3D Numerical Studies on Jets Acoustic Characteristics of Chevron Nozzles for Aerospace Applications
The present environmental issues have made aircraft jet noise reduction a crucial problem in aero-acoustics research. Acoustic studies reveal that addition of chevrons to the nozzle reduces the sound pressure level reasonably with acceptable reduction in performance. In this paper comprehensive numerical studies on acoustic characteristics of different types of chevron nozzles have been carried out with non-reacting flows for the shape optimization of chevrons in supersonic nozzles for aerospace applications. The numerical studies have been carried out using a validated steady 3D density based, k-ε turbulence model. In this paper chevron with sharp edge, flat edge, round edge and U-type edge are selected for the jet acoustic characterization of supersonic nozzles. We observed that compared to the base model a case with round-shaped chevron nozzle could reduce 4.13% acoustic level with 0.6% thrust loss. We concluded that the prudent selection of the chevron shape will enable an appreciable reduction of the aircraft jet noise without compromising its overall performance. It is evident from the present numerical simulations that k-ε model can predict reasonably well the acoustic level of chevron supersonic nozzles for its shape optimization.
[1] Bridges, J., Brown, C. A., "Parametric testing of chevrons on single flow hot jets”, AIAA-2004-2824; NASA/TM 2004-213107, 2004.
[2] K.B.M.Q. Zaman, J.E. Bridges and D.L. Huff, "Evolution from 'Tabs' to 'Chevron Technology’ – a Review,” Proceedings of the 13th Asian Congress of Fluid Mechanics 17-21 December 2010, Dhaka, Bangladesh.
[3] Saiyed, N., "Separate flow nozzle test status meeting”, NASA/TM 2000-210524.
[4] Saiyed, N. Mikkelsen K.L. and Bridges, J., 2000. Acoustics and thrust of separate-flow exhaust nozzles with mixing devices for high-bypass-ratio engines, NASA/TM 2000-209948.
[5] Hao Xia, Numerical study of chevron jet noise using parallel flow solver. Science Direct Procedia Engineering 61 ( 2013 ) 40 – 47.
[6] Fan Shi Kong, Heuy Dong Kim, Yingzi Jin and Toshiaki Setoguchi, "Application of Chevron nozzle to a supersonic ejector–diffuser system,” 5th BSME International Conference on Thermal Engineering, Procedia Engineering 56 (2013) 193 – 200.
[7] Khalid, S., Sokhey, J., Chakka, P., and Pierluissi, A., "Ejector/Engine/Nacelle Integration for Increased Thrust minus Drag,” 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Nashville, TN, USA, AIAA-2010-6501, June 2010.
[8] Gregory A. Blaisdell, Anastasios S. Lyrintzis and John P. Sullivan, "Preliminary Design and Computational Analysis of an Ejector Nozzle withChevrons” 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Florida, 2011.
[9] Callendar, B., Gutmark, E. and Martens, S., 2005, "Far-field acoustic investigation into chevron nozzle mechanisms and trends”, AIAA J., 43(1), pp. 87-95.
[10] Callendar, B., Gutmark, E. and Martens, S., 2008, "Nearfield investigation of chevron mechanisms”, AIAA J., 46(1), pp. 36-44.
[11] Calkins F.T., Butler, G and Mabe, J.H , "Variable geometry Chevrons for jet noise reduction,” AIAA Paper 2006-2546, 12th AIAA/CEAS aeroacostic conference, Cambridge, MA, May 8-10, 2006.
[12] Tide P.S and V. Babuy, dynamic and Acoustic Predictions from Chevron Nozzles Using URANS Simulation, 47th AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition 5 - 8 January 2009, Orlando, Florida, AIAA 2009-449.
[13] Engblom, W. A., Khavaran, A., Bridges, J., "Numerical prediction of chevron nozzle noise reducton using WIND-MGBK methodology”,10th AIAA/CEAS Aeroacoustics Conference, UK, AIAA-2004-2979.
[14] Birch, S. F., Lyubimov, D, A., Maslov, V. P., Secundov, A. N., "Noise Predictions for Chevron Nozzle Flows”, 12th AIAA/CEAS Aeroacoustics Conference, Cambridge, AIAA-2006-2600.
[15] Massey, S. J., Elmiligui, A. A., Hunter, C. A., Thomas, R. H., Pao, S. P., Mengle, V. G., "Computational Analysis of a Chevron NozzleUniquely Tailored for Propulsion Airframe Aeroacoustics”, 12th AIAA/CEAS Aeroacoustic Conference, Cambridge, AIAA-2006-2436.
[16] Uzun, A., Hussaini, M. Y., "Noise Generation in the Near-Nozzle Region of a Chevron Nozzle Jet Flow”, 13th AIAA/CEAS AeroacousticConference, Rome, AIAA-2007-3596.
[17] Shur, M. L., Spalart, P. R., Strelets, M. K., Garbaruk, A. V., "Analysis of jet-noise-reduction concepts by large-eddy simulation”, International Journal of Aeroacoustics, Vol.6, No.3, 2007, 243-285.
[18] Massey, S. J., Thomas, R. H., Abdol-Hamid, K. S., Elmiligui, A. A., "Computational and experimental flow field analyses of separate flow chevron nozzles and pylon interaction”, AIAA-2003-3212.
[19] Birch, S. F., Lyubimov, D. A., Secundov, A. N., Yakubovsky, K. Y., "Numerical Modeling Requirements for Coaxial and Chevron Nozzle Flows”, 9th AIAA/CEAS Aeroacoustic Conference and Exhibit, South Carolina, AIAA-2003-3287
[20] Daniel Crunteanu, Petre-Claudiu Cojan, Accoustic characteristics of the flow over different shapes of nozzle chevron, Incas Bulletin, Volume 5, Issue 3/ 2013, pp. 53 – 59 ISSN 2066 – 8201.
[1] Bridges, J., Brown, C. A., "Parametric testing of chevrons on single flow hot jets”, AIAA-2004-2824; NASA/TM 2004-213107, 2004.
[2] K.B.M.Q. Zaman, J.E. Bridges and D.L. Huff, "Evolution from 'Tabs' to 'Chevron Technology’ – a Review,” Proceedings of the 13th Asian Congress of Fluid Mechanics 17-21 December 2010, Dhaka, Bangladesh.
[3] Saiyed, N., "Separate flow nozzle test status meeting”, NASA/TM 2000-210524.
[4] Saiyed, N. Mikkelsen K.L. and Bridges, J., 2000. Acoustics and thrust of separate-flow exhaust nozzles with mixing devices for high-bypass-ratio engines, NASA/TM 2000-209948.
[5] Hao Xia, Numerical study of chevron jet noise using parallel flow solver. Science Direct Procedia Engineering 61 ( 2013 ) 40 – 47.
[6] Fan Shi Kong, Heuy Dong Kim, Yingzi Jin and Toshiaki Setoguchi, "Application of Chevron nozzle to a supersonic ejector–diffuser system,” 5th BSME International Conference on Thermal Engineering, Procedia Engineering 56 (2013) 193 – 200.
[7] Khalid, S., Sokhey, J., Chakka, P., and Pierluissi, A., "Ejector/Engine/Nacelle Integration for Increased Thrust minus Drag,” 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Nashville, TN, USA, AIAA-2010-6501, June 2010.
[8] Gregory A. Blaisdell, Anastasios S. Lyrintzis and John P. Sullivan, "Preliminary Design and Computational Analysis of an Ejector Nozzle withChevrons” 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Florida, 2011.
[9] Callendar, B., Gutmark, E. and Martens, S., 2005, "Far-field acoustic investigation into chevron nozzle mechanisms and trends”, AIAA J., 43(1), pp. 87-95.
[10] Callendar, B., Gutmark, E. and Martens, S., 2008, "Nearfield investigation of chevron mechanisms”, AIAA J., 46(1), pp. 36-44.
[11] Calkins F.T., Butler, G and Mabe, J.H , "Variable geometry Chevrons for jet noise reduction,” AIAA Paper 2006-2546, 12th AIAA/CEAS aeroacostic conference, Cambridge, MA, May 8-10, 2006.
[12] Tide P.S and V. Babuy, dynamic and Acoustic Predictions from Chevron Nozzles Using URANS Simulation, 47th AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition 5 - 8 January 2009, Orlando, Florida, AIAA 2009-449.
[13] Engblom, W. A., Khavaran, A., Bridges, J., "Numerical prediction of chevron nozzle noise reducton using WIND-MGBK methodology”,10th AIAA/CEAS Aeroacoustics Conference, UK, AIAA-2004-2979.
[14] Birch, S. F., Lyubimov, D, A., Maslov, V. P., Secundov, A. N., "Noise Predictions for Chevron Nozzle Flows”, 12th AIAA/CEAS Aeroacoustics Conference, Cambridge, AIAA-2006-2600.
[15] Massey, S. J., Elmiligui, A. A., Hunter, C. A., Thomas, R. H., Pao, S. P., Mengle, V. G., "Computational Analysis of a Chevron NozzleUniquely Tailored for Propulsion Airframe Aeroacoustics”, 12th AIAA/CEAS Aeroacoustic Conference, Cambridge, AIAA-2006-2436.
[16] Uzun, A., Hussaini, M. Y., "Noise Generation in the Near-Nozzle Region of a Chevron Nozzle Jet Flow”, 13th AIAA/CEAS AeroacousticConference, Rome, AIAA-2007-3596.
[17] Shur, M. L., Spalart, P. R., Strelets, M. K., Garbaruk, A. V., "Analysis of jet-noise-reduction concepts by large-eddy simulation”, International Journal of Aeroacoustics, Vol.6, No.3, 2007, 243-285.
[18] Massey, S. J., Thomas, R. H., Abdol-Hamid, K. S., Elmiligui, A. A., "Computational and experimental flow field analyses of separate flow chevron nozzles and pylon interaction”, AIAA-2003-3212.
[19] Birch, S. F., Lyubimov, D. A., Secundov, A. N., Yakubovsky, K. Y., "Numerical Modeling Requirements for Coaxial and Chevron Nozzle Flows”, 9th AIAA/CEAS Aeroacoustic Conference and Exhibit, South Carolina, AIAA-2003-3287
[20] Daniel Crunteanu, Petre-Claudiu Cojan, Accoustic characteristics of the flow over different shapes of nozzle chevron, Incas Bulletin, Volume 5, Issue 3/ 2013, pp. 53 – 59 ISSN 2066 – 8201.
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:67984", author = "R. Kanmaniraja and R. Freshipali and J. Abdullah and K. Niranjan and K. Balasubramani and V. R. Sanal Kumar", title = "3D Numerical Studies on Jets Acoustic Characteristics of Chevron Nozzles for Aerospace Applications", abstract = "The present environmental issues have made aircraft jet noise reduction a crucial problem in aero-acoustics research. Acoustic studies reveal that addition of chevrons to the nozzle reduces the sound pressure level reasonably with acceptable reduction in performance. In this paper comprehensive numerical studies on acoustic characteristics of different types of chevron nozzles have been carried out with non-reacting flows for the shape optimization of chevrons in supersonic nozzles for aerospace applications. The numerical studies have been carried out using a validated steady 3D density based, k-ε turbulence model. In this paper chevron with sharp edge, flat edge, round edge and U-type edge are selected for the jet acoustic characterization of supersonic nozzles. We observed that compared to the base model a case with round-shaped chevron nozzle could reduce 4.13% acoustic level with 0.6% thrust loss. We concluded that the prudent selection of the chevron shape will enable an appreciable reduction of the aircraft jet noise without compromising its overall performance. It is evident from the present numerical simulations that k-ε model can predict reasonably well the acoustic level of chevron supersonic nozzles for its shape optimization.
", keywords = "Supersonic nozzle, Chevron, Acoustic level, Shape Optimization of Chevron Nozzles, Jet noise suppression.", volume = "8", number = "9", pages = "1587-7", }
