公开(公告)号：US20180003128A1

公开(公告)日：2018-01-04

申请号：US15686052

申请日：2017-08-24

申请人： Jetoptera, Inc.

发明人： Andrei Evulet

IPC分类号： F02K1/30 ,  F02K1/38

CPC分类号： F02K1/30 ,  F02B27/06 ,  F02B37/00 ,  F02B39/04 ,  F02C3/04 ,  F02C7/143 ,  F02K1/36 ,  F02K1/38 ,  F05D2260/4023 ,  F05D2260/601 ,  F05D2270/173 ,  F05D2270/18 ,  F05D2300/6033 ,  F23R3/22 ,  Y02T10/144 ,  Y02T10/146 ,  Y02T50/672

摘要： A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.

公开(公告)号：US20170204807A1

公开(公告)日：2017-07-20

申请号：US14995661

申请日：2016-01-14

申请人： General Electric Company

发明人： Durga Srinivas Chillapalli ,  Hemanth Gudibande Sathyakumar Kumar ,  Bhaskar Nanda Mondal ,  Kishanjit Pal ,  Sushilkumar Gulabrao Shevakari ,  Thomas Ory Moniz

IPC分类号： F02K1/06 ,  F02K3/06

CPC分类号： F02K1/06 ,  F02C7/18 ,  F02K1/38 ,  F02K3/06 ,  F05D2220/36 ,  F05D2260/205 ,  F05D2260/608 ,  Y02T50/675

摘要： A variable core cowl vent nozzle system is described herein, the system including a core casing at least partially surrounding a core engine of a gas turbine engine, and a core cowl extending aftward from the core casing. The core cowl defines a core cowl vent area between the core cowl and a primary nozzle. At least one of the core cowl and the primary nozzle is movable to vary the core cowl vent area. A method for varying the core cowl vent area by moving one or more of the core cowl and the primary nozzle is also described herein.

公开(公告)号：US09617954B2

公开(公告)日：2017-04-11

申请号：US14346602

申请日：2012-09-24

申请人： SNECMA

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

IPC分类号： F02K1/28 ,  F02K1/34 ,  F02K1/30 ,  F02K3/02 ,  F02K3/075 ,  F02K1/46 ,  F02K1/38

CPC分类号： F02K1/34 ,  F02K1/28 ,  F02K1/30 ,  F02K1/38 ,  F02K1/386 ,  F02K1/46 ,  F02K3/025 ,  F02K3/075 ,  Y02T50/671

摘要： The invention relates to a primary cowl for a turbofan comprising a primary body generating a primary stream to be ejected through a primary nozzle, and a secondary body generating a secondary stream to be ejected through a secondary nozzle, the primary cowl being shaped so as to be positioned downstream from the primary body and to define, on the inside of the turbofan, the path followed by the primary stream downstream from the primary nozzle and, on the outside, the path followed by the secondary stream downstream from the secondary nozzle. The primary cowl comprises a coupling to a system for supplying a pressurized gas and at least one perforation for injecting the pressurized gas, through the perforation, into the secondary stream. The primary cowl preferably comprises a ring which has perforations and which is rotated about the axis of rotation of the turbofan.

公开(公告)号：US20170088275A1

公开(公告)日：2017-03-30

申请号：US14870401

申请日：2015-09-30

申请人： The Boeing Company

发明人： Robert H. Willie ,  Paul R. Tretow ,  David F. Cerra

IPC分类号： B64D27/12 ,  F02K1/82 ,  B64D29/00 ,  F02K3/04

CPC分类号： B64D27/12 ,  B64D29/00 ,  F01D25/26 ,  F02C7/18 ,  F02K1/38 ,  F02K1/82 ,  F02K1/822 ,  F02K3/04 ,  F05D2220/36 ,  F05D2240/128 ,  F05D2260/605 ,  F05D2260/608 ,  Y02T50/671 ,  Y02T50/675

摘要： A turbine engine nozzle can include a primary outer wall extending from an engine core area to an annular wall terminus that surrounds an engine tail cone, to form a core nozzle. The turbine engine nozzle also includes a single engine core cowl extending from the engine core area to an annular cowl terminus to form a core compartment vent nozzle. The core compartment vent nozzle exhausts air from a core compartment in a trailing edge between the single engine core cowl and the primary outer wall.

公开(公告)号：US20160003187A1

公开(公告)日：2016-01-07

申请号：US14768714

申请日：2014-02-14

申请人： UNITED TECHNOLOGIES CORPORATION

发明人： Gary D. ROBERGE

IPC分类号： F02K1/12 ,  F02K3/02

CPC分类号： F02K1/1207 ,  F02K1/008 ,  F02K1/1292 ,  F02K1/38 ,  F02K3/02 ,  F02K3/075 ,  F02K3/077 ,  F05D2240/128 ,  F05D2250/36

摘要： A turbofan engine that includes a first flowpath, a second flowpath, a third flowpath, and a third flowpath exhaust nozzle is provided. The first flowpath is radially inboard of the second flowpath at a location upstream of a core section of the turbofan engine. The third flowpath is radially outboard of the second flowpath at the location upstream of the core section. The third flowpath exhaust nozzle defines a plurality of third flowpath exhaust exit ports through which gas traveling along the third flowpath may be discharged. An area or a geometry of each of the plurality of third flowpath exhaust exit ports is independently and selectively adjustable. A method for operating the turbofan engine includes independently and selectively adjusting an area or a geometry of at least one of the plurality of third flowpath exhaust exit ports to achieve a desired engine operation.

摘要翻译： 提供了包括第一流路，第二流路，第三流路和第三流路排气喷嘴的涡轮风扇发动机。 第一流路在涡轮风扇发动机的核心部分的上游的位置处径向地位于第二流动路径的内侧。 第三流路径位于第二流路径的外侧，位于核心部分的上游位置处。 第三流路排气喷嘴限定了多个第三流路排气出口，通过该排出口可以排出沿第三流路行进的气体。 多个第三流路排出口中的每一个的区域或几何形状是可独立且有选择地调节的。 用于操作涡扇发动机的方法包括独立地和选择性地调节多个第三流路排气出口中的至少一个的面积或几何形状，以实现期望的发动机操作。

公开(公告)号：US20150211441A1

公开(公告)日：2015-07-30

申请号：US14553284

申请日：2014-11-25

申请人： United Technologies Corporation

发明人： Francis R. Moon ,  Daniel B. Kupratis

IPC分类号： F02K1/46

CPC分类号： F02K1/12 ,  F02K1/06 ,  F02K1/36 ,  F02K1/38 ,  F02K1/386 ,  F02K1/46 ,  F02K3/06 ,  F02K3/077 ,  F05D2220/323

摘要： A gas turbine engine includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is included inboard of the outer case structure. An inner case structure is included inboard of the intermediate case structure. A variable area exhaust mixer is included, which is movable between a closed position adjacent to the intermediate case structure and an open position adjacent to the inner case structure.

摘要翻译： 燃气涡轮发动机包括围绕中心纵向发动机轴线的外壳结构。 中间壳体结构包括在外壳结构内。 内壳结构包括在中间壳结构的内侧。 包括可变面积排气混合器，其可在与中间壳体结构相邻的关闭位置和与内壳结构相邻的打开位置之间移动。

公开(公告)号：US20140245715A1

公开(公告)日：2014-09-04

申请号：US14346602

申请日：2012-09-24

申请人： SNECMA

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

IPC分类号： F02K1/34 ,  F02K3/02 ,  F02K1/38

CPC分类号： F02K1/34 ,  F02K1/28 ,  F02K1/30 ,  F02K1/38 ,  F02K1/386 ,  F02K1/46 ,  F02K3/025 ,  F02K3/075 ,  Y02T50/671

摘要： The invention relates to a primary cowl for a turbofan comprising a primary body generating a primary stream to be ejected through a primary nozzle, and a secondary body generating a secondary stream to be ejected through a secondary nozzle, the primary cowl being shaped so as to be positioned downstream from the primary body and to define, on the inside of the turbofan, the path followed by the primary stream downstream from the primary nozzle and, on the outside, the path followed by the secondary stream downstream from the secondary nozzle. The primary cowl comprises a coupling to a system for supplying a pressurised gas and at least one perforation for injecting the pressurised gas, through the perforation, into the secondary stream. The primary cowl preferably comprises a ring which has perforations and which is rotated about the axis of rotation of the turbofan.

摘要翻译： 本发明涉及一种用于涡轮风扇的主罩，其包括主体，其产生要通过主喷嘴喷射的主流，以及产生要通过次喷嘴喷射的次流的次体，该主罩被成形为 位于主体的下游并且在涡轮风扇的内侧上限定了从主喷嘴下游的初级流的路径，并且在外部将辅助流的下游路径跟随在二次喷嘴的下游。 主罩包括与用于供应加压气体的系统的联接件和用于将加压气体通过穿孔注入次流中的至少一个穿孔。 主罩盖优选地包括具有穿孔并且围绕涡轮风扇的旋转轴线旋转的环。

公开(公告)号：US20100018213A1

公开(公告)日：2010-01-28

申请号：US12440785

申请日：2006-10-12

申请人： Edward F. Migliaro, JR.

发明人： Edward F. Migliaro, JR.

IPC分类号： F02K1/06

CPC分类号： F02K1/06 ,  F02K1/38 ,  F02K1/48 ,  F02K3/06 ,  F05D2250/411

摘要： A turbofan engine includes a fan variable area nozzle having a rotationally overlapped nozzle assembly having a first tab section and a second tab section rotationally mounted relative to the first tab section. The rotationally overlapped nozzle assembly changes the physical area and geometry of the bypass flow path during particular flight conditions.

摘要翻译： 涡轮风扇发动机包括风扇可变区域喷嘴，其具有旋转重叠的喷嘴组件，其具有第一突出部分和相对于第一突出部分旋转地安装的第二突出部分。 旋转重叠的喷嘴组件在特定的飞行条件期间改变旁路流动路径的物理面积和几何形状。

公开(公告)号：US20090235639A1

公开(公告)日：2009-09-24

申请号：US12200265

申请日：2008-08-28

申请人： Tatsuya KIMURA ,  Yoshihiro KAWAMATA ,  Kenichi NIU

发明人： Tatsuya KIMURA ,  Yoshihiro KAWAMATA ,  Kenichi NIU

IPC分类号： F02K9/08

CPC分类号： F02K1/38 ,  F02K9/48 ,  F02K9/58 ,  F02K9/82 ,  F02K9/972 ,  F05D2250/713

摘要： A rocket nozzle includes a dual-bell nozzle and a gas introducing section configured to introduce gas into space surrounded by the dual-bell nozzle. Combustion gas flows in the space. The dual-bell nozzle includes a first stage nozzle bell-shaped and surrounding an upstream portion of the space, and a second stage nozzle bell-shaped and surrounding a downstream portion of the space. The dual-bell nozzle has an inflection point between the first stage nozzle and the second stage nozzle. The gas introducing section includes a gas inlet provided to an inner wall surface of the first stage nozzle. The gas is introduced into the space from the gas inlet.

摘要翻译： 火箭喷嘴包括双钟形喷嘴和构造成将气体引入由双钟形喷嘴包围的空间中的气体导入部。 燃烧气体在空间中流动。 双钟形喷嘴包括钟形状的第一级喷嘴并且围绕该空间的上游部分，以及第二级喷嘴钟形并围绕该空间的下游部分。 双钟形喷嘴在第一级喷嘴和第二级喷嘴之间具有拐点。 气体导入部包括设置在第一级喷嘴的内壁面的气体入口。 气体从气体入口引入空间。

公开(公告)号：US20070062199A1

公开(公告)日：2007-03-22

申请号：US11232508

申请日：2005-09-22

申请人： Curtis Cowan ,  Debora Kehret

发明人： Curtis Cowan ,  Debora Kehret

IPC分类号： B63H11/10

CPC分类号： F02K1/1223 ,  F02K1/1292 ,  F02K1/38 ,  Y02T50/671

摘要： A turbine engine nozzle assembly has an upstream flap assembly having a main flap and a liner, a cooling passageway formed between the main flap and liner. A downstream flap is pivotally coupled to the upstream flap assembly for relative rotation about a hinge axis. The liner has a trailing end spaced upstream from a trailing end of the main flap by at least 40% of a length of the main flap.

摘要翻译： 涡轮发动机喷嘴组件具有具有主瓣和衬垫的上游翼片组件，形成在主翼片和衬垫之间的冷却通道。 下游翼片枢转地联接到上游翼片组件，以围绕铰链轴线相对旋转。 衬里具有与主瓣的后端上游相距主瓣的至少40％的后端。