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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
23 Jun 1989
TL;DR: In this paper, an optical flame detector is provided, suitable for sensing by sensing module (1) flame-out in the afterburner of a gas turbine aircraft engine, and its absence is used to trigger fuel flow shutoff.
Abstract: An optical flame detector is provided, suitable for sensing by sensing module (1) flame-out in the afterburner of a gas turbine aircraft engine. A phosphor (9) senses the UV radiation emanating from the flame, and in response thereto emits radiation in the visible region. The visible radiation is sensed by detector module (2); its absence is used to trigger fuel flow shut-off to the afterburner.

5 citations

Proceedings ArticleDOI
05 Jun 1995
TL;DR: In this paper, active control of a subscale, atmospheric pressure nozzle/combustor arrangement was used to mitigate the effects of combustion instability in afterburner and dump combustor applications, and cyclic injection of small quantities of control fuel was proposed to counteract the periodic heat release that contributes to undesired pressure oscillations.
Abstract: A number of recent articles have demonstrated the use of active control to mitigate the effects of combustion instability in afterburner and dump combustor applications. In these applications, cyclic injection of small quantities of control fuel has been proposed to counteract the periodic heat release that contributes to undesired pressure oscillations. This same technique may also be useful to mitigate oscillations in gas turbine combustors, especially in test rig combustors characterized by acoustic modes that do not exist in the final engine configuration. To address this issue, the present paper reports on active control of a subscale, atmospheric pressure nozzle/combustor arrangement. The fuel is natural gas. Cyclic injection of 14% control fuel in a premix fuel nozzle is shown to reduce oscillating pressure amplitude by a factor of 0.30 (i.e., {approximately}10 dB) at 300 Hz. Measurement of the oscillating heat release is also reported.

5 citations

Book ChapterDOI
08 Sep 2019
TL;DR: Developed database of aviation materials and expert system of decision-making of computer-aided design of aviation engines and ground power plants on their basis to optimize the weight dimension characteristics of the main components of aircraft engines in the early stages of design are described.
Abstract: In the article it is described developed database of aviation materials and expert system of decision-making of computer-aided design of aviation engines and ground power plants on their basis. The database of aviation materials contains information on the properties and characteristics of a large number of materials used in the design of aircraft engines. The system allows automated selection of materials for parts and assembly units. In this case, the thermogasdynamic calculation of the engine as a whole, a detailed aerodynamic calculation of the assembly units and its strength calculation are performed. In the article it is shown description of mathematical model scheme of expert system. There are simulation results of low-pressure compressor (with different laws of profiling flow passage and different number of stages) for turbojet bypass engine with afterburner of the fourth generation of military high-maneuverable aircraft; there are shown also simulation results of high-pressure compressor for turbofan engine with a high bypass ratio for a civil aircraft, and also results of modelling of rotor blade of fan. Results of simulation were compared with construction of series-produced engines. Using the developed system, it is possible to optimize the weight dimension characteristics of the main components of aircraft engines in the early stages of design.

5 citations

Journal ArticleDOI
TL;DR: In this article, conjugated heat transfer experiments were conducted using IR thermography for double-wall heat shields with three open areas of the impingement plate ( σ ǫ = 0.5, 0.7, and 0.8%).

5 citations

Patent
29 Apr 1965

5 citations


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