Results 21 to 30 of about 22,484 (217)

Acoustic Boundary Conditions for Can-Annular Combustors

International Journal of Turbomachinery, Propulsion and Power, 2023
This paper derives and validates an analytical model for acoustic boundary conditions on a can-annular gas turbine combustion system composed of discrete cans connected to an open annulus upstream of a turbine.
James Brind
doaj   +1 more source

Influence of Fluidic Control in a Staged Lean Jet Engine Burner on Combustor Performance

Fluids, 2019
To improve the turn-down ratio of a lean combustor, which has the greatest potential for reducing NOx emissions from jet engines, fuel staging is commonly employed.
Seiji Yoshida, Christoph Hassa, Takeshi Yamamoto, Johannes Heinze, Michael Schroll   +4 more
doaj   +1 more source

Jet engine combustor parametric analyzes [PDF]

INCAS Bulletin
The combustion processes specific to jet engines involve aerodynamic, thermodynamic, combustion chemistry and heat transfer aspects with implications on performance and environmental pollution reduction. The operating performances of a combustion chamber
Vasile PRISACARIU, Irina ANDREI, Ionica CIRCIU   +2 more
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Linear Instability Analysis of Lean Premixed Combustion

Journal of Thermal Science and Technology, 2012
Combustion oscillation of a self excited combustion-acoustic phenomenon occurs inside the gas turbine combustor. In general, excessive pressure fluctuation of combustion oscillation may impair the gas turbine engine operation and may result in hardware ...
Kazufumi IKEDA, Keisuke MATSUYAMA, Mitsunori ISONO, Masaharu NISHIMURA   +3 more
doaj   +1 more source

Experimental and Numerical Investigations of Plasma Ignition Characteristics in Gas Turbine Combustors

Energies, 2019
Reliable ignition is critical for improving the operating performance of modern combustor and gas turbines. As an alternative to the traditional spark discharge ignition, plasma assisted ignition has attracted more interest and been shown to be more ...
Shizheng Liu, Ningbo Zhao, Jianguo Zhang, Jialong Yang, Zhiming Li, Hongtao Zheng   +5 more
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Study on the Influence of the Pilot Stage Swirl Intensity on the Double-Swirl Combustor’s Ignition Process via Large Eddy Simulation

Machines, 2023
The ignition reliability of the combustion chamber is crucial for the overall performance of an engine. As the aero-engine combustion chambers continue to advance, the scope of the ignition problem has also expanded.
Pengfei Zhu, Hongyu Ju, Yue Li, Yue Yan, Jianqin Suo, Zhenxia Liu   +5 more
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Optimal Design and Application of Gas Analysis System

Xibei Gongye Daxue Xuebao, 2020
To accurately measure the performance parameters of an aero-engine combustor under high-temperature and high-pressure environment, such as outlet temperature, combustion efficiency and pollutant emission, the optimal design of the existing gas sampling ...

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Gas Turbine Combustion and Ammonia Removal Technology of Gasified Fuels

Energies, 2010
From the viewpoints of securing a stable supply of energy and protecting our global environment in the future, the integrated gasification combined cycle (IGCC) power generation of various gasifying methods has been introduced in the world.
Takeharu Hasegawa
doaj   +1 more source

Simulation of the GOx/GCH4 Multi-Element Combustor Including the Effects of Radiation and Algebraic Variable Turbulent Prandtl Approaches

Energies, 2020
Multi-element thrusters operating with gaseous oxygen (GOX) and methane (GCH4) have been numerically studied and the results were compared to test data from the Technical University of Munich (TUM).
Evgenij Strokach, Igor Borovik, Oscar Haidn   +2 more
doaj   +1 more source

Heat Transfer Characteristics of Pin-Fin Arrays with Ribs to Cool Combustor Liners

Journal of Thermal Science and Technology, 2009
Enhancement of heat transfer by pin-fin channels with turbulence promoters has been investigated with an aim to improve the cooling efficiency of combustor liners in gas turbines.
Yutaka ODA, Kenichiro TAKEISHI, Yusuke MOTODA, Shinsuke SUGIMOTO, Yoshiaki MIYAKE   +4 more
doaj   +1 more source