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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
06 Jun 2017
TL;DR: In this article, an afterburner mixing chamber is proposed, which includes an outer annular body, a kok-drainer and a shell on which are located radially directed pylon ducts fixed on the opposite side on a common divider that divides the inner contour into the central andvernal parts and also provides air supply of the external circuit, through the pylon cavity, directly to the central part of the internal circuit, thereby ensuring an even distribution of oxygen along the radius of the mixing chamber, one native temperature field at the outlet from the mixing
Abstract: FIELD: power industry.SUBSTANCE: afterburner mixing chamber is proposed. It includes an outer annular body, a kok-drainer and a shell on which are located radially directed pylon ducts fixed on the opposite side on a common divider that divides the inner contour into the central and vernal parts and also provides air supply of the external circuit, through the pylon cavity, directly to the central part of the internal circuit, thereby ensuring an even distribution of oxygen along the radius of the mixing chamber, one native temperature field at the outlet from the mixing chamber and effective cooling of the nozzle and afterburner stabiliser assemblies.EFFECT: invention makes it possible to create conditions in which a homogeneous temperature field at the exit from the mixing chamber was provided, a uniform distribution of oxygen along the radius of the afterburner, and effective cooling of the nozzle and stabiliser assemblies.9 dwg
Patent
28 Sep 2018
TL;DR: In this article, a method for determining the gas temperature in front of the turbine in the afterburner operation mode of a turbojet engine is presented. But the method is not suitable for the case of aircraft engines.
Abstract: FIELD: motors and pumps.SUBSTANCE: method for determining the gas temperature in front of turbine in the afterburner mode of a turbojet engine (TJE) refers to aircraft engine building. Preliminary calculation method is used to determine the coefficient K taking into account the change in the gas temperature in front of turbine when the rotor speed of high pressure is changed by 1 %, and the coefficient C, taking into account the increase in the gas temperature in front of turbine when the afterburner is switched on in full forced mode, and when testing the engines, the rotational speed of the high-pressure rotor nthen output the engine to the afterburner mode of operation, measure the frequency of the high-pressure rotor n, the total air flow through the motor G, the total fuel consumption G. Following is the formula for determining the gas temperature in front of the turbine in the afterburner operation mode TEFFECT: method makes it possible to determine the gas temperature in the afterburner mode both at the same rotational speeds of the motor rotors at the maximum and afterburner modes, and in the afterburner mode, different in frequency of rotation of the rotors of the engine from the maximum operating mode of the engine, and thus improve the reliability of the engine.1 cl
01 Jan 2010
TL;DR: In this paper, a 5 kW power class planar SOFC stack from Research Centre Julich is assembled to the demo unit and a long-term experiment is conducted to assess the characteristic performance and durability of different components of the unit.
Abstract: A technical description and experimental analysis of a SOFC demonstration unit is presented. The unit contains most of the primary BoP-components of a complete SOFC system, except of air and fuel recirculation equipment or fuel system compressor. Natural gas is used as the fuel and electricity is supplied to the electric grid. A 5 kW power class planar SOFC stack from Research Centre Julich is assembled to the demo unit and a long-term experiment is conducted to assess the characteristic performance and durability of different components of the unit (e.g. the SOFC stack, the fuel pre-reformer and air heat exchangers). The evolution of absolute voltage drop of the stack over time is found to be of the same magnitude when compared to short stack experiments. Thus, other system components are not observed to cause an increase in the characteristic voltage drop of the stack. Two BoP-components, the afterburner and the power conversion unit failed to operate as designed. The performance of other BoP-components i.e. fuel pre-reformer and heat exchangers were satisfactory during the test run, and no significant performance loss could be measured.
Patent
13 Jun 2017
TL;DR: In this paper, the authors proposed a method to increase the efficiency of fuel heating reduction in the fuel system of a GTE in deep choke modes by changing the impeller speed and position of the pump on the pump pressure characteristics flow axis.
Abstract: FIELD: engines and pumps.SUBSTANCE: invention can be used in their fuel supply systems to reduce the heating of fuel delivered to the injectors of the main and/or afterburner combustion chambers in deep choke modes. Reduced fuel heating in the gas turbine engine fuel system is performed by controlling the parameters of the centrifugal pump of the fuel system, which is used as the number of impeller speed and position of the maximum efficiency of the pump on the pump pressure characteristics flow axis, wherein the transition of the pump to the deep throttling modes to reduce fuel preheating fuel discharge characteristic is changed from the impeller, which is carried out by shifting the maximum efficiency of the pump to the minimum fuel consumption field, leaving a constant number of revolutions of the pump impeller.EFFECT: invention makes it possible to increase the efficiency of fuel heating reduction in the fuel system of a GTE in deep choke modes.6 dwg
Patent
25 Nov 2020
TL;DR: In this paper, an air-breathing turbojet engine for a hypersonic vehicle is shown, which consists of a pump for pumping a cryogenic fuel, an inlet (102) configured to compress inlet air by one or more shocks, a cooler (103) to cool the compressed inlet using the liquid nitrogen, and a turbo-compressor (104) to compress the air further.
Abstract: An air-breathing turbojet engine (101) for a hypersonic vehicle is shown. The engine comprises a pump for pumping a cryogenic fuel, an inlet (102) configured to compress inlet air by one or more shocks, a cooler (103) to cool the compressed inlet air using the cryogenic fuel, and a turbo-compressor (104) to compress the air further. A combustor (105) receives compressed cooled air from the turbo-compressor and a first portion of the cryogenic fuel for combustion. A first turbine (106) expands and is driven by combustion products, and a second turbine (107) expands and is driven by a second portion of the cryogenic fuel. The first turbine and the second turbine drive the turbo-compressor via a shaft. An afterburner (109) receives combustion products from the first turbine and the second portion of the cryogenic fuel from the second turbine for combustion therein.

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