Large Eddy Simulation for the Analysis of Supersonic Jet Noise Suppression Devices
Doktorsavhandling, 2010

Stricter noise regulations for commercial and military aircraft have increased interest in noise reduction techniques within the aerospace industry. To meet the requirements, new noise suppression technologies have to be developed and numerical methods need to be validated and possibly improved for the correct assessment of these technologies. In this thesis the main focus is to explore techniques to reduce the noise from the exhaust part of a typical military fighter engine. In this investigation, two techniques, which have been proven to be effective on subsonic jets, are studied. The first technique is the use of passive flow control devices, such as chevrons, for increasing the mixing rate in the shear layer of the jet. The second technique is the use of fluidic injection, through micro-jets, which have the capability to be controlled during flight to minimize thrust loss and maximize noise reduction. Large eddy simulation (LES) is used as a numerical prediction tool to predict the flow field and a Kirchhoff surface integral technique is used to extend the acoustic domain. In all cases studied, the nozzle geometry is included in the calculation domain. The numerically predicted flow field and acoustic results are compared with experimental data. The impact on flow field and acoustic signature by the different nozzle designs are evaluated. Also, the effect of forward flight is investigated at different free stream Mach numbers. Specific numerical issues when simulating supersonic jet flows and dealing with complex geometries are addressed and the applied methods are evaluated.

fluidic injection

mixer-ejector

jet noise

Kirchhoff

forward flight effects

LES

acoustic liner

supersonic turbulent jets

broadband time-domain impedance boundary condition

chevrons

shock-associated noise

CAA

aeroacoustics

HC2
Opponent: Prof. Paul G. Tucker, Rank Professor of Turbomachinery Computational Aerodynamics, The University of Cambridge, Whittle Laboratory, England

Författare

Markus Olander Burak

Chalmers, Tillämpad mekanik, Strömningslära

LES based jet noise prediction for mixer-ejector configurations including acoustic liner model

Inter-Noise 2006 Congress, Honolulu, Hawaii, USA,; (2006)

Konferensbidrag (offentliggjort, men ej förlagsutgivet)

Near-Field Jet Noise from a Supersonic C-D Chevron Nozzle

16th AIAA/CEAS Aeroacoustics Conference, 7-9 June, Stockholm, Sweden,; (2010)

Konferensbidrag (offentliggjort, men ej förlagsutgivet)

Flow and noise predictions for a mixer-ejector engine configuration using LES

13th AIAA/CEAS Aeroacoustics Conference, Rome, Italy, 2007,; (2007)

Konferensbidrag (offentliggjort, men ej förlagsutgivet)

Experimental and Numerical Investigation of a Supersonic C-D Nozzle

15th AIAA/CEAS Aeroacoustics Conference, 11-13 May, Miami, Florida,; (2009)

Konferensbidrag (offentliggjort, men ej förlagsutgivet)

Micro-Jet Flow Control for Noise Reduction of a Supersonic Jet from a Practical C-D Nozzle

16th AIAA/CEAS Aeroacoustics Conference, 7-9 June, Stockholm, Sweden,; (2010)

Konferensbidrag (offentliggjort, men ej förlagsutgivet)

Supersonic Jet Noise from a Conical C-D Nozzle with Forward Flight Effects

47th AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition, , 5-8 January, Orlando, Florida,; (2009)

Konferensbidrag (offentliggjort, men ej förlagsutgivet)

Comparison of Flow Control Methods Applied to Conical C-D Nozzles

16th AIAA/CEAS Aeroacoustics Conference, 7-9 June, Stockholm, Sweden,; (2010)

Konferensbidrag (offentliggjort, men ej förlagsutgivet)

Experimental and Numerical Investigation of a Supersonic C-D Chevron Nozzle

39th AIAA Fluid Dynamics Conference, 22-25 June, San Antonio, Texas,; (2009)

Konferensbidrag (offentliggjort, men ej förlagsutgivet)

Experimental and Numerical Investigation of a Novel Acoustic Liner Concept

16th AIAA/CEAS Aeroacoustics Conference, 7-9 June, Stockholm, Sweden,; (2010)

Konferensbidrag (offentliggjort, men ej förlagsutgivet)

Validation of a Time- and Frequency-Domain Grazing Flow Acoustic Liner Model

AIAA Journal,; Vol. 47(2009)p. 1841-1848

Artikel i vetenskaplig tidskrift

Forward Flight Effects on the Shock Structure From a Chevron C-D Nozzle

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, 4-7 January, Orlando, Florida,; (2010)

Konferensbidrag (offentliggjort, men ej förlagsutgivet)

Ämneskategorier

Strömningsmekanik och akustik

ISBN

978-91-7385-459-7

Doktorsavhandlingar vid Chalmers tekniska högskola. Ny serie: 3140

HC2

Opponent: Prof. Paul G. Tucker, Rank Professor of Turbomachinery Computational Aerodynamics, The University of Cambridge, Whittle Laboratory, England

Mer information

Skapat

2017-10-08