Journal articles: 'Combustion Phenomena'

1

Faeth, G. M. "Spray combustion phenomena." Symposium (International) on Combustion 26, no. 1 (January 1996): 1593–612. http://dx.doi.org/10.1016/s0082-0784(96)80383-3.

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2

Meinköhn, Dirk. "Characteristic phenomena in combustion." Discrete Dynamics in Nature and Society 1, no. 2 (1997): 147–59. http://dx.doi.org/10.1155/s1026022697000150.

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For the case of a reaction–diffusion system, the stationary states may be represented by means of a state surface in a finite-dimensional state space. In the simplest example of a single semi-linear model equation given. in terms of a Fredholm operator, and under the assumption of a centre of symmetry, the state space is spanned by a single state variable and a number of independent control parameters, whereby the singularities in the set of stationary solutions are necessarily of the cuspoid type. Certain singularities among them represent critical states in that they form the boundaries of sheets of regular stable stationary solutions. Critical solutions provide ignition and extinction criteria, and thus are of particular physical interest. It is shown how a surface may be derived which is below the state surface at any location in state space. Its contours comprise singularities which correspond to similar singularities in the contours of the state surface, i.e., which are of the same singularity order. The relationship between corresponding singularities is in terms of lower bounds with respect to a certain distinguished control parameter associated with the name of Frank-Kamenetzkii.

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NIIOKA, Takashi. "Fascinated by Combustion Phenomena." Transactions of the Japan Society of Mechanical Engineers Series B 73, no. 736 (2007): 2391–92. http://dx.doi.org/10.1299/kikaib.73.2391.

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4

IINUMA, Kazuo. "Combustion phenomena and their modeling." Journal of the Fuel Society of Japan 64, no. 1 (1985): 19–25. http://dx.doi.org/10.3775/jie.64.19.

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Lu, Chuan, and Yannis C. Yortsos. "Percolation Phenomena in Filtration Combustion." Industrial & Engineering Chemistry Research 43, no. 12 (June 2004): 3008–18. http://dx.doi.org/10.1021/ie0306372.

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Dreizin, Edward L., and Michael A. Trunov. "Surface phenomena in aluminum combustion." Combustion and Flame 101, no. 3 (May 1995): 378–82. http://dx.doi.org/10.1016/0010-2180(94)00241-j.

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7

Odgers, J., D. Kretschmer, and G. F. Pearce. "The Combustion of Droplets Within Gas Turbine Combustors: Some Recent Observations on Combustion Efficiency." Journal of Engineering for Gas Turbines and Power 115, no. 3 (July 1, 1993): 522–32. http://dx.doi.org/10.1115/1.2906739.

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For many years investigators studying the combustion behavior within gas turbines have presumed droplet size to play a very important role in defining combustion efficiency. Recently a very large number of experiments have been conducted jointly by Laval University and the Aeronautical Research Laboratory in Melbourne. In the course of these investigations, over a wide range of operating conditions, a single combustor has been investigated using three different Simplex atomizers at each of the conditions for three fuels. In addition, the same combustor has been used to investigate a very wide range of fuels (87) at ambient inlet conditions. The measured combustion efficiencies show no measurable effects due to droplet size, although volatility effects have been noted (measured as TAV). It is thought that these effects are reflected in terms of a transfer number and related to diffusional phenomena, rather than evaporative phenomena. A great number of experimental data are reviewed, and in addition to showing the absence of effects of droplets, a small section deals with the precision of experimental values of combustion efficiency and how it might influence models predicting combustion efficiency, especially with respect to possible future pollution requirements.

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8

Correa, S. M., A. J. Dean, and I. Z. Hu. "Combustion Technology for Low-Emissions Gas-Turbines:Selected Phenomena Beyond NOx." Journal of Energy Resources Technology 118, no. 3 (September 1, 1996): 193–200. http://dx.doi.org/10.1115/1.2793862.

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Since recent reviews cover the issues in NOx formation under gas-turbine canditions, and since regulations essentially dictate use of the premixed mode of combustion for minimum NOx, this review concentrates on phenomena that can arise in premixed combustion. Specifically, 1) the initial unmixedness in a fuel-air premixer has been shown to make overall lean mixtures autoignite sooner than might be expected based on the overall fuel-air ratio, because the richer portions of the mixture lead the process;2) combustion pressure oscillations caused by the interplay between acoustic waves and unsteady heat release in a one-dimensional system can be calculated in good accordance with measured data, and set the stage for multi-dimensional CFD;3) carbon deposition arising from the flow of liquid fuel over metal surfaces such as found in fuel injectors and swirl cups has been described as a function of temperature and of surface composition; and 4) quenching and subsequent emissions of carbon monoxide can be minimized by preservation of a boundary-layer rather than an impingement type of flow over combustor liners.

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9

Eckl, Wilhelm, Norbert Eisenreich, W. Liehmann, K. Menke, Th Rohe, and Volker Weiser. "COMBUSTION PHENOMENA OF BORON CONTAINING PROPELLANTS." International Journal of Energetic Materials and Chemical Propulsion 4, no. 1-6 (1997): 896–905. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop..v4.i1-6.830.

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10

Curran, E. T., W. H. Heiser, and D. T. Pratt. "Fluid Phenomena in Scramjet Combustion Systems." Annual Review of Fluid Mechanics 28, no. 1 (January 1996): 323–60. http://dx.doi.org/10.1146/annurev.fl.28.010196.001543.

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11

Chung, T. J., Y. M. Kim, and J. L. Sohn. "Finite element analysis in combustion phenomena." International Journal for Numerical Methods in Fluids 7, no. 10 (October 1987): 989–1012. http://dx.doi.org/10.1002/fld.1650071002.

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12

Takacs, Laszlo. "Combustion Phenomena Induced by Ball Milling." Materials Science Forum 269-272 (January 1998): 513–22. http://dx.doi.org/10.4028/www.scientific.net/msf.269-272.513.

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13

Austin, Joanna M. "Irreversible Phenomena: Ignitions, Combustion and Detonation Waves." AIAA Journal 46, no. 2 (February 2008): 541–42. http://dx.doi.org/10.2514/1.34579.

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14

Eisenreich, Norbert, Volker Weiser, Wilhelm Eckl, Thomas Fischer, Stefan Kelzenberg, and Gesa Langer. "COMBUSTION PHENOMENA OF THE GUN PROPELLANT JA2." International Journal of Energetic Materials and Chemical Propulsion 5, no. 1-6 (2002): 251–62. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.v5.i1-6.270.

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15

Bozzano, G., M. Dente, T. Faravelli, and E. Ranzi. "Fouling phenomena in pyrolysis and combustion processes." Applied Thermal Engineering 22, no. 8 (June 2002): 919–27. http://dx.doi.org/10.1016/s1359-4311(02)00009-1.

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16

Cerimele, M. M., and F. Pistella. "Simulation of planar high speed combustion phenomena." International Journal of Numerical Methods for Heat & Fluid Flow 6, no. 5 (May 1996): 63–70. http://dx.doi.org/10.1108/09615539610125971.

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17

Anthony, E. J., and D. L. Granatstein. "Sulfation phenomena in fluidized bed combustion systems." Progress in Energy and Combustion Science 27, no. 2 (January 2001): 215–36. http://dx.doi.org/10.1016/s0360-1285(00)00021-6.

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18

Kirdyashkin, A. I., V. D. Kitler, V. G. Salamatov, R. A. Yusupov, and Yu M. Maksimov. "Capillary hydrodynamic phenomena in gas-free combustion." Combustion, Explosion, and Shock Waves 43, no. 6 (November 2007): 645–53. http://dx.doi.org/10.1007/s10573-007-0087-1.

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19

Maksimov, Yu M., A. I. Kirdyashkin, R. M. Gabbasov, and V. G. Salamatov. "Emission phenomena in a SHS combustion wave." Combustion, Explosion, and Shock Waves 45, no. 4 (July 2009): 454–60. http://dx.doi.org/10.1007/s10573-009-0056-y.

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20

Margolis, Stephen B. "Higher-order bifurcation phenomena in premixed combustion." Nuclear Physics B - Proceedings Supplements 2 (November 1987): 608. http://dx.doi.org/10.1016/0920-5632(87)90077-6.

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21

Caridi, A., E. Cereda, S. Fazinic, M. Jaksic, G. M. Braga Marcazzan, O. Valkovic, and V. Valkovic. "Fluorine enrichment phenomena in coal combustion cycle." Nuclear Instruments and Methods in Physics Research Section B: Beam Interactions with Materials and Atoms 66, no. 1-2 (March 1992): 298–301. http://dx.doi.org/10.1016/0168-583x(92)96168-x.

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22

Weber, R. O., and S. D. Watt. "Combustion waves." Journal of the Australian Mathematical Society. Series B. Applied Mathematics 38, no. 4 (April 1997): 464–76. http://dx.doi.org/10.1017/s0334270000000801.

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AbstractFinding critical phenomena in two-dimensional combustion is normally done numerically. By using a centre-manifold reduction, we can find a reduced equation in one dimension. Once we have found the reduced equation, it is simpler to find critical phenomena. We consider two different problems. One is spontaneous ignition. We compare our results with known critical parameters to give some validity to our reduction technique. We also look at a combustion model with three equilibrium states. For this model, the possible transitions can occur as travelling waves between the unstable to either of the stable equilibrium or from one stable to the other stable state. For the latter transition, the direction of the transition tells us whether we have an extinction or ignition wave. We find the critical parameters when the direction of the wave changes.

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23

Cui, T., and Z. Liu. "Numerical investigation of symmetry breaking and multi-loop hysteresis phenomena in a symmetric supersonic combustor." Aeronautical Journal 119, no. 1221 (November 2015): 1437–49. http://dx.doi.org/10.1017/s0001924000011337.

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AbstractNumerical investigations are performed to study the features of symmetry breaking phenomena in a symmetric supersonic combustor. By changing the fuel equivalence ratio, the symmetry breaking phenomena are numerically observed. Further, the hysteresis behaviours are observed along with the phenomena of symmetry breaking by increasing and then decreasing the the fuel equivalence ratio. Furthermore, more complex hysteresis phenomenon, i.e., multi-loop hysteresis, is observed numerically. The multi-loop hysteresis consists of both major and minor loops, and is associated with the interaction between multiple flow structures. Due to the fact that different flow structures would result in different flow conditions, the findings regarding the existence of hysteresis behaviours can significantly affect the combustion process and even the performance of the engine. It is hoped that the observation of the (multi-loop) hysteresis phenomenon may bring it to the attention of those investigators whose experiments maybe affected by its occurrence.

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24

Tsai, Hsin-Luen, and Huei-Huang Chiu. "ANOMALOUS GROUP COMBUSTION PHENOMENA IN DI DIESEL ENGINES." Atomization and Sprays 15, no. 4 (2005): 377–400. http://dx.doi.org/10.1615/atomizspr.v15.i4.20.

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25

Laurence, S. J., S. Karl, J. Martinez Schramm, and K. Hannemann. "Transient fluid-combustion phenomena in a model scramjet." Journal of Fluid Mechanics 722 (March 28, 2013): 85–120. http://dx.doi.org/10.1017/jfm.2013.56.

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AbstractAn experimental and numerical investigation of the unsteady phenomena induced in a hydrogen-fuelled scramjet combustor under high-equivalence-ratio conditions is carried out, focusing on the processes leading up to unstart. The configuration for the study is the fuelled flow path of the HyShot II flight experiment. Experiments are performed in the HEG reflected-shock wind tunnel, and results are compared with those obtained from unsteady numerical simulations. High-speed schlieren and OH∗ chemiluminescence visualization, together with time-resolved surface pressure measurements, allow links to be drawn between the experimentally observed flow and combustion features. The transient flow structures signalling the onset of unstart are observed to take the form of an upstream-propagating shock train. Both the speed of propagation and the downstream location at which the shock train originates depend strongly on the equivalence ratio. The physical nature of the incipient shock system, however, appears to be similar for different equivalence ratios. Both experiments and computations indicate that the primary mechanism responsible for the transient behaviour is thermal choking, though localized boundary-layer separation is observed to accompany the shock system as it moves upstream. In the numerical simulations, the global choking behaviour is dictated by the limited region of maximum heat release around the shear layer between the injected hydrogen and the incoming air flow. This leads to the idea of ‘local’ thermal choking and results in a lower choking limit than is predicted by a simple integral analysis. Such localized choking makes it possible for new quasi-steady flow topologies to arise, and these are observed in both experiments and simulation. Finally, a quasi-unsteady one-dimensional analytical model is proposed to explain elements of the shock-propagation behaviour.

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26

Saeed, M. N., and N. A. Henein. "Combustion Phenomena of Alcohols in C. I. Engines." Journal of Engineering for Gas Turbines and Power 111, no. 3 (July 1, 1989): 439–44. http://dx.doi.org/10.1115/1.3240273.

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A study was conducted on a direct-injection, single-cylinder, research-type diesel engine to determine the effect of adding ethanol or isopropanol to diesel fuel on the ignition delay period. The test parameters were alcohol content, intake-air properties, and fuel-air ratio. It was found that the ignition delay of alcohol-diesel blends is prolonged as the alcohol content is increased. Ethanol-diesel blends developed longer ignition delays than those developed by isopropanol-diesel blends. The results showed that ignition delay of alcohol-diesel blends can be effectively shortened using intake-air preheating and/or supercharging. The high activation energy of alcohols with respect to diesel fuel is believed to be responsible for the long ignition delays associated with the use of alcohols as alternate fuels in compression ignition engines.

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27

Rafidi, Nabil, Wlodzimierz Blasiak, and Ashwani K. Gupta. "High-Temperature Air Combustion Phenomena and Its Thermodynamics." Journal of Engineering for Gas Turbines and Power 130, no. 2 (2008): 023001. http://dx.doi.org/10.1115/1.2795757.

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28

Yamaguchi, Akira, and Yuji Tajima. "Sodium pool combustion phenomena under natural convection airflow." Nuclear Engineering and Design 239, no. 7 (July 2009): 1331–37. http://dx.doi.org/10.1016/j.nucengdes.2009.04.004.

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29

Monagheddu, M., N. Bertolino, P. Giuliani, C. Zanotti, and U. Anselmi Tamburini. "Ignition phenomena in combustion synthesis: An experimental methodology." Journal of Applied Physics 92, no. 1 (July 2002): 594–99. http://dx.doi.org/10.1063/1.1486254.

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30

Lee, Dae Hoon. "SCALE EFFECTS ON COMBUSTION PHENOMENA IN A MICROCOMBUSTOR." Microscale Thermophysical Engineering 7, no. 3 (January 2003): 235–51. http://dx.doi.org/10.1080/10893950390219074.

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31

Melik-Gaikazov, G. V. "Critical phenomena in the combustion of condensed substances." Combustion, Explosion, and Shock Waves 29, no. 1 (1993): 1–7. http://dx.doi.org/10.1007/bf00755318.

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32

Yuan, Yi Xiang, Peng Fu Xie, Wen Yu Cao, Cong Chen, Chao Yu, De Jun Zhan, and Chun Qing Tan. "A Preliminary Study on Lean Blowout of One Combustion Stability Device." Advanced Materials Research 732-733 (August 2013): 63–66. http://dx.doi.org/10.4028/www.scientific.net/amr.732-733.63.

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The lean blowout experiments of the combustion stability device A (multi-vortexes-dome combustor model) have been carried out at atmospheric pressure. In contrast with the experimental data of device B, and the result shows that the lean blowout performance of the device A is superior to the device B at low operating condition. Furthermore, both the devices A and B were modeled, and the combustion numerical simulations were performed with the steady Flamelet model of non-premixed combustion and the simplified mechanism of methane-air reaction with 14 species and 26 step elementary reactions. The numerical results are in agreement with the experimental phenomena.

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33

Gany, Alon. "Micro and Nano Scale Phenomena of Aluminum Agglomeration During Solid Propellant Combustion." Eurasian Chemico-Technological Journal 18, no. 3 (November 5, 2016): 161. http://dx.doi.org/10.18321/ectj422.

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Combustion of aluminized solid propellants exhibits phenomena associated with accumulation, agglomeration, ignition, and combustion of micro and nano-size aluminum particles. In general, agglomeration is an undesirable phenomenon, as it turns small particles into relatively large agglomerates, each containing many original particles, resulting in long combustion times which may lead to incomplete reaction, reduced jet momentum, and enhanced slag formation which adds parasite mass and may damage the motor insulation. This article presents a physical mechanism explaining the agglomeration process, revealing that small particles tend to agglomerate more than large particles. In addition, it suggests ways to reduce agglomeration of the aluminum particles via nano-coatings generating reactive heating and promoting ignition.

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34

Grimm, Felix, Jürgen Dierke, Roland Ewert, Berthold Noll, and Manfred Aigner. "Modelling of combustion acoustics sources and their dynamics in the PRECCINSTA burner test case." International Journal of Spray and Combustion Dynamics 9, no. 4 (July 7, 2017): 330–48. http://dx.doi.org/10.1177/1756827717717390.

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A stochastic, hybrid computational fluid dynamics/computational combustion acoustics approach for combustion noise prediction is applied to the PRECCINSTA laboratory scale combustor (prediction and control of combustion instabilities in industrial gas turbines). The numerical method is validated for its ability to accurately reproduce broadband combustion noise levels from measurements. The approach is based on averaged flow field and turbulence statistics from computational fluid dynamics simulations. The three-dimensional fast random particle method for combustion noise prediction is employed for the modelling of time-resolved dynamics of sound sources and sound propagation via linearised Euler equations. A comprehensive analysis of simulated sound source dynamics is carried out in order to contribute to the understanding of combustion noise formation mechanisms. Therefrom gained knowledge can further on be incorporated for the investigation of onset of thermoacoustic phenomena. The method-inherent stochastic Langevin ansatz for the realisation of turbulence related source decay is analysed in terms of reproduction ability of local one- and two-point statistical input and therefore its applicability to complex test cases. Furthermore, input turbulence statistics are varied, in order to investigate the impact of turbulence on the resulting sound pressure spectra for a swirl stabilised, technically premixed combustor.

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35

Chambers, Steven, Horia Flitan, Paul Cizmas, Dennis Bachovchin, Thomas Lippert, and David Little. "The Influence of In Situ Reheat on Turbine-Combustor Performance." Journal of Engineering for Gas Turbines and Power 128, no. 3 (March 1, 2004): 560–72. http://dx.doi.org/10.1115/1.2135812.

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This paper presents a numerical and experimental investigation of the in situ reheat necessary for the development of a turbine-combustor. The flow and combustion were modeled by the Reynolds-averaged Navier-Stokes equations coupled with the species conservation equations. The chemistry model used herein was a two-step, global, finite rate combustion model for methane and combustion gases. A numerical simulation was used to investigate the validity of the combustion model by comparing the numerical results against experimental data obtained for an isolated vane with fuel injection at its trailing edge. The numerical investigation was then used to explore the unsteady transport phenomena in a four-stage turbine-combustor. In situ reheat simulations investigated the influence of various fuel injection parameters on power increase, airfoil temperature variation, and turbine blade loading. The in situ reheat decreased the power of the first stage, but increased more the power of the following stages, such that the power of the turbine increased between 2.8% and 5.1%, depending on the parameters of the fuel injection. The largest blade excitation in the turbine-combustor corresponded to the fourth-stage rotor, with or without combustion. In all cases analyzed, the highest excitation corresponded to the first blade passing frequency.

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36

Shchepakina, Elena. "A geometric approach to the modelling of critical phenomena for a spray combustion model." MATEC Web of Conferences 209 (2018): 00014. http://dx.doi.org/10.1051/matecconf/201820900014.

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The paper is devoted to the modelling of the critical phenomena in multiscale combustion models. Such models are usually described by singularly perturbed systems of differential equations to reflect the significant distinction in characteristic relaxation times of different physicochemical processes. The paper proposes an approach for modelling of critical phenomena on the basis of the geometric asymptotic method of invariant manifolds. The critical phenomenon means as a sharp change in the dynamics of the process under consideration. As an illustration of this approach a dynamic model of fuel spray ignition and combustion is considered. The realizability conditions for the critical regime is obtained in the form of the asymptotic expression for the control parameter. The main feature of the critical regime is that during it the temperature of the combustible mixture can reach a high value within the framework of a safe process. It is shown that the critical regime plays the role of a watershed between the slow combustion regimes and the thermal explosion.

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37

Bychkov, V., M. Modestov, and C. K. Law. "Combustion phenomena in modern physics: I. Inertial confinement fusion." Progress in Energy and Combustion Science 47 (April 2015): 32–59. http://dx.doi.org/10.1016/j.pecs.2014.10.001.

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38

Hurt, Robert H. "Reactivity distributions and extinction phenomena in coal char combustion." Energy & Fuels 7, no. 6 (November 1993): 721–33. http://dx.doi.org/10.1021/ef00042a005.

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39

KOBAYASHI, Hideaki. "Research of Combustion Phenomena in a High-Pressure Environment." Transactions of the Japan Society of Mechanical Engineers Series B 66, no. 645 (2000): 1257–63. http://dx.doi.org/10.1299/kikaib.66.1257.

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40

SUZUKI, Minoru. "Prediction of Flow and Combustion Phenomena in MSW Incinerator." Proceedings of the Symposium on Environmental Engineering 2002.12 (2002): 277–80. http://dx.doi.org/10.1299/jsmeenv.2002.12.277.

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41

Križan, Gregor, Janez Križan, Ivan Bajsić, and Miran Gaberšček. "Control of a pulse combustion reactor with thermoacoustic phenomena." Instrumentation Science & Technology 46, no. 1 (May 19, 2017): 43–57. http://dx.doi.org/10.1080/10739149.2017.1320288.

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42

PEARLMAN, H. G., and S. H. SOHRAB. "SHORT COMMUNICATION Some Examples of Hysteresis Phenomena in Combustion." Combustion Science and Technology 76, no. 4-6 (April 1991): 311–19. http://dx.doi.org/10.1080/00102209108951715.

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43

Vlasenko, V. V., V. A. Sabelnikov, S. S. Molev, O. V. Voloshchenko, M. A. Ivankin, and S. M. Frolov. "Transient combustion phenomena in high-speed flows in ducts." Shock Waves 30, no. 3 (April 2020): 245–61. http://dx.doi.org/10.1007/s00193-020-00941-4.

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44

Ivashchenko, Yu S., V. M. Zenchenko, V. L. Pavlenko, and A. L. Sadyrin. "Ionization phenomena near the combustion surface of ballistic powder." Combustion, Explosion, and Shock Waves 20, no. 5 (1985): 525–27. http://dx.doi.org/10.1007/bf00782242.

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45

Cherepnin, S. N. "Investigations of electrophysical phenomena in jet engine combustion chambers." Combustion, Explosion, and Shock Waves 26, no. 2 (1990): 178–80. http://dx.doi.org/10.1007/bf00742406.

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46

Huang, Xinyan, and Yuji Nakamura. "A Review of Fundamental Combustion Phenomena in Wire Fires." Fire Technology 56, no. 1 (October 30, 2019): 315–60. http://dx.doi.org/10.1007/s10694-019-00918-5.

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47

Ramos, J. I. "Adaptive and nonadaptive Hermitian operator methods for combustion phenomena." Computer Methods in Applied Mechanics and Engineering 90, no. 1-3 (September 1991): 609–30. http://dx.doi.org/10.1016/0045-7825(91)90174-5.

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48

Wattanavichien, Kanit, and Akihiko Azetsu. "Studies of Visualized Diesohol Combustion Phenomena in IDI Engine(CNG and Alternative Fuels, Oxygenated Fuels)." Proceedings of the International symposium on diagnostics and modeling of combustion in internal combustion engines 2004.6 (2004): 423–30. http://dx.doi.org/10.1299/jmsesdm.2004.6.423.

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49

Vanoverberghe, K. P., E. V. Van den Bulck, M. J. Tummers, and W. A. Hu¨bner. "Multiflame Patterns in Swirl-Driven Partially Premixed Natural Gas Combustion." Journal of Engineering for Gas Turbines and Power 125, no. 1 (December 27, 2002): 40–45. http://dx.doi.org/10.1115/1.1520159.

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Five different flame states are identified in a compact combustion chamber that is fired by a 30 kW swirl-stabilized partially premixed natural gas burner working at atmospheric pressure. These flame states include a nozzle-attached tulip shaped flame, a nonattached torroidal-ring shaped flame (SSF) suitable for very low NOx emission in a gas turbine combustor and a Coanda flame (CSF) that clings to the bottom wall of the combustion chamber. Flame state transition is generated by changing the swirl number and by premixing the combustion air with 70% of the natural gas flow. The flame state transition pathways reveal strong hysteresis and bifurcation phenomena. The paper also presents major species concentrations, temperature and velocity profiles of the lifted flame state and the Coanda flame and discusses the mechanisms of flame transition and stabilization.

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50

Zhu, M., A. P. Dowling, and K. N. C. Bray. "Self-Excited Oscillations in Combustors With Spray Atomizers." Journal of Engineering for Gas Turbines and Power 123, no. 4 (October 1, 2000): 779–86. http://dx.doi.org/10.1115/1.1376717.

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Combustors with fuel-spray atomizers are susceptible to a low-frequency oscillation, particularly at idle and sub-idle conditions. For aero-engine combustors, the frequency of this oscillation is typically in the range 50–120 Hz and is commonly called “rumble.” In the current work, computational fluid dynamics (CFD) is used to simulate this self-excited oscillation. The combustion model uses Monte Carlo techniques to give simultaneous solutions of the Williams’ spray equation together with the equations of turbulent reactive flow. The unsteady combustion is calculated by the laminar flamelet presumed pdf method. A quasi-steady description of fuel atomizer behavior is used to couple the inlet flow in the combustor. A choking condition is employed at turbine inlet. The effects of the atomizer and the combustor geometry on the unsteady combustion are studied. The results show that, for some atomizers, with a strong dependence of mean droplet size on air velocity, the coupled system undergoes low-frequency oscillations. The numerical results are analyzed to provide insight into the rumble phenomena. Basically, pressure variations in the combustor alter the inlet air and fuel spray characteristics, thereby changing the rate of combustion. This in turn leads to local “hot spots,” which generate pressure fluctuations as they convect through the downstream nozzle.

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Journal articles on the topic 'Combustion Phenomena'

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