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Journal articles on the topic 'Combustion Acoustic'

Author: Grafiati

Published: 4 June 2021

Last updated: 6 February 2022

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1

Krishnan, Abin, R. I. Sujith, Norbert Marwan, and Jürgen Kurths. "On the emergence of large clusters of acoustic power sources at the onset of thermoacoustic instability in a turbulent combustor." Journal of Fluid Mechanics 874 (July 9, 2019): 455–82. http://dx.doi.org/10.1017/jfm.2019.429.

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In turbulent combustors, the transition from stable combustion (i.e. combustion noise) to thermoacoustic instability occurs via intermittency. During stable combustion, the acoustic power production happens in a spatially incoherent manner. In contrast, during thermoacoustic instability, the acoustic power production happens in a spatially coherent manner. In the present study, we investigate the spatiotemporal dynamics of acoustic power sources during the intermittency route to thermoacoustic instability using complex network theory. To that end, we perform simultaneous acoustic pressure meas

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2

Yang, Yao, Gaofeng Wang, Yuanqi Fang, YIfan Xia, and Liang Zhong. "IMAGING DIAGNOSTICS OF COMBUSTION INSTABILITY IN PREMIXED SWIRLING COMBUSTION." Journal of the Global Power and Propulsion Society 4 (May 22, 2020): 80–93. http://dx.doi.org/10.33737/jgpps/120536.

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An experimental study on combustion instability is presented with focus on propane-air premixed swirling flames. Swirling flames under self-excited oscillation are studied by imaging of visible light and OH* chemiluminescence filter under several typical conditions. The dynamical characteristics of swirling flames were analysed by Dynamic Mode Decomposition (DMD) method. Three types of unstable modes in the combustor system were observed, which correspond to typical acoustic resonant modes (LF mode, C1/4 mode and P1/2 mode) of the combustor system. The combustion instability is in the longitud

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3

Paschereit, C. O., B. Schuermans, W. Polifke, and O. Mattson. "Measurement of Transfer Matrices and Source Terms of Premixed Flames." Journal of Engineering for Gas Turbines and Power 124, no. 2 (2002): 239–47. http://dx.doi.org/10.1115/1.1383255.

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An experimental method to determine the thermoacoustic properties of a gas turbine combustor using a lean-premixed low emission swirl stabilized burner is presented. To model thermoacoustic oscillations, a combustion system can be described as a network of acoustic elements, representing for example fuel and air supply, burner and flame, combustor, cooling channels, suitable terminations, etc. For most of these elements, simple analytical models provide an adequate description of their thermoacoustic properties. However, the complex response of burner and flame (involving a three-dimensional f

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4

Giuliani, Fabrice, Lukas Andracher, Vanessa Moosbrugger, Nina Paulitsch, and Andrea Hofer. "Combined Optic-Acoustic Monitoring of Combustion in a Gas Turbine." International Journal of Turbomachinery, Propulsion and Power 5, no. 3 (2020): 15. http://dx.doi.org/10.3390/ijtpp5030015.

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The need for better combustion monitoring in gas turbines has become more acute with the latest technical requirements, standards, and policies in terms of safety, environment, efficiency, operation flexibility, and operation costs. Combustion Bay One e.U. and FH JOANNEUM GmbH initiated in 2015 an experimental research program about the feasibility and first assessments of placing optical systems near the combustor. The project’s acronym “emootion” stands for “Engine health MOnitOring and refined combusTION control based on optical diagnostic techniques embedded in the combustor”. The motivati

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5

Serbin, Sergey. "THERMO ACOUSTIC PROCESSES IN LOW EMISSION COMBUSTION CHAMBER OF GAS TURBINE ENGINE CAPACITY 25 MW." Science Journal Innovation Technologies Transfer, no. 2019-2 (May 5, 2019): 86–90. http://dx.doi.org/10.36381/iamsti.2.2019.86-90.

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The appliance of modern tools of the computational fluid dynamics for the investigation of the pulsation processes in the combustion chamber caused by the design features of flame tubes and aerodynamic interaction compressor, combustor and turbine is discussed. The aim of the research is to investigate and forecast the non-stationary processes in the gas turbine combustion chambers. The results of the numerical experiments which were carried out using three-dimensional mathematical models in gaseous fuels combustion chambers reflect sufficiently the physical and chemical processes of the unste

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6

Duan, Runze, Yifan Cao, Hongbin Duan, et al. "Effect of the inner-surface baffles on the tangential acoustic mode in the cylindrical combustor." Open Physics 18, no. 1 (2020): 1215–22. http://dx.doi.org/10.1515/phys-2020-0187.

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Abstract The combustion instability in a propulsion system is a ubiquitous problem. The radial baffles usually installed on the injector faceplate eliminate the combustion instability (acoustic pressure oscillation) in the propulsion system. In this article, the longitudinal baffles are installed on the inner surface of the combustor wall to control the combustion instabilities. The first-order and second-order tangential modes are induced in the experiments. The effects of the parameters of the baffle on the acoustic pressure oscillation in the cylindrical combustor are investigated. The effe

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7

Sarkar, Soumalya, Satyanarayanan R. Chakravarthy, Vikram Ramanan, and Asok Ray. "Dynamic data-driven prediction of instability in a swirl-stabilized combustor." International Journal of Spray and Combustion Dynamics 8, no. 4 (2016): 235–53. http://dx.doi.org/10.1177/1756827716642091.

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Combustion instability poses a negative impact on the performance and structural durability of both land-based and aircraft gas turbine engines, and early detection of combustion instabilities is of paramount importance not only for performance monitoring and fault diagnosis, but also for initiating efficient decision and control of such engines. Combustion instability is, in general, characterized by self-sustained growth of large-amplitude pressure tones that are caused by a positive feedback arising from complex coupling of localized hydrodynamic perturbations, heat energy release, and acou

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8

Qian, Yu Fen, Yan Ying Xu, and Ti Hai Xu. "Combustion Characteristics of a Helmholtz-Type Valveless Self-Excited Pulse Combustor." Applied Mechanics and Materials 291-294 (February 2013): 1719–22. http://dx.doi.org/10.4028/www.scientific.net/amm.291-294.1719.

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Combustion characteristics of a Helmholtz-type valveless self-excited pulse combustor with continuous supply of gas and air were studied. The physical and mathematical models are established based on the actual pulse combustor, and the combustion characteristics are simulated with CFD. The results show that the possible re-ignition sources for the pulse combustion may be three. The first source may be the hot remnant gas near gas/air mixture. The second re-ignition source may be the high-temperature combustion chamber wall. The third ignition source is the unburned mixture. The pressure, tempe

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9

Nair, Vineeth, and R. I. Sujith. "Multifractality in combustion noise: predicting an impending combustion instability." Journal of Fluid Mechanics 747 (April 23, 2014): 635–55. http://dx.doi.org/10.1017/jfm.2014.171.

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AbstractThe transition in dynamics from low-amplitude, aperiodic, combustion noise to high-amplitude, periodic, combustion instability in confined, combustion environments was studied experimentally in a laboratory-scale combustor with two different flameholding devices in a turbulent flow field. We show that the low-amplitude, irregular pressure fluctuations acquired during stable regimes, termed ‘combustion noise’, display scale invariance and have a multifractal signature that disappears at the onset of combustion instability. Traditional analysis often treats combustion noise and combustio

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10

Motheau, Emmanuel, Franck Nicoud, and Thierry Poinsot. "Mixed acoustic–entropy combustion instabilities in gas turbines." Journal of Fluid Mechanics 749 (May 16, 2014): 542–76. http://dx.doi.org/10.1017/jfm.2014.245.

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AbstractA combustion instability in a combustor terminated by a nozzle is analysed and modelled based on a low-order Helmholtz solver. A large eddy simulation (LES) of the corresponding turbulent, compressible and reacting flow is first performed and analysed based on dynamic mode decomposition (DMD). The mode with the highest amplitude shares the same frequency of oscillation as the experiment (approximately 320 Hz) and shows the presence of large entropy spots generated within the combustion chamber and convected down to the exit nozzle. The lowest purely acoustic mode being in the range 700

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11

Férand, Mélissa, Thomas Livebardon, Stéphane Moreau, and Marlène Sanjosé. "Numerical Prediction of Far-Field Combustion Noise from Aeronautical Engines." Acoustics 1, no. 1 (2019): 174–98. http://dx.doi.org/10.3390/acoustics1010012.

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A hybrid methodology combining a detailed Large Eddy Simulation of a combustion chamber sector, an analytical propagation model of the extracted acoustic and entropy waves at the combustor exit through the turbine stages, and a far-field acoustic propagation through a variable exhaust temperature field was shown to predict far-field combustion noise from helicopter and aircraft propulsion systems accurately for the first time. For the single-stream turboshaft engine, the validation was achieved from engine core to the turbine exit. Propagation to the far field was then performed through a mode

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12

Li, Jie, Hua Guan, Dong Ming Song, Qi Wang, Jun Du, and Jia Yang Qi. "Application of Hartmann Acoustic Generator in Source of Underwater Pyrotechnic Combustion." Advanced Materials Research 787 (September 2013): 638–43. http://dx.doi.org/10.4028/www.scientific.net/amr.787.638.

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In order to investigate acoustic radiation characteristics of underwater pyrotechnic combustion, Hartmann acoustic generator was applied and its main structural parameters effecting acoustic radiation characteristics were studied by using underwater acoustic measurement system. Experimental studies have shown that, when Hartmann acoustic generator was applied, the sound pressure level of underwater pyrotechnic combustion increased significantly because of the strengthening of turbulence degree. The distance between the nozzle and the resonant cavity is an important factor of affecting acoustic

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13

Novozhilov, B. V. "Acoustic resonance upon propellant combustion." Combustion, Explosion, and Shock Waves 36, no. 1 (2000): 3–9. http://dx.doi.org/10.1007/bf02701508.

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14

Hoffmann, T. L., W. Chen, G. H. Koopmann, A. W. Scaroni, and L. Song. "Experimental and Numerical Analysis of Bimodal Acoustic Agglomeration." Journal of Vibration and Acoustics 115, no. 3 (1993): 232–40. http://dx.doi.org/10.1115/1.2930338.

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The interaction between fly ash particles (first mode) and sorbent particles (second mode) in coal combustion processes is studied under the influence of a low frequency, high intensity acoustic field. The effect of bimodal acoustic agglomeration is evaluated in a numerical sensitivity analysis on parameters such as residence time in the combustion chamber and mass loading of the particle modes. An Acoustic Agglomeration Simulation Model (AASM) developed by Song at the Pennsylvania State University is used for these numerical studies. Experimental examinations carried out in a down-fired combu

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15

Ivannikova, Olena. "THE USE OF ACOUSTIC WAVES TO SUPPRESS THE COMBUSTION PROCESS IN THE FIRE SEAT." Information and Public Safety, no. 2021-2 (May 15, 2021): 10–17. http://dx.doi.org/10.53029/2786-4529-2021-2-2.

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Іn this article, the foundations of the formation of the acoustic method of impact on the combustion center have been considered. The relationship between the parameters of the acoustic impact on the source of an emergency arising from a fire, depending on the burning substance has been established. Separate proposals on the parameters of acoustic impact (power, frequency, pulse shape) and design solutions for acoustic systems for suppressing the combustion process in the fire source at the initial stage of the development of an emergency have been developed. Key words: acoustic method, acoust

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16

Ai, Yan Ting, Song Jin Li, Bang Hui Yin, and Shi Mo Bai. "Vibro-Acoustic Coupling Analysis of Aero-Engine Combustion Chamber Model." Applied Mechanics and Materials 44-47 (December 2010): 4100–4104. http://dx.doi.org/10.4028/www.scientific.net/amm.44-47.4100.

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The combustion instability is an important reason for fatigue failure of the vibro-acoustic coupling combustion chamber thin-walled structure. The vibro-acoustic coupling equations of closed cavity are derived; The vibro-acoustic coupling coefficient matrix is calculated, it indicates that couplings between the acoustic modes and the structure modes are strictly selective; The vibro-acoustic coupling characteristics of the finite length simply supported closed cylindrical space and the combustion chamber flame tube modals are studied with the finite element method, and the little effect of mod

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17

Kim, Jong-Chan, Won-Chul Jung, Ji-Seok Hong, and Hong-Gye Sung. "The Effects of Turbulent Burning Velocity Models in a Swirl-Stabilized Lean Premixed Combustor." International Journal of Turbo & Jet-Engines 35, no. 4 (2018): 365–72. http://dx.doi.org/10.1515/tjj-2016-0053.

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Abstract The effects of turbulent burning velocities in a turbulent premixed combustion simulation with a G-equation are investigated using the 3D LES technique. Two turbulent burning velocity models – Kobayashi model, which takes into account the burning velocity pressure effect, and the Pitsch model, which considers the flame regions on the premixed flame structure – are implemented. An LM6000 combustor is employed to validate the turbulent premixed combustion model. The results show that the flame structures in front of the injector have different shapes in each model because of the differe

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18

Santana Jr., A., M. S. Silva, P. T. Lacava, and L. C. S. Góes. "ACOUSTIC CAVITIES DESIGN PROCEDURES." Revista de Engenharia Térmica 6, no. 2 (2007): 27. http://dx.doi.org/10.5380/reterm.v6i2.61687.

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Combustion instability is recognized as one of the major problems frequently faced by engineers during the development of either liquid or solid propellant rocket engines. The performance of the engine can be highly affected by these high frequencies instabilities, possibly leading the rocket to an explosion. The main goal while studying combustion chambers instability, either by means of baffles or acoustic absorbers, is to achieve the stability needed using the simplest possible manner. This paper has the purpose of studying combustion chambers instabilities, as well as the design of acousti

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19

Wu, Xuesong. "Asymptotic approach to combustion instability." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 363, no. 1830 (2005): 1247–59. http://dx.doi.org/10.1098/rsta.2005.1565.

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This paper presents an asymptotic approach to combustion instability in premixed flames under the assumptions of large activation energy and small Mach number. The entire flow consists of four distinct yet fully interactive sub-regions, which accommodate the chemical reaction, heat transport, hydrodynamics and acoustics, respectively. A reduced system was derived to describe the intricate coupling between the flame and acoustics that underlies the combustion instability. The asymptotically reduced system was employed to study the weakly nonlinear interaction between the Darrieus–Landau instabi

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20

Akbari, N., and N. S. Mehdizadeh. "Thermo-Acoustic Instability Simulation in Gas Turbine." Journal of Mechanics 25, no. 4 (2009): 433–40. http://dx.doi.org/10.1017/s1727719100002914.

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ABSTRACTThe main aims of this research are, at first, combustion instability study based on equivalence ratio oscillation, and, secondly, investigation various frequency modes of combustion instability, taking combustion chamber geometry into account. Considering the configuration of the simulated combustion chamber, excitation probability of the longitudinal modes is higher than that of transversal modes. The reason of this fact is that the resonance frequency values of the longitudinal modes are less than those of transversal modes. So, the most important frequency mode, during combustion in

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21

Hubbard, S., and A. P. Dowling. "Acoustic Resonances of an Industrial Gas Turbine Combustion System." Journal of Engineering for Gas Turbines and Power 123, no. 4 (2000): 766–73. http://dx.doi.org/10.1115/1.1370975.

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A theory is developed to describe low-frequency acoustic waves in the complicated diffuser/combustor geometry of a typical industrial gas turbine. This is applied to the RB211-DLE geometry to give predictions for the frequencies of the acoustic resonances at a range of operating conditions. The main resonant frequencies are to be found around 605 Hz (associated with the plenum) and around 461 Hz and 823 Hz (associated with the combustion chamber), as well as one at around 22 Hz (a bulk mode associated with the system as a whole). The stabilizing effects of a Helmholtz resonator, which models d

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22

Rouwenhorst, Driek, Jakob Hermann, and Wolfgang Polifke. "Bifurcation study of azimuthal bulk flow in annular combustion systems with cylindrical symmetry breaking." International Journal of Spray and Combustion Dynamics 9, no. 4 (2017): 438–51. http://dx.doi.org/10.1177/1756827717715858.

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In annular combustion systems, azimuthal thermoacoustic modes manifest themselves predominantly as travelling or standing waves. Several phenomena can influence the modal behaviour of annular thermoacoustics. To monitor the stability of azimuthal thermoacoustics in industrial installations, a better understanding of the dynamics is required to correctly interpret online measurements. In this work, thermoacoustic eigensolutions of annular combustion systems are investigated, using a low-order analytic model. Heat release fluctuations are considered as a weak source term for a given acoustic eig

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23

Steele, Robert C., Luke H. Cowell, Steven M. Cannon, and Clifford E. Smith. "Passive Control of Combustion Instability in Lean Premixed Combustors." Journal of Engineering for Gas Turbines and Power 122, no. 3 (2000): 412–19. http://dx.doi.org/10.1115/1.1287166.

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A Solar fuel injector that provides lean premixed combustion conditions has been studied in a combined experimental and numerical investigation. Lean premixed conditions can be accompanied by excessive combustion driven pressure oscillations which must be eliminated before the release of a final combustor design. In order to eliminate the pressure oscillations the location of fuel injection was parametrically evaluated to determine a stable configuration. It was observed that small axial changes in the position of the fuel spokes within the premix duct of the fuel injector had a significant po

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24

Semenova, E. V., V. M. Larionov, and Yu V. Vankov. "THERMODYNAMIC AND ACOUSTIC ANALYSIS OF THE SOLID FUEL PULSATING COMBUSTION IN A HELMHOLTZ RESONATOR TYPE DEVICE." Proceedings of the higher educational institutions. ENERGY SECTOR PROBLEMS 20, no. 5-6 (2018): 141–47. http://dx.doi.org/10.30724/1998-9903-2018-20-5-6-141-147.

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One of the perspective applications of pulsating combustion is the utilization of industrial waste. There is a mathematical model and the results of calculating the frequency and amplitude of acoustic gas oscillations in a Helmholtz resonator type device using solid fuel. In this paper, pulsating combustion is considered as a result of the interaction of acoustic oscillations with the process of heat release in the combustion zone. It is shown that the frequency and amplitude of gas oscillations, the amplitude and phase of the heat release rate pulsations, the acoustic energy generated in the

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25

Pirk, Rogério, Carlos d'Andrade Souto, Dimas Donizeti da Silveira, Cândido Magno de Souza, and Luiz Carlos Sandoval Góes. "Liquid rocket combustion chamber acoustic characterization." Journal of Aerospace Technology and Management 2, no. 3 (2010): 269–78. http://dx.doi.org/10.5028/jatm.2010.02038810.

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26

Saito, Masahiro, Masayuki Sato, and Akira Nishimura. "Soot suppression by acoustic oscillated combustion." Fuel 77, no. 9-10 (1998): 973–78. http://dx.doi.org/10.1016/s0016-2361(97)00286-x.

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27

MIKAMI, Masato, Takashi MINEYAMA, Katsuyuki ITO, and Michikata KONO. "Fuel Droplet Combustion in Acoustic Field." Transactions of the Japan Society of Mechanical Engineers Series B 62, no. 600 (1996): 3178–84. http://dx.doi.org/10.1299/kikaib.62.3178.

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28

Oran, Elaine S., and John H. Gardner. "Chemical-acoustic interactions in combustion systems." Progress in Energy and Combustion Science 11, no. 4 (1985): 253–76. http://dx.doi.org/10.1016/0360-1285(85)90003-6.

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29

Hwang, D., Y. Song, and K. Ahn. "Combustion instability characteristics in a dump combustor using different hydrocarbon fuels." Aeronautical Journal 123, no. 1263 (2019): 586–99. http://dx.doi.org/10.1017/aer.2019.19.

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ABSTRACTThe combustion instability characteristics in a model dump combustor with an exhaust nozzle were experimentally investigated. The first objective was to understand the effects of operating conditions and geometric conditions on combustion instability. The second objective was to examine more generalised parameters that affect the onset of combustion instability. Three different premixed gases consisting of air and hydrocarbon fuels (C2H4, C2H6, C3H8) were burnt in the dump combustor at various inlet velocity, equivalence ratio and combustion chamber length. Dynamic pressure transducer

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30

Murugesan, Meenatchidevi, Balasubramanian Singaravelu, Abhijit K. Kushwaha, and Sathesh Mariappan. "Onset of flame-intrinsic thermoacoustic instabilities in partially premixed turbulent combustors." International Journal of Spray and Combustion Dynamics 10, no. 3 (2018): 171–84. http://dx.doi.org/10.1177/1756827718758511.

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We investigate the onset of thermoacoustic instabilities in a turbulent combustor terminated with an area contraction. Flow speed is varied in a swirl-stabilized, partially premixed combustor and the system is observed to undergo a dynamical transition from combustion noise to instability via intermittency. We find that the frequency of thermoacoustic oscillations does not lock-on to any of the acoustic modes. Instead, we observe that the dominant mode in the dynamics of combustion noise, intermittency and thermoacoustic instability is a function of the flow speed. We also find that the observ

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31

Innocenti, Alessandro, Antonio Andreini, Bruno Facchini, and Antonio Peschiulli. "Numerical analysis of the dynamic flame response of a spray flame for aero-engine applications." International Journal of Spray and Combustion Dynamics 9, no. 4 (2017): 310–29. http://dx.doi.org/10.1177/1756827717703577.

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Incoming standards on NO x emissions are motivating many aero-engine manufacturers to adopt the lean burn combustion concept. One of the most critical issues affecting this kind of technology is the occurrence of thermo-acoustic instabilities that may compromise combustor life and integrity. Therefore the prediction of the thermo-acoustic behaviour of the system becomes of primary importance. In this paper, the complex interaction between the system acoustics and a turbulent spray flame for aero-engine applications is numerically studied. The dynamic flame response is computed exploiting react

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BAILLOT, F., J. B. BLAISOT, G. BOISDRON, and C. DUMOUCHEL. "Behaviour of an air-assisted jet submitted to a transverse high-frequency acoustic field." Journal of Fluid Mechanics 640 (December 2, 2009): 305–42. http://dx.doi.org/10.1017/s002211200999139x.

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Acoustic instabilities with frequencies roughly higher than 1 kHz remain among the most harmful instabilities, able to drastically affect the operation of engines and even leading to the destruction of the combustion chamber. By coupling with resonant transverse modes of the chamber, these pressure fluctuations can lead to a large increase of heat transfer fluctuations, as soon as fluctuations are in phase. To control engine stability, the mechanisms leading to the modulation of the local instantaneous rate of heat release must be understood. The commonly developed global approaches cannot ide

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Tupov, Vladimir, and O. Matasova. "Calculation of Acoustic Efficiency of Exhaust Silencers for Automotive Internal Combustion Engines." Safety in Technosphere 9, no. 3 (2021): 41–47. http://dx.doi.org/10.12737/1998-071x-2021-9-3-41-47.

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Insertion losses as the main characteristic that mathematically describes the acoustic efficiency of a noise silencer has been considered. This characteristic shows the reduction of noise generated by its source, in particular by the internal combustion engine’s exhaust system, at the control point as a silencer use result. Has been presented a mathematical description of the insertion losses, and have been considered parameters necessary for calculating this characteristic. Has been demonstrated the analytical dependence of impedance for the sound emission by the exhaust system’s end hole fro

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34

Yap, Jin Teck, Noor Zafirah Abu Bakar, Nur Fadzilah Shaikh Dawood, and Muhammad Adam Rosli. "Design Improvements of Acoustic Response of an Automotive Air Intake System." MATEC Web of Conferences 335 (2021): 03017. http://dx.doi.org/10.1051/matecconf/202133503017.

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This study aims to improve the acoustic response of an automotive air intake system (AIS) using harmonics acoustics analysis system. Noise pollution imposes adverse health effects on human beings. One of the sources of noise pollution comes from the transportation sector. Combustion engines produce noise through the act of combustion during operation. Noise generated by the AIS affects the comfort and long-term health of humans during operations. The noise produced by the AIS can be reduced through the introduction to resonators. A baseline result was modelled through creating an internal cavi

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35

Bellucci, Valter, Bruno Schuermans, Dariusz Nowak, Peter Flohr, and Christian Oliver Paschereit. "Thermoacoustic Modeling of a Gas Turbine Combustor Equipped With Acoustic Dampers." Journal of Turbomachinery 127, no. 2 (2005): 372–79. http://dx.doi.org/10.1115/1.1791284.

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In this work, the TA3 thermoacoustic network is presented and used to simulate acoustic pulsations occurring in a heavy-duty ALSTOM gas turbine. In our approach, the combustion system is represented as a network of acoustic elements corresponding to hood, burners, flames and combustor. The multi-burner arrangement is modeled by describing the hood and combustor as Multiple Input Multiple Output (MIMO) acoustic elements. The MIMO transfer function (linking acoustic pressures and acoustic velocities at burner locations) is obtained by a three-dimensional modal analysis performed with a Finite El

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36

Józsa, Viktor. "Experimental Comparison of Diesel and Crude Rapeseed Oil Combustion in a Swirl Burner." Applied Sciences 10, no. 14 (2020): 4907. http://dx.doi.org/10.3390/app10144907.

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In pursuing maximum energy efficiency, local utilization of various crude fuels came into view. The present paper compares the combustion characteristics of standard diesel oil and crude rapeseed oil; the latter is an excellent model for high-viscosity liquid fuels. The combustion tests were performed in a 15 kW atmospheric turbulent swirl burner; the liquid fuels were atomized by a plain-jet airblast atomizer. Firstly, the acoustic signal is evaluated, since the instabilities of swirl combustion are accompanied by characteristic pressure fluctuations. The spectral analysis was performed by Wa

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CHA, DONG-JIN. "COMBUSTION INSTABILITY ANALYSIS OF A MODEL GAS TURBINE COMBUSTOR WITH CLOSED ACOUSTIC BOUNDARIES AT BOTH ENDS." International Journal of Air-Conditioning and Refrigeration 19, no. 03 (2011): 231–38. http://dx.doi.org/10.1142/s2010132511000569.

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Combustion instability is a major issue in designing gas turbine combustors for an efficient operation with low emissions. Combustion instability is induced by the interaction of the unsteady heat release of the combustion process and changes in the acoustic pressure in the combustion chamber. In an effort to develop a technique to predict self-excited combustion instability of gas turbine combustors, a new stability analysis method based on the transfer matrix method was developed. The method views the combustion system as a one-dimensional acoustic system with a side branch and describes the

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Richards, G. A., R. S. Gemmen, and M. J. Yip. "A Test Device for Premixed Gas Turbine Combustion Oscillations." Journal of Engineering for Gas Turbines and Power 119, no. 4 (1997): 776–82. http://dx.doi.org/10.1115/1.2817054.

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We report the design and operation of a test device suitable for studying combustion oscillations produced by commercial-scale gas turbine fuel nozzles. Unlike conventional test stands, this test combustor uses a Helmholtz acoustic geometry to replicate the acoustic response that would otherwise be observed only during complete engine testing. We suggest that successful simulation of engine oscillations requires that the flame geometry and resonant frequency of the test device should match the complete engine environment. Instrumentation for measuring both pressure and heat release variation i

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SCHMITT, PATRICK, T. POINSOT, B. SCHUERMANS, and K. P. GEIGLE. "Large-eddy simulation and experimental study of heat transfer, nitric oxide emissions and combustion instability in a swirled turbulent high-pressure burner." Journal of Fluid Mechanics 570 (January 3, 2007): 17–46. http://dx.doi.org/10.1017/s0022112006003156.

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Nitric oxide formation in gas turbine combustion depends on four key factors: flame stabilization, heat transfer, fuel–air mixing and combustion instability. The design of modern gas turbine burners requires delicate compromises between fuel efficiency, emissions of oxides of nitrogen (NOx) and combustion stability. Burner designs allowing substantial NOx reduction are often prone to combustion oscillations. These oscillations also change the NOx fields. Being able to predict not only the main species field in a burner but also the pollutant and the oscillation levels is now a major challenge

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40

Kru¨ger, U., J. Hu¨ren, S. Hoffmann, W. Krebs, P. Flohr, and D. Bohn. "Prediction and Measurement of Thermoacoustic Improvements in Gas Turbines With Annular Combustion Systems." Journal of Engineering for Gas Turbines and Power 123, no. 3 (2000): 557–66. http://dx.doi.org/10.1115/1.1374437.

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Environmental compatibility requires low emission burners for gas turbine power plants. In the past, significant progress has been made developing low NOx and CO burners by introducing lean premixed techniques in combination with annular combustion chambers. Unfortunately, these burners often have a more pronounced tendency to produce combustion-driven oscillations than conventional burner designs. The oscillations may be excited to such an extent that the risk of engine failure occurs. For this reason, the prediction of these thermoacoustic instabilities in the design phase of an engine becom

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Pastrone, Dario, Lorenzo Casalino, Matteo Rosa Sentinella, and Carmine Carmicino. "Acoustic Analysis of Hybrid Rocket Combustion Chambers." Journal of Propulsion and Power 26, no. 3 (2010): 415–20. http://dx.doi.org/10.2514/1.39578.

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Fichera, A., C. Losenno, and A. Pagano. "Experimental analysis of thermo-acoustic combustion instability." Applied Energy 70, no. 2 (2001): 179–91. http://dx.doi.org/10.1016/s0306-2619(01)00020-4.

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AMANO, Takuya, Ikki KUBOTA, Mikiya ARAKI, Seiji SHIBA, Mitsuhiro TSUE, and Michikata KONO. "Effects of Acoustic Disturbance on Supersonic Combustion." Transactions of the Japan Society of Mechanical Engineers Series B 66, no. 644 (2000): 1211–16. http://dx.doi.org/10.1299/kikaib.66.1211.

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Bodine, Albert G. "Acoustic detonation suppression in internal combustion engine." Journal of the Acoustical Society of America 88, no. 4 (1990): 2049. http://dx.doi.org/10.1121/1.400163.

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Dowling, Ann. "Combustion and acoustic waves—A damaging combination." Journal of the Acoustical Society of America 107, no. 5 (2000): 2815. http://dx.doi.org/10.1121/1.429079.

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Al-Masoud, N., and T. Singh. "Parametric control of combustion thermo-acoustic instabilities." IEEE Transactions on Control Systems Technology 13, no. 6 (2005): 1076–83. http://dx.doi.org/10.1109/tcst.2005.854343.

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Moshkov, P. A. "Acoustic characteristics of aero internal combustion engines." Journal of Physics: Conference Series 1891, no. 1 (2021): 012006. http://dx.doi.org/10.1088/1742-6596/1891/1/012006.

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Scarinci, Thomas, and John L. Halpin. "Industrial Trent Combustor—Combustion Noise Characteristics." Journal of Engineering for Gas Turbines and Power 122, no. 2 (2000): 280–86. http://dx.doi.org/10.1115/1.483207.

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Thermoacoustic resonance is a difficult technical problem that is experienced by almost all lean-premixed combustors. The Industrial Trent combustor is a novel dry-low-emissions (DLE) combustor design, which incorporates three stages of lean premixed fuel injection in series. The three stages in series allow independent control of two stages—the third stage receives the balance of fuel to maintain the desired power level—at all power conditions. Thus, primary zone and secondary zone temperatures can be independently controlled. This paper examines how the flexibility offered by a 3-stage lean

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Ghirardo, G., F. Boudy, and M. R. Bothien. "Amplitude statistics prediction in thermoacoustics." Journal of Fluid Mechanics 844 (April 4, 2018): 216–46. http://dx.doi.org/10.1017/jfm.2018.173.

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We discuss the statistics of acoustic pressure of thermoacoustic oscillations, either axial or azimuthal in nature. We derive a model where the describing functions of the fluctuating heat release rate of the flame and of the acoustic losses appear directly in the equations. The background combustion noise is assumed to be additive, and we show how one can recover, from the measurement of the acoustic pressure at the flame location, the projected describing function of the flame minus the acoustic losses. Using the same equations, one can predict the statistics of the amplitude of acoustic pre

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Kendrick, D. W., T. J. Anderson, W. A. Sowa, and T. S. Snyder. "Acoustic Sensitivities of Lean-Premixed Fuel Injectors in a Single Nozzle Rig." Journal of Engineering for Gas Turbines and Power 121, no. 3 (1999): 429–36. http://dx.doi.org/10.1115/1.2818491.

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An experimental and numerical investigation into the attenuation of combustion induced pressure oscillations in a single nozzle rig was undertaken at the United Technologies Research Center. Results from these investigations indicated a high combustor exit Mach number, similar to that used in a gas turbine engine, was required to correctly simulate the combustor dynamics and evaluate acoustic characteristics of lean premixed fuel injectors. Comparisons made between aerodynamically stabilized and bluff-body stabilized nozzles and the use of premixed and diffusion pilots showed that small levels

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