Hostname: page-component-586b7cd67f-t7czq Total loading time: 0 Render date: 2024-11-23T15:16:40.808Z Has data issue: false hasContentIssue false

Physical processes influencing acoustic radiation from jet engine inlets

Published online by Cambridge University Press:  14 May 2013

Christopher K. W. Tam*
Affiliation:
Department of Mathematics, Florida State University, Tallahassee, FL 32306-4510, USA
Sarah A. Parrish
Affiliation:
Department of Mathematics, Florida State University, Tallahassee, FL 32306-4510, USA
Edmane Envia
Affiliation:
NASA Glenn Research Center, Cleveland, OH 44135, USA
Eugene W. Chien
Affiliation:
Goodrich Aerostructures Group, Chula Vista, CA 91910, USA
*
Email address for correspondence: [email protected]

Abstract

Numerical simulations of acoustic radiation from a jet engine inlet are performed using advanced computational aeroacoustics algorithms and high-quality numerical boundary treatments. As a model of modern commercial jet engine inlets, the inlet geometry of the NASA Source Diagnostic Test is used. Fan noise consists of tones and broadband sound. This investigation considers the radiation of tones associated with upstream-propagating duct modes. The primary objective is to identify the dominant physical processes that determine the directivity of the radiated sound. Two such processes have been identified. They are acoustic diffraction and refraction. Diffraction is the natural tendency for an acoustic duct mode to follow a curved solid surface as it propagates. Refraction is the turning of the direction of propagation of a duct mode by mean flow gradients. Parametric studies on the changes in the directivity of radiated sound due to variations in forward flight Mach number, duct mode frequency, azimuthal mode number and radial mode number are carried out. It is found there is a significant difference in directivity for the radiation of the same duct mode from an engine inlet when operating in static condition versus one in forward flight. It will be shown that the large change in directivity is the result of the combined effects of diffraction and refraction.

Type
Papers
Copyright
©2013 Cambridge University Press 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

Achunche, I., Astley, J., Sugimoto, R. & Kempton, A. 2009 Prediction of forward fan noise propagation and radiation from intakes. AIAA Paper 2009-3239.CrossRefGoogle Scholar
Ahuja, V., Ozyoruk, Y. & Long, L. N. 2000 Computational simulations of fore and aft radiation from ducted fans. AIAA Paper 2000-1943.CrossRefGoogle Scholar
Astley, R. J., Hamilton, J. A., Baker, N. & Kitchen, E. H. 2002 Modelling tone propagation from turbofan inlets – the effect of extended lip liners. AIAA Paper 2002-2449.Google Scholar
Baumeister, K. J. & Horowitz, S. J. 1984 Finite element-integral acoustic simulation of JT15D turbofan engine. Trans. ASME: J. Vib. Acoust. Stress Reliab. Design 106, 405413.Google Scholar
Callender, B., Janardan, B., Uellenberg, S., Premo, J., Kwan, H. W. & Abeysinghe, A. 2007 The Quiet Technology Demonstrator program: static test of an acoustically smooth inlet. AIAA Paper 2007-3671.CrossRefGoogle Scholar
Candel, S. M. 1973 Acoustic radiation from the end of a two-dimensional duct, effects of uniform flow and duct lining. J. Sound Vib. 28, 113.Google Scholar
Cantrell, R. H. & Hart, R. W. 1964 Interaction between sound and flow in acoustic cavities: mass, momentum and energy considerations. J. Acoust. Soc. Am. 36, 697706.Google Scholar
Dougherty, R. P. 1996 Nacelle acoustic design by ray tracing in three dimensions. AIAA Paper 96-1773.Google Scholar
Eversman, W., Parrett, A. V., Preisser, J. S. & Silcox, R. J. 1985 Contributions to the finite element solution of the fan noise radiation problem. Trans. ASME 107, 216223.Google Scholar
Ffowcs Williams, J. E. & Hawkings, D. L. 1969 Sound generation by turbulence and surfaces in arbitrary motion. Proc. R. Soc. Lond. A 264, 321342.Google Scholar
Heidelberg, L. 2002 Fan noise source diagnostic test – tone modal structure results. AIAA Paper 2002-2428.Google Scholar
Heidelberg, L. J., Rice, E. J. & Homyak, J. 1981 Acoustic performance of inlet suppressors on an engine generating a single mode. AIAA Paper 81-1965.CrossRefGoogle Scholar
Heidmann, M. F., Saule, A. V. & McArdle, J. G. 1980 Predicted and observed modal radiation pattern from JT15D engine with inlet rods. J. Aircraft 17, 493499.Google Scholar
Herkes, W. H., Olser, R. F. & Uellenberg, S. 2006 The Quiet Technology Demonstrator program: flight validation of airplane noise-reduction concepts. AIAA Paper 2006-2720.Google Scholar
Homicz, G. F. & Lordi, J. A. 1975 A note on the radiative directivity patterns of duct acoustic modes. J. Sound Vib. 41, 283290.Google Scholar
Hu, F. Q. 2001 A stable perfectly matched layer for linearized Euler equations in unsplit physical variables. J. Comput. Phys. 173, 455480.Google Scholar
Hu, F. Q. 2008 Development of PML absorbing boundary conditions for computational aeroacoustics: a progress review. Comput. Fluids 37, 336348.Google Scholar
Kempton, A. J. & Smith, M. G. 1982 Ray theory predictions of sound radiation from realistic engine intakes. AIAA Paper 81-1982.CrossRefGoogle Scholar
Lan, J., Premo, J., Zlavog, G., Bread, C., Callender, B. & Martinez, M. 2007 Phased array measurements of full-scale engine inlet noise. AIAA Paper 2007-3434.Google Scholar
Lansing, D. L. 1970 Exact solution for radiation of sound from a semi-infinite circular duct with application to fan and compressor noise. Analytic Methods in Aircraft Aerodynamics, NASA SP-228, pp. 323–334.Google Scholar
Lyrintzis, A. S. 2003 Surface integral methods in computational aeroacoustics – from the (CFD) near-field to the (acoustic) far-field. Intl J. Aeroacoust. 2, 95128.Google Scholar
Ozyoruk, Y. 2002 Parallel computation of forward radiated noise of ducted fans including acoustic treatment. AIAA J. 40, 450455.Google Scholar
Ozyoruk, Y., Ahuja, V. & Long, L. N. 2001 Time domain simulations of radiation from ducted fans with liners. AIAA Paper 2001-2171.Google Scholar
Ozyoruk, Y., Alpman, E., Ahuja, V. & Long, L. N. 2004 Frequency-domain prediction of turbofan noise radiation. J. Sound Vib. 270, 933950.Google Scholar
Ozyoruk, Y. & Long, L. N. 1996 Computation of sound radiation from engine inlets. AIAA J. 34, 894901.CrossRefGoogle Scholar
Parrett, A. & Eversman, W. 1986 Wave envelope and finite element approximation for turbofan noise radiation in flight. AIAA J. 24, 753760.Google Scholar
Pilon, A. R. & Lyrintzis, A. S. 1998 Development of an improved Kirchhoff method for jet aeroacoustics. AIAA J. 36, 783790.Google Scholar
Preisser, J. S., Silcox, R. J., Eversman, W. & Parrettt, A. V. 1985 Flight study of induced turbofan acoustic radiation with theoretical comparisons. J. Aircraft 22, 5762.Google Scholar
Premo, J., Bread, C. & Lan, J. 2007 Prediction of the inlet splice effects from the QDT2 static test. AIAA Paper 2007-3544.Google Scholar
Premo, J. & Joppa, P. 2002 Fan noise source diagnostic test – wall measured circumferential array mode results. AIAA Paper 2002-2429.Google Scholar
Reba, R. A., Narayana, S., Colonius, T. & Suzuki, T. 2005 Modelling jet noise from organized structures using near-field hydrodynamics pressure. AIAA Paper 2005-3093.Google Scholar
Reba, R. A., Simonich, J. & Schlinker, R. 2008 Measurement of source wave-packets in high- speed jets and connection to far-field sound. AIAA Paper 2008-2891.CrossRefGoogle Scholar
Rice, E. J., Heidmann, M. F. & Sofrin, T. G. 1979 Modal propagation angles in a cylindrical duct with flow and their relation to sound radiation. AIAA Paper 79-0183.CrossRefGoogle Scholar
Roy, I. D. & Eversman, W. 1995 Improved finite element modelling of the turbofan engine inlet radiation problem. Trans. ASME: J. Vib. Acoust. 117, 109115.Google Scholar
Shen, H. & Tam, C. K. W. 2002 Three-dimensional numerical simulation of the jet screech phenomenon. AIAA J. 36, 3341.Google Scholar
Tam, C. K. W. 1998 Advances in numerical boundary conditions for computational aeroacoustics. J. Comput. Acoust. 6, 377402.Google Scholar
Tam, C. K. W. 2012 Computational Aeroacoustics: a Wavenumber Approach. Cambridge University Press.Google Scholar
Tam, C. K. W. & Dong, Z. 1996 Radiation and outflow boundary conditions for direct computation of acoustic and flow disturbances in a non-uniform mean flow. J. Comput. Acoust. 4, 175201.Google Scholar
Tam, C. K. W. & Hu, F. Q. 2004 An optimized multi-dimensional interpolation scheme for computational aeroacoustics applications using overset grid. AIAA Paper 2004-2812.Google Scholar
Tam, C. K. W. & Ju, H. 2012 Airfoil tones at moderate Reynolds number. J. Fluid Mech. 690, 536570.CrossRefGoogle Scholar
Tam, C. K. W. & Kurbatskii, K. A. 2003 Multi-size-mesh multi-time step dispersion relation preserving scheme for multiple-scales aeroacoustics problems. Intl J. Comput. Fluid Dyn. 17, 119132.CrossRefGoogle Scholar
Tam, C. K. W., Pastouchenko, N. N. & Viswanathan, K. 2010 Continuation of the near acoustic field of a jet to the far field. Part I. Theory. AIAA Paper 2010-3728.Google Scholar
Tam, C. K. W. & Webb, J. C. 1993 Dispersion-relation-preserving scheme for computational acoustics. J. Comput. Phys. 107, 262281.Google Scholar
White, F. M. 1991 Viscous Fluid Flow, 2nd edn. McGraw-Hill.Google Scholar
Woodward, R. P., Hughes, C. E., Jeracki, R. J. & Miller, C. J. 2002 Source diagnostic test – far field acoustic results. AIAA Paper 2002-2427.Google Scholar
Wright, S. E. 1972 Waveguides and rotating sources. J. Sound Vib. 25, 163178.Google Scholar
Yu, J., Nesbitt, E., Kwan, H. W., Uellenberg, S., Chien, E., Premo, J., Ruiz, M. & Czech, M. 2006 Quiet Technology Demonstrator 2 intake liner design and validation. AIAA Paper 2006-2458.Google Scholar
Zhang, X., Chen, X., Morfey, C. L. & Nelson, P. A. 2002 Computation of spinning modal radiation from an unflanged duct. AIAA Paper 2002-2475.CrossRefGoogle Scholar