Afterburner

About: Afterburner is a research topic. Over the lifetime, 811 publications have been published within this topic receiving 5944 citations.

Double-oil-way jet integrated afterburner

Abstract: The invention provides a double-oil-way jet integrated afterburner. A double-oil-way jet mode is adopted in the integrated afterburner. Jet positions for fuel oil jetting are the central position of the tail of a fairing spoke flameholder and the central position of a thrust augmentation inner cone. Compared with the prior art, the fuel oil jetting mode is changed, and as for an outer oil way, the jetted fuel oil is mixed with high-temperature mixed gas, and the atomizing effect is improved under the effect of the shear force of the high-temperature mixed gas; and as for a central oil way, since the thrust augmentation inner cone enables a wide low-speed backflow area to be formed behind the afterburner, the jetted fuel oil of the part is fully mixed with high-temperature mixed gas in the low-speed area, and the premixing effect is enhanced. Combustion is jointly conducted through the two oil ways in the afterburner, so that the combustion efficiency of the afterburner is improved, and the combustion stability is good. Meanwhile, the fuel oil can effectively decrease the temperature of the thrust augmentation inner cone to improve the infrared stealth performance of an engine.

Weak Extinction Limits of Large Scale Flameholders

Abstract: Weak extinction data obtained from an experimental apparatus designed to simulate the characteristics of practical afterburner combustion systems are presented. The apparatus supplies mixtures of varied composition (equivalence ratio and degree of vitiation), temperature and velocity to Vee-gutter flame holders of various widths and shapes similar to those found in jet engine systems. The fuel employed is a liquid hydrocarbon whose chemical composition and physical properties correspond to those of aviation kerosine, JP5. An equation for predicting weak extinction limits which accounts for upstream vitiation and the chemical characteristics of the fuel is derived from stirred reactor theory. The correlation between the predictions and experimental results indicates that the stirred reactor approach can provide a framework for predicting the lean blowout limits of practical flameholders over wide ranges of engine operating conditions.Copyright © 1991 by ASME

Method of operation of triple-flow aircraft turbojet engine and design of said engine

Abstract: FIELD: aero-engine manufacturing; supersonic turbojet engines. SUBSTANCE: in process of operation of proposed aircraft turbojet engine, air is delivered into outer direct flow and inner loops of engine, air is compressed in sections of main compressor and fuel is combusted in compressed air in combustion chamber and combustion products, thus formed, are expanded in turbine and propulsive jet nozzle. Combustion products are divided at combustion chamber outlet into two flows, one of which is directed to direct flow loop. Other flow is mixed with part of air from cooling loop and is directed to turbine input. Combustion products outflowing from propulsive jet nozzle of direct flow loop at supersonic speed are directed into mixing chamber to eject expanded combustion products getting of turbine. At afterburner power, temperature in combustion chamber is decreased to braking temperature, and delivery of cooling air to turbine input is decreased owing to bypassing to provide mixing of cooling air with combustion products getting into direct flow loop. In process of operation of the ground and at low altitudes air is delivered into engine inner loop from direct flow loop to input of main compressor. At increase of aircraft flight altitude higher than4000 m, air delivery into direct flow loop is cut off, and delivery of air to input of main compressor is provided through section of low-pressure additional compressor by successively connecting its stages, starting from last one, and finishing by first one at attaining designed altitude of flight. At increase of aircraft flight speed higher than supersonic speed, compressor stages are successively disconnected starting from section of low-pressure additional compressor to last stage of main compressor, and direct flow loop is cut in. Simultaneously operation of sections of compressors and turbine is coordinated owing to adjusting of propulsive jet nozzle and changing of mixing chamber passage area. Invention makes it possible to increase thrust at minimum consumption of fuel at increase of flight altitude, air single shaft engine is used, owing to preservation of constant second air consumption at all flight conditions. EFFECT: increased thrust. 7 cl, 1 dwg

Method for controlling a fuel cell

Abstract: The invention relates to a method for controlling the fuel gas supply a fuel cell installation. In a first control circuit 1, the temperature in the fuel cell stack 7 is controlled by the manipulated variable of the air supply. In a second control loop, a temperature is controlled in the afterburner via the command value of the fuel gas supply 2, which represents the fuel gas utilization. This makes it possible to operate a fuel cell even with fluctuating gas qualities perfectly.

Model test and full-scale checkout of dry-cooled jet runup sound suppressors

Abstract: Jet aircraft runup sound suppressors featuring complete enclosure of the aircraft, dry cooling of the exhaust sound suppressor (even during afterburner operation), and adaptability to a variety of aircraft types are now employed at a number of U.S. Navy and Air Force airfields. The design, model testing, and full-scale checkout of the existing U.S. Navy hush house is described herein. Also the extension of the hush house concept to unusual aircraft designs and to dry-cooled jet engine test cells is covered.