Topic
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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TL;DR: In this paper, a model based on one-dimensional approach which considers the radiation within each zone and between immediately adjacent zones as well as conduction and convection is proposed, where the kiln and afterburner are splitted of axially into equal width zones, where each stream is considered well stirred.
4 citations
TL;DR: In this paper, the initiation causes of damage to flame tubes of a basic combustion chamber and turbine units, which are the most common in the operation process of aircraft turbine engines (ATE), were presented.
Abstract: Abstract In the paper, the initiation causes of damage to flame tubes of a basic combustion chamber and turbine units, which are the most common in the operation process of aircraft turbine engines (ATE), were presented. They were illustrated with the use of numerous examples of progressing degradation of the surface condition of parts and components of various types of aircraft engines which was found during endoscopic controls. On the basis of the systematic observation results, the process of destruction of the turbine rotor ring blades’ surface was discussed. The attention was paid to the current and still valid evaluation of the aircraft turbine engine’s suitability for further operation, taking into account the specifics of its use.
4 citations
09 Jan 2012
TL;DR: The GOJETT (Graduate Organization Jet Engine Technology Team) team at the University of Colorado at Boulder as discussed by the authors designed a supersonic (Mach 1.4) unmanned aerial system to be used as a flight test bed for research such as sonic boom minimization, storm penetration, thrust vectoring, control algorithms, and other system level tests.
Abstract: The University of Colorado at Boulder has been researching improvements to small turbojet engines designed for unmanned aerial system for the past three years. The GOJETT (Graduate Organization Jet Engine Technology Team) team continued this work, focusing on designing a supersonic (Mach 1.4) unmanned aerial system to be used as a flight test bed for research such as sonic boom minimization, storm penetration, thrust vectoring, control algorithms, and other system level tests. The current goal, with the addition of an afterburner, a variable area nozzle, and fluidic injection thrust vectoring system, the team seeks to build the world's fastest 50kg UAS in accordance with Federation Aeronautique Internationale guidelines. The current aircraft and propulsion system design details are presented. The vehicle has been through preliminary design review and wind tunnel testing at the US Air Force Academy. Along with ongoing propulsion system test, the team is preparing for integrated vehicle and thrust-vectoring system tests.
4 citations
Patent•
08 Jun 2018
TL;DR: In this paper, a worm gear rear rectification supporting plate and a flame stabilizer are integrated, two stages of rectification supportplates and the stabilizer were subjected to radially misplaced structure design, and in this way, a stable low speed backflow area large in size range and high in swirl flowing is more easily formed at the downstream of the annular oil supply type integrated afterburner.
Abstract: The invention provides an annular oil supply type integrated afterburner. A worm gear rear rectification supporting plate and a flame stabilizer are integrated, two stages of rectification supportingplates and the flame stabilizer are subjected to radially misplaced structure design, and in this way, a stable low speed backflow area large in size range and high in swirl flowing is more easily formed at the downstream of the annular oil supply type integrated afterburner. A whole-ring groove stabilizer is arranged between the two stages of rectification supporting plates. An oil cavity is formed inside a force-adding inner cone and is connected with a fuel channel inside the first-stage rectification supporting plate, and after absorbing heat of the force-adding inner cone, fuel finally reaches the inside of the whole-ring groove stabilizer. Main fuel is sprayed out longitudinally from the two sides of the whole-ring groove stabilizer, on-duty fuel is sprayed out from a groove of the whole-ring groove stabilizer to form on-duty flame, and soft ignition is achieved. By reasonably forming nozzle small holes, the atomization effect of the fuel can be effectively improved, and thus thestability and combustion efficiency are improved. The annular oil supply type integrated afterburner has the advantages that the two stages of rectification supporting plates which are radially misplaced are adopted, and a better backflow area is formed; meanwhile, through longitudinal oil spray of the whole-ring groove stabilizer, the fuel-gas mixing effect is improved, the on-duty flame is formed, the soft ignition is achieved, and thus the combustion stability is effectively improved.
4 citations
TL;DR: In this paper, the effect of combustion-chamber length on afterburner combustion performance has been experimentally determined with two full-scale turbojet-engine afterburners, and the influence of combustor-inlet velocity, equivalence ratio, and pressure level is discussed, as well as a consideration of the structural-cooling requirements.
4 citations