| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 41 | Exhaust thrust augmenter | US36330940 | 1940-10-29 | US2401941A | 1946-06-11 | LEE JOHN G |
| 42 | Auxiliary power plant for airplanes | US55412144 | 1944-09-14 | US2395919A | 1946-03-05 | SUNDELL ALBERT T |
| 43 | Discharge nozzle | US25808239 | 1939-02-23 | US2297239A | 1942-09-29 | FRANZ NEUGEBAUER; ANSELM FRANZ; SIEGFRIED DECHER; KURT MEISSNER |
| 44 | Production of opaque glasses and enamels | US46713830 | 1930-07-10 | US1948461A | 1934-02-20 | IGNAZ KREIDL |
| 45 | Propulsion device | US67064223 | 1923-10-25 | US1493753A | 1924-05-13 | KOLEROFF BORIS T |
| 46 | AIR INLET ARRANGEMENT AND METHOD OF MAKING THE SAME | EP12825921.5 | 2012-08-17 | EP2744995B1 | 2018-05-16 | Conners, Timothy R.; Henne, Preston A.; Howe, Donald C. |
| An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate. | ||||||
| 47 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT | EP15819516.4 | 2015-08-14 | EP3168147A1 | 2017-05-17 | Noroian, Gevorg Serezhaevich |
The invention relates to aviation technology, specifically to vertical take-off and landing aircraft. The vertical take-off and landing aircraft comprises two turbines, the lower of which is of plate-like shape, and the upper is of flat or plate-like shape. Each turbine comprises a reactive power plant. The body of each turbine is mounted on a metallic disc connected to a vertical shaft of the aircraft, and is equipped with vanes. The vanes are mounted such that the position thereof can be changed. The aircraft can comprise intermediate turbines which are mounted between the upper and lower turbine and are flat or plate-like. The reactive power plant of each turbine comprises an air engine and receivers which are connected to a compressor. The body of each turbine is metallic and comprises two rings, one of which is connected to the disc, and also radial struts which are mounted along the perimeter of the turbine body and are connected to the rings and vanes. The vanes are mounted in a single row along the perimeter of the body or are arranged in a single tier. The result is an increase in the reliability and economy of the aircraft, and the possibility of the latter moving vertically, horizontally or at any inclination. |
||||||
| 48 | SYSTEM FOR THE RECOVERY, STORAGE AND UTILISATION OF ATMOSPHERIC GAS FOR USE AS A VEHICLE PROPELLANT | EP11749927.7 | 2011-07-27 | EP2621812A1 | 2013-08-07 | REED, Jaime Simon |
| A system for the recovery and management of atmospheric gas is disclosed, such as for use as a vehicle propellant in a vehicle propulsion system. The system can include a compressor configured to compress atmospheric gas and first and second storage tanks configured to store liquefied atmospheric gas from the compressor. The second storage tank can have a heater operable to heat liquefied atmospheric gas therein to convert it to a high pressure gas. The second storage tank includes an outlet duct fluidly coupled to the first storage tank for supplying high pressure gas to the first storage tank. | ||||||
| 49 | Moteur à onde de détonation continue et engin volant pourvu d'un tel moteur | EP12290157.2 | 2012-05-09 | EP2525071A1 | 2012-11-21 | Falempin, François |
Le moteur à onde de détonation continue (1) fonctionne avec un mélange combustible/oxydant détonant et comporte notamment une chambre de détonation (3) comprenant un fond d'injection (10) dont la longueur est définie selon une ligne ouverte (17), de manière à former une chambre de détonation (3) présentant une forme allongée dans un plan transversal, ainsi qu'un système d'injection (4) qui est agencé de manière à injecter le mélange combustible/oxydant dans ladite chambre de détonation (3) au niveau d'au moins un tronçon dudit fond d'injection (10).
|
||||||
| 50 | SHAPED CHARGE ENGINE | EP01941451.5 | 2001-03-02 | EP1264100A1 | 2002-12-11 | DUNCAN, Ronnie, J. |
| A shaped charge engine includes an annular blast-forming chamber (3) formed by joining inner (1) and outer (2) housings. A central through hole in the inner housing allows exhaust gases to exit. The outer housing comprises a generally round disk with an inner conical concave depression and through holes for the insertion of fuel and ignition. The blast chamber is preferably taper-conical in shape, wider at the base, and gradually decreasing in cross-sectional area as it rises to the apex. This construction forms a circular pinch point or throat toward the apex that produces a primary compression zone. A secondary compression zone is created at the apex of the outer housing, just beyond the throat, producing hypersonic gases as generally opposing exhaust streams collide and are forced to exit the through hole in the inner housing. The shaped charge engine may be used in a variety of applications, including as a pulsed direct propulsion device, as a turbine driver, or in a wide array of tools and appliances. | ||||||
| 51 | Compression wave former | EP82108253.4 | 1982-09-08 | EP0102411A1 | 1984-03-14 | Adams, Joseph S. |
@ Compression waves are formed by detonating a mixture of fuel and air confined within a chamber that has a constricted output opening. The mixture is ignited instantaneously throughout a peripheral region of the chamber opposite the output opening, and this region is shaped relative to the dimensions of the chamber and the output opening so that the burning of the mixture accelerates toward the output opening and inward from the peripheral region. This dynamically compresses and detonates the mixture to form a high pressure compression wave and direct it out of the output opening. The instantaneous ignition can be by plasma jets or flames injected into the ignition region from an ignition chamber adjacent to the detonation chamber. The device can directly transform the chemical energy of a fuel into a high pressure thrust directed against a relatively movable resistance to serve as a prime mover suitable for many tasks. It can drive a piston, plunger, or rotor vane; provide propulsive thrust; or direct a compression wave through open air. |
||||||
| 52 | 레이크 장치 및 그 제작방법 | KR1020080129339 | 2008-12-18 | KR1020100070684A | 2010-06-28 | 이보화; 양수석 |
| PURPOSE: A rake device and a manufacturing method thereof are provided to reduce manufacturing costs and times by simplifying processes for forming a working fluid flow path. CONSTITUTION: A rake device comprises a rake body(101), a flow path forming unit(120), and a measuring unit. In order to fix the flow path forming unit, into which a part of working fluid enters, to the rake body, rubber or silicon are injected around the flow path forming unit. The measuring unit measures the state of the working fluid transferred through the flow path forming unit. The measuring unit is connected to the flow path forming unit. The measuring unit measures the temperature of the working fluid. | ||||||
| 53 | 쉐입드 차지 엔진 | KR1020027011503 | 2001-03-02 | KR1020030025908A | 2003-03-29 | 던컨,로니제이. |
| 쉐입드 차지 엔진(shaped charge engine)은 내부 하우징(1)과 외부 하우징(2)을 결합함으로써 형성된 환상 폭파-성형 챔버(blast-forming chamber)(3)를 포함한다. 내부 하우징의 중앙 관통공은 배기 가스를 배출시킨다. 외부 하우징은 내부 원뿔 볼록 디프레션(depression)과 연료와 점화의 삽입을 위한 관통공을 갖는 일반적으로 둥근 디스크를 포함한다. 폭파 챔버는 바람직하게 베이스에서 더 넓고, 정점으로 올라갈수록 단면적이 점차 감소하는 테이퍼-원뿔 형태이다. 이와 같은 구조는 원형 핀치 포인트(pinch point) 또는 제1압축영역을 생성하는 정점을 향하는 스로트를 형성한다. 제2압축영역은 스로트 바로 넘어 외부 하우징의 정점에서 발생되고, 일반적으로 대향하는 배출 스트림이 충돌하고 내부 하우징의 관통공을 빠져나감에 따라 극초음속 가스를 생성시킨다. 쉐입드 차지 엔진은 펄스 다이렉트 추진 장치와 터빈 드라이버를 포함하는 다양한 어플리케이션(applications)에서 사용되거나, 또는 광범위한 툴과 어플리케이션에서 사용될 수 있다. | ||||||
| 54 | JET ENGINE, FLYING VEHICLE, AND METHOD FOR OPERATING JET ENGINE | EP15773405.4 | 2015-02-18 | EP3098420A1 | 2016-11-30 | UENO, Yoshihiko; FURUYA, Shojiro |
A jet engine has an inlet which takes in air, a combustor (12) which combusts fuel by using the air, and a fuel control section (37) which controls supply of the fuel. The combustor (12) has a fuel supplying section (22) which supplies the fuel, injectors (20) which inject the fuel. Each injector (20) contains openings (30-1 to 30-5) which inject the fuel. The fuel supplying section (22) supplies the fuel to the injector (20) in a flow rate according to a command of an autopilot. The fuel control section (37) controls the injectors (20) such that the number of the openings (30) which inject the fuel or flow-path cross-section areas of the pipes which send the fuel in case of the low-speed is more than the number of the openings (30) which inject the fuel or the flow-path cross-section areas of the pipes which send the fuel in case of the high-speed. |
||||||
| 55 | AIR INLET ARRANGEMENT AND METHOD OF MAKING THE SAME | EP12825921.5 | 2012-08-17 | EP2744995A1 | 2014-06-25 | Conners, Timothy R.; Henne, Preston A.; Howe, Donald C. |
| An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate. | ||||||
| 56 | Moteur à onde de détonation continue et engin volant pourvu d'un tel moteur | EP12290157.2 | 2012-05-09 | EP2525071B8 | 2013-12-25 | Falempin, François |
| The motor (1) has a priming unit (8) arranged in a detonation chamber (3) for initiating detonation mixture. The detonation chamber is provided with an injection base (10), where length of the base is defined along an open line (17) to form the detonation chamber having elongated shape in a transverse plane. An injection system (4) injects fuel/oxidant detonation mixture into the detonation chamber at the level of a segment of the base. A cooling circuit extends along a side wall of the detonation chamber. | ||||||
| 57 | Statoréacteur à chambre de détonation et engin volant comprenant un tel statoréacteur | EP12290156.4 | 2012-05-09 | EP2525070A1 | 2012-11-21 | Falempin, François; Le Naour, Bruno |
Selon l'invention, le statoréacteur (S1) comprend une chambre détonation (2) annulaire à onde de détonation continue et des moyens d'injection de combustible (6) pour injecter en continu du combustible (F2) directement dans ladite chambre (2) juste en aval d'un fond d'injection d'air (3). L'injection de combustible (F2) et l'injection d'air (F1) dans la chambre de détonation (2) sont réalisées séparément l'une de l'autre, de façon permanente au cours du fonctionnement dudit statoréacteur (S1).
|
||||||
| 58 | ANTRIEB VON FAHRZEUGEN ODER TRANSPORT EINES MEDIUMS MIT HILFE EINES KEGELFÖRMIGEN KÖRPERS | EP03720779.2 | 2003-05-02 | EP1718856A1 | 2006-11-08 | PAYNE, Michael |
| An apparatus works on the basis of the cyclone principle, as in a whirlwind or liquid or gas whirl or cosmic whirl, to transmit motor energy to a medium (liquid, gas, or vacuum) and to use this energy for various purposes, such as a drive for pumps, vehicles and appliances in water, air and vacuum, and for accelerating media of all kinds. A cone which is as smooth as possible and has as fine a point as possible is rotated in the medium about the axis of the cone, creating a homogeneous whirl which is driven in the medium. The whirl sucks in all that is movable around it, especially the used medium. In order to use the whirling motion, the suction is diverted into a medium-guiding housing adapted to the intended purpose. For the purpose of propulsion, the medium accelerated by the whirl is extracted from the total medium volume through the front of the medium guiding-housing, is separated and is returned to the housing in the opposite direction to the direction of displacement. | ||||||
| 59 | Energetic detonation propulsion | EP05254546.4 | 2005-07-21 | EP1621753A1 | 2006-02-01 | Minick, Alan B.; Goldberg, Benjamin; Knauer, Larry |
A propulsion system (10) for creating a propulsive force has a combustion chamber (12), a pair of electrodes (18,20) within the combustion chamber (12) and a power supply (16) attached to the electrodes (18,20) to create a high voltage field within an initiation zone of the combustion chamber (12), and an injector (26) for introducing a propellant, preferably in atomized form, into the high voltage field for creating the propulsive force. In a preferred embodiment of the present invention, the propellant is hydrogen peroxide. In another embodiment of the present invention, a second propellant is introduced into the combustion chamber (12) for increasing the propulsive force.
|
||||||
| 60 | SHAPED CHARGE ENGINE | EP01941451 | 2001-03-02 | EP1264100A4 | 2003-09-10 | DUNCAN RONNIE J |
| A shaped charge engine includes an annular blast-forming chamber (3) formed by joining inner (1) and outer (2) housings. A central through hole in the inner housing allows exhaust gases to exit. The outer housing comprises a generally round disk with an inner conical concave depression and through holes for the insertion of fuel and ignition. The blast chamber is preferably taper-conical in shape, wider at the base, and gradually decreasing in cross-sectional area as it rises to the apex. This construction forms a circular pinch point or throat toward the apex that produces a primary compression zone. A secondary compression zone is created at the apex of the outer housing, just beyond the throat, producing hypersonic gases as generally opposing exhaust streams collide and are forced to exit the through hole in the inner housing. The shaped charge engine may be used in a variety of applications, including as a pulsed direct propulsion device, as a turbine driver, or in a wide array of tools and appliances. | ||||||
