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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01 Aug 1952
TL;DR: In this article, sound measurements were made on a pulsejet and a subsonic ramjet of the types used for helicopter rotor drive and on a turbojet with afterburner.
Abstract: : Sound measurements were made on a pulsejet and a subsonic ramjet of the types used for helicopter rotor drive and on a turbojet with afterburner. The pulsejet was found to produce a discrete-frequency spectrum having a single predominant component corresponding to the engine firing frequency. The angular distribution was slightly directional, with the largest sound pressure occurring to the rear of the engine and near its axis. It was found that an estimate of the noise level from a pulsejet could be made by application of resonant-tube theory, if certain of the average flow parameters of the engine are known or can be reasonably approximated. The small subsonic ramjet and turbojet with afterburner were both found to produce discrete-frequency noise spectrums. Their spectrums, however, contrasted with that of the pulsejet in that they contained several harmonic components of magnitude comparable with that of the fundamental.
3 citations
TL;DR: In this paper, a numerical model of propulsion and heat transfer is established for the nuclear jet engine to verify the feasibility of the novel nuclear heat exchanger, which is directly put into the combustion chamber to heat compressed air.
3 citations
TL;DR: In this paper, experiments were performed to reveal the cooling characteristics and flow loss of various sinusoidal corrugated liners for an advanced afterburner, and it was found that there are alternate high temperature and low temperature zones corresponding to the wave crests and troughs of the liners, respectively.
Abstract: Abstract The need of improved cooling effectiveness for hot components in jet engines has led to new designs of afterburner liners. In the present paper, experiments were performed to reveal the cooling characteristics and flow loss of various sinusoidal corrugated liners for an advanced afterburner. It is found that there are alternate high temperature and low temperature zones corresponding to the wave crests and troughs of the corrugated liner, respectively. Compared to the flat liner, the corrugated liner increases cooling effectiveness by 10 % at the blowing ratio of 0.5, by 4.5 % at the blowing ratio of 3.2. However, the difference in discharge coefficients for these two kinds of liners is only 4.3 %. The increased opening ratio of film holes from 1.42 % to 3.72 % for corrugated liners is able to improve the cooling effectiveness by 9.8 %. However, the discharge coefficient is decreased by 34.1 %. The augment of amplitude of liners can enhance the ram effect of cooling air, which has an advantage to increase the local blowing ratio, and to form good cooling film at the windward of wave troughs. The flow loss is bigger while the cooling effectiveness is enhanced due to the change of amplitude of the liner.
3 citations
Patent•
27 Oct 1994
TL;DR: In this article, the pollutant content in the combustion prods is measured by a sensor and signalled to a computer, which provides optimal control of the individual fuel delivery devices and blower.
Abstract: The space (7) to be heated is traversed by a number of tubes (2) each leading from a combustor (11) and afterburner (8) to a corrosion-resistant inlet (10) of the common smokebox.The pollutant content in the combustion prods. is measured by a sensor (6) and signalled to a computer (5) which provides optimal control of the individual fuel delivery devices (3) and blower (4). The number of burners in operation and the speed of the blower are adjusted for min. emission.
3 citations