• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Jet engine with continuous and discontinuous impulse. Reaction engine (1) with continuous and discontinuous impulse, comprising a diffuser (2) of cylindrical external shape, a combustion chamber (3) and a fuel injection means (19) and, a nozzle (4), both in the same way exterior as the diffuser, a rotating disc chamber (5) that allows the passage of air from the diffuser (2) to the combustion chamber (3) continuously or discontinuously, an alternative motor with an alternative shaft (13) connected to a main shaft (9) of the motor (1) by means of a first cam (14), stop means of the main shaft (9), and a pressurized air chamber (16) connected to the main shaft (9) , wherein the fuel injection means (19) are able to trigger the injection in a synchronized manner with the passage of air from the diffuser (2) to the combustion chamber (3). (Machine-translation by Google Translate, not legally binding)
    公开号:ES2693983A1
    申请号:ES201730800
    申请日:2017-06-15
    公开日:2018-12-17
    发明作者:Antonio ACCION PENAS
    申请人:Antonio ACCION PENAS；
    IPC主号:
    专利说明:

    image 1
    image2
    image3
    image4
    image5
    5
    10
    fifteen
    twenty
    25
    30
    35


    In this way, thanks to the geometry of the rotary disk chamber (5) and the second cam
    (20) actuation of the fuel injection means (19), it is achieved that when rotating the second wheel (8) the three closed areas (12) of the same with the holes (11) of both caps (6) coincide . At that moment the activation of the fuel injection means (19) takes place, by the eccentricity of the second cam (20) and, the ignition of the fuel-air mixture by a spark produced by the spark plug.
    This generates the combustion of the fuel-air mixture and the increase of the temperature up to 2300ºC and of the air pressure to approximately 50 bars, leaving the air at high speed through the nozzle (4) and propelling the aircraft with a discontinuous impulse. .
    By varying the rotation of the main shaft (9), a position of coincidence is reached between the holes (11) of the second wheel (8) and those of both caps (6) of the rotary disc chamber (5). The second cam (20) has also rotated and in this case no longer operates the fuel injection means (19). Thus, in this position of coincidence of the holes (11), no fuel injection occurs and the air from the diffuser (2) circulates through the rotating disc chamber (5) towards the combustion chamber (3) and the nozzle (4) due to the vacuum generated when the air exits at high speed through the combustion chamber (3) in the opposite direction to the rotary disc chamber (5).
    At the moment when the aircraft exceeds the minimum speed which in this preferred embodiment of the invention has been considered to be 320 km / h, the reciprocating engine is switched off and the means for stopping the main shaft are activated. In this preferred embodiment of the invention, said stop means are formed by a hydraulic brake connected to a braking disk (22) acting on the main shaft (9) and makes it stop rotating and stand in a indeterminate angle.
    Subsequently, said hydraulic brake is stopped, and pressurized air is injected into the pressurized air chamber (16).
    In this preferred embodiment of the invention, the compressor of the pressurized air chamber (16) is formed by an inner piston joined at its center and perpendicular thereto to the second sliding handle (17). When injecting air under pressure, the piston lowers by actuating the second sliding handle (17) and the second connecting rod (18), such that the main shaft (9) remains fixed at an angle in which the holes (11) of the second wheel
    (8) and the two caps (6) coincide. At this moment the injection means are operated
    7


    of fuel (19) and proceed to the ignition of the mixture formed by air and fuel through the spark plug.
    Thus, at that moment fuel can be injected constantly and the engine (1) 5 operates continuously. In this case the hot air does not exit through the diffuser (2) because the plane has exceeded the minimum speed considered 320km / h.
    On the other hand, when the airplane moves above said minimum speed of 320 km / h and without exceeding the maximum speed for discontinuous operation of 640 10 km / h, the engine (1) operating in ramjet mode can return to operate in discontinuous mode.
    To do this, we reduce the pressure in the pressurized air chamber (16), stop operating the fuel injection means (19) and turn on the alternative motor so that it returns to operate in discontinuous mode.
    In this preferred embodiment of the invention, the motor (1) comprises means for electronic control of the switching on and off of the reciprocating motor, of the piston drive of the pressurized air chamber (16), of the stop means and
    20 of spark plug spark.
    The embodiment described is only an example of the present invention, therefore, the details, terms and specific phrases used herein are not to be considered as limiting, but should be understood only as a basis
    25 for the claims and as a representative basis that provides an understandable description as well as sufficient information to the person skilled in the art to apply the present invention.
    With the jet engine with continuous and discontinuous impulse that is presented here, significant improvements are obtained with respect to the state of the art.
    Thus, a simple and efficient engine is achieved that allows aircraft equipped with it to fly at hypersonic speeds without needing complex, heavy mechanisms or an auxiliary vehicle to achieve a minimum speed. On the other hand,
    35 aircraft that fly at subsonic speeds get a simpler, lighter engine with a better thrust-to-weight ratio than a turbojet engine.
    8


    Therefore, the dual operation of the engine as a ramjet is permitted when the aircraft exceeds the minimum speed for ramjet to hypersonic speeds and, as a batch pulse reactor while not exceeding this minimum speed.
    image6
    9
    权利要求:
    Claims (1)
    [1]
    image 1
    image2
    类似技术:
    公开号 | 公开日 | 专利标题
    ES2693983A1|2018-12-17|Jet engine with continuous and discontinuous impulse |
    US10208598B2|2019-02-19|Rotary energy converter with retractable barrier
    US8061327B2|2011-11-22|Tangential combustion turbine
    WO2011155248A1|2011-12-15|Engine
    US3702746A|1972-11-14|Rotary free piston gas generator
    CN102971519B|2016-04-27|Rocket engine and the method to rocket engine generation active thrust
    WO2015181512A1|2015-12-03|A new ramjet engine
    JP2017122578A|2017-07-13|Engine ejecting combustion gas as driving force
    RU2643274C1|2018-01-31|Rotary internal combustion engine
    US3781146A|1973-12-25|Rotary apparatus having two rotors engaging rotary dividers in a housing
    BRPI1009259A2|2019-07-02|compressed air engine, use of motor and motor vehicle
    JP2002004873A|2002-01-09|Internal combustion engine
    US1973887A|1934-09-18|Engine
    US20130047625A1|2013-02-28|Enhanced pulse detonation engine system
    JP6247873B2|2017-12-13|Gas flow control device
    US1094097A|1914-04-21|Starter for internal-combustion engines.
    RU2278986C1|2006-06-27|Combination air-jet engine
    US3525214A|1970-08-25|Piston-cylinder combustion,gas turbine engine
    CN210105990U|2020-02-21|Multi-cylinder turbine rotary engine
    CN102155292B|2013-07-17|Fan-type one-stroke engine
    CN107735555A|2018-02-23|The internal combustion engine of auxiliary power is used as using water
    Patel et al.2015|A Review on ram jet engine
    US1069742A|1913-08-12|Continuous-action rotary engine.
    ES2411829B1|2014-07-02|AXIAL INJECTION MOTOR
    RU2591071C1|2016-07-10|Rotary engine
    同族专利:
    公开号 | 公开日
    ES2693983B2|2019-08-02|
    RU2738672C1|2020-12-15|
    WO2018229317A1|2018-12-20|
    CA3066537A1|2018-12-20|
    EP3693594A1|2020-08-12|
    US20200182195A1|2020-06-11|
    WO2018229317A4|2019-01-31|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3008292A|1961-02-15|1961-11-14|Jr Joseph G Logan|Wave engines|
    US20030154707A1|2000-09-08|2003-08-21|Sanders Bobby W.|Rotary inlet flow controller for pulse detonation combustion engines|
    CN101059097A|2006-04-19|2007-10-24|章成谊|Ring-shape cylinder piston wheel engine|
    DE202009009764U1|2009-07-17|2009-10-29|Ramadani, Samet|Jet engine for propulsion of a missile|
    WO2014018416A1|2012-07-24|2014-01-30|Lee Brent Wei-Teh|Internal detonation engine, hybrid engines including the same, and methods of making and using the same|
    US7621118B2|2002-07-03|2009-11-24|Rolls-Royce North American Technologies, Inc.|Constant volume combustor having a rotating wave rotor|
    JP3952202B2|2004-02-19|2007-08-01|独立行政法人宇宙航空研究開発機構|Pulse detonation engine|
    RU2592124C1|2014-12-23|2016-07-20|Иван Иванович Михайлов|Rotary chute internal combustion engine|
    RU2610362C1|2015-10-06|2017-02-09|федеральное государственное автономное образовательное учреждение высшего образования "Самарский государственный аэрокосмический университет имени академика С.П. Королева " |Pulsating combustion chambers unit method of operation and design|RU2754976C2|2019-12-23|2021-09-08|Михаил Иванович Решетников|Universal jet engine |
    法律状态:
    2018-12-17| BA2A| Patent application published|Ref document number: 2693983 Country of ref document: ES Kind code of ref document: A1 Effective date: 20181217 |
    2019-08-02| FG2A| Definitive protection|Ref document number: 2693983 Country of ref document: ES Kind code of ref document: B2 Effective date: 20190802 |
    优先权:
    申请号 | 申请日 | 专利标题
    ES201730800A|ES2693983B2|2017-06-15|2017-06-15|Jet engine with continuous and discontinuous pulse|ES201730800A| ES2693983B2|2017-06-15|2017-06-15|Jet engine with continuous and discontinuous pulse|
    EP18783051.8A| EP3693594A1|2017-06-15|2018-06-11|Jet engine with continuous and discontinuous impulse|
    CA3066537A| CA3066537A1|2017-06-15|2018-06-11|Jet engine with continuous and discontinuous impulse|
    PCT/ES2018/070419| WO2018229317A1|2017-06-15|2018-06-11|Jet engine with continuous and discontinuous impulse|
    RU2019137538A| RU2738672C1|2017-06-15|2018-06-11|Jet engine with continuous and intermittent pulse|
    US16/623,094| US20200182195A1|2017-06-15|2018-06-11|Jet engine with continuous and discontinuous impulse|
    [返回顶部]