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Afterburner

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


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Patent
21 Feb 2018
TL;DR: In this article, a turbo-jet engine consisting of an inlet device, a compressor, a main combustion chamber, a single-stage turbine, a gas ejector, the high and low pressures channels of the ejector at the entrance to the mixing chamber, and a damper, the turbine blades are cooled by air, to which the fuel and water are mixed.
Abstract: FIELD: engines and pumps.SUBSTANCE: turbo-jet engine consisting of an inlet device, a compressor, a main combustion chamber, a single-stage turbine, a gas ejector, the high-pressure channel of which is connected on one side with the compressor through the main combustion chamber, and on the other side – with the turbine through a mixing chamber, the low pressure channel on one side is connected to the atmosphere through the inlet device, and on the other side – with the turbine through the mixing chamber, a mixing heat exchanger located before the compressor, an afterburner combustion chamber, an outlet device. In the high and low pressures channels of the gas ejector at the entrance to the mixing chamber there are nozzle assemblies, in the low-pressure channel of the gas ejector there is a damper, the turbine blades are cooled by air, to which the fuel and water are mixed. Method for the turbo-jet engine control is to use the control law n= const (constant specific speed of the compressor) within the entire operational range of the aircraft, as well as – the hyperforsed mode – an increase of the engine thrust due to the supply of a liquid (water, liquid air, liquid oxygen, kerosene in an amount not exceeding 3 % of the air flow rate) to the compressor inlet at flight speeds of more than four Mach numbers. Use of turbo-jet engines will let increase speed and altitude of the booster aircraft flight up to M ~ 7 and H ~ 40 km, at which the first stage of the Space and Missile System becomes unnecessary.EFFECT: this will increase the power of the second stage of the Space and Missile System by times and, accordingly, increase the payload by dozens of times.6 cl, 7 dwg
Patent
30 Aug 2018
TL;DR: In this paper, an afterburner for exhaust gas of an engine was proposed, which reburns and removes residual fuel and harmful substance included in exhaust gas emitted from an engine generating power by burning fuel, and supplies the engine with hydrogen generated by electrolyzing water included in the exhaust gas.
Abstract: The present invention relates to an afterburner for exhaust gas of an engine and, more specifically, to an afterburner for exhaust gas of an engine, which reburns and removes residual fuel and harmful substance included in exhaust gas emitted from an engine generating power by burning fuel, and supplies the engine with hydrogen generated by electrolyzing water included in the exhaust gas, thereby increasing the engine power The present invention can burn out all the residual fuel remaining after a burning process in the engine, and remove a nitrogen oxide or a sulfur compound in a high-temperature burning process
Patent
12 Apr 2019
TL;DR: In this paper, an aero engine thermal management system with hot oil tank returnable oil is described, and an oil return oil-way is additionally arranged on an after-burner fuel flow path and located in front of a afterburner.
Abstract: The invention discloses an aero engine thermal management system with hot oil tank returnable oil. The aero engine thermal management system with the hot oil tank returnable oil is characterized in that an oil return oil-way is additionally arranged on an afterburner fuel flow path and located in front of a afterburner 17, and oil mass of an afterburner oil-way is increased; during high-speed flight, after the fuel of the afterburner fuel flow path flows through an afterburner fuel distributer of an afterburner oil-way assembly accessory 16, the fuel oil flow entering the afterburner 17 is controlled to meet requirements, and the remaining fuel flows into a high-temperature fuel tank 7 for temporary storage; during low-speed flight, the fuel in the high-temperature fuel tank 7 penetrates through a first empty-oil heat exchanger 5, and the low-temperature incoming flow air is used for cooling the high-temperature fuel, and finally the fuel is collected into the fuel tank. According to the aero engine thermal management system with the hot oil tank returnable oil, the problem of insufficient fuel heat sink at the time of high-speed flight is solved without changing a conventional thermal management system solution, and the aero engine thermal management system with the hot oil tank returnable oil has the advantages of easy implementation, easy transformation and high efficiency.
Patent
28 May 2019
TL;DR: In this paper, a modular device for a fuel cell system, including a start-up burner, a reformer, an after-burner, and a heat exchanger which are all disposed in one chamber.
Abstract: A modular device for a fuel cell system, includes a start-up burner, a reformer, an afterburner, and a heat exchanger which are all disposed in one chamber. The reformer surrounds the start-up burner,and the afterburner is located above the start-up burner and surrounds the reformer. The heat exchanger surrounds the afterburner and the reformer.
Patent
29 May 2002
TL;DR: In this article, the afterburner of a gas turbine has a main duct, a burner assembly, and a branch pipe to deliver fresh air to the turbine, and the main duct contains a system for distributing the fresh air flows and pressures at the intake to the burner assembly.
Abstract: The afterburner (1) for gas and/or liquid fuels, situated between a gas turbine (2) and a recovery heater (3), has a main duct (4), a burner assembly (7) and a branch pipe (9) to deliver fresh air. The main duct contains a system (11) for distributing the fresh air flows and pressures at the intake to the burner assembly, comprising two or more deflectors (12) lying parallel to the mean direction of the gas flow from the turbine. Each deflector has an upstream edge in the zone where the branch pipe meets the main duct.

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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202130
202037
201926
201834
201734
201619