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12 条记录 (耗时 0.012 秒)

    Pulsed detonation engine
    1.
    发明授权
    Pulsed detonation engine 有权
    脉冲引爆机

    公开(公告)号：US08813474B2

    公开(公告)日：2014-08-26

    申请号：US12995269

    申请日：2009-06-04

    申请人： Emeric Daniau ,  François Falempin ,  Etienne Bobo ,  Jean-Pierre Minard

    发明人： Emeric Daniau ,  François Falempin ,  Etienne Bobo ,  Jean-Pierre Minard

    IPC分类号： F23R7/00 ,  F02K5/02 ,  F02K7/06

    CPC分类号： F23R7/00 ,  F02K5/02 ,  F02K7/06

    摘要： An engine including a means for supplying fuel to the combustion chamber of the fire tube, that includes a variable-volume transfer chamber for receiving fuel, a fuel transfer means from the tank of the engine towards the transfer chamber, and injection means for injecting fuel into the combustion chamber from the transfer chamber. The engine further includes an elastic return at least partially defined by the fuel contained in the transfer chamber.

    摘要翻译： 一种发动机，包括用于向燃烧管的燃烧室供应燃料的装置，其包括用于接收燃料的可变体积传送室，从发动机箱向传送室的燃料传递装置，以及用于喷射燃料的喷射装置 从传送室进入燃烧室。 发动机还包括至少部分地由包含在传送室中的燃料限定的弹性返回。

    Turbine engine including a continuous wave detonation chamber and cooling bypass flow and aircraft provided with such a turbine engine
    2.
    发明授权
    Turbine engine including a continuous wave detonation chamber and cooling bypass flow and aircraft provided with such a turbine engine 有权
    涡轮发动机包括连续波爆轰室和冷却旁路流，以及设有这种涡轮发动机的飞机

    公开(公告)号：US09556794B2

    公开(公告)日：2017-01-31

    申请号：US14116001

    申请日：2012-05-09

    申请人： François Falempin ,  Bruno Le Naour

    发明人： François Falempin ,  Bruno Le Naour

    IPC分类号： F02C5/02 ,  F02C7/22 ,  F02C3/14 ,  F02K7/08 ,  F23R3/50 ,  F23R7/00

    CPC分类号： F02C7/22 ,  F02C3/14 ,  F02C5/02 ,  F02K7/08 ,  F23R3/50 ,  F23R7/00 ,  Y02T50/671

    摘要： The chamber (4) of the turbine engine (1) comprises a continuous detonation wave engine (6) provided with an annular detonation chamber (7) and associated means (8, 9) that can be used to generate a continuous production of hot gases from a detonation mixture of fuel and air. The continuous detonation wave engine (6) is arranged such as to form, from a flow of incoming air (E), a first flow (F1) which enters the detonation chamber (7) and which is used by the engine (6) and a second flow (F2) which bypasses the chamber. The turbine engine (1) also includes auxiliary means (10) for mixing the hot gases (F3) leaving the detonation chamber (7) with the second flow of air (F2) before directing same towards the turbine (5). A plurality of detonation chambers (7) are arranged concentrically to one another relative to the axis of the turbine engine.

    摘要翻译： 涡轮发动机（1）的室（4）包括连续的爆震波发动机（6），其设置有环形爆震室（7）和相关联的装置（8,9），其可用于产生连续产生热气体 来自燃油和空气的爆燃混合物。 连续爆轰波发动机（6）布置成从进气（E）的流动形成进入爆震室（7）并被发动机（6）使用的第一流（F1）和 绕过室的第二流（F2）。 涡轮发动机（1）还包括辅助装置（10），用于在将其引导到涡轮机（5）之前将离开引爆室（7）的热气体（F3）与第二空气流（F2）混合。 多个引爆室（7）相对于涡轮发动机的轴线彼此同心地布置。

    RAMJET INCLUDING A DETONATION CHAMBER AND AIRCRAFT COMPRISING SUCH A RAMJET
    3.
    发明申请
    RAMJET INCLUDING A DETONATION CHAMBER AND AIRCRAFT COMPRISING SUCH A RAMJET 有权
    RAMJET包括一个爆炸室和包含这样一个RAMJET的飞机

    公开(公告)号：US20140196460A1

    公开(公告)日：2014-07-17

    申请号：US14116003

    申请日：2012-05-09

    申请人： François Falempin ,  Bruno Le Naour

    发明人： François Falempin ,  Bruno Le Naour

    IPC分类号： F02K7/20

    CPC分类号： F02K7/20 ,  F02K7/00 ,  F02K7/08 ,  F02K7/10

    摘要： The invention relates to a ramjet including a detonation chamber and an aircraft comprising such a ramjet. According to the invention, the ramjet (S1) comprises an annular detonation chamber (2) having a continuous detonation wave and fuel injection means (6) for continuously injecting fuel (F2) directly into the chamber (2) just downstream of an air injection base (3). The fuel (F2) and the air (F1) are injected separately into the detonation chamber (2) in a permanent manner throughout the operation of the ramjet (S1).

    摘要翻译： 本发明涉及一种包括爆震室的冲压喷气发动机和包括这种冲压喷气式飞机的飞机。 根据本发明，冲压喷气发动机（S1）包括具有连续爆震波的环形爆炸室（2）和燃料喷射装置（6），用于将燃料（F2）直接喷射到空气喷射器下游的腔室（2）中 基地（3）。 燃料（F2）和空气（F1）在整个冲压喷气机（S1）的操作过程中以永久的方式分别注入到引爆室（2）中。

    CONTINUOUS DETONATION WAVE ENGINE AND AIRCRAFT PROVIDED WITH SUCH AN ENGINE
    4.
    发明申请
    CONTINUOUS DETONATION WAVE ENGINE AND AIRCRAFT PROVIDED WITH SUCH AN ENGINE 有权
    连续发射波浪发动机和这种发动机提供的飞机

    公开(公告)号：US20140182295A1

    公开(公告)日：2014-07-03

    申请号：US14115530

    申请日：2012-05-09

    申请人： François Falempin

    发明人： François Falempin

    IPC分类号： F02K7/08

    CPC分类号： F02K7/08 ,  F02K7/00 ,  F02K9/62 ,  F23R3/425 ,  F23R7/00

    摘要： The invention relates to a continuous detonation wave engine and aircraft provided with such an engine. The continuous detonation wave engine (1) operates with a detonation mixture of fuel and oxidant and includes, in particular, a detonation chamber (3) comprising an injection base (10), the length of which is defined along an open line (17), such as to form a detonation chamber (3) having an elongate form in a transverse plane, as well as an injection system (4) arranged such as to inject the fuel/oxidant mixture into the detonation chamber (3) at at least one segment of the injection base (10).

    摘要翻译： 本发明涉及具有这种发动机的连续爆震波发动机和飞机。 连续爆震波发动机（1）用燃料和氧化剂的爆炸混合物操作，并且特别包括包括喷射基座（10）的爆炸室（3），该喷射基座的长度沿开放线（17）限定， ，诸如在横向平面中形成具有细长形式的引爆室（3）以及设置成将燃料/氧化剂混合物喷射到爆炸室（3）中的至少一个喷射系统（4）的喷射系统（4） 注射基底（10）的段。

    Pulse detonation engine
    7.
    发明授权
    Pulse detonation engine 有权
    脉冲爆震引擎

    公开(公告)号：US08850794B2

    公开(公告)日：2014-10-07

    申请号：US12988604

    申请日：2009-04-16

    申请人： Emeric Daniau ,  François Falempin ,  Etienne Bobo ,  Jean-Pierre Minard

    发明人： Emeric Daniau ,  François Falempin ,  Etienne Bobo ,  Jean-Pierre Minard

    IPC分类号： F02K7/06 ,  F02K5/02 ,  F23R7/00 ,  F02B71/06 ,  F02K7/075 ,  F02K7/02

    CPC分类号： F02B71/06 ,  F02K7/02 ,  F02K7/06 ,  F02K7/075 ,  Y02T50/672

    摘要： According to the invention, the said engine (I), which comprises at least one flame tube (2) with a mobile transverse end wall (18), comprises an external envelope (3) around the said flame tube (2), which defines a peripheral annular space (4) in which fixed flow guides (11, 12, 13, 14) are positioned, these flow guides forming flow channels (10) for the air, and at least one mobile plug (25), connected to the said mobile end wall (18), to close off and open one of the flow channels (10).

    摘要翻译： 根据本发明，所述发动机（I）包括具有可动横向端壁（18）的至少一个火焰管（2），包括围绕所述火焰管（2）的外壳（3），其限定 固定的流动引导件（11,12,13,14）定位在其中，这些流动导向件形成用于空气的流动通道（10），以及至少一个移动塞（25），其连接到所述外部环形空间 所述移动端壁（18）关闭并打开所述流动通道（10）中的一个。

    Ramjet engine combustion chamber and ramjet engine equipped with same
    9.
    发明授权
    Ramjet engine combustion chamber and ramjet engine equipped with same 有权
    喷气发动机燃烧室和配备相同的冲压式发动机

    公开(公告)号：US07000398B2

    公开(公告)日：2006-02-21

    申请号：US10476648

    申请日：2003-02-27

    申请人： Marc Bouchez ,  François Falempin

    发明人： Marc Bouchez ,  François Falempin

    IPC分类号： F02K7/10 ,  F02K9/64

    CPC分类号： F02K7/10 ,  F02K9/64

    摘要： The invention concerns a combustion chamber whereof the inner wall (17)is made at least partly of a thermostructural composite material, which is porous to the fuel passing through the double wall (14); and the porosity of said inner wall (17) is adjusted so that the proportion of said fuel passing through said inner skin ranges between 5% and 15% of the total amount of fuel input in said ramjet engine.

    摘要翻译： 本发明涉及一种燃烧室，其中内壁（17）至少部分地由热结构复合材料制成，其对通过双壁（14）的燃料是多孔的; 并且调整所述内壁（17）的孔隙率，使得通过所述内表皮的所述燃料的比例在所述冲压式喷气发动机中输入的燃料总量的5％至15％之间。