Afterburner

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

Numerical simulation on thrust correction of an aero-engine in indoor engine test cell

Abstract: The thrust aerodynamic correction of an aero-engine in an indoor engine test cell is researched under the rating state,the maximum power state and the full afterburner state.The work is based on a 3D computational fluid dynamic(CFD) method with NUMECA software and it includes a preliminary validation about calculation accuracy.The results demonstrate that the flow of air in the indoor engine test cell is predicted successfully,and the thrust correction terms are reasonable and reliable in the trend and range of values.Under high engine mass-flow conditions,Inlet Momentum Drag has significant impact on thrust correction.At the same time,Additive Drag and Suction Drag also affect the thrust correction to some extent.

Afterburner annular flame tube structure with cyclones

Abstract: The invention provides an afterburner annular flame tube structure with cyclones According to the structure, the six cyclones are additionally mounted in the middle of an afterburner, a wide-range recirculation zone can be generated in the afterburner, and therefore the air flow speed can be reduced to the largest degree, and stable burning of the afterburner can be guaranteed Meanwhile, an expansion air inlet segment is arranged at the tail of an afterburning tail cone, expansion air inlet holes are formed in the centers of the cyclones, the internal air flow flowing speed can be greatly reduced after afterburning through multiple ways, and space is provided for stable burning After air flow passes through the cyclones, a shearing function can be generated on fuel oil, fuel oil atomization is more thorough, and therefore burning can be more sufficient After the air flow passes through the expansion air inlet segment, part of the air flow passes through a channel between the inner wall and the outer wall of the afterburner, the wall temperature of the afterburner can be effectively reduced, and the infrared stealth performance of an airplane can be improved

Fuel igniter for a jet turbine engine afterburner

Abstract: 1, 103, 933. Jet propulsion plant; reciprocating pumps. M.A.N. TURBO G.m.b.H. July 13, 1965 [July 15, 1964], No. 29748/65. Headings F1A and F1J. A gas turbine jet propulsion engine has a reheat igniting arrangement comprising two nozzles one of which is mounted in the combustion chamber upstream of the turbine to produce a "hot streak" which ignites the second nozzle in the jet pipe downstream of the turbine thus igniting the adjacent reheat nozzles. Fuel is supplied to the ignition nozzles by a device comprising a charging piston 3 movable in a cylinder 2. When reheat ignition is required, a hydraulic pressure is applied to the left of a piston 13 displacing the piston to the right against a spring 15. This allows valve 11 to move off its seat and place high-pressure fuel line 200 in communication with the right hand side of charging piston 3 by way of chamber 20 and passage 21. Piston 3 is thus forced to the left to urge fuel through non-return valve 5 to the ignition nozzle in the jet pipe and, an instant later, through annular groove 25 and non-return valve 8 to the ignition nozzle upstream of the turbine. As piston 3 moves further to the left it obturates valve 8 but continues to force fuel through valve 5 until it reaches a position, Fig. 2 (not shown), in which it opens a valve 7 to allow the remaining fuel to flow out from cylinder 2 into the engine low-pressure fuel system 100. The position of annular groove 25 is such that the "hot streak" through the turbine is prevented from burning too long and the issuing of unburned fuel from the nozzle in the jet pipe is prevented. For recharging the device, pressure is removed from the left of piston 13 so that spring 15 relaxes, thus closing valve 11. Spring 4 then returns piston 3 to the right hand end of cylinder 2 thus drawing in low-pressure fuel through a non- return valve 6. Cooling is effected by fuel flowing through bores 22, 23 and 24.

Waste gas surface afterburner - has ignition gas pipe and igniter inside combustion gas pipe

Abstract: The surface burner is for the direct gas-heated afterburning of incompletely burnt waste gas, having a housing in the path of the latter with perforated mixing plates inclined in the flow direction. The combustion and ignition gases and air are supplied via pipes from outside the waste gas pipe, as is the ignition energy. The ignition gas pipe and igniter or ignition wire are mounted inside the combustion gas pipe (10), which extends to the burner housing (6) from the rear in the waste gas flow direction and is joined to the rear housing wall (9).