Afterburner

About: Afterburner is a research topic. Over the lifetime, 811 publications have been published within this topic receiving 5944 citations.

Reusable booster rocket

Abstract: FIELD: space equipment.SUBSTANCE: invention relates to space engineering, particularly, to reusable spacecrafts. Manned or unmanned reusable carrier rocket includes module with cruise rocket engines, lateral accelerating modules and integrated control system. Lateral radial engines are used in vertical landing mode to create stable total balancing reactive moment relative to center of gravity of lower part of carrier rocket and to ensure flight in dense layers of atmosphere. Engines are made by turbojet two-circuit turbojet engines or turbojet two-circuit turbojets with afterburner. During operation of mid-flight rocket engines in upper layers of atmosphere, inlet openings of air intakes for engines of turbojet engine or turbojet engine are closed with retractable fairings.EFFECT: reusable transport space system is achieved.1 cl, 51 dwg

Method for controlling fuel flow into afterburner combustion chamber of by-pass engine

Abstract: FIELD: engine building.SUBSTANCE: invention relates to aircraft engine building and can be used in automatic control system of by-pass engine with afterburner combustion chamber (BEACC) with mixing of contour flows. Method of fuel flow rate control in afterburner with mixer and fuel collectors with sprayers of by-pass engine, in which, for a given engine boost mode, fuel flow to the afterburner is determined using a mathematical model based on the following measured parameters: total air temperature at the engine inlet, low-pressure rotor shaft rotation frequency, total air pressure behind the compressor, gas pressure downstream the turbine, fuel flow to the main combustion chamber. In addition, actual concentration of oxygen is measured before sprayers of fuel manifolds of afterburner chamber by free oxygen sensors and on the basis of measurement data there performed is distribution of fuel consumption between fuel manifolds of afterburner chamber, providing normalized value of excess oxygen coefficient.EFFECT: method to control fuel flow into august chamber according to invention provides optimum distribution of fuel along section of afterburner chamber for its effective combustion.1 cl, 1 dwg

Device and method for providing ignition to a post-combustor for bypass gas turbine

Abstract: The method involves guiding a fraction of primary flow (10) in an ignition zone (34) of an afterburner in order to maintain the temperature in the zone at a value greater than value of secondary flow (20) in a manner to favor ignition of the afterburner. The primary flow is hot and the secondary flow is cool, where the fraction of primary flow is injected in an upstream part of the zone. An independent claim is also included for an afterburner device for a turbofan engine.

System for combustion of fuel to provide high efficiency, low pollution energy

Abstract: An afterburner system and method for reducing the CO 2 and other pollutants produced by the combustion of a fuel in a combustion chamber while maintaining or increasing the efficiency of said combustion includes feeding a catalyst, preferably lithium and/or boron to the afterburner, or a preconditioning afterburner, along with the exhaust from the combustion chamber. The presence of the catalyst in the after burner results in further reduction of pollutants generated by the combustion in the combustion chamber.

Propulsion Models Implemented in Finite Element CFD

Abstract: Fast and efficient models are presented for three means of propulsion: Rocket, turbojet, and ram/scramjet systems. These propulsion models are desirable for evaluating vehicle performance, stability, and control, especially dur ing the early design stages. Rocket and turbojet boundary conditions along with quasi-combustion terms are investigated using an inviscid finite element approach. Results are pres ented for rocket nozzle, three turbojet inlets, coupled turbojet, simple afterburner, and g eneric hypersonic vehicle with a scramjet. These results show the application of the rocket, t urbojet, and quasi-combustion terms. The simplicity of the models lend themselves to concept ual and early trade studies. Such applications are discussed briefly as they apply as an early design tool.