IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0659888
(2006-04-19)
|
등록번호 |
US7980058
(2011-07-06)
|
우선권정보 |
CN-2005-005 1 0034447(2005-04-30) |
국제출원번호 |
PCT/CN2006/000730
(2006-04-19)
|
§371/§102 date |
20070926
(20070926)
|
국제공개번호 |
WO06/116907
(2006-11-09)
|
발명자
/ 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
6 |
초록
▼
The present invention relates to an air compression type engine for aviation. The conventional aircraft engine is complicated in structure, consumes expensive aero fuel, and produces extremely loud noise during operation. Therefore, the present invention employs a turbo-charged air compressor to gen
The present invention relates to an air compression type engine for aviation. The conventional aircraft engine is complicated in structure, consumes expensive aero fuel, and produces extremely loud noise during operation. Therefore, the present invention employs a turbo-charged air compressor to generate high temperature and high pressure gas in the pressure chamber, and uses the reaction thrust force generated by ejecting the compressed air through the nozzle to make the aircraft vertically take off/land, suspend in the air and fly forwardly. Benefited from the simple structure, the manufacture cost of the aircraft engine can be dramatically decreased. Vertically raising and landing the aircraft can be achieved by changing the ejection directed of the compressed air in the pressure chamber. The commonly used gasoline or diesel, which is cost saving and capable of combusting with a high combustion value, can be used instead of the expensive aviation kerosene. Further, the generated noise is quite small. By means of above arrangement, it is possible to manufacture a jet type manned craft like a car, which can be operated by common people to vertically take off/land and shuttle conveniently in the downtown area through simple operation procedure.
대표청구항
▼
The invention claimed is: 1. An air compression type engine for aviation, comprising:an air intake port (4),a turbo-charged air compressor (1),a combustion chamber (1),a rear nozzle member, characterized in that a pressure chamber (3) containing high temperature, high pressure gas generated by the t
The invention claimed is: 1. An air compression type engine for aviation, comprising:an air intake port (4),a turbo-charged air compressor (1),a combustion chamber (1),a rear nozzle member, characterized in that a pressure chamber (3) containing high temperature, high pressure gas generated by the turbo-charged air compressor is arranged between the rear nozzle for providing thrust force for forward flying and the combustion chamber, anda lower nozzle member receiving and ejecting the high temperature, high pressure gas for thrust in a vertical direction, all nozzle members being connected with this pressure chamber;wherein the turbo-charged air compressor includes an intake compressor (10), a large supercharging compressor module (11), and a small supercharging compressor (12) which are coupled to a front transmission shaft (35), and further includes a front driving turbine (25) and a rear driving turbine (26) which are coupled to a rear transmission shaft (16); a speed changed gear box (13) is arranged between the front transmission shaft (35) and the rear transmission shaft (16), the combustion chamber is arranged behind the speed changed gear box (13), and a fuel nozzle is arranged at the front end of the combustion chamber (3); after being pressurized by the intake compressor (10) and the large supercharging compressor module (11) for few levels, a large portion of the air enters into a main intake passage, while a small portion of the air enters into a sub-intake passage after being further pressurized by the small supercharging compressor (12); the air entering the sub-intake passage is mixed with fuel sprayed by the fuel nozzle (15) at the front part of the combustion chamber for effecting strong explosive combustion, the air entering the main intake passage is mixed with the gas in explosive combustion at the rear part of the combustion chamber (20), and the oxygen contained in the air facilitates the combustion of the remained unburnt fuel; the high temperature and high pressure gas generated by the explosive combustion is ejected through an exhausting port (19) of an ejection fence to drive the front driving turbine (25) to rotate, then passes through an intake port (28) of a cover of the rear driving turbine to drive the rear driving turbine (26) to rotate, and finally enters the pressure chamber (3); a large torque generated by rotation of the front driving turbine and the rear driving turbine exerts to the speed changed gear box (13) via the rear transmission shaft (16), increasing a rotation speed of the front transmission shaft, and thereby making the intake compressor (11), the large supercharging compressor module (12), and the small supercharging compressor (13) coupled to the front transmission shaft rotate in a high speed, brings in more air and generates large pressure to force the intake air passing through the main intake passage and the sub-intake passage and entering the combustion chamber; the high temperature and the high pressure gas entering the pressure chamber can be ejected through the rear nozzle member to push the aircraft flying forwardly, or ejected through the lower nozzle member to make the aircraft take off/land vertically, decelerate, suspend in the air, or move slowly forward, backward, leftward and rightward;the high pressure air-flow generated by the turbo-charged air compressor (1) is not ejected to the outside immediately, but is ejected into the pressure chamber (3) to generate high temperature and high pressure gas within the pressure chamber (3), thus the pressure chamber can be used as a buffer for the ejection air-flow;the pressure chamber (3) is positioned behind the combustion chamber (20), the noise produced by explosive combustion of the fuel in the combustion chamber (20) can be isolated and absorbed by the high pressure gas in the pressure chamber (3) and without being spread to the outside.
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