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公开(公告)号：US11408343B1
公开(公告)日：2022-08-09
申请号：US17313618
申请日：2021-05-06
IPC分类号： F02K3/02 , F02K3/077 , F02K3/11 , F02C7/36 , F02C7/052 , B64D27/10 , F02C6/20 , F02C9/18 , B64C27/12
摘要： A turboshaft engine includes a core section extending between an inlet and an outlet of the turboshaft engine. The core section includes a compressor, a main combustor, and a main turbine, such that combustion products from the main combustor drives rotation of the turbine and the compressor. A power turbine is fluidly connected to the main turbine and driven by exhaust from the main turbine. A primary bypass is fluidly connected to the inlet and the outlet. The primary bypass directs a portion of an airflow entering the inlet around the core section to the outlet. A secondary bypass is located in the core section and is configured to divert a portion of a core airflow of the core section around the main combustor and the main turbine to the power turbine.
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公开(公告)号：US10590849B2
公开(公告)日：2020-03-17
申请号：US14663871
申请日：2015-03-20
IPC分类号： F02C1/00 , F02C7/14 , F02C7/16 , F02C9/18 , F02C7/143 , F02C3/30 , F02C6/00 , F02K3/11 , F02K3/075 , F02K7/14 , F02K3/10 , F01D13/02 , F01D13/00 , F01D25/12
摘要： A cooling system for a turbine engine including a heat exchanger in fluid communication with a first fluid inlet stream and disposed upstream and in fluid communication with a core engine. The heat exchanger operative to cool the first fluid inlet stream. The heat exchanger including a heat exchanger inlet for input of a heat exchanging medium for exchange of heat from the first fluid inlet stream to the heat exchanging medium. The heat exchanger further including a heat exchanger outlet for discharge of a heated output stream into one of a turbine of a downstream engine, an augmentor or a combustor of the core engine. The heated output stream provides an additional flow to the downstream engine. A turbine engine including the cooling system is disclosed.
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公开(公告)号：US10094279B2
公开(公告)日：2018-10-09
申请号：US14764186
申请日：2013-01-29
发明人： Daniel B. Kupratis , Francis R Moon
IPC分类号： F02C3/14 , F02K3/11 , F23R7/00 , F02K3/06 , F02C5/02 , F02C7/06 , F02C7/36 , F23G7/06 , F02C3/107
摘要： The engine (10) includes a low spool (16) disposed aft of an air inlet (12) and a high spool (34) disposed aft of the low spool (16). An intake reverse-duct (44) is disposed radially outward of the high spool (34) and reverses direction of low pressure compressed air from the low spool (16) into a forward-flow high pressure compressor (40) of the high spool (34). A discharge reverse-manifold (48) directs flow of an exhaust gas stream (50} from a forward-flow low pressure turbine (20) into a rearward-flow direction and into at least one pulse detonation firing tube (54). An annular bypass air duct (72) directs cooling air along the engine (10)—The at least, one firing tube is positioned radially outward of the high spool (34), overlies the high spool (34) and is also positioned within the bypass air duct (72).
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25.发明授权Methods and apparatus for generating gas turbine engine thrust using a pulse detonator 有权使用脉冲雷管产生燃气涡轮发动机推力的方法和装置公开(公告)号：US07228683B2
公开(公告)日：2007-06-12
申请号：US10895585
申请日：2004-07-21
申请人： John Leslie Henry
发明人： John Leslie Henry
IPC分类号： F02K3/11
摘要： Methods and apparatus for generating thrust from a gas turbine engine using a pulse detonation system is provided. The gas turbine engine includes a fan assembly, and a bypass duct channeling air to a core engine and the pulse detonation system. The method includes injecting a charge of fuel into a pulse detonation tube that is coupled radially outward from the core engine, and controlling a supply of air from the fan into the pulse detonation tube through an opening in the inlet end of the pulse detonation tube using a rotary valve that is positioned radially outward from the core engine.
摘要翻译： 提供了使用脉冲爆震系统从燃气涡轮发动机产生推力的方法和装置。 燃气涡轮发动机包括风扇组件和将空气引导到核心发动机和脉冲爆震系统的旁路管道。 该方法包括将燃料的燃料喷射到从核心发动机径向向外连接的脉冲爆管中，并通过脉冲爆管的入口端的开口控制从风扇进入脉冲爆管的空气供应，使用 从核心发动机径向向外定位的旋转阀。
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公开(公告)号：US6112516A
公开(公告)日：2000-09-05
申请号：US177492
申请日：1998-10-23
CPC分类号： F23R3/20
摘要： A carbureted flameholder (30) with optial cooling is provided for a bypass turbojet-engine. The flameholder (30) comprises a body (34) which extends radially into the primary flow. The body (34) is formed by a V-dihedral having two outer plates (35, 36) which intersect at a common ridge apex (37). An air tube (38) is mounted between the two outer plates (35, 36) and at least one fuel conduit (44, 45) is disposed to the rear of the air tube (38). The overall cross-section of the air tube (38) is approximately triangular and the air tube (38) includes a transverse downstream wall that is curved to define a trough (42) in which the fuel conduit (44, 45) is located. The air tube (38) includes orifices (41, 46) directed against the dihedral plates (35, 36) and the fuel conduit (44, 45) to cool them. The fuel conduit includes a nozzle injector (46) directed downstream towards the afterburner chamber (23).
摘要翻译： 为旁路涡轮喷气发动机提供了具有光冷却的化油火焰稳定器（30）。 火焰稳定器（30）包括径向延伸到主流体的主体（34）。 主体（34）由具有在公共脊顶（37）相交的两个外板（35,36）的V形二面体形成。 空气管（38）安装在两个外板（35,36）之间，并且至少一个燃料管道（44,45）设置在空气管（38）的后部。 空气管（38）的整个横截面近似为三角形，并且空气管（38）包括弯曲的横向下游壁，以限定燃料导管（44,45）所在的槽（42）。 空气管（38）包括指向二面板（35,36）和燃料导管（44,45）的孔口（41,46）以冷却它们。 燃料管道包括朝向后燃室（23）的下游的喷嘴喷射器（46）。
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27.发明授权Method of preventing instabilities produced by combustion in a turbojet engine 失效防止涡轮喷气发动机燃烧产生的不稳定性的方法
公开(公告)号：US5699663A
公开(公告)日：1997-12-23
申请号：US622279
申请日：1996-03-27
摘要： A method of preventing instabilities due to combustion in a multi-flow turbojet engine including an afterburner into which an air-fuel mixture is injected in proportions measured in richness terms, which includes the steps of detecting experimentally, when tuning the turbojet engine, the zones of vibrations due to afterburn as a function of the operating conditions of the engine and as a function of the afterburn operating region, and selecting operating points for regulating the fuel richness of each flow to enable the detected vibration zones to be avoided.
摘要翻译： 一种防止在多流量涡轮喷气发动机中由于燃烧引起的不稳定性的方法，所述多流量涡轮喷气发动机包括其中注入空气燃料混合物的再燃烧器，其浓度以测量的比例包括在内，其包括以下步骤：在对涡轮喷气发动机进行调谐时， 根据发动机的操作条件和作为再燃烧操作区域的函数的随后的振动的振动，以及选择用于调节每个流量的燃料浓度的操作点以使得能够避免检测到的振动区域。
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公开(公告)号：US5311735A
公开(公告)日：1994-05-17
申请号：US58182
申请日：1993-05-10
申请人： Robert J. Orlando
发明人： Robert J. Orlando
摘要： A combined turbofan and ramjet aircraft engine includes a forward bypass duct which allows the engine to operate more efficiently during the turbofan mode of operation. By mounting a ramjet preburner in the forward duct and isolating this duct from the turbofan bypass air, a transition from turbofan operation to ramjet operation can take place at lower flight Mach numbers without incurring pressure losses or blockage in the turbofan bypass air.
摘要翻译： 组合的涡扇风扇和冲压式喷气式飞机发动机包括前向旁路管道，其允许发动机在涡轮风扇运行模式期间更有效地操作。 通过将冲压式预燃机安装在前进管道中并将该管道与涡扇风扇旁路空气隔离，从涡轮风扇操作到冲压喷气操作的过渡可以在较低的飞行马赫数下进行，而不会在涡扇风扇旁路空气中引起压力损失或堵塞。
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公开(公告)号：US5271222A
公开(公告)日：1993-12-21
申请号：US702407
申请日：1984-12-20
申请人： Ronald Coe , Douglas F. Kerr
发明人： Ronald Coe , Douglas F. Kerr
CPC分类号： F02K1/006 , B64C29/0066 , F02K1/70 , F02K1/74 , F02K3/11
摘要： A flow diverter arrangement for an aircraft comprises a first duct 17 for receiving propulsion fluid from the powerplant 11 and delivering it to a first location 18, a second duct 19 merging with the first duct 17 at a communication aperture 23 and adapted to deliver propulsion fluid to a second location, a flap member 24 pivotted for movement between a first position in which it closes the communication aperture 23 and a second position in which it closes the first duct, and a diverter device 31 for diverting propulsion fluid into the second duct when the flap member is in its second position.
摘要翻译： 用于飞行器的分流器装置包括用于从动力装置11接收推进流体并将其输送到第一位置18的第一管道17，在连通孔23处与第一管道17合并并适于输送推进流体的第二管道19 枢转到第二位置的挡片构件24在第一位置和第二位置之间运动，第一位置闭合连通孔23，第二位置关闭第一管道;以及分流装置31，用于将推进流体转向第二管道， 襟翼构件处于其第二位置。
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公开(公告)号：US4899539A
公开(公告)日：1990-02-13
申请号：US295998
申请日：1989-01-12
摘要： A flow mixer and flame stabilizer structure for an afterburner of a turbofan engine is disclosed having a variable mixer to mix a portion of the cold flow with the hot flow gasses and which also forms a flame stabilizer for a secondary afterburner fuel injection manifold which injects fuel into the cold flow air during afterburner operation. The device forms a flame stabilizer around the secondary, annular fuel injection manifold and has a generally "U" shaped cross-section. One of the legs forming the "U" shape is fixed, while the opposite leg is movable so as to vary the downstream facing opening between the legs. The movable leg also blocks a portion of the cold flow duct to generate localized increases in pressure upstream of the stabilizer. An air scoop located in this upstream portion communicates with the primary afterburner flame stabilizer to direct pressurized air to cool the primary flame stabilizer.
摘要翻译： 公开了一种用于涡轮风扇发动机的后燃器的流动混合器和火焰稳定器结构，其具有可变混合器以将冷流的一部分与热流体气体混合，并且还形成用于喷射燃料的二次加力燃料喷射歧管的火焰稳定器 在后燃器运行期间进入冷流空气。 该装置在次级环形燃料喷射歧管周围形成火焰稳定器，并且具有大致“U”形的横截面。 形成“U”形状的一个腿是固定的，而相对的腿是可移动的，以便改变腿之间的下游面向开口。 可移动的腿还阻挡冷流道的一部分以产生稳定器上游压力的局部增加。 位于该上游部分的空气勺与主辅助燃烧器火焰稳定器连通，以引导加压空气冷却主火焰稳定器。
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