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    Injection manifold with Tesla valves for rotating detonation engines
    1.
    发明授权
    Injection manifold with Tesla valves for rotating detonation engines 有权

    公开(公告)号：US12098848B2

    公开(公告)日：2024-09-24

    申请号：US18372796

    申请日：2023-09-26

    申请人： Purdue Research Foundation

    发明人： Qili Liu ,  Li Qiao

    IPC分类号： F23R7/00 ,  F02C5/02 ,  F02K7/067 ,  F02K9/52

    CPC分类号： F23R7/00 ,  F02C5/02 ,  F02K7/067 ,  F02K9/52

    摘要： A combustion method is disclosed, which includes the steps of mixing fuel and an oxidizer into a mixture, wherein fuel originates from a fuel manifold and the oxidizer originates from an oxidizer manifold, and combusting the mixture in a combustion chamber, the fuel manifold, the oxidizer manifold, and the combustion chamber forming parts of an injector assembly wherein each of the fuel and oxidizer manifolds communicates with the combustion chamber via a plurality of dedicated radially disposed Tesla valves around the combustion chamber each via a corresponding port with only one Tesla valve between the fuel manifold and the corresponding port on the combustion chamber and with only one Tesla valve between the oxidizer manifold and the corresponding port on the combustion chamber, wherein the plurality of Tesla valves substantially eliminate reverse flow of exhaust gases from the combustion chamber back to the fuel manifold or the oxidizer manifold.

    INJECTION MANIFOLD WITH TESLA VALVES FOR ROTATING DETONATION ENGINES
    2.
    发明公开
    INJECTION MANIFOLD WITH TESLA VALVES FOR ROTATING DETONATION ENGINES 审中-公开

    公开(公告)号：US20240019126A1

    公开(公告)日：2024-01-18

    申请号：US18372796

    申请日：2023-09-26

    申请人： Purdue Research Foundation

    发明人： Qili Liu ,  Li Qiao

    IPC分类号： F23R7/00 ,  F02K9/52 ,  F02C5/02 ,  F02K7/067

    CPC分类号： F23R7/00 ,  F02K9/52 ,  F02C5/02 ,  F02K7/067

    摘要： A combustion method is disclosed, which includes the steps of mixing fuel and an oxidizer into a mixture, wherein fuel originates from a fuel manifold and the oxidizer originates from an oxidizer manifold, and combusting the mixture in a combustion chamber, the fuel manifold, the oxidizer manifold, and the combustion chamber forming parts of an injector assembly wherein each of the fuel and oxidizer manifolds communicates with the combustion chamber via a plurality of dedicated radially disposed Tesla valves around the combustion chamber each via a corresponding port with only one Tesla valve between the fuel manifold and the corresponding port on the combustion chamber and with only one Tesla valve between the oxidizer manifold and the corresponding port on the combustion chamber, wherein the plurality of Tesla valves substantially eliminate reverse flow of exhaust gases from the combustion chamber back to the fuel manifold or the oxidizer manifold.

    Multitube valveless pulse detonation engine
    5.
    发明授权
    Multitube valveless pulse detonation engine 有权
    多管无阀脉冲爆震引擎

    公开(公告)号：US09359973B2

    公开(公告)日：2016-06-07

    申请号：US13160840

    申请日：2011-06-15

    申请人： Soheil Farshchian ,  Alejandro Juan

    发明人： Soheil Farshchian ,  Alejandro Juan

    IPC分类号： F02K7/067 ,  F02K7/04 ,  F02C5/11 ,  F23C15/00

    CPC分类号： F02K7/04 ,  F02C5/11 ,  F02K7/067 ,  F23C15/00 ,  F23C2900/03004

    摘要： Disclosed herein is a valveless multitube pulse detonation engine including: a plurality of detonation tubes, wherein each detonation tube comprises an independent discharge outlet, and the plurality of detonation tubes interconnected at a common air/fuel mixture intake port. In the disclosed engine, an air and fuel mixture is detonated in the detonation tubes simultaneously, and the common air/fuel mixture intake port minimizes back-pressure caused by detonating the air/fuel mixture by directing multiple reverse shock waves into one another and effectively using the back-pressures as reacting surfaces for one another and effectively reducing the effect of back flowing shock waves moving towards upstream. The detonation tubes may be non-linear, and may have independent discharges. The independent discharges may be coupled to an adapter nozzle terminating in a combined exhaust outlet.

    摘要翻译： 本文公开了一种无阀多管脉冲爆震发动机，其包括：多个爆管，其中每个爆管包括独立的排放口，并且所述多个引爆管在公共空气/燃料混合物进气口处相互连接。 在所公开的发动机中，空气和燃料混合物同时在引爆管中引爆，并且公共空气/燃料混合物进气口通过将多个反向冲击波相互引导并有效地使由空气/燃料混合物引爆引起的背压最小化 使用背压作为彼此的反应表面，并且有效地减少向上游移动的回流冲击波的影响。 引爆管可以是非线性的，并且可以具有独立的放电。 独立放电可以连接到终止于组合排气出口的适配器喷嘴。

    Jet engine, in particular a jet engine for an aircraft
    6.
    发明授权
    Jet engine, in particular a jet engine for an aircraft 有权
    喷气发动机，特别是用于飞机的喷气发动机

    公开(公告)号：US08925296B2

    公开(公告)日：2015-01-06

    申请号：US13142673

    申请日：2010-01-15

    申请人： Michel Aguilar

    发明人： Michel Aguilar

    IPC分类号： F02C5/12 ,  F01D17/14 ,  F02K9/40 ,  F02K7/067

    CPC分类号： F01D17/14 ,  F02C5/12 ,  F02K7/067 ,  F02K9/40

    摘要： The invention relates to a jet engine (1), in particular an aircraft jet engine, including at least one combustion chamber (3). The combustion chamber (3) is connected to at least one compressed gas intake (4) and to at least one burnt gas outlet (5). Said burnt gas outlet(s) (5) include an exhaust valve. The exhaust valve includes two rotary parts (7), referred to as rotary exhaust parts, the rotary exhaust parts (7) including curved walls (8) and intermediate walls (9) connecting the curved walls (8), and rotating in a coordinated, continuous fashion such that said valve is in a closed position in order to block the gas during at least one combustion step, and in an open position in order to define a space (10) through which the gas flows out from the combustion chamber (3) during at least one expansion step.

    摘要翻译： 本发明涉及一种包括至少一个燃烧室（3）的喷气发动机（1），特别是飞机喷气发动机。 燃烧室（3）连接到至少一个压缩气体入口（4）和至少一个燃烧气体出口（5）。 所述燃烧气体出口（5）包括排气阀。 排气阀包括两个被称为旋转排气部的旋转部分（7），包括连接弯曲壁（8）的弯曲壁（8）和中间壁（9）的旋转排气部分（7） 连续的方式，使得所述阀处于关闭位置，以便在至少一个燃烧步骤期间阻挡气体，并且在打开位置以限定气体从燃烧室流出的空间（10） 3）在至少一个膨胀步骤期间。

    PULSE JET ENGINE
    7.
    发明申请
    PULSE JET ENGINE 审中-公开
    脉冲喷气发动机

    公开(公告)号：US20110167787A1

    公开(公告)日：2011-07-14

    申请号：US13001559

    申请日：2009-06-26

    申请人： H. Brooks Herndon

    发明人： H. Brooks Herndon

    IPC分类号： F02K7/04

    CPC分类号： F02K7/067 ,  F05D2260/99

    摘要： The present invention relates to pulse jet engines. More specifically, the present invention concerns a pulse jet engine which uses fluidic valving rather than unreliable mechanical valves, incorporates two combustion chambers with approximately the same but approximately 180 degree out-of-phase resonance frequencies to reduce noise through destructive interference of sound waves, and controls fuel injection and ignition within the two combustion chambers to increase efficiency by achieving more rapid and complete combustion.

    摘要翻译： 本发明涉及脉冲喷气发动机。 更具体地说，本发明涉及一种使用流体阀而不是不可靠的机械阀的脉冲喷气发动机，其结合了具有大约相同但约180度异相共振频率的两个燃烧室，以通过声波的破坏性干扰来减少噪声， 并控制两个燃烧室内的燃料喷射和点火，以通过实现更快速和完全的燃烧来提高效率。