Acoustic Radiation of Coherent Structures in a Turbulent Round Jet

2021 ◽  
Author(s):  
Nishanth Muthichur ◽  
Santosh Hemchandra ◽  
Arnab Samanta
2001 ◽  
Vol 448 ◽  
pp. 367-385 ◽  
Author(s):  
T. B. NICKELS ◽  
IVAN MARUSIC

This paper examines and compares spectral measurements from a turbulent round jet and a turbulent boundary layer. The conjecture that is examined is that both flows consist of coherent structures immersed in a background of isotropic turbulence. In the case of the jet, a single size of coherent structure is considered, whereas in the boundary layer there are a range of sizes of geometrically similar structures. The conjecture is examined by comparing experimental measurements of spectra for the two flows with the spectra calculated using models based on simple vortex structures. The universality of the small scales is considered by comparing high-wavenumber experimental spectra. It is shown that these simple structural models give a good account of the turbulent flows.


2010 ◽  
Vol 13 (4) ◽  
pp. 279-280
Author(s):  
Shuihua Zheng ◽  
Jiegang Mou ◽  
Jianbo Jin ◽  
Si Li

1999 ◽  
Vol 379 ◽  
pp. 71-104 ◽  
Author(s):  
LESTER L. YUAN ◽  
ROBERT L. STREET ◽  
JOEL H. FERZIGER

This paper reports on a series of large-eddy simulations of a round jet issuing normally into a crossflow. Simulations were performed at two jet-to-crossflow velocity ratios, 2.0 and 3.3, and two Reynolds numbers, 1050 and 2100, based on crossflow velocity and jet diameter. Mean and turbulent statistics computed from the simulations match experimental measurements reasonably well. Large-scale coherent structures observed in experimental flow visualizations are reproduced by the simulations, and the mechanisms by which these structures form are described. The effects of coherent structures upon the evolution of mean velocities, resolved Reynolds stresses, and turbulent kinetic energy along the centreplane are discussed. In this paper, the ubiquitous far-field counter-rotating vortex pair is shown to originate from a pair of quasi-steady ‘hanging’ vortices. These vortices form in the skewed mixing layer that develops between jet and crossflow fluid on the lateral edges of the jet. Axial flow through the hanging vortex transports vortical fluid from the near-wall boundary layer of the incoming pipe flow to the back side of the jet. There, the hanging vortex encounters an adverse pressure gradient and breaks down. As this breakdown occurs, the vortex diameter expands dramatically, and a weak counter-rotating vortex pair is formed that is aligned with the jet trajectory.


2015 ◽  
Vol 44 ◽  
pp. 108-115 ◽  
Author(s):  
D.S. Souza ◽  
D. Rodríguez ◽  
L.G.C. Simões ◽  
M.A.F. Medeiros

2004 ◽  
Vol 33 (5) ◽  
pp. 342-356 ◽  
Author(s):  
Hitoshi Suto ◽  
Koji Matsubara ◽  
Mutsuo Kobayashi ◽  
Hidehito Watanabe ◽  
Yusaku Matsudaira

2004 ◽  
Vol 7 (3) ◽  
pp. 177-177
Author(s):  
Shuihua Zheng ◽  
Jianren Fan ◽  
Xueming Shao ◽  
Kun Luo ◽  
Kefa Cen

Author(s):  
Xiaosa Li ◽  
Zegang Qian ◽  
Qichao Yang

The compressor aerodynamic noise consists of suction, exhausting noise, gas power noise and so on, and the exhausting noise is dominating. Gas which is compressed released instantaneously to form vortex injection noise and exhausting pulsation noise, yet will cause pipe vibration. Large Eddy Simulation model in fluid software FLUENT have been adopted to analyze unsteady flow field and the acoustic field and research unsteady vortex shedding and its noise radiation characteristics in compressor pipes. The results show that: the trailing edge vortex shedding phenomenon, interaction between separation vortex and the trailing vortex of downstream lead to a large gas pulsation which makes noise radiation enhanced in the compressor pipe flow field in screw compressor exhausting orifice. Combination turbulence and vortex-pair phenomena in coherent structures, based on the vortex sound equation, a mathematical model of vortex-pair acoustic radiation is established. Finally unit length sound power of the whirlpool is draw to lρ0U3M4.


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