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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Patent•
12 Sep 2018
TL;DR: In this article, a group of inventions relates to the field of aircraft engine building is presented, where the afterburner system transfer to the intermediate and full after-burner mode is performed by the ACAS TCL sequential movement from the angular position α into the angular ranges α and performing the "second-third" and "first-fourth" structurally coupled collectors sequential automatic switching in the second-third first-fourth order.
Abstract: FIELD: motors and pumps.SUBSTANCE: group of inventions relates to the field of aircraft engine building. In the turbojet engine operation method, the afterburner system transfer to the intermediate and full afterburner mode is performed by the ACAS TCL sequential movement from the angular position αinto the angular ranges αand performing the “second-third” and “first-fourth” structurally coupled collectors sequential automatic switching in the "second-third-first-fourth" order, increasing the intermediate forced modes thrust by the sequential increase in the afterburner fuel supply intensity. With the threshold pressure in the second collector reaching, by the ACAS command opening the fuel supply to the third FC collector through the FABR. With the total fuel consumption in the second and third collectors reaching (45±1) % of the total consumption in the full afterburner, the ACAS switches on the fuel supply to the first collector and by the TCL subsequent movement increasing the fuel supply through the FABR and building up pressure in the collector to the threshold value, at which achievement the ACAS switches on the FC fourth collector. Using the similar technique increasing the total fuel consumption in the FC collectors to the 100 % consumption level at full afterburner. To achieve the full afterburner mode, moving the TCL to the αand increasing the fuel consumption in all working collectors of the FC and the afterburner thrust increment with the engine transfer to the full afterburner mode. When entering the high-altitude mode, pressure in all collectors is automatically reduced by the ACAS command through the NABR, depending on the external pressure decrease in the atmosphere.EFFECT: achieved by the group of inventions technical result consists in increase in the efficiency by 2 % and more than double increase in the engine life.16 cl, 4 dwg
Patent•
11 Aug 2020
TL;DR: In this article, a radial grading-knocking afterburner is proposed to implement high-efficiency and high-speed flight without obviously increasing energy consumption or aggravating structural complexity.
Abstract: The invention discloses a radial grading knocking afterburner. The radial grading knocking afterburner radially comprises a thrust augmentation inner cone, an afterburner main combustion area, an afterburner inner wall surface, a knocking annular chamber and an afterburner outer wall surface. A cross ignition annular chamber exists in the head part of the knocking annular chamber. The cross ignition annular chamber is connected with a gas inlet channel and the afterburner internal combustion area. The radial grading knocking afterburner can work in the state that the knocking annular chamber does not run; when the knocking annular chamber needs further acceleration, oil is ejected out of a fuel oil nozzle, flames in the afterburner enters the cross ignition annular chamber to implement ignition, detonation is implemented in the knocking annular chamber, and then further acceleration of an aircraft can be implemented. The radial grading knocking afterburner, namely a pulse knocking combustion chamber, is simple in structure, high in circulating thermal efficiency and low in oil consumption; and because of integrated radial grading designing, the aircraft with the radial grading knocking afterburner can implement high-efficiency and high-speed flight without obviously increasing energy consumption or obviously aggravating structural complexity.
01 Jan 2021
TL;DR: In this article, a versatile test facility using a single V-gutter flame holder was used to generate the predetermined screech frequency of 2000 Hz in a controlled and sustained manner, which was found that the cause for the onset of screech was the vortex shedding frequency from the flame holder locking on to the duct transverse acoustic resonant mode frequency.
Abstract: Screech combustion instabilities continue to be one of the most detrimental and, in fact, fatal issues for the development of a high-performance afterburner. It is essential to study the underlying flow-physics related to the crucial thermo-acoustic coupling to acquire a predictive capability and to evolve a methodology for the attenuation of screech. A versatile test facility using a single V-gutter flame holder was used to generate the predetermined screech frequency of 2000 Hz in a controlled and sustained manner. The test facility had the capability to run the afterburner model under simulated inlet conditions of pressure and temperatures. The critical zone of flame stabilization near the V-gutter flame holder had complete optical access with quartz glass windows to study the vortex shedding phenomena during the afterburner operation. The critical operating parameters of the test rig were measured using a high-speed NI-based data acquisition system. Flow visualization studies using a high-speed shadowgraph technique was effectively used to understand the onset of screech. A FASTCAM SA-4 Photron high-speed camera was used in this experimental investigation. It was found that the cause for the onset of screech was the vortex shedding frequency from the flame holder locking on to the duct transverse acoustic resonant mode frequency.
01 Jan 2010
TL;DR: In this article, a single-spool single jet engine with afterburner for thrust augmentation is presented, based on the simplified mathematical models of the main parts of the system, models already determined and presented by other papers mentioned in the references section.
Abstract: This paper deals with a single-spool single jet engine with afterburner for thrust augmentation. The afterburning system consists of a special combustor with its own fuel pump, turned round by the engine's spool and operating with respect to the gas-turbine's pressure ratio. The authors have built the mathematical model for the interconnected engine-afterburning system (EAS), based on the simplified mathematical models of the main parts of the system, models already determined and presented by other papers mentioned in the references section. The EAS was identified as controlled object and described by its mathematical model, as well as by its block diagram with transfer functions. Based on these elements, the authors have studied EAS time behavior, by studying its quality, which means its time response, performing some computer aided simulations; the simulations were based on some co-efficient, experimentally determined and calculated for the VK-1F jet engine. The paper is based on some similar works of the first author, as well as on similar works presented in the reference list, about aircraft jet engines and engines' main parts as controlled object(s). The used methods, as well as the conclusions and results, can be extended in further works, concerning multi-spool engines with afterburning systems.