Results 101 to 110 of about 49,628 (234)

Experimental Study of Ignition Characteristics in Oblique-Injected Annular Combustors Using a Pre-Chamber Ignition System

Aerospace Research Communications
In this work, a pre-chamber ignition system is used to initiate the ignition in a premixed oblique-injected annular combustor. Although the introduction of the oblique-injecting burner in the gas turbine improved the gyratory flow motion and flow ...
Haroun Hassan, Haroun Hassan, Chenghao Qian, Hui Wang, Jinxiang Zhu, Haiwen Ge, Elsayed Barakat, Elsayed Barakat, Elsayed Barakat, Gaofeng Wang   +9 more
doaj   +1 more source

Combustor concepts for aircraft gas turbine low-power emissions reduction [PDF]

Several combustor concepts were designed and tested to demonstrate significant reductions in aircraft engine idle pollutant emissions. Each concept used a different approach for pollutant reductions: the hot wall combustor employs a thermal barrier ...
Dodds, W. J., Gleason, C. C., Mularz, E. J.   +2 more
core   +1 more source

Fuel combustor [PDF]

, 1977
A fuel combustor comprises a chamber with air and fuel inlets and a combination gas outlet. The fuel is supplied to a vaporization zone and fuel and air are mixed in a pair of mixing chambers, each exemplified by a swirl can.
Marek, C. J.
core   +1 more source

Combustor design and analysis using the Rocket Combustor Interactive Design (ROCCID) methodology [PDF]

The ROCket Combustor Interactive Design (ROCCID) Methodology is a newly developed, interactive computer code for the design and analysis of a liquid propellant rocket combustion chamber.
Klem, Mark D., Pieper, Jerry L., Walker, Richard E.   +2 more
core   +1 more source

Shock wave enhanced turbulent mixing in a wide-speed-range strut-based scramjet combustor

Propulsion and Energy
The efficient mixing of fuel and oxidizer in a scramjet combustor is a critical issue for achieving future wide-speed-range flight. A numerical study is conducted using Reynolds-averaged Navier–Stokes equations coupled with shear stress transport k-ω ...
Xiaofei Niu, Qian Chen
doaj   +1 more source

Research on substitutability of single-dome versus triple-dome center staged combustor

Case Studies in Thermal Engineering
To investigate the substitutability of the simulation results using the single-dome combustor as the computational domain to the triple-dome combustor, three-dimensional numerical simulations were conducted on both models and the differences in various ...
Duo Wang, Feng Li, Hongjun Lin, Tao Zhou, Kai Zhao   +4 more
doaj   +1 more source

Gas turbine engine with recirculating bleed [PDF]

, 1978
Carbon monoxide and unburned hydrocarbon emissions in a gas turbine engine are reduced by bleeding hot air from the engine cycle and introducing it back into the engine upstream of the bleed location and upstream of the combustor inlet. As this hot inlet
Adamson, A. P.
core   +1 more source

Pollution reduction technology program for small jet aircraft engines: Class T1 [PDF]

, 1977
Small jet aircraft engines (EPA class T1, turbojet and turbofan engines of less than 35.6 kN thrust) were evaluated with the objective of attaining emissions reduction consistent with performance constraints.
Bruce, T. W., Davis, F. G., Mongia, H. C.   +2 more
core   +1 more source

Combustion performance of n-butane-fueled mesoscale annular combustor

Journal of Thermal Science and Technology
The lower vapor pressure of n-butane than gaseous fuels, such as hydrogen, methane, and propane, enables its fuel containers to be compact and highly portable.
Yosuke SUENAGA, Hideki YANAOKA
doaj   +1 more source

Energy efficient engine [PDF]

The feasibility of meeting or closely approaching the emissions goals established for the Energy Efficient Engine (E3) Project with an advanced design, single annular combustor was determined.
Bahr, D. W., Burrus, D., Sabla, P. E.
core   +1 more source