Two regenerative cooling afterburners with sound cavities and application thereof

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...

AI Technical Summary

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, The present invention refers to the acoustic cavity technology and regenerative cooling technology of the aerospace power plant, and combines the characteristics of the aviation power plant, and proposes two kinds of regenerative cooling afterburner chambers with the acoustic cavity

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