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1. 发明授权

EP4198292B1 VARIABLE AREA NOZZLE ASSEMBLY AND METHOD FOR OPERATING SAME 有权
公开(公告)号：EP4198292B1
公开(公告)日：2024-10-23
申请号：EP22214736.5
申请日：2022-12-19
IPC分类号： F02K1/12 , F02K1/36 , F02K1/46
CPC分类号： F02K1/1215 , F02K1/36 , F02K1/46

2. 发明公开

EP3214290A1 EFFIZIENTER STRAHLANTRIEB 审中-公开
标题翻译：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。

3. 发明公开

EP2204567A2 Gas turbine engine with ejector and corresponding operating method 有权转让
标题翻译： 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。

4. 发明授权

EP1320674B1 JET ENGINE WITH UNSTEADY FLOW EJECTOR 无效
标题翻译： WITH非平稳流喷嘴喷气发动机
公开(公告)号：EP1320674B1
公开(公告)日：2006-10-18
申请号：EP01977080.9
申请日：2001-08-30
申请人： The Boeing Company
发明人： CLARK, Larry, T.
IPC分类号： F02K1/36 , F02K1/38 , F02C3/10 , F02K1/46
CPC分类号： F02K1/386 , F02K1/40 , Y02T50/671
摘要： A jet engine assembly (60, 90) having a jet engine and an unsteady flow ejector (10). The unsteady flow ejector (10) segregates the exhaust flow (80, 106) from the jet engine (62, 92) into a plurality of rotating high velocity, low density jets (32) and a plurality of rotating low pressure voids (34). The low pressure voids (34) are employed to entrain at least a portion of a secondary flow (82, 120) of air which is mixed with the jets (32) to produced a mixed flow (86, 128) having a relatively higher flow rate and a relatively lower velocity than the exhaust flow (80, 106). A method for attenuating the noise that is produced by the exhaust flow (80, 106) of a jet engine (62, 92) is also provided.

5. 发明公开

EP1373702A1 TORTUOUS PATH EXHAUST EDUCTOR SYSTEM 审中-公开
标题翻译：与螺旋流管理排气系统JETS
公开(公告)号：EP1373702A1
公开(公告)日：2004-01-02
申请号：EP02723630.6
申请日：2002-03-26
申请人： Honeywell International Inc.
发明人： SHEORAN, Yogendra, Y. , EDMONDS, David, H. , BROWN, Daniel, V.
IPC分类号： F02K1/82 , F02K1/36 , B64D41/00 , B64D33/08
CPC分类号： B64D33/06 , B64D41/00 , B64D2041/002 , F02C7/14 , F02K1/36 , F02K1/827 , F05D2220/50 , F05D2250/314 , F05D2260/601 , F05D2260/96 , Y02T50/44 , Y02T50/671 , Y02T50/675
摘要： A tortuous path quiet exhaust eductor system may be mounted to a gas turbine engine, such as commercial aircraft APU. The system includes an oil cooler, eductor primary nozzle, oil cooler nozzle, and surge air dump nozzle. The primary nozzle, oil cooler air nozzle, and surge air dump nozzle direct exhaust flow to entrain APU compartment cooling air, oil cooling air and surge air in a direction having both radial and axial components with respect to the APU centerline axis. The exhaust flow is directed into an eductor mixing duct angled away from the centerline axis and then is turned to enter an exit duct angled toward the centerline axis so that direct line of sight acoustic paths from the tail pipe exit to the turbine exit are blocked, suppressing core noise. The tail pipe ducts may be acoustically treated, further enhancing noise suppresion.

6. 发明公开

EP0991860A1 MULTI-STAGE MIXER/EJECTOR FOR SUPPRESSING INFRARED RADIATION 失效
标题翻译： 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。

7. 发明授权

EP0626039B1 EXHAUST EDUCTOR COOLING SYSTEM 有权
标题翻译： ABGASDÜSENKÜHLSYSTEM
公开(公告)号：EP0626039B1
公开(公告)日：1996-06-05
申请号：EP93904985.4
申请日：1993-02-09
申请人： AlliedSignal Inc.
发明人： SHEORAN, Yogendra, Y. , SCHMITTENBERG, Marc , LYON, Craig, A. , ROYALTY, Charles, M. , KENZLER, Kurt, T. , DAVIS, Thomas, W.
IPC分类号： F02K1/36 , F02K1/82
CPC分类号： B64D41/00 , B64D33/08 , B64D2033/0213 , B64D2041/002 , F02K1/36 , F05D2220/50
摘要： A method and apparatus for cooling the heat generated by a gas turbine engine mounted in a compartment is provided. The apparatus comprises a novel eductor (60) that incorporates a mixer nozzle (70) to entrain sufficient air flow through the compartment to provide all the necessary cooling. The engine's oil cooler (62) is mounted to the eductor so that the entrained air flow passes through it and cools the engine's oil. The novel eductor also has means for receiving a flow of high velocity air (68) from the engine and injecting this air downstream of the mixer nozzle to enhance the entraining of the cooling flow.

8. 发明授权

EP3504418B1 VARIABLE GEOMETRY THRUSTER 有权
公开(公告)号：EP3504418B1
公开(公告)日：2022-04-06
申请号：EP17844440.2
申请日：2017-08-24
发明人： EVULET, Andrei
IPC分类号： F02K1/36 , F02K1/00 , F02K1/06 , F02K1/08 , F02K1/09 , F02K1/11 , F02K1/28

9. 发明公开

EP3421759A1 MICRO-TURBINE GAS GENERATOR AND PROPULSIVE SYSTEM 审中-公开
公开(公告)号：EP3421759A1
公开(公告)日：2019-01-02
申请号：EP18185310.2
申请日：2016-12-02
申请人： Jetoptera, Inc.
发明人： EVULET, Andrei
IPC分类号： F02C3/04 , F02C7/08 , F02K1/00 , F02K1/36 , F02K3/10 , F23R3/52 , F23R3/00
摘要： A combustor includes a first toroidal casing (302) circumscribing an axis and having an inlet configured to receive fluid, the first casing defining a first internal chamber in fluid communication with the inlet; a second toroidal casing (303) disposed within the first internal chamber and circumscribing the axis, the second casing having an outer wall defining a second internal chamber, the outer wall having a plurality of orifices formed therethrough, the orifices providing fluid communication between the first and second chambers; a plurality of fuel injectors (310) positioned to inject fuel into the second chamber through the orifices; and outlet structure defining at least one channel in fluid communication with the second chamber, the at least one channel being oriented parallel to the axis.

10. 发明公开

EP2204568A3 Gas turbine engine with ejector and corresponding operating method 有权
标题翻译：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。

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