Two regenerative cooling afterburners with sound cavities and application thereof

An afterburner, cooling technology, applied in the direction of combustion chamber, continuous combustion chamber, combustion method, etc., can solve the problems of short working time, not too long life, not many applications, etc., to suppress high frequency unstable combustion and vibration reduction, increase working time and life, improve reliability

Active Publication Date: 2016-01-06
南通明艺玻璃科技有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] In view of the disadvantages of the existing afterburner, such as large vibration, short working time, not too long life, and few applications, in order to overcome these shortcomings and use the afterburner on the engine that propels a new type of supersonic passenger aircraft

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  • Two regenerative cooling afterburners with sound cavities and application thereof
  • Two regenerative cooling afterburners with sound cavities and application thereof
  • Two regenerative cooling afterburners with sound cavities and application thereof

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Embodiment Construction

[0028] figure 1 , figure 2 , image 3 , Figure 4 ,Include Figure 5-1 , Figure 5-2 and Figure 5-3 of Figure 5 and Figure 6 It is the preferred embodiment of two types of regenerative cooling afterburner chambers with acoustic cavity in the present invention.

[0029] Such as figure 1 and figure 2 As shown, the first regenerative cooling afterburner with acoustic cavity in the present invention is composed of a middle part, an outer ring part and a kerosene pipeline or a liquid hydrogen system. Tube 3, the outer ring part includes straight groove acoustic cavity 4, screw pile 5, nut 6, coolant outflow collector 7, coolant outlet pipe 8, afterburner inner wall 9, afterburner outer wall 10, coolant inflow Collector 11 and coolant inlet pipe 12, kerosene pipeline including kerosene supply pipe 71 for cooling, kerosene output pipe 72 for cooling, kerosene tee linking with the kerosene main pipe 81 and combustion chamber 82 of aviation gas turbine engine 80. Pipe 7...

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Abstract

The invention relates to two regenerative cooling afterburners with sound cavities. In order to overcome the defects of the existing afterburners and enlarge the application ranges, a straight-groove sound cavity for shock absorption is arranged and an integrated groove-milled connection structure employing kerosene or liquid hydrogen fuel or hydrogen peroxide having a medium concentration within the range of 70-79% as a regenerative cooling agent is adopted so that the reliability of the afterburner can be improved, and the working time, the service life, and the flight height and the speed can be increased. A schematic diagram of a related supply system is given in addition to the structures of the afterburners. The afterburners are mounted at the rear portion of an aero-gas turbine engine to form a long-augmentation aero-gas turbine engine and a tandem turbo-rocket combined engine. The afterburners can be provided for a plurality of high-speed airplanes as power devices, and are particularly applicable to novel supersonic airliners and advanced space tourism aircrafts. Besides, the afterburners also can be used as auxiliary winged rocket propulsion and withdrawal engines or low-turbine total temperature gas turbine engines for other purposes.

Description

technical field [0001] The invention relates to two regenerative cooling afterburning chambers with acoustic chambers, and belongs to the field of novel engines propelling high-speed aircraft. Background technique [0002] The exhaust of an aviation gas turbine engine contains a lot of oxygen. Setting the afterburner to inject fuel for afterburning can significantly increase the thrust and unit thrust and reduce the oxygen content of the exhaust. Especially in the high-altitude anoxic environment, it is more reasonable to use the afterburner. It is a good thing if the afterburner can propel a high-speed aircraft for a longer period of time. [0003] Since the complete combustion temperature of compressed air and kerosene reaches 2000°C, in order to prevent the wall of the afterburner from being burned, the afterburner of the aviation gas turbine engine is cooled by air flow without sufficient afterburner, and the afterburner time is short. Even so, the life of the afterburn...

Claims

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Application Information

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IPC IPC(8): F23R3/58F02K9/42
Inventor 葛明龙
Owner 南通明艺玻璃科技有限公司
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