Experimental and Computational Approach for Jet Noise Mitigation by Mixing Control Devices

2011 ◽  
Author(s):  
Nozomi Tanaka ◽  
Tsutomu Oishi ◽  
Yoshinori Ooba ◽  
Shunji Enomoto ◽  
Kazuomi Yamamoto ◽  
...  
Keyword(s):  
Mach Number ◽  
Shear Layer ◽  
Nozzle Exit ◽  
High Frequency ◽  
Nozzle Design ◽  
Noise Mitigation ◽  
Eddy Simulation ◽  
Large Eddy ◽  
Noise Measurements ◽  
Chevron Nozzle

The notched nozzle as a new concept has been investigated for conventional nozzle design together with the Chevron nozzle and Micro-jets, through feasibility studies. The notched nozzle has a plurality of triangular pyramid-shaped dent positioned in a circumferential direction along the nozzle exit. These studies include acoustic experiments that utilize a lab-scale simple model in an anechoic chamber and numerical approaches. The results of the Large Eddy Simulation are compared with the results of either acoustic or aerodynamic experiments. The objective of these investigations is to verify the effects of noise mitigation and to gain understanding of the physics of fluid dynamics around the nozzle exit, especially within the shear layer between high velocity jet flow and external flow/or ambient air. One concept of conventional noise mitigation devices involves mixing enhancements in the shear layer, but this sometimes produces high frequency self noise. Moreover it will result in a penalty in terms of thrust loss, additional weight and extra manufacturing cost due to the complicated shapes around the nozzle exit. It is difficult to produce a nozzle design without affecting high frequency self-noise and decreasing low-frequency noise towards to down stream of the jet engines even though there is no thrust loss. Most of this study, the experimental data were physically validated by three kinds of nozzle concepts designed to be equal to the conventional model in terms of size of nozzle exit diameter and Mach number. Essentially far-fields noise measurements and pressure measurements are conducted by polar angle microphones and arch-shaped pitot tubes are located downstream of the jet. The noise benefit which is produced by the notched nozzle as a lab-scale in far-fields noise measurements is up to 1.3dB at the side of the jet and 0.5dB at downstream, in terms of size of small-engine. Furthermore this provided an advantage over the chevron nozzle due to the decreasing self-noise production when the Mach number of the jet was lower than 0.9. Moreover, numerical predictions which are provided by the Large Eddy Simulation were used to estimate the noise mitigation by performing turbulence statistical analysis. Numerical results which refer to the turbulent statistics are discussed in order to define how they can be affected to the acoustic results at the side of the jet. This shows how each device can deform the shear layer without producing additional streamwise and small scale vortices.

Assessment of a Noise Reduction Concept for a Hot Supersonic Jet Using Large Eddy Simulation

2013 ◽  
Author(s):  
James P. Erwin ◽  
Neeraj Sinha
Keyword(s):  
Large Eddy Simulation ◽  
Noise Reduction ◽  
Shear Layer ◽  
Nozzle Exit ◽  
Supersonic Jet ◽  
Broadband Noise ◽  
Shock Cell ◽  
Testing Procedures ◽  
Eddy Simulation ◽  
Large Eddy

Noise emissions of a hot, supersonic jet at laboratory scale are predicted with and without a noise reduction concept. The hot jet is representative of an over-expanded, low bypass ratio military gas turbine engine exhaust. The reduction device consists of twelve non-penetrating chevrons that are equilateral triangles, extending tangentially from the inner nozzle wall and to the flow at the nozzle exit. The chevrons are idealized and not a result of any design or testing procedures. Hybrid Reynolds Averaged Navier Stokes and Large Eddy Simulation (HRLES) is performed at both 5.5 million and 128 million cell grid resolutions. A novel structured topology is used to perform the HRLES with and without the chevrons using the same grid, and the chevrons are turned on and off through a boundary condition switch. The noise emissions are then predicted on a circular array one hundred jet exit diameters from the nozzle exit with the permeable Ffowcs Williams and Hawkings equation method. The chevrons modify the entrained flow at the over-expanded power setting, impacting the shear layer and associated far-field noise. The chevrons stabilize the jet shock cell structure, and also reduce turbulent fluctuations throughout the length of the shear layer. An overall sound pressure level reduction of between one and four decibels is predicted at all angles to the jet, including the elimination of jet screech relative to the baseline jet with no chevrons. A significant reduction in broadband noise is also predicted downstream. The jet with chevrons is also predicted with the higher resolution grid and noise levels are compared with the low resolution grid. Upstream noise level predictions are increased due to enhanced resolution of fine scale turbulence.

Numerical Investigation on Frequency Jump of Flow Over a Cavity Using Large Eddy Simulation

2015 ◽  
Vol 137 (8) ◽  
Author(s):  
Yuchuan Wang ◽  
Lei Tan ◽  
Binbin Wang ◽  
Shuliang Cao ◽  
Baoshan Zhu
Keyword(s):  
Large Eddy Simulation ◽  
Shear Layer ◽  
Cavity Length ◽  
Nonlinear Process ◽  
Sustained Oscillation ◽  
Time Lags ◽  
Frequency Jump ◽  
Eddy Simulation ◽  
Large Eddy ◽  
Flow Over A Cavity

Large eddy simulation (LES) approach was used to investigate jumps of primary frequency of shear layer flow over a cavity. Comparisons between computational results and experimental data show that LES is an appropriate approach to accurately capturing the critical values of velocity and cavity length of a frequency jump, as well as characteristics of the separated shear layer. The drive force of the self-sustained oscillation of impinging shear layer is fluid injection and reinjection. Flow patterns in the shear layer and cavity before and after the frequency jump demonstrate that the frequency jump is associated with vortex–corner interaction. Before frequency jump, a mature vortex structure is observed in shear layer. The vortex is clipped by impinging corner at approximately half of its size, which induces strong vortex–corner interaction. After frequency jump, successive vortices almost escape from impinging corner without the generation of a mature vortex, thereby indicating weaker vortex–corner interaction. Two wave peaks are observed in the shear layer after the frequency jump because of: (1) vortex–corner interaction and (2) centrifugal instability in cavity. Pressure fluctuations inside the cavity are well regulated with respect to time. Peak values of correlation coefficients close to zero time lags indicate the existence of standing waves inside the cavity. Transitions from a linear to a nonlinear process occurs at the same position (i.e., x/H = 0.7) for both velocity and cavity length variations. Slopes of linear region are solely the function of cavity length, thereby showing increased steepness with increased cavity length.

Large Eddy Simulation of Wake-Shear Layer Interactions Over a Multi-Element Aerofoil

2020 ◽  
Author(s):  
Souvik Naskar ◽  
S. Sarkar
Keyword(s):  
Large Eddy Simulation ◽  
Shear Layer ◽  
Separation Bubble ◽  
Turbine Blades ◽  
Leading Edge ◽  
Aerodynamic Characteristics ◽  
Suction Surface ◽  
Free Stream Turbulence ◽  
Eddy Simulation ◽  
Large Eddy

Abstract Modern commercial airliners use multi-element aerofoils to enhance take-off and landing performance. Further, multielement aerofoil configurations have been shown to improve the aerodynamic characteristics of wind turbines. In the present study, high resolution Large Eddy Simulation (LES) is used to explore the low Reynolds Number (Re = 0.832 × 104) aerodynamics of a 30P30N multi-element aerofoil at an angle of attack, α = 4°. In the present simulation, wake shed from a leading edge element or slat is found to interact with the separated shear layer developing over the suction surface of the main wing. High receptivity of shear layer via amplification of free-stream turbulence leads to rollup and breakdown, forming a large separation bubble. A transient growth of fluctuations is observed in the first half of the separation bubble, where levels of turbulence becomes maximum near the reattachment and then decay depicting saturation of turbulence. Results of the present LES are found to be in close agreement with the experiment depicting high vortical activity in the outer layer. Some features of the flow field here are similar to those occur due to interactions of passing wake and the separated boundary layer on the suction surface of high lift low pressure turbine blades.

LES Analysis of Turbulence Effects on Unsteady Flows Past a Circular Cylinder

2003 ◽  
Author(s):  
Tetsuro Tamura ◽  
Yoshiyuki Ono ◽  
Kohji Hashida
Keyword(s):  
Circular Cylinder ◽  
Shear Layer ◽  
Bluff Body ◽  
Unsteady Flows ◽  
Aerodynamic Characteristics ◽  
Cylinder Wake ◽  
Eddy Simulation ◽  
Inflow Boundary Condition ◽  
Large Eddy ◽  
Turbulence Effects

Recent advancement of LES (Large Eddy Simulation) technique for turbulent wake has made it possible to numerically investigate the turbulence effects on aerodynamic characteristics of a bluff body. Here we carry out LES of wake flows past a circular cylinder in the subcritical Reynolds number regime. For inflow boundary condition, homogeneous turbulence generated statistically is given time-sequentially. We bring into focus the interaction between the oncoming turbulence and the shear layer separated from a circular cylinder. Shear layer instability easily occurs under such a stimulation and details of its behavior are visualized. Turbulence effects on unsteady flows in the cylinder wake are discussed. The resulting aerodynamic characteristics and their physical mechanism are clarified.

Large Eddy Simulation of Self-Sustained Cavity Oscillation for Subsonic and Supersonic Flows

2016 ◽  
Vol 139 (1) ◽  
Author(s):  
K. M. Nair ◽  
S. Sarkar
Keyword(s):  
Large Eddy Simulation ◽  
Shear Layer ◽  
Acoustic Waves ◽  
Large Scale ◽  
Hydrodynamic Instability ◽  
Supersonic Flows ◽  
Large Scale Structures ◽  
Eddy Simulation ◽  
Large Eddy ◽  
Scale Structures

The primary objective is to perform a large eddy simulation (LES) using shear improved Smagorinsky model (SISM) to resolve the large-scale structures, which are primarily responsible for shear layer oscillations and acoustic loads in a cavity. The unsteady, three-dimensional (3D), compressible Navier–Stokes (N–S) equations have been solved following AUSM+-up algorithm in the finite-volume formulation for subsonic and supersonic flows, where the cavity length-to-depth ratio was 3.5 and the Reynolds number based on cavity depth was 42,000. The present LES resolves the formation of shear layer, its rollup resulting in large-scale structures apart from shock–shear layer interactions, and evolution of acoustic waves. It further indicates that hydrodynamic instability, rather than the acoustic waves, is the cause of self-sustained oscillation for subsonic flow, whereas the compressive and acoustic waves dictate the cavity oscillation, and thus the sound pressure level for supersonic flow. The present LES agrees well with the experimental data and is found to be accurate enough in resolving the shear layer growth, compressive wave structures, and radiated acoustic field.

Numerical Simulation of the Supersonic Planar Mixing Layer

2011 ◽  
Vol 347-353 ◽  
pp. 922-926
Author(s):  
Jin Liang Gu ◽  
Huan Hao Zhang ◽  
Zhi Hua Chen ◽  
Xiao Hai Jiang
Keyword(s):  
Numerical Simulation ◽  
Mach Number ◽  
Large Eddy Simulation ◽  
Engineering Design ◽  
Mixing Layer ◽  
Eddy Simulation ◽  
Layer Structures ◽  
Eddy Characteristics ◽  
Large Eddy ◽  
Convective Mach Number

Large eddy simulation (LES) has been used to simulate both non-reacting and reacting supersonic planar mixing layers at convective Mach number Mc=0.3. The different eddy characteristics of two cases have been visualized and discussed based on our calculated results, and the differences of mixing layer structures have also been shown, which can provide some important guide for future relative engineering design.

Sign in / Sign up

Export Citation Format

Share Document