Micro-Channel Regeneratively Cooled Micro-Combustor

A micro-combustion chamber, regenerative cooling technology, applied in the field of aero-engines, to achieve the effect of reducing weight, improving combustion efficiency, and good ignition performance

Active Publication Date: 2018-10-26
XIAMEN UNIV +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the above-mentioned problems existing in the prior art, the present invention provides a combustor structure that uses microchannels to realize regenerative cooling. Regenerative cooling is to use fuel as a coolant at the same time, and use the fuel to absorb the heat released by the combustor and heat it to a certain level. temperature, thereby cracking into small molecular flammable substances, entering the combustion chamber for further combustion, and releasing the absorbed heat to the combustion chamber, while improving the combustion efficiency and realizing the cooling of the wall of the combustion chamber. The micro-scale effect strengthens the advantages of heat transfer, improves the heat transfer effect of fuel oil, reduces the wall temperature and temperature gradient of the combustion chamber, and thus solves the problem of excessive thermal stress, and realizes effective thermal protection of the combustion chamber

Method used

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  • Micro-Channel Regeneratively Cooled Micro-Combustor

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Embodiment Construction

[0024] See figure 1 with figure 2 , A micro-combustion chamber with micro-channel regenerative cooling, such as figure 1 As shown, it is composed of the combustion chamber 1 and its upper and lower intermediate pads 6, 7, microchannel plates 4, 5, and top cover plates 2, 3 by stacking and combining, the combustion chamber 1, the middle pad The plates 6, 7, and the microchannel plates 4, 5 form a closed combustion chamber. The front end of the combustion chamber 1 is provided with a fuel nozzle 8, the rear end is an exhaust outlet 11, one side wall is provided with an air inlet 12, and the other side is provided There is a connection port 13 for the igniter 9; the top cover plates 2, 3 are provided with fuel inlets 21, 31 and outlets 22, 32 respectively; the microchannel plates 4, 5 contain 10-20 microchannels arranged in parallel and equally spaced. Channel 41. When assembling, stack the top cover plate 2, the microchannel plate 4, the middle backing plate 6, and the combustio...

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Abstract

The invention discloses a micro-channel regenerative cooling micro-combustor. By the aid of a combustion cavity body, a middle base plate, a micro-channel plate and a top cover plate, the combustion cavity, the middle base plate and the micro-channel plate form a closed combustion cavity, wherein the middle base plate, the micro-channel plate and the top cover plate are sequentially arranged on the upper side and the lower side of the combustion cavity in a laminated manner. Fuel oil flows through the micro-channel plate and then is sprayed into the combustion cavity body through a fuel oil atomizing nozzle, the fuel oil is ignited after mixed with air entering an air inlet, the fuel oil simultaneously serves as a coolant, heat released by the combustor is absorbed by a micro-channel, and the wall of the combustor is cooled while combustion efficiency is improved, so that regenerative cooling is realized. By taking the advantages of large surface area and micro-size effect enhanced heat exchange of the micro-channel, the wall temperature and the temperature gradient of the combustor are reduced, the problem of excessive heat stress is solved, and effective heat protection of the combustor is realized. Besides, preheated fuels are cracked, ignition performance is improved, and extinction limit and combustion efficiency are increased.

Description

Technical field [0001] The invention relates to the field of aeroengines, in particular to a micro-channel regenerative cooling micro-combustion chamber. Background technique [0002] With the improvement of the thrust-to-weight ratio of aviation gas turbine engines, the design of the combustion chamber is developing in the direction of high temperature rise and high heat capacity. The combustion chamber, as a place for organizing combustion, works in a high temperature and high pressure environment for a long time. It has to withstand great thermal stress, creep stress and fatigue stress. Its life and reliability have become the key to determining the life and reliability of the engine. The combustion chamber is generally made of high temperature resistant alloy, but the current temperature resistance of metal materials is below 1000 degrees Celsius, which is far lower than the gas temperature; and the temperature resistance level of metal materials is much lower than the increa...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/58
CPCF23R3/58
Inventor 邓大祥谢炎林万伟黄青松陈小龙付沁林
Owner XIAMEN UNIV
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