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Journal articles on the topic 'Fuel rich combustion'

Author: Grafiati

Published: 4 June 2021

Last updated: 8 February 2022

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1

Nakata, T., M. Sato, T. Ninomiya, and T. Hasegawa. "A Study on Low NOx Combustion in LBG-Fueled 1500°C-Class Gas Turbine." Journal of Engineering for Gas Turbines and Power 118, no. 3 (1996): 534–40. http://dx.doi.org/10.1115/1.2816680.

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Developing integrated coal gasification combined-cycle systems ensures cost-effective and environmentally sound options for supplying future power generation needs. The reduction of NOx emissions and increasing the inlet temperature of gas turbines are the most significant issues in gas turbine development in Integrated Coal Gasification Combined Cycle (IGCC) power generation systems. The coal gasified fuel, which is produced in a coal gasifier of an air-blown entrained-flow type has a calorific value as low as 1/10 of natural gas. Furthermore, the fuel gas contains ammonia when a gas cleaning

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2

Micklow, G. J., S. Roychoudhury, H. L. Nguyen, and M. C. Cline. "Emissions Reduction by Varying the Swirler Airflow Split in Advanced Gas Turbine Combustors." Journal of Engineering for Gas Turbines and Power 115, no. 3 (1993): 563–69. http://dx.doi.org/10.1115/1.2906744.

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A staged combustor concept for reducing pollutant emissions is currently under investigation. A numerical study was performed to investigate the chemically reactive flow with liquid spray injection for staged combustion. The staged combustor consists of an airblast atomizer fuel injector, a rich burn section, a converging connecting pipe, a quick mix zone, a diverging connecting pipe and a lean combustion zone. For computational efficiency, the combustor was split into two subsystems, i.e., the fuel nozzle/rich burn section and the quick mix/lean burn section. The current study investigates th

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3

Li, Chaolong, Zhixun Xia, Likun Ma, Xiang Zhao, and Binbin Chen. "Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity." Energies 12, no. 7 (2019): 1235. http://dx.doi.org/10.3390/en12071235.

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Scramjet based on solid propellant is a good supplement for the power device of future hypersonic vehicles. A new scramjet combustor configuration using solid fuel, namely, the solid fuel rocket scramjet (SFRSCRJ) combustor is proposed. The numerical study was conducted to simulate a flight environment of Mach 6 at a 25 km altitude. Three-dimensional Reynolds-averaged Navier–Stokes equations coupled with shear stress transport (SST) k − ω turbulence model are used to analyze the effects of the cavity and its position on the combustor. The feasibility of the SFRSCRJ combustor with cavity is dem

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4

MORITA, Takakazu, Kenichi TAKANO, Hidenori NAKAZAWA, Satoru YOSHIDA, and Yousuke TACHIBANA. "Combustion Characteristics of Fuel-Rich Solid Propellants." Proceedings of Conference of Kanto Branch 2004.10 (2004): 549–50. http://dx.doi.org/10.1299/jsmekanto.2004.10.549.

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5

Ahn, Kyubok, and Hwan-Seok Choi. "Combustion Dynamics of Swirl Coaxial Injectors in Fuel-Rich Combustion." Journal of Propulsion and Power 28, no. 6 (2012): 1359–67. http://dx.doi.org/10.2514/1.b34448.

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6

Chen, Yi, Li Fei, Liming He, Lei Zhang, Chunchang Zhu, and Jun Deng. "The Influence of Dielectric Barrier Discharge Plasma on the Characteristics of Aero-Engine Combustion Chamber." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 37, no. 2 (2019): 369–77. http://dx.doi.org/10.1051/jnwpu/20193720369.

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A test platform was developed to investigate the performance of aero-engine combustor by the dielectric barrier discharge (DBD) plasma assisted combustion (PAC) in the simulated maximum condition. Conventional combustion experiments and plasma-assisted combustion conditions were conducted to study the effect of PAC on the performances including average outlet temperature, combustion efficiency and pattern factor under four different excessive air coefficients five different voltages. The comparative experiment shows that the combustion efficiency is improved after PAC compared with the normal

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7

Cowell, L. H., R. T. LeCren, and C. E. Tenbrook. "Two-Stage Slagging Combustor Design for a Coal-Fueled Industrial Gas Turbine." Journal of Engineering for Gas Turbines and Power 114, no. 2 (1992): 359–66. http://dx.doi.org/10.1115/1.2906599.

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A full-size combustor for a coal-fueled industrial gas turbine engine has been designed and fabricated. The design is based on extensive work completed through one-tenth scale combustion tests. Testing of the combustion hardware will be completed with a high pressure air supply in a combustion test facility before the components are integrated with the gas turbine engine. The combustor is a two-staged, rich-lean design. Fuel and air are introduced in the primary combustion zone where the combustion process is initiated. The primary zone operates in a slagging mode inertially removing coal ash

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8

Wu, Horng-Wen, Tzu-Ting Hsu, and Rong-Fang Horng. "Hydrogen-Rich Gas for Clean Combustion in a Dual-Fuel Compression Ignition Engine." Journal of Clean Energy Technologies 5, no. 2 (2017): 135–41. http://dx.doi.org/10.18178/jocet.2017.5.2.358.

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9

Pein, Roland, and S. Anders. "INVESTIGATION OF FUEL-RICH BORON COMBUSTION IN A PRESSURIZED COMBUSTION BOMB." International Journal of Energetic Materials and Chemical Propulsion 5, no. 1-6 (2002): 427–37. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.v5.i1-6.460.

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10

Foelsche, Robert O., Joseph M. Keen, Wayne C. Solomon, Parker L. Buckley, and Edwin Corporan. "Nonequilibrium combustion model for fuel-rich gas generators." Journal of Propulsion and Power 10, no. 4 (1994): 461–72. http://dx.doi.org/10.2514/3.23796.

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11

Ahn, Kyubok, Seonghyeon Seo, and Hwan-Seok Choi. "Fuel-Rich Combustion Characteristics of Biswirl Coaxial Injectors." Journal of Propulsion and Power 27, no. 4 (2011): 864–72. http://dx.doi.org/10.2514/1.b34121.

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12

Lindgren, Eric R., David W. Pershing, D. A. Kirchgessner, and D. C. Drehmel. "Fuel rich sulfur capture in a combustion environment." Environmental Science & Technology 26, no. 7 (1992): 1427–33. http://dx.doi.org/10.1021/es00031a022.

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13

Song, Eunhye, and Juhun Song. "Modeling of kerosene combustion under fuel-rich conditions." Advances in Mechanical Engineering 9, no. 7 (2017): 168781401771138. http://dx.doi.org/10.1177/1687814017711388.

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The turbo-pump and turbine are driven by liquid fuel fed into a gas generator, where the fuel is oxidized with a liquid oxidizing agent. For stable operation of the turbine, the combustion temperature of the gas generator must be maintained below 1000 K. The thermodynamic characteristics of kerosene oxidation in the gas generator must be understood to optimize the design and operation conditions of the liquid-fueled rocket engine system. Herein, the 3-species surrogate mixture model for kerosene was selected, and the detailed Dagaut’s kerosene oxidation mechanism consisting of 225 chemical spe

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14

Yuliati, Lilis, Mega Nur Sasongko, and Slamet Wahyudi. "Flammability Limit and Flame Visualization of Gaseous Fuel Combustion Inside Meso-scale Combustor with Different Thermal Conductivity." Applied Mechanics and Materials 493 (January 2014): 204–9. http://dx.doi.org/10.4028/www.scientific.net/amm.493.204.

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This study experimentally investigated effect of thermal conductivity on the combustioncharacteristics of gaseous fuel inside a meso-scale combustor. Combustion characteristics that wereobserved in this research include flame visualization and flammability limit. Quartz glass, stainlesssteel and copper tubes with inner diameters of 3.5 mm were used as combustors. Stainless steel wiremesh was inserted inside meso-scale combustor as a flame holder. Liquid petroleum gas (LPG),which is common fuel use by Indonesian people, was used as a gaseous fuel. A stable blue flame wasestablished inside meso-

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15

Hu, Jichao, Juntao Chang, and Wen Bao. "Ignition and Flame Stabilization of a Strut-Jet RBCC Combustor with Small Rocket Exhaust." Scientific World Journal 2014 (2014): 1–6. http://dx.doi.org/10.1155/2014/675498.

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A Rocket Based Combined Cycle combustor model is tested at a ground direct connected rig to investigate the flame holding characteristics with a small rocket exhaust using liquid kerosene. The total temperature and the Mach number of the vitiated air flow, at exit of the nozzle are 1505 K and 2.6, respectively. The rocket base is embedded in a fuel injecting strut and mounted in the center of the combustor. The wall of the combustor is flush, without any reward step or cavity, so the strut-jet is used to make sure of the flame stabilization of the second combustion. Mass flow rate of the keros

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16

Fyffe, John R., Mark A. Donohue, Maria C. Regalbuto, and Chris F. Edwards. "Mixed combustion–electrochemical energy conversion for high-efficiency, transportation-scale engines." International Journal of Engine Research 18, no. 7 (2016): 701–16. http://dx.doi.org/10.1177/1468087416665936.

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This article discusses an approach to exceeding current peak exergy efficiencies of approximately 50% for transportation-scale engines. A detailed model was developed for an internal combustion engine and a fuel cell, where the internal combustion engine is operated under fuel-rich conditions to produce a hydrogen-rich exhaust gas as a fuel for the fuel cell. The strategy of using combustion and electrochemical energy conversion processes has been shown to reduce reaction-related exergy losses while providing the balance of plant necessary to achieve efficient thermal management. Prior approac

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17

Wu, X., K. Li, and D. Jiang. "Investigation of air-fuel ratio control using ionic current signal." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 221, no. 9 (2007): 1139–46. http://dx.doi.org/10.1243/09544070jauto359.

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The objective of this paper is to investigate the control of air-fuel ratio (AFR) using an ionic current signal. Experimental measurements have been carried out to study the characteristics of the ionic current signal near ignition poles in a constant-volume combustion bomb. The ionic signal is characterized by a front flame and post flame during combustion. The intensity of the ionic signal strongly depends on the AFR at the time of combustion. The maximum values in both the front flame and the post flame will occur at close to the stoichiometric value. Furthermore, minimum values of the dura

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18

Schultze, Marco, and John Mantzaras. "Hetero-/homogeneous combustion of hydrogen/air mixtures over platinum: Fuel-lean versus fuel-rich combustion modes." International Journal of Hydrogen Energy 38, no. 25 (2013): 10654–70. http://dx.doi.org/10.1016/j.ijhydene.2013.06.069.

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19

Kidoguchi, Y., M. Sanda, and K. Miwa. "Experimental and Theoretical Optimization of Combustion Chamber and Fuel Distribution for the Low Emission Direct-Injection Diesel Engine." Journal of Engineering for Gas Turbines and Power 125, no. 1 (2002): 351–57. http://dx.doi.org/10.1115/1.1501077.

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Effects of combustion chamber geometry and initial mixture distribution on the combustion process were investigated in a direct-injection diesel engine. In the engine experiment, a high squish combustion chamber with a squish lip could reduce both NOx and particulate emissions with retarded injection timing. According to the results of CFD computation and phenomenological modeling, the high squish combustion chamber with a central pip is effective to keep the combusting mixture under the squish lip until the end of combustion and the combustion region forms rich and highly turbulent atmosphere

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20

Liu, Ting, Xin Chen, Hui Xiang Xu, et al. "The Effect of Li-Al Alloy on Combustion Performance of B/PTFE Fuel-Rich Propellant." Advanced Materials Research 904 (March 2014): 222–27. http://dx.doi.org/10.4028/www.scientific.net/amr.904.222.

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In order to increase the ignition performance and combustion performance of B/PTFE fuel-rich propellant,Li-Al alloy is used to increase the sensitivity of B/PTFE fuel-rich propellant.The impact sensitivity、friction sensitivity、 combustion temperature、 burning rate combustion heat and TGA are tested.The results showed that the sensitivity、combustion heat and ignition performance increase much.The burning rate increased 30~50% and the combustion temperature was relatively stable about 800°C.

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21

Feitelberg, A. S., and M. A. Lacey. "The GE Rich-Quench-Lean Gas Turbine Combustor." Journal of Engineering for Gas Turbines and Power 120, no. 3 (1998): 502–8. http://dx.doi.org/10.1115/1.2818173.

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The General Electric Company has developed and successfully tested a full-scale, F-class (2550°F combustor exit temperature), rich-quench-lean (RQL) gas turbine combustor, designated RQL2, for low heating value (LHV) fuel and integrated gasification combined cycle applications. Although the primary objective of this effort was to develop an RQL combustor with lower conversion of fuel bound nitrogen to NOx than a conventional gas turbine combustor, the RQL2 design can be readily adapted to natural gas and liquid fuel combustion. RQL2 is the culmination of a 5 year research and development effor

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22

Shaykin, A. P., and I. R. Galiev. "Influence Intensity Turbulence on the Width of the Zone Chemical Reactions and Speed Distribution of Methane-Hydrogen Flame." Siberian Journal of Physics 14, no. 4 (2019): 69–73. http://dx.doi.org/10.25205/2541-9447-2019-14-4-28-69-73.

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The prospects using methane-hydrogen fuel in power plants are shown. The effect of turbulence intensity on propagation velocity and width of the zone of chemical reactions methane-hydrogen flame in combustion chamber of variable volume is investigated. The article shows that effect of turbulence intensity on propagation velocity and flame width depends on fuel excess coefficient. During combustion of stoichiometric fuel-air mixtures, an increase in turbulence leads to a more noticeable increase in flame velocity than when burning poor and rich mixtures. It was experimentally found that increas

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23

Hussain, Dr Mohammad N., and Rusul M. Khazaal. "Effects of Fuel - Air Ratio on the Flame Propagation for S.I. Engines." Journal of Petroleum Research and Studies 2, no. 1 (2021): 117–24. http://dx.doi.org/10.52716/jprs.v2i1.39.

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As a result of the rapid development in the various transport means, a great concern was shown in the design and development of spark-ignition engines to achieve the best efficiency and performance and to guarantee a full combustion of the fuel inside the combustion chamber to avail all the energy of the fuel entering the cylinder. This work involves the study of the reaction equations of the combustion for stochiometric and rich cases, and the study of combustion products and their effects on the environment.

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24

Colantonio, R. O. "The Applicability of Jet-Shear-Layer Mixing and Effervescent Atomization for Low-NOx Combustors." Journal of Engineering for Gas Turbines and Power 120, no. 1 (1998): 17–23. http://dx.doi.org/10.1115/1.2818073.

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An investigation has been conducted to develop appropriate technologies for a low-NOx, liquid-fueled combustor. The combustor incorporates an effervescent atomizer used to inject fuel into a premixing duct. Only a fraction of the combustion air is used in the premixing process. This fuel-rich mixture is introduced into the remaining combustion air by a rapid jet-shear-layer mixing process involving radial fuel–air jets impinging on axial air jets in the primary combustion zone. Computational modeling was used as a tool to facilitate a parametric analysis appropriate to the design of an optimum

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25

Lyubovsky, Maxim, Lance L. Smith, Marco Castaldi, et al. "Catalytic combustion over platinum group catalysts: fuel-lean versus fuel-rich operation." Catalysis Today 83, no. 1-4 (2003): 71–84. http://dx.doi.org/10.1016/s0920-5861(03)00217-7.

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26

Chen, D. M., S. P. Luh, T. K. Liu, G. K. Wu, and H. C. Perng. "COMBUSTION STUDY OF BORON-BASED FUEL-RICH SOLID PROPELLANT." International Journal of Energetic Materials and Chemical Propulsion 2, no. 1-6 (1991): 375–85. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.v2.i1-6.220.

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27

Maggi, Filippo, and Francesco Zadra. "Combustion of Nanoaluminum and Magnesium in Fuel‐Rich Propellants." Propellants, Explosives, Pyrotechnics 45, no. 5 (2020): 724–29. http://dx.doi.org/10.1002/prep.201900354.

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28

Lee, Dongeun, and Changjin Lee. "Fuel-Rich Combustion Characteristic of a Combined Gas Generator." Journal of the Korean Society for Aeronautical & Space Sciences 43, no. 7 (2015): 593–600. http://dx.doi.org/10.5139/jksas.2015.43.7.593.

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29

Landi, G., P. S. Barbato, S. Cimino, L. Lisi, and G. Russo. "Fuel-rich methane combustion over Rh-LaMnO3 honeycomb catalysts." Catalysis Today 155, no. 1-2 (2010): 27–34. http://dx.doi.org/10.1016/j.cattod.2009.01.020.

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30

Vaughn, Craig B., Jack B. Howard, and John P. Longwell. "Benzene destruction in fuel-rich jet-stirred reactor combustion." Combustion and Flame 87, no. 3-4 (1991): 278–88. http://dx.doi.org/10.1016/0010-2180(91)90113-p.

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31

Wang, Guodong, Jing Suming, Guoqing Liu, and Xingyong Gao. "Review on the Synthesis and Properties of the Energetic Compound Containing Boron." Current Organic Chemistry 24, no. 10 (2020): 1097–107. http://dx.doi.org/10.2174/1385272824999200516180719.

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Boron possesses the second greatest heating value of any element that can be adopted as an energetic material in the processing of propellants and explosives. It has become the first choice as a high energy fuel for solid fuel-rich propellants because of its advantages of high theoretical combustion heat. In the actual condition, the combustion efficiency of boron-containing fuel-rich propellants is low, and the potential energy of boron cannot be fully utilized. The compound containing-boron can be used as a new way to improve the combustion efficiency of fuel-rich propellants. In this paper,

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32

Yang, Pengnian, Zhixun Xia, Likun Ma, et al. "Direct-Connect Test of Solid Scramjet with Symmetrical Structure." Energies 14, no. 17 (2021): 5589. http://dx.doi.org/10.3390/en14175589.

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The solid scramjet has become one of the most promising engine types. In this paper, we report the first direct-connect test of a solid scramjet with symmetrical structure, carried out using boron-based fuel-rich solid propellant as fuel. During the test, which simulated a flight environment at Mach 5.6 and 25 km, the performance of the solid scramjet was obtained by measuring the pressure, thrust, and mass flow. The results show that, due to the change in the combustion area of the propellant and the deposition of the throat in the gas generator during the test, the equivalence ratio graduall

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33

Smith, Lance L., Hasan Karim, Marco J. Castaldi, et al. "Rich-Catalytic Lean-Burn Combustion for Low-Single-Digit NOx Gas Turbines." Journal of Engineering for Gas Turbines and Power 127, no. 1 (2005): 27–35. http://dx.doi.org/10.1115/1.1787510.

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A new rich-catalytic lean-burn combustion concept (trademarked by PCI as RCL) was tested at industrial gas turbine conditions, in Solar Turbines’ high-pressure (17 atm) combustion rig and in a modified Solar Turbines engine, demonstrating ultralow emissions of NOx<2 ppm and CO<10 ppm for natural gas fuel. For the single-injector rig tests, an RCL catalytic reactor replaced a single swirler/injector. NOx<3 ppm and CO<10 ppm were achieved over a 110°C operating range in flame temperature, including NOx<1 ppm at about 1350°C flame temperature. Combustion noise was less than 0.15% p

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34

Apicella, B., A. Ciajolo, R. Barbella, et al. "Size Exclusion Chromatography of Particulate Produced in Fuel-Rich Combustion of Different Fuels." Energy & Fuels 17, no. 3 (2003): 565–70. http://dx.doi.org/10.1021/ef020149r.

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35

Di Sarli, Valeria. "Stability and Emissions of a Lean Pre-Mixed Combustor with Rich Catalytic/Lean-burn Pilot." International Journal of Chemical Reactor Engineering 12, no. 1 (2014): 77–89. http://dx.doi.org/10.1515/ijcre-2013-0112.

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Abstract In this work, a reactor network model was developed to study homogeneous gas-phase methane combustion taking place under typical operating conditions of lean pre-mixed combustors piloted by rich catalytic/lean-burn (RCL) systems. In particular, the thermo-kinetic interaction between the pilot stream (i.e. the stream exiting the RCL stage) and the main feeding stream to the homogeneous reactor was investigated in terms of combustion stability and emissions. The homogeneous combustor was modeled as a perfectly stirred reactor (PSR). The pilot stream was mixed with the main feeding strea

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36

Wan'e, Wu, and Zhu Zuoming. "Calculation for Primary Combustion Characteristics of Boron-Based Fuel-Rich Propellant Based on BP Neural Network." Journal of Combustion 2012 (2012): 1–6. http://dx.doi.org/10.1155/2012/635190.

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A practical scheme for selecting characterization parameters of boron-based fuel-rich propellant formulation was put forward; a calculation model for primary combustion characteristics of boron-based fuel-rich propellant based on backpropagation neural network was established, validated, and then was used to predict primary combustion characteristics of boron-based fuel-rich propellant. The results show that the calculation error of burning rate is less than %; in the formulation range (hydroxyl-terminated polybutadiene 28%–32%, ammonium perchlorate 30%–35%, magnalium alloy 4%–8%, catocene 0%–

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37

Seo, Seonghyeon, Seong-Ku Kim, and Hwan-Seok Choi. "Combustion Dynamics and Stability of a Fuel-Rich Gas Generator." Journal of Propulsion and Power 26, no. 2 (2010): 259–66. http://dx.doi.org/10.2514/1.46568.

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38

Fox, Dennis S., Elizabeth J. Opila, and Raiford E. Hann. "Paralinear Oxidation of CVD SiC in Simulated Fuel-Rich Combustion." Journal of the American Ceramic Society 83, no. 7 (2004): 1761–67. http://dx.doi.org/10.1111/j.1151-2916.2000.tb01461.x.

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39

Nakata, T., M. Sato, and T. Hasegawa. "Reaction of Fuel NOx Formation for Gas Turbine Conditions." Journal of Engineering for Gas Turbines and Power 120, no. 3 (1998): 474–80. http://dx.doi.org/10.1115/1.2818169.

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Ammonia contained in coal-gasified fuel is converted to nitrogen oxides (NOx) in the combustion process of a gas turbine in integrated coal gasification combined cycle (IGCC) system. Research data on fuel-NOx formation are insufficient, and there still remains a wide explored domain. The present research aims at obtaining fundamental knowledge of fuel-NOx formation characteristics by applying reaction kinetics to gas turbine conditions. An instantaneous mixing condition was assumed in the cross section of a gas turbine combustor and both gradual mixing condition and instantaneous mixing condit

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40

Nakata, T., M. Sato, T. Ninomiya, T. Yoshine, and M. Yamada. "Effect of Pressure on Combustion Characteristics in LBG-Fueled 1300°C-Class Gas Turbine." Journal of Engineering for Gas Turbines and Power 116, no. 3 (1994): 554–58. http://dx.doi.org/10.1115/1.2906855.

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Developing integrated coal gasification combined cycle systems ensures that Japan will have cost-effective and environmentally sound options for supplying future power generation needs. Reduction of NOx emissions and increasing the inlet temperature of gas turbines are the most significant issues in gas turbine development in IGCC. The coal gasified fuel, which is produced in a coal gasifier of air blown entrained-flow type has a calorific value as low as 1/10 of natural gas. Furthermore, the fuel gas contains ammonia when a gas cleaning system is a hot type, and ammonia will be converted to n

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41

Yoshizawa, Koudai, Atsushi Teraji, Hiroshi Miyakubo, Koichi Yamaguchi, and Tomonori Urushihara. "Study of High Load Operation Limit Expansion for Gasoline Compression Ignition Engines." Journal of Engineering for Gas Turbines and Power 128, no. 2 (2006): 377–87. http://dx.doi.org/10.1115/1.1805548.

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In this research, combustion characteristics of gasoline compression ignition engines have been analyzed numerically and experimentally with the aim of expanding the high load operation limit. The mechanism limiting high load operation under homogeneous charge compression ignition (HCCI) combustion was clarified. It was confirmed that retarding the combustion timing from top dead center (TDC) is an effective way to prevent knocking. However, with retarded combustion, combustion timing is substantially influenced by cycle-to-cycle variation of in-cylinder conditions. Therefore, an ignition timi

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42

Gejji, Rohan M., Cheng Huang, Christopher Fugger, Changjin Yoon, and William Anderson. "Parametric investigation of combustion instabilities in a single-element lean direct injection combustor." International Journal of Spray and Combustion Dynamics 11 (July 13, 2018): 175682771878585. http://dx.doi.org/10.1177/1756827718785851.

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Self-excited combustion dynamics in a liquid-fueled lean direct injection combustor at high pressure (1 MPa) are described. Studied variables include combustor and air plenum length, inlet air temperature, equivalence ratio, fuel nozzle location, and fuel composition. Measured pressure oscillations were dependent on combustor geometry and ranged from about 1% of mean chamber pressure at low equivalence ratio, up to 20% at high equivalence ratio. In the most unstable cases, strong pressure modes were measured throughout the frequency spectrum including a band around 1.2–1.5 kHz representing the

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43

Nazri, Mohammad, and Mohd Jaafar. "Reduction of NOx Emission from Gas TURBINE COMBUSTOR Applying Fuel-Staged Combustion." ASEAN Journal of Chemical Engineering 2, no. 1 (2008): 61. http://dx.doi.org/10.22146/ajche.50804.

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A two-stage lean/lean gas turbine combustor was developed with low NOx characteristics in each stage using a small radial swirler of 40-mm outlet diameter in the pilot stage. Both flame tubes were arranged in series with the smaller combustor (76 mm inside diameter) as the pilot stage and the larger combustor (140 mm inside diameter) as the main stage. The pilot stage was fuelled via vane passage fuel injector, while the main stage was fuelled around the wall of the exit plane of the pilot stage, using wall fuel injectors. Low NOx emissions were obtained when using fuel staging for methane fue

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44

Pei, Yiqiang, Jing Qin, Yuli Dai, and Kun Wang. "Investigation on the spray development, the combustion characteristics and the emissions of Fischer–Tropsch fuel and diesel fuel from direct coal liquefaction." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 231, no. 13 (2017): 1829–37. http://dx.doi.org/10.1177/0954407016687861.

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Diesel fuel is largely consumed by transportation services, and diesel fuel from direct coal liquefaction and Fischer–Tropsch fuel have been produced as alternatives in coal-rich areas. However, the physicochemical characteristics of the two fuels are not quite the same as those of diesel fuel derived from crude oil. Therefore, the spray development, the combustion characteristics and the emissions of diesel fuel from direct coal liquefaction, Fischer–Tropsch fuel and commercial diesel fuel were studied in this paper. The spray development was investigated by using planar laser-induced fluores

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Garland, R. V., and P. W. Pillsbury. "Status of Topping Combustor Development for Second-Generation Fluidized Bed Combined Cycles." Journal of Engineering for Gas Turbines and Power 114, no. 1 (1992): 126–31. http://dx.doi.org/10.1115/1.2906294.

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Addition of a fluidized bed combustor to a high-efficiency combined cycle plant enables direct firing of inexpensive run-of-the-mine coal in an environmentally acceptable manner. To attain high thermal efficiencies, coal pyrolysis is included. The low heating value fuel gas from the pyrolyzer is burned in a topping combustion system that boosts gas turbine inlet temperature to state of the art while the pyrolyzer-produced char is burned in the bed. The candidate topping combustor, the multi-annular swirl burner, based on a design by J. M. Bee´r, is presented and discussed. Design requirements

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McGuirk, J. J. "The aerodynamic challenges of aeroengine gas-turbine combustion systems." Aeronautical Journal 118, no. 1204 (2014): 557–99. http://dx.doi.org/10.1017/s0001924000009386.

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Abstract The components of an aeroengine gas-turbine combustor have to perform multiple tasks – control of external and internal air distribution, fuel injector feed, fuel/air atomisation, evaporation, and mixing, flame stabilisation, wall cooling, etc. The ‘rich-burn’ concept has achieved great success in optimising combustion efficiency, combustor life, and operational stability over the whole engine cycle. This paper first illustrates the crucial role of aerodynamic processes in achieving these performance goals. Next, the extra aerodynamic challenges of the ‘lean-burn’ injectors required t

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Akselvoll, Knut, and Parviz Moin. "Large-eddy simulation of turbulent confined coannular jets." Journal of Fluid Mechanics 315 (May 25, 1996): 387–411. http://dx.doi.org/10.1017/s0022112096002479.

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Large-eddy simulation (LES) was used to study mixing of turbulent, coannular jets discharging into a sudden expansion. This geometry resembles that of a coaxial jet-combustor, and the goal of the calculation was to gain some insight into the phenomena leading to lean blow-out (LBO) in such combustion devices. This is a first step in a series of calculations, where the focus is on the fluid dynamical aspects of the mixing process in the combustion chamber. The effects of swirl, chemical reactions and heat release were not taken into account. Mixing of fuel and oxidizer was studied by tracking a

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Miyoshi, Masaki, Yudai Yamasaki, Shigehiko Kaneko, and Akane Uemichi. "Influence of In-cylinder Fuel Reformation by Over-rich SI Combustion on Methane HCCI Combustion." Proceedings of the National Symposium on Power and Energy Systems 2016.21 (2016): C113. http://dx.doi.org/10.1299/jsmepes.2016.21.c113.

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Hasegawa, T., M. Sato, and T. Ninomiya. "Effect of Pressure on Emission Characteristics in LBG-Fueled 1500°C-Class Gas Turbine." Journal of Engineering for Gas Turbines and Power 120, no. 3 (1998): 481–87. http://dx.doi.org/10.1115/1.2818170.

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Developing integrated coal gasification combined cycle (IGCC) systems ensures cost-effective and environmentally sound options for supplying future power generation needs. In order to enhance thermal efficiency of IGCC and to reduce NOx emission, a 1500°C-class gas turbine combustor for IGCC was designed, tested, and the performance of the combustor was evaluated under pressurized conditions. The designed combustor had the following three characteristics: (1) in order to assure the stable combustion burning low-Btu gas (LBG), an auxiliary combustion chamber was installed at the entrance of the

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Makita, Takurou, Takahisa Yamamoto, Tomohiko Furuhata, and Norio Arai. "Numerical Simulation of High-Pressure and Fuel-Rich Turbulent Combustion Field." Journal of Propulsion and Power 19, no. 2 (2003): 226–34. http://dx.doi.org/10.2514/2.6122.

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