rd AIAA Aerospace Sciences Meeting

PB - American Institute of Aeronautics and Astronautics Inc, AIAA

ER -