公开(公告)号：US11884414B2

公开(公告)日：2024-01-30

申请号：US16451459

申请日：2019-06-25

申请人： ROLLS-ROYCE plc

发明人： Robert J Corin ,  John R Whurr

IPC分类号： B64D33/02 ,  B64C30/00 ,  F02C7/04 ,  F02K1/08 ,  F02K1/38 ,  F02K3/075

CPC分类号： B64D33/02 ,  B64C30/00 ,  F02C7/04 ,  F02K1/08 ,  B64D2033/026 ,  B64D2033/0286 ,  F02K1/386 ,  F02K3/075 ,  F05D2220/80 ,  F05D2250/51

摘要： Engine has core compressor, combustor and turbine, fan located upstream of core and supersonic intake for slowing down incoming air at inlet formed by intake, bypass duct surrounding engine core, fan generates airflow to engine core and bypass airflow through bypass duct. Engine has mixer for exhaust gas flow exiting engine core, bypass airflow exiting bypass duct, thrust nozzle for discharging mixed flows, and controller for thrust produced by engine. To change level of engine thrust between transonic push operation and supersonic cruise operation, controller adjusts one or more components which vary relative areas available for hot exhaust gas flow and cold bypass airflow at mixer while holding fan inlet non-dimensional mass flow w √{square root over ( )} T/P substantially constant, where w is mass flow of incoming air at fan inlet, T is stagnation temperature of incoming air at fan inlet and P is stagnation pressure of incoming air at fan inlet.

公开(公告)号：US20180355821A1

公开(公告)日：2018-12-13

申请号：US15619029

申请日：2017-06-09

申请人： United Technologies Corporation

发明人： Andre L. Bent ,  Steven H. Zysman ,  Nigel David Sawyers-Abbott

IPC分类号： F02K1/70 ,  F02K3/06 ,  F02C3/04

CPC分类号： F02K1/70 ,  F02C3/04 ,  F02K1/08 ,  F02K1/16 ,  F02K1/72 ,  F02K3/06 ,  F05D2260/57 ,  F05D2270/62 ,  F05D2270/65

摘要： An exhaust section of a gas turbine engine includes an exhaust plug, and an exhaust nozzle radially offset from the exhaust plug defining an exhaust pathway between the exhaust plug and the exhaust nozzle. The exhaust plug is configured for axial translation relative to exhaust nozzle between a first position and a second position to selectably change a cross-sectional area of the exhaust pathway during thrust reversal operation of the gas turbine engine to reduce an amount of reverse thrust necessary. A method of operating a gas turbine engine includes actuating a fan thrust reverser to divert a fan airflow from a fan airflow pathway, and translating an exhaust plug from a first position to a second position, thereby increasing a cross-sectional area of an exhaust pathway to reduce an amount of reverse thrust necessary.

公开(公告)号：US09828943B2

公开(公告)日：2017-11-28

申请号：US14709654

申请日：2015-05-12

申请人： United Technologies Corporation

发明人： Richard Alan Weiner

IPC分类号： F02K1/08 ,  F02K1/76 ,  F02K1/12 ,  F02C7/14 ,  F02K1/15 ,  F02K1/62

CPC分类号： F02K1/763 ,  F02C7/14 ,  F02K1/08 ,  F02K1/085 ,  F02K1/1223 ,  F02K1/15 ,  F02K1/62 ,  F05D2260/213 ,  Y02T50/676

摘要： A variable area fan nozzle comprises an actuator flap and a follower flap. The actuator flap has a portion in contact with a portion of the follower flap. A bias member biases the follower flap outwardly. An actuator actuates the actuator flap inwardly and outwardly to, in turn, move the follower flap against the bias member and to vary an area of an exhaust nozzle. The flap actuator is operable to drive the actuator flap out of contact with the follower flap into a thrust reverser position.

公开(公告)号：US20160377026A1

公开(公告)日：2016-12-29

申请号：US14753637

申请日：2015-06-29

申请人： United Technologies Corporation

发明人： Gary D. Roberge

IPC分类号： F02K1/08 ,  F02K1/15 ,  F02K1/00 ,  F02K3/02

CPC分类号： F02K1/08 ,  F02K1/002 ,  F02K1/15 ,  F02K1/42 ,  F02K1/58 ,  F02K1/763 ,  F02K3/02

摘要： An exhaust nozzle for a gas turbine engine according to an example of the present disclosure includes, among other things, a duct having a first surface and a second surface extending about a duct axis to define an exhaust flow path, and at least one effector positioned along the first surface. The at least one effector is pivotable about an effector axis to vary a throat area of the exhaust flow path. The at least one effector tapers along the effector axis. A method of exhaust control for a gas turbine engine is also disclosed.

摘要翻译： 根据本公开的示例的用于燃气涡轮发动机的排气喷嘴包括具有第一表面和第二表面的管道，管道围绕管道轴线延伸以限定排气流动路径，并且至少一个效应器定位 沿着第一个表面。 所述至少一个效应器围绕效应器轴线枢转以改变排气流动路径的喉部区域。 至少一个效应器沿着效应器轴线逐渐变细。 还公开了一种用于燃气涡轮发动机的排气控制方法。

公开(公告)号：US09328695B2

公开(公告)日：2016-05-03

申请号：US12442547

申请日：2006-10-12

申请人： Constantine Baltas ,  Amr Ali

发明人： Constantine Baltas ,  Amr Ali

IPC分类号： F02K3/00 ,  F02K3/075 ,  F02K1/08 ,  F02K1/38 ,  F03G7/06 ,  B64C9/38 ,  F02K1/12 ,  F02K3/04 ,  F02K3/06

CPC分类号： F01D17/14 ,  B64C9/38 ,  F01D5/02 ,  F01D9/02 ,  F01D17/105 ,  F01D25/24 ,  F02C3/04 ,  F02K1/08 ,  F02K1/085 ,  F02K1/12 ,  F02K1/1207 ,  F02K1/386 ,  F02K3/00 ,  F02K3/04 ,  F02K3/06 ,  F02K3/075 ,  F03G7/065 ,  F05D2220/36 ,  F05D2240/128 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2260/606 ,  F05D2300/174 ,  F05D2300/177 ,  F05D2300/505

摘要： A gas turbine engine (10) includes a fan (14), a nacelle (28) arranged about the fan, and an engine core at least partially within the nacelle. A fan bypass passage (30) downstream of the fan between the nacelle and the gas turbine engine conveys a bypass airflow (1) from the fan. A nozzle (40) associated with the fan bypass passage is operative to control the bypass airflow. The nozzle includes a shape memory material having a first solid state phase that corresponds to a first nozzle position and a second solid state phase that corresponds to a second nozzle position.

摘要翻译： 燃气涡轮发动机（10）包括风扇（14），围绕风扇布置的机舱（28）和至少部分地在机舱内的发动机核心。 在机舱和燃气涡轮发动机之间的风扇下游的风扇旁路通道（30）从风扇传送旁路气流（1）。 与风扇旁路通道相关联的喷嘴（40）可操作以控制旁路气流。 喷嘴包括具有对应于第一喷嘴位置的第一固态相和对应于第二喷嘴位置的第二固态相的形状记忆材料。

公开(公告)号：US09181899B2

公开(公告)日：2015-11-10

申请号：US12198959

申请日：2008-08-27

申请人： Mustafa Dindar ,  Scott Andrew Burton ,  Keith Edward James Blodgett ,  Richard David Cedar

发明人： Mustafa Dindar ,  Scott Andrew Burton ,  Keith Edward James Blodgett ,  Richard David Cedar

IPC分类号： F02K3/02 ,  F02K3/06 ,  B64D33/04 ,  F02K1/08 ,  F02K1/52 ,  F02K3/04 ,  F02K9/86

CPC分类号： F02K3/06 ,  B64D33/04 ,  F02K1/08 ,  F02K1/52 ,  F02K3/02 ,  F02K3/04 ,  F02K9/86 ,  F05D2250/14 ,  F05D2250/231

摘要： A turbine exhaust nozzle includes an inner shell disposed coaxially inside an outer shell to define a flow duct terminating in an outlet at a trailing edge of the outer shell. The inner shell is non-axisymmetric and varies in axial slope angle circumferentially around the duct.

摘要翻译： 涡轮机排气喷嘴包括同轴地设置在外壳内的内壳，以限定终止在外壳的后缘处的出口中的流动管道。 内壳是非轴对称的，并且围绕管道周向地以轴向倾斜角度变化。

公开(公告)号：US08943794B2

公开(公告)日：2015-02-03

申请号：US12681219

申请日：2008-07-04

申请人： Pierre Moradell-Casellas ,  Pierre Andre Marcel Baudu ,  Guy Bernard Vauchel

发明人： Pierre Moradell-Casellas ,  Pierre Andre Marcel Baudu ,  Guy Bernard Vauchel

IPC分类号： F02K1/72 ,  F16H25/20 ,  F02K1/76 ,  F02K1/08 ,  F16H25/22

CPC分类号： F16H25/20 ,  F02K1/08 ,  F02K1/72 ,  F02K1/763 ,  F05D2220/36 ,  F05D2250/41 ,  F16H25/2056 ,  F16H25/2204 ,  Y02T50/671 ,  Y10T74/18568 ,  Y10T74/18672

摘要： The invention relates to a linear telescopic actuator for moving a first (10b) and a second (10a) element relative to a stationary element (102). Said actuator comprises a base (101) that is to be connected to the stationary element (102) and is used as a cavity for a first rotationally locked rod (106) which can be translated by a drive shaft (104) that is to be connected to rotational driving means (107). One end (108) of said first rod is to be connected to the first element that is to be moved. The actuator is characterized in that the first rod (106) supports a second rod (117) which is aligned therewith and one end (118) of which is to be connected to the second element that is to be moved. Said second rod (117) can be rotationally locked and can be translated by a second drive shaft (112, 115) which extends through the base and is connected to rotational driving means (113, 111).

摘要翻译： 本发明涉及一种用于相对于固定元件（102）移动第一（10b）和第二（10a）元件的线性伸缩致动器。 所述致动器包括要连接到固定元件（102）的基座（101），并且用作用于第一旋转锁定杆（106）的空腔，所述第一旋转锁定杆（106）能够被驱动轴（104）平移 连接到旋转驱动装置（107）。 所述第一杆的一端（108）将连接到待移动的第一元件。 致动器的特征在于，第一杆（106）支撑与其对准的第二杆（117），并且其一端（118）将被连接到待移动的第二元件。 所述第二杆（117）可被旋转地锁定并且可以通过延伸穿过基座并连接到旋转驱动装置（113,111）的第二驱动轴（112,115）平移。

公开(公告)号：US20140060005A1

公开(公告)日：2014-03-06

申请号：US13756140

申请日：2013-01-31

申请人： Richard H. Lugg

发明人： Richard H. Lugg

IPC分类号： F02C3/04

CPC分类号： F02C3/04 ,  F01D15/10 ,  F02C7/32 ,  F02K1/08 ,  F02K3/025 ,  F02K3/06 ,  F02K5/00 ,  F05D2270/172 ,  F05D2300/507 ,  H05H1/50

摘要： Supersonic Magnetic Advanced Generation Jet Electric Turbine (S-MAGJET) described herein, and a subsonic derivative, MAGJET, integrate a gas power turbine, superconducting electric power and propulsion generation, and magnetic power flux field systems along with an ion plasma annular injection combustor which utilizes alternative petroleum-based fuel and combustion cycles to create a hybrid turbine turbomachine for aerospace propulsion. The propulsion unit is able to achieve a dramatic increase in horsepower, combustion and propulsion efficiency, and weight reduction. In addition, the turbomachinery structures may be disposed within an exoskeleton architecture that achieves an increase in thrust to weight ratio with a concomitant increase in fuel efficiency and power generation. The engine continuously adjusts the temperature, pressure and mass airflow requirements using an electromagnetic power management system architecture. Engine performance may be controlled across the entire desired flight envelope, whether subsonic, transonic or supersonic flight conditions.

摘要翻译： 本文所述的超音速磁性高级发电喷射式电动涡轮机（S-MAGJET）以及亚音速导出装置MAGJET将气体动力涡轮机，超导电力和推进发电以及磁力通量场系统与离子等离子体环形喷射燃烧器 利用替代的石油基燃料和燃烧循环来创建用于航空航天推进的混合涡轮机涡轮机。 推进装置能够大幅提高马力，燃烧和推进效率，减轻重量。 此外，涡轮机械结构可以设置在外骨骼结构内，其实现了推力与重量比的增加，伴随着燃料效率和发电的增加。 引擎使用电磁功率管理系统架构连续调节温度，压力和质量气流要求。 发动机性能可以跨越整个所需的飞行范围进行控制，无论是亚音速，跨音速还是超音速飞行条件。

公开(公告)号：US20120279198A1

公开(公告)日：2012-11-08

申请号：US13198958

申请日：2011-08-05

申请人： Kaare Erickson ,  Randall E. Yount

发明人： Kaare Erickson ,  Randall E. Yount

IPC分类号： F02K3/075 ,  F02C9/18

CPC分类号： F02K3/075 ,  F02K1/08 ,  F05D2270/62 ,  F05D2270/66

摘要： One embodiment of the present invention is a gas turbine engine with a bypass mixer. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and bypass mixers. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

摘要翻译： 本发明的一个实施例是具有旁路混合器的燃气涡轮发动机。 其他实施例包括用于燃气涡轮发动机和旁路混合器的装置，系统，装置，硬件，方法和组合。 本申请的其它实施例，形式，特征，方面，益处和优点将从本文提供的描述和附图中变得显而易见。

公开(公告)号：US20120192543A1

公开(公告)日：2012-08-02

申请号：US13362826

申请日：2012-01-31

申请人： Sébastien Jean-Paul Aeberli ,  Guillaume Bodard ,  Alexandre Alfred Gaston Vuillemin

发明人： Sébastien Jean-Paul Aeberli ,  Guillaume Bodard ,  Alexandre Alfred Gaston Vuillemin

IPC分类号： F02K3/02

CPC分类号： F02C7/24 ,  F02K1/08 ,  F02K1/09 ,  F05D2260/96 ,  Y02T50/671

摘要： The invention relates to an exhaust nozzle for a bypass airplane turbojet comprising an annular central body, an annular primary cover surrounding the central body to define a hot stream flow channel, and an annular secondary cover surrounding the primary cover to define a cold stream flow channel, each of the central body and the secondary cover comprising a stationary portion and a movable portion connected to a downstream end of the stationary portion, the movable portion of the central body being suitable for being retracted longitudinally upstream relative to the stationary portion, and the movable portion of the secondary cover being suitable for being deployed longitudinally downstream relative to the stationary portion.

摘要翻译： 本发明涉及一种用于旁路飞机涡轮喷气发动机的排气喷嘴，其包括环形中心体，围绕中心体以限定热流流动通道的环形主盖，以及围绕主盖的环形次盖，以限定冷流流动通道 中央主体和次盖的每一个包括固定部分和连接到固定部分的下游端的可移动部分，中心体的可移动部分适于相对于固定部分纵向上游地缩回，并且 辅助盖的可移动部分适于相对于静止部分纵向下游地展开。