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    Gas turbine engine with ejector and corresponding operating method
    2.
    发明公开
    Gas turbine engine with ejector and corresponding operating method 审中-公开
    带喷射器的燃气轮机发动机及相应的操作方法

    公开(公告)号：EP2204568A3

    公开(公告)日：2015-06-24

    申请号：EP09015974.0

    申请日：2009-12-23

    申请人： Rolls-Royce Corporation

    发明人： Khalid, Syed Jalaluddin

    IPC分类号： F02K1/36 ,  F02K3/077 ,  B64C21/06 ,  F04D29/64 ,  F02K3/02 ,  F02K3/075

    CPC分类号： F02K3/077 ,  B64C7/02 ,  B64D2033/0226 ,  F02K1/36 ,  F02K3/025 ,  F02K3/075 ,  F05D2260/601 ,  F05D2270/17

    摘要： The present inventions include a boundary layer ejector fluidically connecting boundary layer bleed slots from an external surface of an aircraft to reduce aircraft/nacelle/pylon drag, reduce jet noise and decrease thrust specific fuel consumption. In one embodiment a boundary layer withdrawn through the boundary layer bleed slots is entrained with an exhaust flow of a gas turbine engine. In another embodiment a boundary layer withdrawn through the boundary layer bleed slots is entrained with a flow stream internal to the gas turbine engine, such as a fan stream of a turbofan. Members can be provided near an outlet of a passageway conveying the withdrawn boundary layer air to locally reduce the pressure of the fluid in which the withdrawn boundary layer air is to be entrained. A lobed mixer can be used in some embodiments to effect mixing between the boundary layer and a primary fluid of the ejector.

    摘要翻译： 本发明包括边界层喷射器，其从飞机外表面流体连接边界层泄放狭槽以减少飞机/机舱/吊挂阻力，减少喷气噪声并降低推力比燃料消耗。 在一个实施例中，通过边界层泄放槽排出的边界层与燃气涡轮发动机的排气流夹带。 在另一个实施例中，通过边界层泄放狭槽抽出的边界层与燃气涡轮发动机内部的流动流一起夹带，例如涡扇的扇形流。 可以在通道的出口附近提供构件，该通道输送抽出的边界层空气以局部地降低其中夹带抽出的边界层空气的流体的压力。 在一些实施例中可以使用叶状混合器来实现边界层和喷射器的主要流体之间的混合。

    EFFIZIENTER STRAHLANTRIEB
    5.
    发明公开
    EFFIZIENTER STRAHLANTRIEB 审中-公开
    高效应变齿轮

    公开(公告)号：EP3214290A1

    公开(公告)日：2017-09-06

    申请号：EP16158557.5

    申请日：2016-03-03

    申请人： Alpha Velorum AG

    发明人： ZIEGLER, Martin

    IPC分类号： F02C7/04 ,  F02K3/062 ,  F02K1/36 ,  B63H11/00 ,  F02C7/055

    CPC分类号： F02K1/36 ,  F02C7/04 ,  F02C7/055 ,  F02K3/062 ,  F05D2250/51 ,  Y02T50/671

    摘要： Die Erfindung betrifft ein Verfahren zur Erzeugung von Schub, eine Antriebsmaschine zum Fahrzeugantrieb in einem Fluid, sowie ein Modul zum Anbau an die Front eines Triebwerks oder zur Integration in Teile eines Fahrzeuges, die einer Strömung ausgesetzt sind, mit einem fluiddynamischen Verdrängungskörper (VK) mit einer Längsachse, und einem statischen Propulsor (SP) mit einem mittleren Aussendurchmesser, welcher statische Propulsor sich dem Verdrängungskörper entlang der Längsachse entgegen einer Antriebsrichtung anschliesst und starr mit diesem verbunden ist, wobei der statische Propulsor eine Mehrzahl an Tragflächenelementen (SFi) aufweist, deren jeweiliger Querschnitt ein Tragflächenprofil hat, wobei Profilsehnen des Tragflächenprofils schräg zur Längsachse ausgerichtet sind, und wobei eine Profilsehne als Verbindungslinie zwischen einer Profilnase und einer Profilhinterkante definiert ist.

    摘要翻译： 本发明涉及一种用于推力的产生的过程中，原动机的车辆驱动的流体，以及用于安装在发动机的前部或用于整合到被暴露于流动，流体动态位移体（VK）与车辆的部件的模块 纵向轴线，并且具有的平均外径，其静态推进加入位移体沿纵向轴线计数器与驱动方向和与其刚性连接，其中，所述静态推进器具有多个翼元件（SFI）的静态推进器（SP），相应的 横截面具有的翼型轮廓，所述翼面轮廓的轮廓弦的倾斜取向的纵向轴线，并且其中，弦被定义为连接的前缘的线和后缘。

    Gas turbine engine with ejector and corresponding operating method
    6.
    发明公开
    Gas turbine engine with ejector and corresponding operating method 有权
    Vorrichtung und Verfahren zur Steuerung der Grenzschicht in einem Gasturbinentriebwerk

    公开(公告)号：EP2204567A2

    公开(公告)日：2010-07-07

    申请号：EP09015894.0

    申请日：2009-12-22

    申请人： Rolls-Royce Corporation

    发明人： Syed Jalaluddin, Khalid

    IPC分类号： F02K1/36 ,  F02K3/077 ,  B64C21/06 ,  F04D29/64

    CPC分类号： B64C7/02 ,  B64D2033/0226 ,  F01D9/065 ,  F02K1/36 ,  F02K3/025 ,  F02K3/075 ,  F02K3/077 ,  F04D29/684 ,  F05D2260/601 ,  F05D2270/17

    摘要： The present inventions include a boundary layer ejector fluidically connecting boundary layer bleed slots from an external surface of an aircraft to reduce aircraft/nacelle/pylon drag, reduce jet noise and decrease thrust specific fuel consumption. In one embodiment a boundary layer withdrawn through the boundary layer bleed slots is entrained with an exhaust flow of a gas turbine engine. In another embodiment a boundary layer withdrawn through the boundary layer bleed slots is entrained with a flow stream internal to the gas turbine engine, such as a fan stream of a turbofan. Members can be provided near an outlet of a passageway conveying the withdrawn boundary layer air to locally reduce the pressure of the fluid in which the withdrawn boundary layer air is to be entrained. A lobed mixer can be used in some embodiments to effect mixing between the boundary layer and a primary fluid of the ejector.

    摘要翻译： 本发明包括边界层喷射器从飞行器的外表面流体连接边界层排放槽以减少飞机/机舱/塔架阻力，减少喷气噪声并减小推力特定燃料消耗。 在一个实施例中，通过边界层排出槽排出的边界层与燃气涡轮发动机的排气流一起被夹带。 在另一个实施例中，通过边界层排放槽排出的边界层与气体涡轮发动机内部的流动流（例如涡轮风扇的风扇流）一起被夹带。 构件可以设置在通道的出口附近，该通道输送被排出的边界层空气，以局部地减小被抽出的边界层空气被夹带的流体的压力。 在一些实施例中，可以使用裂片混合器来实现边界层和喷射器的初级流体之间的混合。

    Lobed mixer/ejector nozzle
    8.
    发明公开
    Lobed mixer/ejector nozzle 审中-公开
    星形排气喷管

    公开(公告)号：EP0913568A3

    公开(公告)日：2000-07-26

    申请号：EP98120601.4

    申请日：1998-10-30

    申请人： Stage III Technologies L.C.

    发明人： Presz Jr., Walter M. ,  Reynolds, Gary

    IPC分类号： F02K1/48

    CPC分类号： F02K1/386 ,  F02K1/36 ,  Y02T50/672

    摘要： A mixer/ejector suppressor is disclosed for reducing the noise level created by the exhaust flows in gas turbines. In the preferred embodiment, the suppressor comprises a mixing ring of alternating lobes attached to the engine's tailpipe; an ejector shroud mounted onto the mixing ring; and a plurality of arcuate gaps, between the mixing ring and ejector shroud, that permit ambient air to be entrained into the shroud. The preferred mixing ring has ten curved lobes of alternating designs. Five of the mixing lobes are shallow, with contours similar to those of mixing lobes in an earlier TSMEC version, disclosed in a related U.S. utility patent application, Serial No. 08/729,571. The other five lobes are much longer, and they are designed to penetrate deeply into the engine's hot core flow. Together, the ten lobes rapidly mix (mostly at supersonic conditions) the engine exhaust flows with secondary ambient air inside the shroud. The lobes thereby increase the spread rate of the exhaust jet, dissipate its velocity and greatly decrease the core length of the exhaust jet. Hence, noise levels are reduced, which enable older engines to meet new federal noise regulations, known as "Stage 3", at static and takeoff conditions.

    MULTI-STAGE MIXER/EJECTOR FOR SUPPRESSING INFRARED RADIATION
    9.
    发明公开
    MULTI-STAGE MIXER/EJECTOR FOR SUPPRESSING INFRARED RADIATION 失效
    MEHRSTUFIGE EJEKTOR-MISCHERDÜSEZUR VERMEIDUNG VON INFRAROTSTRAHLUNG

    公开(公告)号：EP0991860A1

    公开(公告)日：2000-04-12

    申请号：EP98931220.2

    申请日：1998-06-19

    申请人： Sikorsky Aircraft Corporation

    发明人： HAMMOND, Mark, H. ,  PRESZ, Walter, M., Jr.

    IPC分类号： F02K1/48 ,  F02K1/38 ,  F02K1/36 ,  B64D33/04

    CPC分类号： F02K1/48 ,  B33Y80/00 ,  B64D33/04 ,  B64D2033/045 ,  F02K1/36 ,  F02K1/386 ,  F02K1/825 ,  Y02T50/671

    摘要： A multi-stage mixer-ejector (20) having at least one exhaust nozzle (24 or 28) which includes inlet conduit adapted for receiving a primary flow PF of engine exhaust and a plurality of adjoined lobes (30) integrally formed in combination with the inlet conduit. The adjoined lobes (30) of the exhaust nozzle (24 or 28) are characterized by a first and second plurality of penetrating lobes (60, 62 or 70, 72) which are axially staggered with respect to each other and which are adapted for admixing low-temperature gaseous fluid with the high-temperature exhaust. In the preferred embodiment, at least one of the plurality of penetrating lobes (60 or 62, 70 or 72) extends into a core region (CR) of the exhaust nozzle (24 or 28) to effect thorough mixing of the low temperature gaseous fluid with the engine exhaust.

    摘要翻译： 一种具有至少一个排气喷嘴（24或28）的多级混合器/喷射器（20），其包括适于容纳发动机排气的主流体PF的入口导管和多个相邻的叶片（30），其与 入口导管。 排气喷嘴（24或28）的邻接的叶片（30）的特征在于第一和第二多个穿孔（60,62或70,72），它们相对于彼此轴向交错，并且适于混合 低温气态液体与高温排气。 在优选实施例中，多个穿透叶片（60或62,70或72）中的至少一个延伸到排气喷嘴（24或28）的芯区域（CR）中，以实现低温气态流体 与发动机排气。

    CONVERTIBLE EJECTOR COOLED NOZZLE
    10.
    发明公开
    CONVERTIBLE EJECTOR COOLED NOZZLE 失效
    敞篷，通过喷射冷却喷管

    公开(公告)号：EP0852669A1

    公开(公告)日：1998-07-15

    申请号：EP96932295.0

    申请日：1996-09-20

    申请人： GENERAL ELECTRIC COMPANY

    发明人： HAUER, Thomas, Anthony ,  LIPPMEIER, William, Charles

    IPC分类号： F02K1

    CPC分类号： F02K1/805 ,  F02K1/008 ,  F02K1/36 ,  F02K1/825 ,  F05D2230/60 ,  F05D2230/70 ,  F05D2250/10 ,  F05D2260/202 ,  F05D2260/30 ,  F05D2260/601 ,  Y02T50/671 ,  Y02T50/675

    摘要： A nozzle cooling system (2) for selectively cooling longitudinally extending and circumferentially adjacent divergent exhaust flow confining elements (54 & 55) bounding a hot exhaust gas flowpath (4) in a divergent section (48) of an aircraft gas turbine engine exhaust nozzle (14) and providing pivoting capability for divergent flaps (54) and seals (55) in an axisymmetric vectoring nozzle (14). The apparatus includes axially adjacent foward and aft sections (49F & 49A) of at least one of the exhaust flow confining elements (typically referred to as flaps and seals), the adjacent forward and aft sections have forward and aft interior hot surfaces (47F & 47A) respectively, and mounting apparatus (56) for mounting the aft section to the forward section in one of at least two positions. A first one of these two positions spaces apart the sections to form a gap (106) between the sections which allows cooling air (102) to flow onto the aft interior hot surface and a second one of these two positions places the sections in close abutting relationship so as to essentially prevent cooling air from flowing onto the aft interior hot surface.