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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
16 Oct 2020
TL;DR: In this article, the authors proposed an afterburner ignition system for turbojet engines, where only two oil ways are arranged, the design of the oil way system is simpler, and the engine thrust-weight ratio can be improved by improving the ignition device and the oilway system.
Abstract: The invention relates to the technical field of ignition systems for turbojet engines, in particular to an ignition system for an afterburner, and solves the problems that ignition systems and oil waysystems of the afterburners of small and medium-sized turbojet engines are complex and the engine thrust-weight ratio is insufficient in the prior art. The ignition system comprises an ignition oil way system, wherein the ignition oil way system comprises an oil pump; the oil pump is respectively connected to an ignition device and an afterburner fuel manifold through a pipeline; the ignition device comprises a shell; an electric heating plug is arranged in the shell; a cable is arranged above the electric heating plug; an afterburner ignition oil pipe is arranged on the shell and is connected to the pipeline; a fuel circuit is formed by a circular seam between the electric heating plug and the inner wall of the shell; and the fuel circuit communicates with the afterburner ignition oil pipe. According to the ignition system, only two oil ways are arranged, the design of the oil way system is simpler, and the engine thrust-weight ratio can be improved by improving the ignition device and the oil way system.
Patent
10 Jun 2013
TL;DR: In this article, a method of using residual liquid components of rocket fuel in spent stages of carrier rockets by their simultaneous supply to an afterburner at the step of lowering the stage with afterburning of residual fuel, after oxidiser ends, with air oxygen and by ejection of combustion products through side surface of the stage housing is described.
Abstract: FIELD: engines and pumpsSUBSTANCE: utilisation method of residual liquid components of rocket fuel in spent stages of carrier rockets by their simultaneous supply to an afterburner at the step of lowering the stage with afterburning of residual fuel, after oxidiser ends, with air oxygen and by ejection of combustion products through side surface of the stage housing, according to the invention, ejection of combustion products is performed through convergent-divergent nozzles located in structural planes of the stage in the directions perpendicular to its longitudinal axis, and reaction forces occurring from convergent-divergent nozzles are used for changing angles of attack and wobbling of the stage housing and control of its lowering due to its aerodynamic quality of the stage housingEFFECT: invention provides utilisation of rocket fuel components by using their energy for control of the stage lowering2 dwg
12 Apr 1957
TL;DR: In this paper, a high-energy fuel suitable for turbojet-powered aircraft has been proposed, including thermal and combustion properties, experiments with combustors designed to use boron compounds.
Abstract: Report presenting NACA work through 1954 on a high-energy fuel suitable for turbojet-powered aircraft The work includes thermal and combustion properties, experiments with combustors designed to use boron compounds, evaluation of boron fuels in full-scale turbojets with and without afterburners, and ramjet flights on boron fuels Satisfactory combustion of pentabornae and high-concentration blends of pentaborane has been demonstrated in a turbojet, an afterburner, and a ram jet
Patent
17 May 2017
TL;DR: In this paper, a three-level rotational flow structure of an afterburner head was proposed to improve the performance of the burning of a flame in an FPGA.
Abstract: The invention provides a three-level rotational flow structure of an afterburner head. A large-ranged recirculation zone can be generated by the structure in an afterburner, so that flame burning is stabilized, and meanwhile, the pressure loss can be reduced, the fuel oil atomization degree in the afterburner is reinforced, burning efficiency is improved, and the wall face can be effectively cooled; by reasonably setting the rotary angle of a whole flow supporting plate, an airflow reversely flows in a rotational-flow mode, so that shear force between fuel oil and air is increased, and the fuel oil atomization degree is improved; the flowing direction of the airflow is not suddenly changed, and thus flowing resistance is small; and an airflow rotational flow is subjected to wall-adherent movement, so that an air film is formed between the afterburner wall face and a burning zone, and the cooling effect of the afterburner wall face is guaranteed. The three-level rotational flow structure of the afterburner head has the advantages that the difficulty, caused by the over-high airflow speed in the afterburner, of igniting and maintaining stable burning of flame can be effectively improved, and the smaller pressure loss is achieved; and meanwhile, the fuel oil atomization level can be improved, and further efficient burning can be ensured.
Journal ArticleDOI
TL;DR: In this paper, a steady laminar flamelet model has been conducted to model the flow field of the afterburning chamber of a solid-ducted rocket based on OpenFOAM.
Abstract: Simulation of combustion in the afterburner of solid ducted rocket is still a big challenge due to the interaction of turbulent and combustion. In the current study, a steady laminar flamelet model has been conducted to model the flow field of the afterburning chamber of solid ducted rocket based on OpenFOAM. The predicted main flow features in different transverse and longitudinal planes are analyzed. The performance parameter of the afterburning chamber is analyzed.

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