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Journal articles on the topic 'Control of the combustion'

Author: Grafiati

Published: 4 June 2021

Last updated: 3 February 2022

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1

Jackson, M. D., and A. K. Agrawal. "Active Control of Combustion for Optimal Performance." Journal of Engineering for Gas Turbines and Power 121, no. 3 (July 1, 1999): 437–43. http://dx.doi.org/10.1115/1.2818492.

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Combustion-zone stoichiometry and fuel-air premixing were actively controlled to optimize the combustor performance over a range of operating conditions. The objective was to maximize the combustion temperature, while maintaining NOx within a specified limit. The combustion system consisted of a premixer located coaxially near the inlet of a water-cooled shroud. The equivalence ratio was controlled by a variable-speed suction fan located downstream. The split between the premixing air and diffusion air was governed by the distance between the premixer and shroud. The combustor performance was characterized by a cost function evaluated from time-averaged measurements of NOx and oxygen concentrations in products. The cost function was minimized by the downhill simplex algorithm employing closed-loop feedback. Experiments were conducted at different fuel flow rates to demonstrate that the controller optimized the performance without prior knowledge of the combustor behavior.

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2

Yang, Xiaojian, and Guoming G. Zhu. "A control-oriented hybrid combustion model of a homogeneous charge compression ignition capable spark ignition engine." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 226, no. 10 (May 31, 2012): 1380–95. http://dx.doi.org/10.1177/0954407012443334.

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To implement the homogeneous charge compression ignition combustion mode in a spark ignition engine, it is necessary to have smooth mode transition between the spark ignition and homogeneous charge compression ignition combustions. The spark ignition–homogeneous charge compression ignition hybrid combustion mode modeled in this paper describes the combustion mode that starts with the spark ignition combustion and ends with the homogeneous charge compression ignition combustion. The main motivation of studying the hybrid combustion mode is that the percentage of the homogeneous charge compression ignition combustion is a good parameter for combustion mode transition control when the hybrid combustion mode is used during the transition. This paper presents a control oriented model of the spark ignition–homogeneous charge compression ignition hybrid combustion mode, where the spark ignition combustion phase is modeled under the two-zone assumption and the homogeneous charge compression ignition combustion phase under the one-zone assumption. Note that the spark ignition and homogeneous charge compression ignition combustions are special cases in this combustion model. The developed model is capable of simulating engine combustion over the entire operating range, and it was implemented in a real-time hardware-in-the-loop simulation environment. The simulation results were compared with those of the corresponding GT-Power model, and good correlations were found for both spark ignition and homogeneous charge compression ignition combustions.

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3

Seume, J. R., N. Vortmeyer, W. Krause, J. Hermann, C. C. Hantschk, P. Zangl, S. Gleis, D. Vortmeyer, and A. Orthmann. "Application of Active Combustion Instability Control to a Heavy Duty Gas Turbine." Journal of Engineering for Gas Turbines and Power 120, no. 4 (October 1, 1998): 721–26. http://dx.doi.org/10.1115/1.2818459.

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During the prototype shop tests, the Model V84.3A ring combustor gas turbine unexpectedly exhibited a noticeable “humming” caused by self-excited flame vibrations in the combustion chamber for certain operating conditions. The amplitudes of the pressure fluctuations in the combustor were unusually high when compared to the previous experience with silo combustor machines. As part of the optimization program, the humming was investigated and analyzed. To date, combustion instabilities in real, complex combustors cannot be predicted analytically during the design phase. Therefore, and as a preventive measure against future surprises by “humming,” a feedback system was developed which counteracts combustion instabilities by modulation of the fuel flow rate with rapid valves (active instability control, AIC). The AIC achieved a reduction of combustion-induced pressure amplitudes by 86 percent. The Combustion instability in the Model V84.3A gas turbine was eliminated by changes of the combustor design. Therefore, the AIC is not required for the operation of customer gas turbines.

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4

Ravaglioli, Vittorio, Fabrizio Ponti, Matteo De Cesare, Federico Stola, Filippo Carra, and Enrico Corti. "Combustion Indexes for Innovative Combustion Control." SAE International Journal of Engines 10, no. 5 (September 4, 2017): 2371–81. http://dx.doi.org/10.4271/2017-24-0079.

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5

Paschereit, Christian Oliver, Peter Flohr, and Ephraim J. Gutmark. "Combustion Control by Vortex Breakdown Stabilization." Journal of Turbomachinery 128, no. 4 (February 1, 2002): 679–88. http://dx.doi.org/10.1115/1.2218521.

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Flame anchoring in a swirl-stabilized combustor occurs in an aerodynamically generated recirculation region which is a result of vortex breakdown (VBD). The characteristics of the recirculating flow are dependent on the swirl number and on axial pressure gradients. Coupling with downstream pressure pulsations in the combustor affects the VBD process. The present paper describes combustion instability that is associated with vortex breakdown. The mechanism of the onset of this instability is discussed. Passive control of the instability was achieved by stabilizing the location of vortex breakdown using an extended lance. The reduction of pressure pulsations for different operating conditions and the effect on emissions in a laboratory scale model atmospheric combustor, in a high pressure combustor facility, and in a full scale land-based gas-turbine are described. The flashback safety, one of the most important features of a reliable gas turbine burner, was assessed by CFD, water tests, and combustion tests. In addition to the passive stabilization by the extended lance it enabled injection of secondary fuel directly into the recirculation zone where the flame is stabilized. Tests were conducted with and without secondary fuel injection. Measurements and computations optimized the location of the extended lance in the mixing chamber. The effect of variation of the amount of secondary fuel injection at different equivalence ratios and output powers was determined. Flow visualizations showed that stabilization of the recirculation zone was achieved. Following the present research, the VBD stabilization method has been successfully implemented in engines with sufficient stability margins and good operational flexibility. This paper shows the development process from lab scale tests to full scale engine tests until the implementation into field engines.

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6

Corbett, N. C., and N. P. Lines. "Control Requirements for the RB 211 Low-Emission Combustion System." Journal of Engineering for Gas Turbines and Power 116, no. 3 (July 1, 1994): 527–33. http://dx.doi.org/10.1115/1.2906851.

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The RB 211 DLE series staged, premix, lean burn combustor demands total integration of control system and combustion hardware. The controls design process is described from the conception of the Engine Management System (EMS), which provides protection and control in separate environments, through to implementation of engine development testing. The process of devising an acceptable fueling strategy to each combustion stage is discussed. This identified the requirements for the computation of complex routines in order to control combustion zone temperatures. The sensitivity of the control design to external conditions of humidity, ambient temperature, and fuel composition is explored. Extensive simulation was used to determine necessary instrumentation accuracies. The paper concludes with a review of the development testing and the final control system configuration.

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7

SCHADOW, K. C., E. GUTMARK, and K. J. WILSON. "Active Combustion Control in a Coaxial Dump Combustor." Combustion Science and Technology 81, no. 4-6 (February 1992): 285–300. http://dx.doi.org/10.1080/00102209208951807.

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8

Abbondanza, Marco, Nicolò Cavina, Enrico Corti, Davide Moro, Fabrizio Ponti, and Vittorio Ravaglioli. "Development of a Combustion Delay Model in the Control of Innovative Combustions." E3S Web of Conferences 197 (2020): 06013. http://dx.doi.org/10.1051/e3sconf/202019706013.

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In modern internal combustion engines the research for innovative solutions aimed at the simultaneous reduction of engine-out pollutants and fuel consumption requires synergies from different application areas: the thermo-fluid dynamic design of the combustion chamber, the study and production of specific components for air and fuel supply, the development of sensors and related methods of analyzing their signals to control the combustion process. The most promising innovative combustion methodologies suitable to achieve high efficiency and low emissions, commonly named Low Temperature Combustions (LTC), usually require sophisticated techniques for the management of the combustion phase. With respect to the combustion angular position control, directly performed in traditional spark ignition engines through the ignition from the spark plug and in compression ignition engines by the timing of fuel injection, the ignition mechanisms of LTC combustions are characterized by a high sensitivity to the thermal conditions of the combustion chamber which greatly modifies the angular position of the combustion, mainly due to the combination of high ignition delays and lean homogeneous mixture. Once the hardware of the air and fuel supply systems has been defined, it is therefore essential to ensure the correct management of the combustion phase. In this paper a model for the estimation of the delay between the start of injection and the start of combustion is presented. The model has been developed analyzing the experimental data from a modified cylinder of a diesel engine, fueled with gasoline, while the other three cylinders were still running with Diesel fuel. This solution represents a first step that allows analyzing the behavior of the combustion of gasoline in a Diesel engine, with the final goal to inject gasoline in all the engine cylinders. In particular, the approach used is similar to the one already applied in a traditional turbocharged gasoline engine, where the goal was to estimate the time delay between the spark firing and the start of combustion, mainly to detect the presence of undesired pre-ignition due to the presence of hot spots related to slightly knocking conditions. As it is well known, the role of the pilot injection is to reduce the ignition delay of the main injection. However, to significantly accelerate the ignition of the fuel injected with the main injection, it is necessary to burn a sufficient quantity of the fuel injected by the pilot before the Top Dead Center position (TDC). The application of this model has to allow the implementation of a feed-forward control to stabilize the whole combustion process and achieve the best conversion efficiency from energy to work, taking into account the operational constraints that must be satisfied to guarantee the integrity of the engine and the compliance with the homologation rules.

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9

Zhao, Zhelong, and Xianyu Wu. "Control Oriented Model for Expander Cycle Scramjet." MATEC Web of Conferences 257 (2019): 01004. http://dx.doi.org/10.1051/matecconf/201925701004.

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As a efficient and simple design, expander cycle is widely applied in LRE engineering, but it is seldomly used on scramjet research. In order to establish a complete mathematical model for expander cycle scramjet, a control-oriented model for expander cycle scramjet is proposed in this paper. This model consists of four major parts: combustor, cooling channel, turbo pump and nozzle and gives the result of pressure, temperature, mach number and velocity distribution of combustor and cooling channel and is capable of simulate both pure supersonic combustion mode and supersonic shock wave mode of the combustor. Each part is given by specific mathematical description, which contains the calculation of airflow, combustion, heat transfer and thermal cracking of kerosene. By putting all these parts together, a complete model is formed. This model is proposed to calculate the performance and condition of the engine precisely, comprehensively, swiftly and can be directly used in further study.

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10

Yi, Tongxun, and Ephraim J. Gutmark. "Combustion Instabilities and Control of a Multiswirl Atmospheric Combustor." Journal of Engineering for Gas Turbines and Power 129, no. 1 (January 22, 2006): 31–37. http://dx.doi.org/10.1115/1.2181595.

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Thermoacoustic instability and lean blowout (LBO) are investigated experimentally in an atmospheric swirl-stabilized combustor fueled with gaseous propane. Factors affecting combustion instability are identified. Sinusoidal or steady air forcing of either the swirling air shear layer or the fuel line, with less than 1.0% of combustion air, can reduce pressure oscillations amplitude by more than 20dB. Phase-shifted close-loop air forcing of the flame can reduce the pressure oscillations amplitude by 13dB. For a constant air flow rate and air inlet temperature, initially smooth turbulent combustion exhibits relatively intense heat release oscillations with decreasing equivalence ratio, followed by a quiet state before blowout. High outer swirl intensity and a rich burning flame stabilization region can effectively extend the LBO limit.

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11

BRALEWSKI, S. G. "UNDERSTANDING AUTOMATIC COMBUSTION CONTROL." Journal of the American Society for Naval Engineers 73, no. 4 (March 18, 2009): 715–18. http://dx.doi.org/10.1111/j.1559-3584.1961.tb03329.x.

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12

Emiris, I., and J. H. Whitelaw. "Control of combustion oscillations." Combustion Science and Technology 175, no. 1 (January 2003): 157–84. http://dx.doi.org/10.1080/00102200302363.

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13

Wei, Wei, Jing Wang, Dong-hai Li, Min Zhu, and Ya-li Xue. "Feedback control of combustion oscillations in combustion chambers." Communications in Nonlinear Science and Numerical Simulation 15, no. 11 (November 2010): 3274–83. http://dx.doi.org/10.1016/j.cnsns.2009.12.020.

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14

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 (May 15, 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 positive effect on decoupling the excitation of the natural acoustic modes of the combustion system. In order to further understand the phenomenon, a time-accurate 2D CFD analysis was performed. 2D analysis was first calibrated using 3D steady-state CFD computations of the premixer in order to model the radial distribution of velocities in the premixer caused by non-uniform inlet conditions and swirling flow. 2D time-accurate calculations were then performed on the baseline configuration. The calculations captured the coupling of heat release with the combustor acoustics, which resulted in excessive pressure oscillations. When the axial location of the fuel injection was moved, the CFD analysis accurately captured the fuel time lag to the flame-front, and qualitatively matched the experimental findings. [S0742-4795(00)01103-0]

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15

Richards, G. A., and R. S. Gemmen. "Pressure-Gain Combustion: Part II—Experimental and Model Results." Journal of Engineering for Gas Turbines and Power 118, no. 3 (July 1, 1996): 469–73. http://dx.doi.org/10.1115/1.2816669.

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An experimental investigation of aerovalve pulse combustion is presented. The experimental measurements compare favorably with model predictions from a control volume analysis of the pulse combustor. Particular emphasis is placed on the mean pressure differences through the combustor as an indicator of the so-called pressure gain performance. Both the operating conditions and combustor geometry are investigated. It is shown that complex fluid/combustion interactions within the combustor make it difficult to isolate the effect of geometric changes. A scaling rule developed from the control-volume analysis is used to produce a combustor geometry capable of producing pressure gain.

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16

Richards, G. A., M. J. Yip, E. Robey, L. Cowell, and D. Rawlins. "Combustion Oscillation Control by Cyclic Fuel Injection." Journal of Engineering for Gas Turbines and Power 119, no. 2 (April 1, 1997): 340–43. http://dx.doi.org/10.1115/1.2815580.

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A number of recent articles have demonstrated the use of active control to mitigate the effects of combustion instability in afterburner and dump combustor applications. In these applications, cyclic injection of small quantities of control fuel has been proposed to counteract the periodic heat release that contributes to undesired pressure oscillations. This same technique may also be useful to mitigate oscillations in gas turbine combustors, especially in test rig combustors characterized by acoustic modes that do not exist in the final engine configuration. To address this issue, the present paper reports on active control of a subscale, atmospheric pressure nozzle/combustor arrangement. The fuel is natural gas. Cyclic injection of 14 percent control fuel in a premix fuel nozzle is shown to reduce oscillating pressure amplitude by a factor of 0.30 (i.e., −10 dB) at 300 Hz. Measurement of the oscillating heat release is also reported.

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17

Barmina, I., R. Valdmanis, and M. Zaķe. "Control of the Development of Swirling Airflow Dynamics and Its Impact on Biomass Combustion Characteristics." Latvian Journal of Physics and Technical Sciences 54, no. 3 (June 27, 2017): 30–39. http://dx.doi.org/10.1515/lpts-2017-0018.

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AbstractThe development of the swirling flame flow field and gasification/ combustion dynamics at thermo-chemical conversion of biomass pellets has experimentally been studied using a pilot device, which combines a biomass gasifier and combustor by varying the inlet conditions of the fuel-air mixture into the combustor. Experimental modelling of the formation of the cold nonreacting swirling airflow field above the inlet nozzle of the combustor and the upstream flow formation below the inlet nozzle has been carried out to assess the influence of the inlet nozzle diameter, as well primary and secondary air supply rates on the upstream flow formation and air swirl intensity, which is highly responsible for the formation of fuel-air mixture entering the combustor and the development of combustion dynamics downstream of the combustor. The research results demonstrate that at equal primary axial and secondary swirling air supply into the device a decrease in the inlet nozzle diameter enhances the upstream air swirl formation by increasing swirl intensity below the inlet nozzle of the combustor. This leads to the enhanced mixing of the combustible volatiles with the air swirl below the inlet nozzle of the combustor providing a more complete combustion of volatiles and an increase in the heat output of the device.

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18

Zhu, Denghao, Jun Deng, Jinqiu Wang, Shuo Wang, Hongyu Zhang, Jakob Andert, and Liguang Li. "Development and Application of Ion Current/Cylinder Pressure Cooperative Combustion Diagnosis and Control System." Energies 13, no. 21 (October 29, 2020): 5656. http://dx.doi.org/10.3390/en13215656.

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The application of advanced technologies for engine efficiency improvement and emissions reduction also increase the occurrence possibility of abnormal combustions such as incomplete combustion, misfire, knock or pre-ignition. Novel promising combustion modes, which are basically dominated by chemical reaction kinetics show a major difficulty in combustion control. The challenge in precise combustion control is hard to overcome by the traditional engine map-based control method because it cannot monitor the combustion state of each cycle, hence, real-time cycle-resolved in-cylinder combustion diagnosis and control are required. In the past, cylinder pressure and ion current sensors, as the two most commonly used sensors for in-cylinder combustion diagnosis and control, have enjoyed a seemingly competitive relationship, so all related researches only use one of the sensors. However, these two sensors have their own unique features. In this study, the idea is to combine the information obtained from both sensors. At first, two kinds of ion current detection system are comprehensively introduced and compared at the hardware level and signal level. The most promising variant (the DC-Power ion current detection system) is selected for the subsequent experiments. Then, the concept of ion current/cylinder pressure cooperative combustion diagnosis and control system is illustrated and implemented on the engine prototyping control unit. One application case of employing this system for homogenous charge compression ignition abnormal combustion control and its stability improvement is introduced. The results show that a combination of ion current and cylinder pressure signals can provide richer and also necessary information for combustion control. Finally, ion current and cylinder pressure signals are employed as inputs of artificial neural network (ANN) models for combustion prediction. The results show that the combustion prediction performance is better when the inputs are a combination of both signals, instead of using only one of them. This offline analysis proves the feasibility of using an ANN-based model whose inputs are a combination of ion current and pressure signals for better prediction accuracy.

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19

Paschereit, C. O., and B. Schuermans. "Combustion instability suppression by active control of the burner mixing profile(Flow Control 1)." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2005 (2005): 369–74. http://dx.doi.org/10.1299/jsmeicjwsf.2005.369.

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20

Hayashi, A. K., Y. Yamazaki, T. Mizuno, S. Ogawa, T. Yamamoto, S. Kagiya, and T. Motegi. "Active control of combustion oscillations for premixed combustion systems." Journal de Physique IV (Proceedings) 12, no. 7 (August 2002): 281–89. http://dx.doi.org/10.1051/jp4:20020295.

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21

Akhmadullin, A. N., E. N. Ahmethanov, O. V. Iovleva, and G. A. Mitrofanov. "Combustion instability control in the model of combustion chamber." Journal of Physics: Conference Series 479 (December 18, 2013): 012004. http://dx.doi.org/10.1088/1742-6596/479/1/012004.

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22

TUNESTÅL, PER. "Combustion control –an enabler forhigh-efficiency clean combustion engines." Proceedings of the International symposium on diagnostics and modeling of combustion in internal combustion engines 2017.9 (2017): PL—2. http://dx.doi.org/10.1299/jmsesdm.2017.9.pl-2.

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23

Maldonado, Bryan P., Kevin Zaseck, Eiki Kitagawa, and Anna G. Stefanopoulou. "Closed-Loop Control of Combustion Initiation and Combustion Duration." IEEE Transactions on Control Systems Technology 28, no. 3 (May 2020): 936–50. http://dx.doi.org/10.1109/tcst.2019.2898849.

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24

ASAI, Ryouichi, Young Joon YANG, Shohji TSUSHIMA, and Masashi KATSUKI. "522 Unsteady Combustion and Combustion Control by Oscillating Flow." Proceedings of Conference of Kansai Branch 2000.75 (2000): _5–43_—_5–44_. http://dx.doi.org/10.1299/jsmekansai.2000.75._5-43_.

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25

Stone, C., and S. Menon. "Swirl control of combustion instabilities in a gas turbine combustor." Proceedings of the Combustion Institute 29, no. 1 (January 2002): 155–60. http://dx.doi.org/10.1016/s1540-7489(02)80024-4.

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26

Claeys, J. P., K. M. Elward, W. J. Mick, and R. A. Symonds. "Combustion System Performance and Field Test Results of the MS7001F Gas Turbine." Journal of Engineering for Gas Turbines and Power 115, no. 3 (July 1, 1993): 537–46. http://dx.doi.org/10.1115/1.2906741.

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This paper presents the results of the combustion system test of the MS7001F installed at the Virginia Power Chesterfield station. Tests of water and steam injection for NOx control were performed. Results of emissions, combustor dynamics, and combustor hardware performance are presented. Emissions test results include NOx, CO, unburned hydrocarbons, VOC, and formaldehyde levels. Combustor dynamic activity over a range of diluent injection ratios, and the performance of an actively cooled transition duct are also discussed. Combustion system mechanical performance is described following the first combustion system inspection.

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27

HIRVONEN, JUHANI, REIJO LILJA, KARI IKONEN, and JARMO NIHTINEN. "IMAGE PROCESSING IN COMBUSTION CONTROL." International Journal of Pattern Recognition and Artificial Intelligence 10, no. 02 (March 1996): 129–37. http://dx.doi.org/10.1142/s0218001496000116.

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This paper describes an image processing system that calculates real time information from the combustion process itself. The applications of the system on burner and supplemental fuel adjustment, and ignition trend monitoring are also discussed. Finally, new combustion control based on the image information and quantitative model of the furnace is discussed.

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28

Fussey, Peter M., and David J. N. Limebeer. "A control orientated combustion model.*." IFAC Proceedings Volumes 45, no. 30 (2012): 490–97. http://dx.doi.org/10.3182/20121023-3-fr-4025.00020.

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29

Skrjanc, Igor, Jus Kocijan, and Drago Matko. "Novel Fuzzy Adaptive Combustion Control." IFAC Proceedings Volumes 31, no. 29 (October 1998): 71–72. http://dx.doi.org/10.1016/s1474-6670(17)38358-1.

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30

Škrjanc, Igor, Juš Kocijan, and Drago Matko. "Novel Fuzzy Adaptive Combustion Control." IFAC Proceedings Volumes 31, no. 29 (October 1998): 185–89. http://dx.doi.org/10.1016/s1474-6670(17)38942-5.

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31

Dowling, Ann P., and Aimee S. Morgans. "FEEDBACK CONTROL OF COMBUSTION OSCILLATIONS." Annual Review of Fluid Mechanics 37, no. 1 (January 2005): 151–82. http://dx.doi.org/10.1146/annurev.fluid.36.050802.122038.

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32

Oppenheim, A. K. "Perspective—Aerodynamic Control of Combustion." Journal of Fluids Engineering 115, no. 4 (December 1, 1993): 561–67. http://dx.doi.org/10.1115/1.2910180.

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To do useful work, the exothermic process of combustion should be carried out in an enclosure, as is typically the case with i.c. engines—the subject of this paper’s particular concern. To meet the requirements of high efficiency and low pollutant production, this process should be executed at a relatively low temperature—a condition attainable by the use of lean air-fuel mixtures. For this purpose it has to be distributed in space upon multipoint initiation and kept away from the walls to minimize their detrimental effects. In principle, all this can be accomplished by a system referred to as fireball combustion that takes advantage of entrainment and spiral mixing associated with large scale vortex structures of jet plumes. As demonstrated in this paper, the success in such an endeavor depends crucially upon the utilization of the essential elements of classical aerodynamics: the properly distributed sources, expressed in terms of velocity divergences prescribed by the thermodynamic process of combustion and of the vorticity field generated by shear between the jets and the fluid into which they are injected.

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33

Andert, Jakob, Stefan Pischinger, Heinz Pitsch, Dirk Abel, and Thivaharan Abin. "Symposium for Combustion Control 2016." International Journal of Engine Research 19, no. 2 (February 2018): 151–52. http://dx.doi.org/10.1177/1468087418760140.

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34

ZIADA, S., and H. GRAF. "FEEDBACK CONTROL OF COMBUSTION OSCILLATIONS." Journal of Fluids and Structures 12, no. 4 (May 1998): 491–507. http://dx.doi.org/10.1006/jfls.1997.0144.

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35

Burtscher, H., and A. Schmidt-Ott. "Combustion control by aerosol photoemission." Journal of Aerosol Science 20, no. 6 (January 1989): 731. http://dx.doi.org/10.1016/0021-8502(89)90069-4.

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36

Lang, Walter, Thierry Poinsot, and Sebastien Candel. "Active control of combustion instability." Combustion and Flame 70, no. 3 (December 1987): 281–89. http://dx.doi.org/10.1016/0010-2180(87)90109-x.

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37

Raftree, Linda, and Teh Fu Yen. "Particulate control for coal combustion." Organic Geochemistry 12, no. 6 (January 1988): 574. http://dx.doi.org/10.1016/0146-6380(88)90149-0.

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38

Moore, M. J. "Nox emission control in gas turbines for combined cycle gas turbine plant." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 211, no. 1 (February 1, 1997): 43–52. http://dx.doi.org/10.1243/0957650971536980.

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The increase, in recent years, in the size and efficiency of gas turbines burning natural gas in combined cycle has occurred against a background of tightening environmental legislation on the emission of nitrogen oxides. The higher turbine entry temperatures required for efficiency improvement tend to increase NOx production. First-generation emission control systems involved water injection and catalytic reduction and were relatively expensive to operate. Dry low-NOx combustion systems have therefore been developed but demand more primary air for combustion. This gives added incentive to the reduction of air requirements for cooling the combustor and turbine blading. This paper reviews the various approaches adopted by the main gas turbine manufacturers which are achieving very low levels of NOx emission from natural gas combustion. Further developments, however, are necessary for liquid fuels.

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39

KAKUYA, Hiromu. "Development of a Gasoline HCCI Engine Control System : A Combustion Switching Control Method from SI Combustion to HCCI Combustion." Journal of the Society of Mechanical Engineers 112, no. 1092 (2009): 908–11. http://dx.doi.org/10.1299/jsmemag.112.1092_908.

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40

Scarinci, Thomas, and John L. Halpin. "Industrial Trent Combustor—Combustion Noise Characteristics." Journal of Engineering for Gas Turbines and Power 122, no. 2 (January 3, 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 premixed combustion system permits the implementation of a successful combustion noise avoidance strategy at all power conditions and at all ambient conditions. This is because at a given engine condition (power level and day temperature) a characteristic “noise map” can be generated on the engine, independently of the engine running condition. The variable distribution of heat release along the length of the combustor provides an effective mechanism to control the amplitude of longitudinal resonance modes of the combustor. This approach has allowed the Industrial Trent combustion engineers to thoroughly “map out” all longitudinal combustor acoustic modes and design a fuel schedule that can navigate around regions of combustor thermoacoustic resonance. Noise mapping results are presented in detail, together with the development of noise prediction methods (frequency and amplitude) that have allowed the noise characteristics of the engine to be established over the entire operating envelope of the engine. [S0742-4795(00)00802-4]

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Auer, M. P., C. Gebauer, K. G. Mösl, C. Hirsch, and T. Sattelmayer. "Active Instability Control: Feedback of Combustion Instabilities on the Injection of Gaseous Fuel." Journal of Engineering for Gas Turbines and Power 127, no. 4 (March 1, 2004): 748–54. http://dx.doi.org/10.1115/1.1924718.

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Modern low-emission premix combustion systems are often susceptible to combustion instabilities. Active instability control (AIC) systems are commonly used to attenuate these oscillations. For the control authority of AIC systems the effective amplitude and phase of the fuel modulation at the fuel outlet are as critical as the proper injection position. In typical cases the modulation of the fuel at the location of the actuator can be fundamentally different in amplitude and phase from the modulation of the fuel flow at the fuel outlet. In addition to the well-known effects stemming from the acoustics and Mach number of the fuel system, the fuel flow in the fuel system is also modulated by the oscillation of the pressure in the combustor in case of combustion instabilities. The superposition of the upstream modulation by the actuator and the modulation downstream by the combustion instability can result in an unexpected behavior of the fuel injection, from total compensation of the modulation to very high oscillations in the resonant case, accompanied by drastic phase shifts. This paper describes the influence of the secondary fuel modulation because of the combustion instability on the control authority of AIC systems on the basis of theoretical considerations and measurements for an atmospheric test rig with a natural gas-fired swirl burner.

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Narayanaswami, L., and G. A. Richards. "Pressure-Gain Combustion: Part I—Model Development." Journal of Engineering for Gas Turbines and Power 118, no. 3 (July 1, 1996): 461–68. http://dx.doi.org/10.1115/1.2816668.

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A model for aerodynamically valved pulse combustion is presented. Particular emphasis is placed on using the model equations to identify characteristic length and time scales relevant to the design of pressure-gain combustors for gas turbine applications. The model is a control volume description of conservation laws for several regions of the pulse combustor. Combustion is modeled as a bimolecular reaction. Mixing between the fresh charge and the combustion products is modeled using a turbulent eddy time estimated from the combustor geometry and flow conditions. The model equations identify two characteristic lengths, which should be held constant during combustor scaleup, as well as certain exceptions to this approach. The effect of ambient operating pressure and inlet air temperature is also discussed.

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Zheng, Ming, Graham T. Reader, Usman Asad, Yuyu Tan, and Meiping Wang. "DE1-2: Adaptive Control to Improve Low Temperature Diesel Engine Combustion(DE: Diesel Engine Combustion,General Session Papers)." Proceedings of the International symposium on diagnostics and modeling of combustion in internal combustion engines 2008.7 (2008): 143–50. http://dx.doi.org/10.1299/jmsesdm.2008.7.143.

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Erdiwansyah, Mahidin, Husni Husin, Nasaruddin, Muhtadin, Muhammad Faisal, Asri Gani, Usman, and Rizalman Mamat. "Combustion Efficiency in a Fluidized-Bed Combustor with a Modified Perforated Plate for Air Distribution." Processes 9, no. 9 (August 24, 2021): 1489. http://dx.doi.org/10.3390/pr9091489.

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Combustion efficiency is one of the most important parameters especially in the fluidized-bed combustor. Investigations into the efficiency of combustion in fluidized-bed combustor fuels using solid biomass waste fuels in recent years are increasingly in demand by researchers around the world. Specifically, this study aims to calculate the combustion efficiency in the fluidized-bed combustor. Combustion efficiency is calculated based on combustion results from the modification of hollow plates in the fluidized-bed combustor. The modified hollow plate aims to control combustion so that the fuel incorporated can burn out and not saturate. The combustion experiments were tested using palm oil biomass solid waste fuels such as palm kernel shell, oil palm midrib, and empty fruit bunches. The results of the measurements showed that the maximum combustion temperature for the palm kernel shell fuel reached 863 °C for M1 and 887 °C for M2. The maximum combustion temperature measurements for M1 and M2 from the oil palm midrib fuel testing reached 898 °C and 858 °C, respectively, while the maximum combustion temperature for M1 and M2 from the empty fruit bunches fuel was 667 °C and M2 847 °C, respectively. The rate of combustion efficiency with the modification of the hole plate in the fluidized-bed combustor reached 96.2%. Thermal efficiency in fluidized-bed combustors for oil palm midrib was 72.62%, for PKS was 70.03%, and for empty fruit bunches was 52.43%. The highest heat transfer rates for the oil palm midrib fuel reached 7792.36 W/m2, palm kernel shell 7167.38 W/m2, and empty fruit bunches 5127.83 W/m2. Thus, the modification of the holed plate in the fluidized-bed combustor chamber showed better performance of the plate than without modification.

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Mohanraj, Rajendran, Yedidia Neumeier, and Ben T. Zinn. "Combustor Model for Simulation of Combustion Instabilities and Their Active Control." Journal of Propulsion and Power 16, no. 3 (May 2000): 485–91. http://dx.doi.org/10.2514/2.5594.

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Paschereit, Christian Oliver, and Ephraim Gutmark. "Proportional Control of Combustion Instabilities in a Simulated Gas-Turbine Combustor." Journal of Propulsion and Power 18, no. 6 (November 2002): 1298–304. http://dx.doi.org/10.2514/2.6067.

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Kasagi, Nobuhide. "TOWARD SMART CONTROL OF TURBULENT JET MIXING AND COMBUSTION(Keynote Lecture)." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2005 (2005): 45–53. http://dx.doi.org/10.1299/jsmeicjwsf.2005.45.

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Iyengar, Vishwas, Harold Simmons, and David Ransom. "Flash Atomization: A New Concept to Control Combustion Instability in Water-Injected Gas Turbines." Journal of Combustion 2012 (2012): 1–10. http://dx.doi.org/10.1155/2012/718202.

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The objective of this work is to explore methods to reduce combustor rumble in a water-injected gas turbine. Attempts to use water injection as a means to reduce NOXemissions in gas turbines have been largely unsuccessful because of increased combustion instability levels. This pulsation causes chronic fretting, wear, and fatigue that damages combustor components. Of greater concern is that liberated fragments could cause extensive damage to the turbine section. Combustion instability can be tied to the insufficient atomization of injected water; large water droplets evaporate non-uniformly that lead to energy absorption in chaotic pulses. Added pulsation is amplified by the combustion process and acoustic resonance. Effervescent atomization, where gas bubbles are injected, is beneficial by producing finely atomized droplets; the gas bubbles burst as they exit the nozzles creating additional energy to disperse the liquid. A new concept for effervescent atomization dubbed “flash atomization” is presented where water is heated to just below its boiling point in the supply line so that some of it will flash to steam as it leaves the nozzle. An advantage of flash atomization is that available heat energy can be used rather than mechanical energy to compress injection gas for conventional effervescent atomization.

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Haskara, Ibrahim, and Yue-Yun Wang. "Closed-Loop Combustion Noise Limit Control for Modern Diesel Combustion Modes." IEEE Transactions on Control Systems Technology 25, no. 4 (July 2017): 1168–79. http://dx.doi.org/10.1109/tcst.2016.2597747.

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Zhang, Yong, Yuan Yao, and Ting Luan. "Boiler Combustion Control System Optimization Strategy." Applied Mechanics and Materials 397-400 (September 2013): 1064–68. http://dx.doi.org/10.4028/www.scientific.net/amm.397-400.1064.

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Optimal control of the boiler combustion system is related to the economy and stability of the entire production process. To the problem that the boiler main product steam quality and the safe operation of the boiler optimization control, the fuzzy adaptive algorithm combined with the traditional PID control in the DCS system is proposed. The method optimizes the control system parameters and improves the control program. The simulation results show that the control scheme is better than the traditional PID control, and has good dynamic performance and stability. Both the boiler outlet steam quality and the security operation of boiler are improved.

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