Experimental Investigation of Near-Field Pressure Fluctuations Generated by Supersonic Jets

Author(s):  
Ching-Wen Kuo ◽  
Quentin Buisson ◽  
Dennis K. McLaughlin ◽  
Philip J. Morris
Author(s):  
Fernando Rodriguez Varela ◽  
Javier Fernandez Alvarez ◽  
Belen Galocha Iraguen ◽  
Manuel Sierra Castaner ◽  
Olav Breinbjerg

2001 ◽  
Author(s):  
Paul J. Zoccola ◽  
Theodore M. Farabee

Abstract Excitation of cavity resonance by flow over an aperture is often a source of unwanted noise in aerospace, automotive, and marine applications. An experimental investigation of this phenomenon was conducted. Detailed measurements of the cavity pressure and the velocity field in the opening were performed in a quiet flow facility. Spectral data on cavity pressure fluctuations obtained for a variety of configurations were analyzed over a range of speeds to determine the behavior of both sheartones and cavity tones during non-resonant and resonant conditions. The mean and fluctuating velocity profiles as well as the cross-spectral properties between the velocity components and cavity pressure were also obtained within the cavity opening. Phase between the velocity components and the pressure was used to calculate the streamwise convection velocities across the opening. A novel technique used to measure vorticity allowed calculation of the measured energy production in the opening. The data support the finding that the resonant and non-resonant conditions are distinguished by the behavior of the convection velocity and by the distribution of energy production in the flow field.


Author(s):  
C. A. Arana ◽  
B. Sekar ◽  
M. A. Mawid

This paper describes an analytical and experimental investigation to obtain the thermoacoustic response of a demonstrator gas turbine engine combustor. The combustor acoustic response for two different fuel injector design configurations was measured. It was found that the combustor maximum peak to peak pressure fluctuations were 0.6 psi to 2 psi for configuration A and B respectively. Based on the measured acoustic response, another experimental investigation was conducted to identify the design features in configuration B that caused the increase in the acoustic response. The data showed that by changing the fuel injector swirler’s vane to inner passage discharge area ratio, the engine acoustic response could be lowered to an acceptable level. A simplified analytical model based on the lumped-parameter approach was then developed to investigate the effect of geometrical changes upon the engine response. The analytical model predicted the fuel injector/swirlers acoustic response as a function of the swirlers inner passage discharge area ratio and frequency. The predictions were consistent with the experimental observations, in particular, it was predicted that as the area ratio was increased, the system reactance was decreased and as a result the system changed from a damping to an amplifying system.


2017 ◽  
Vol 10 (2) ◽  
pp. 423-431 ◽  
Author(s):  
Adrian Pandal ◽  
Jose M. Pastor ◽  
Raul Payri ◽  
Alan Kastengren ◽  
Daniel Duke ◽  
...  

Sign in / Sign up

Export Citation Format

Share Document