Methodology to Identify the Unsteady Flow Field Associated With the Loss of Acoustic Energy in the Vicinity of Circular Holes

2010 ◽  
Author(s):  
Jochen Rupp ◽  
Jon Carrotte ◽  
Adrian Spencer
Keyword(s):  
Velocity Field ◽  
Flow Field ◽  
Unsteady Flow ◽  
Acoustic Field ◽  
Acoustic Waves ◽  
Large Scale ◽  
Acoustic Power ◽  
Acoustic Energy ◽  
Absorption Mechanism ◽  
Linear Absorption

Thermo-acoustic instabilities in lean gas turbine combustors have been well reported over the past decade. One option by which the generation of potentially damaging, large scale, pressure amplitudes can be avoided is to increase the amount of damping within the combustion system using passive damping devices. Common to these devices is the absorption mechanism by which acoustic energy, associated with incident pressure fluctuations onto an orifice, generates an unsteady flow that cannot be converted back into acoustic energy. This paper is concerned with providing a greater understanding of this fundamental process. Experimental results are presented for a single orifice that is exposed to plane acoustic waves within a rectangular duct. Measurements of unsteady pressure enable the acoustic power absorbed by the orifice to be determined, whilst Particle Image Velocimetry (PIV) is used to measure the unsteady flow field. A method is outlined for identifying those features within the measured unsteady flow field that are responsible for absorption of the acoustic energy. This is based on a Proper Orthogonal Decomposition (POD) analysis of the velocity field and identification of the relevant modes. The method is validated for the non-linear and linear absorption regimes by comparing the energy of the relevant velocity field features with the energy absorbed from the acoustic field. The good agreement obtained indicates the success of the technique presented. The improved understanding of the mechanisms by which energy is transferred out of the acoustic field, and into the unsteady velocity field, explains many of the observed absorption characteristics. This improved understanding should lead to the design of optimized damping systems. The presented methodology is also thought to be the basis by which numerical, CFD based, predictions relating to the absorption of acoustic waves should be analyzed and validated.

scholarly journals Automated Insertion of Objects Into an Acoustic Robotic Gripper

Proceedings ◽  
2020 ◽  
Vol 64 (1) ◽  
pp. 40
Author(s):  
Marc Röthlisberger ◽  
Marcel Schuck ◽  
Laurenz Kulmer ◽  
Johann W. Kolar
Keyword(s):  
Acoustic Field ◽  
Acoustic Waves ◽  
Acoustic Pressure ◽  
Pressure Field ◽  
Acoustic Power ◽  
Industrial Applications ◽  
High Density ◽  
Analytical Models ◽  
Acoustic Levitation ◽  
Mechanical Contact

Acoustic levitation forces can be used to manipulate small objects and liquid without mechanical contact or contamination. To use acoustic levitation for contactless robotic grippers, automated insertion of objects into the acoustic pressure field is necessary. This work presents analytical models based on which concepts for the controlled insertion of objects are developed. Two prototypes of acoustic grippers are implemented and used to experimentally verify the lifting of objects into the acoustic field. Using standing acoustic waves and by dynamically adjusting the acoustic power, the lifting of high-density objects (>7 g/cm3) from acoustically transparent surfaces is demonstrated. Moreover, a combination of different acoustic traps is used to lift lower-density objects from acoustically reflective surfaces. The provided results open up new possibilities for the implementation of acoustic levitation in robotic grippers, which have the potential to be used in a variety of industrial applications.

Unsteady Turbine Rim Sealing and Vane Trailing Edge Flow Effects

2021 ◽  
Author(s):  
Iván Monge-Concepción ◽  
Shawn Siroka ◽  
Reid A. Berdanier ◽  
Michael D. Barringer ◽  
Karen A. Thole ◽  
...  
Keyword(s):  
Flow Field ◽  
Unsteady Flow ◽  
Rotational Speed ◽  
Large Scale ◽  
Trailing Edge ◽  
Time Resolved ◽  
Flow Rates ◽  
Large Scale Structures ◽  
Purge Flow ◽  
Scale Structures

Abstract Hot gas ingestion into the turbine rim seal cavity is an important concern for engine designers. To prevent ingestion, rim seals use high pressure purge flow but excessive use of the purge flow decreases engine thermal efficiency. A single stage test turbine operating at engine-relevant conditions with real engine hardware was used to study time-resolved pressures in the rim seal cavity across a range of sealing purge flow rates. Vane trailing edge (VTE) flow, shown previously to be ingested into the rim seal cavity, was also included to understand its effect on the unsteady flow field. Measurements from high-frequency response pressure sensors in the rim seal and vane platform were used to determine rotational speed and quantity of large-scale structures (cells). In a parallel effort, a computational model using Unsteady Reynolds-averaged Navier-Stokes (URANS) was applied to determine swirl ratio in the rim seal cavity and time-resolved rim sealing effectiveness. The experimental results confirm that at low purge flow rates, the VTE flow influences the unsteady flow field by decreasing pressure unsteadiness in the rim seal cavity. Results show an increase in purge flow increases the number of unsteady large-scale structures in the rim seal and decreases their rotational speed. However, VTE flow was shown to not significantly change the cell speed and count in the rim seal. Simulations point to the importance of the large-scale cell structures in influencing rim sealing unsteadiness, which is not captured in current rim sealing predictive models.

Large-Scale DES Analysis of Unsteady Flow Field in a Transonic Axial Compressor

2016 ◽  
Vol 2016 (0) ◽  
pp. J0520201
Author(s):  
Yuki TAMURA ◽  
Seishiro SAITO ◽  
Masato FURUKAWA ◽  
Kazutoyo YAMADA ◽  
Akinori MATUOKA ◽  
...  
Keyword(s):  
Flow Field ◽  
Unsteady Flow ◽  
Large Scale ◽  
Axial Compressor ◽  
Transonic Axial Compressor

Theoretical investigation of unsteady flow interactions with a premixed planar flame

2001 ◽  
Vol 435 ◽  
pp. 289-303 ◽  
Author(s):  
TIM LIEUWEN
Keyword(s):  
Flame Front ◽  
Acoustic Field ◽  
Acoustic Waves ◽  
Flame Speed ◽  
Acoustic Energy ◽  
Qualitative And Quantitative ◽  
Flow Interactions ◽  
Vorticity Production ◽  
Dissipation Processes ◽  
Release Processes

This paper presents the results of a theoretical study of the interactions between a laminar, premixed flame front and a plane acoustic wave. Its objective is to elucidate the processes that damp or drive acoustic waves as they interact with flames. Using linear analysis, the characteristics of the acoustic field, the flame's movement and wrinkling in response to acoustic perturbations, and the acoustic energy that is produced or dissipated at the flame are calculated. These calculations show that the net acoustic energy flux out of the flame is controlled by competing acoustic energy production and dissipation processes. Energy is added to the acoustic field by unsteady heat release processes resulting from the unsteady flux of unburned reactants through the flame by fluctuations in the flame speed or density of the unburned reactants. Energy is dissipated by the transfer of acoustic energy into fluctuations in vorticity that are generated at the flame front because of the misaligned fluctuating pressure and mean density gradients (i.e. the baroclinic vorticity production mechanism). The paper concludes by showing how these results can be generalized to determine the response of planar flames to an arbitrarily complex acoustic field. The principal contribution of this work is its demonstration that the excitation of vorticity and fluctuations in the flame speed have significant qualitative and quantitative affects on the interactions between flames and acoustic waves.

Simulation of Simplified Three-Dimensional Space Flow Velocity Field in Reservoir on the Condition of Unsteady Flow and its Application

2012 ◽  
Vol 203 ◽  
pp. 514-518
Author(s):  
Shi Ping Fan ◽  
Jian Ming Yang ◽  
Min Quan Feng ◽  
Bang Min Zheng
Keyword(s):  
Numerical Calculation ◽  
Velocity Field ◽  
Flow Field ◽  
Unsteady Flow ◽  
Flow Velocity ◽  
Dimensional Space ◽  
Three Dimensional ◽  
Flow Velocity Field ◽  
Flood Period ◽  
Three Dimensional Space

In view of the complexity of the conventional simulation calculation method of three-dimensional flow field for the reservoir, and to analysis of the change of the reservoir’s flow field in flood period, in this paper, based on the unsteady flow numerical calculation, the simulation method for three-dimensional space flow velocity field of the reservoir in flood period was studied and applied to the Wenyuhe Reservoir. First refining the actual extraction of grid, and then having an unsteady flow numerical calculation for the reservoir, finally through layering and stripping the grid, three-dimensional space flow velocity field the reservoir on the condition of unsteady flow has been studied. The results showed that the reservoir velocity along the flow direction is becoming smaller, and surface velocity is fast; with the flow increase gradually, the unsteady flow has a great effect on the flow field of the reservoir’s concave bank. The grid can at will encryption, so the calculation precision can be effectively controlled and the process of simulation is easy to be programmed. The research results can simplify the complexity of the reservoir for three-dimensional numerical simulation, and up to providing theoretical support for reservoir flood control.

The Role of Streamwise Vorticity in the Control of Impinging Jets

2003 ◽  
Author(s):  
F. S. Alvi ◽  
H. Lou ◽  
C. Shih
Keyword(s):  
Velocity Field ◽  
Shear Layer ◽  
Acoustic Waves ◽  
High Speed ◽  
Feedback Loop ◽  
Large Scale ◽  
Field Measurements ◽  
Impinging Jets ◽  
Streamwise Vorticity

Supersonic impinging jets produce a highly unsteady flowfield leading to very high dynamic pressure loads on nearby surfaces. In earlier studies, we conclusively demonstrated that arrays of supersonic microjet, 400 μm in diameter, effectively disrupted the feedback loop inherent in high-speed impinging jet flows. This feedback disruption results in significant reductions in the adverse effects associated with such flows. In this paper, by primarily using detailed velocity field measurements, we examine the role of streamwise vorticity in order to better understand the mechanisms behind this control scheme. The velocity field measurements clearly reveal the presence of well-organized, streamwise vortices with the activation of microjets. This increase in streamwise vorticity is concomitant with a reduction in the azimuthal vorticity of the primary jet. We propose that the streamwise vorticity is mainly a result of the redirection of the azimuthal vorticity, which leads to a weakening of the large-scale structures in the primary jet. The appearance of strong vortices in the shear layer near the nozzle exit due to microjets further weakens the spatial coherence of the coupling between the acoustic waves and shear layer instability, while thickening the jet shear layer. All these effects are thought to be collectively responsible for the efficient disruption of the feedback loop using microjets.

Effects of the Mean Flow Field on the Thermo-Acoustic Stability of Aero-Engine Combustion Chambers

2012 ◽  
Author(s):  
Jannis Gikadi ◽  
Thomas Sattelmayer ◽  
Antonio Peschiulli
Keyword(s):  
Flow Field ◽  
Acoustic Waves ◽  
Stokes Equations ◽  
Acoustic Energy ◽  
System Stability ◽  
Mean Flow ◽  
Combustion Chambers ◽  
Hydrodynamic Modes ◽  
Aero Engine ◽  
The Mean

This paper presents a finite element methodology to predict the thermoacoustic eigenmodes of combustion chambers using the linearized Navier-Stokes equations (LNSE) in frequency space. The effect of the mean flow on the acoustics is accounted for. Besides scattering and refraction of acoustic waves in shear layers, this set of equation describes two main damping mechanisms. One is related to the generation of entropy waves, so called hot-spots, in flame regions. The other is related to the transformation of acoustic energy into vorticity waves at sharp leading or trailing edges. Both fluctuation types, i.e. entropy and vorticity, are convected by the mean flow, leading to significant damping when the fluid discharges into an open outlet. In combustion chamber environments these waves are accelerated in the downstream high pressure distributor and are partially transformed back into acoustic waves constituting to the feedback loop of thermo-acoustic instabilities. Accurate prediction of the eigenmodes and eigenfrequencies of instability require therefore to take these interaction effects into account. First, the accuracy of the LNSE approach, to capture the damping generated by the first mechanism of entropy generation and convection, is investigated for a generic premixed flame configuration. Solutions of the LNSE are compared to the analytic solutions as well as eigenvalues determined by an Helmholtz ansatz. Later methodology assumes a quiescent medium and neglects all interactions of acoustics with the mean flow. It is shown that large errors are introduced with increasing Mach-number. To illustrate errors assuming a quiescent medium for realistic combustion chambers, the LNSE are used to assess the eigenmodes of a two-dimensional aero-engine combustor including strong shear regions, in the next step. The non-isothermal mean flow field is obtained performing an incompressible RANS simulation. It features an expanding jet with inner and outer recirculation zones. The acoustic computations using LNSE reveal a set of unstable and neutral hydrodynamic modes in addition to acoustic modes. Both damping mechanisms are present and contribute to the overall system stability. Again the obtained solution is compared to the solution of an Helmholtz code and differences are discussed.

scholarly journals Steady and Unsteady Three-Dimensional Flow Field Downstream of an Embedded Stator in a Multistage Axial Flow Compressor: Part 1 — Unsteady Velocity Field

1998 ◽  
Author(s):  
J. Prato ◽  
B. Lakshminarayana ◽  
N. Suryavamshi
Keyword(s):  
Velocity Field ◽  
Flow Field ◽  
Unsteady Flow ◽  
Three Dimensional ◽  
Axial Flow ◽  
High Response ◽  
Axial Flow Compressor ◽  
Flow Features ◽  
Flow Compressor ◽  
Hot Film

A comprehensive investigation of the three-dimensional unsteady flow and thermal field downstream of an embedded stator in a multistage compressor, acquired with a high-response hot-film probe and aspirating probe, is presented and analyzed. Some of the earlier data (five-hole probe and high-response Kulite probe) from the same compressor is used with the present data to provide an integrated and comprehensive interpretation of the flow and thermal fields. The emphasis is on the unsteady flow, unsteady thermal, and integrated flow fields. Part 1 covers the description of the facility and the development of the hot-film technique for multistage flow field measurement. In addition, the unsteady velocity field is presented and interpreted. Part 2 provides an integrated assessment of the stagnation pressure, temperature and velocity fields to derive a comprehensive understanding of the time-averaged flow features. The final part covers velocity-velocity and velocity-temperature correlations and the assessment of their magnitudes in the average-passage equations. The results from an area traverse of the unsteady velocity field derived from a 45 degree slanted film probe downstream of the second stator of a three-stage axial flow compressor are presented and discussed in this paper. The measurements were conducted at the peak efficiency operating point using a four-rotation method. The ensemble-averaged unsteady three-dimensional velocity data is resolved into the time-averaged component, revolution and blade periodic, and aperiodic components. Some of the features of the rotor 2 flow, measured at the exit of stator 2, reveal the extent of the spread of the upstream rotor wakes and the unsteadiness due to rotor hub and leakage flow regions and levels of periodic and aperiodic unsteadiness. Both the revolution and blade periodic velocity fluctuations are seen to be significantly greater than the aperiodic fluctuations.

Experimental Investigation of the Aeroacoustic Sources in a Tandem Cylinder Configuration

2009 ◽  
Author(s):  
Shane Leslie Finnegan ◽  
Craig Meskell ◽  
Samir Ziada
Keyword(s):  
Spatial Distribution ◽  
Flow Field ◽  
Acoustic Wave ◽  
Flow Velocity ◽  
Acoustic Field ◽  
Hydrodynamic Flow ◽  
Acoustic Energy ◽  
Field Of View ◽  
Low Flow ◽  
Element Analysis

The empirical investigation of the spatial distribution of resonant acoustic sources around a tandem cylinder configuration subject to cross flow in a duct and an imposed transverse acoustic wave is described. The imposed wave induced acoustic “lock-in” and the vortex shedding frequency from the cylinders became entrained to the frequency of the imposed wave near acoustic-Strouhal coincidence. Howe’s aeroacoustic theory was used to couple an acoustic field to a hydrodynamic flow field and the spatial distribution of the time-resolved acoustic power and net-acoustic energy throughout a complete acoustic wave cycle at two resonant conditions were calculated. The first resonant condition occurred at a low flow velocity before acoustic-Strouhal coincidence, whilst the second occurred at a higher flow velocity just after acoustic-Strouhal coincidence. The acoustic field was analysed using finite element analysis combined with microphone pressure measurements whilst the hydrodynamic flow field was extracted using particle image velocimetry from a field of view concentrated around the cylinders and roughly three diameters downstream of them. For both resonant conditions, the dominant individual sources were found to lie in the shear layers of the gap region between the cylinders, however, stronger individual sinks were found to be located there also. Thus, for the amplitude of the applied sound wave and for the available field of view, the gap shear layer region contributed an overall acoustic sink whilst the wake contributed an overall acoustic source.

Three-Dimensional Unsteady Flow Field due to IGV-Rotor Interaction in the Tip Region of an Axial Compressor Rotor Passage

2001 ◽  
Author(s):  
Hongwei Ma ◽  
Haokang Jiang ◽  
Qingguo Zhang
Keyword(s):  
Flow Field ◽  
Unsteady Flow ◽  
Large Scale ◽  
Measurement Techniques ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Low Energy ◽  
Suction Surface ◽  
Compressor Rotor ◽  
Flow Mixing

This paper reports an experimental study of the three-dimensional unsteady flow field due to IGV-rotor interaction in the tip region of an axial compressor rotor passage. The measurements were conducted on a low-speed large-scale axial compressor using a 3-component Laser Doppler Velocimetry. Both experimental method and measurement techniques are presented in details. The results indicate that the tip corner flow of the IGV suction surface has deeper effects on the downstream flow than the IGV wake in the tip region. The interaction and the flow mixing among the IGV wake, the IGV comer flow and the rotor leading-edge flow occur at the inlet of a rotor passage, which make the rotor inlet flow three-dimensional, turbulent and unsteady. The low-energy fluids from the upstream tend to accumulate toward the rotor pressure surface after they enter a rotor passage. In the procedure, the interaction and the flow mixing among the rotor tip leakage vortex and the low-energy fluids occur in the rotor passage.

Sign in / Sign up

Export Citation Format

Share Document