Showing papers on "Afterburner published in 1999"

Integrated fan-core twin spool counter-rotating turbofan gas turbine engine

Abstract: A twin spool counter-rotating turbofan gas turbine engine having a counter-rotating fan module integrated with the high pressure compressor and driven by a counter-rotating turbine utilizing only two drive shafts. The two drive shafts are aerodynamically coupled and rotate in opposite directions relative to each other with or without the use of a gearbox. The integration between the fan module and high pressure compressor allows the fan blade rows to operate at the same mechanical speed of the high pressure compressor blade rows. An afterburner module may be added to the present invention to provide thrust augmentation.

Plant with high temperature fuel cells I

Abstract: The plant ( 1 ) contains high temperature fuel cells ( 20 ) which are arranged with planar design in a centrally symmetrical stack ( 2 ). A supply point ( 5 ) is provided for a gaseous or liquid fuel ( 50 ). In a reformer ( 4 ) following the supply point the fuel can be catalytically converted at least partially into CO and H 2 in the presence of H 2 O and with process heat being supplied. An afterburner chamber ( 6 ) follows the output points of the fuel cells ( 20 ). A feedback connection ( 61 ) exists between the supply point and the afterburner chamber via which the exhaust gas ( 60′, 70′ ) can be fed back to the supply point. In case no gas is provided as a fuel, the supply point comprises a means for feeding in a liquid fuel, such as using an atomizer.

AMA 99-2546 CFD Analysis of the LOX-Augmented Nuclear Thermal Rocket (LANTR)

Abstract: Increased rocket thrust can be achieved through the addition of mass and release of chemical energy in the nozzle of a rocket as in a jet engine afterburner. NASA and Aerojet are investigating the feasibility of injecting gaseous oxygen into the exhaust of a nuclear thermal rocket in order to temporarily increase the thrust of such a rocket. This paper describes CFD simulations of such a concept and the predicted performance of a preliminary design. DEFINITIONS OF SYMBOLS

Method for spraying fuel within a gas turbine engine to provide thrust vectoring.

Abstract: of EP0979974A fuel spraybar assembly for spraying fuel within a gas turbine engine. The spraybar assembly includes radial and lateral members that distribute fuel within the flowpath. In one embodiment two lateral members are located at the radially inward end of a radial member and generally form a "T" shape. Circumferentially spaced adjacent spraybars subdivide the flowpath into a plurality of circumferential combustion zone segments. In one embodiment the junction of the radial and lateral members provides a flameholding feature that stabilizes the combustion flame. In another embodiment, fuel is introduced non-uniformly within the afterburner resulting in thermal vectoring of the engine thrust.

System for the production of power/heat on an oil installation, and method and apparatus for the handling of hot exhaust gases from gas turbines

Abstract: In order to reduce discharge of environmentally harmful gases, particularly CO2, hot exhaust gas (G) from gas turbines used on oil recovery installations is injected into the oil reservoir, upon having passed through an afterburner/heat recovery assembly (E) and compressor equipment (C1 - C5) in which the O2 content of the exhaust gas is reduced to desired level. Heat energy recovered by the afterburner/heat recovery assembly (E) is preferably used for operating the compressor equipment (C1 - C5).

Compact, closed-loop controlled waste incinerator

Abstract: Technologies for solid and liquid waste destruction in compact incinerators are being developed in collaboration between industry, universities, and a Government laboratory. This paper reviews progress on one technology, namely active combustion control to achieve efficient and controlled afterburning of air-starved reaction products. This technology which uses synchronized waste gas injection into acoustically stabilized air vortices was transitioned to a simplified afterburner design and practical operational conditions. The full-scale, simplified afterburner, which achieved CO and NO{sub x} emissions of about 30 ppm with a residence time of less than 50 msec, was integrated with a commercially available marine incinerator to increase throughput and reduce emissions. Closed-loop active control with diode laser sensors and novel control strategies was demonstrated on a sub-scale afterburner.