公开(公告)号：US20240151194A1

公开(公告)日：2024-05-09

申请号：US18053294

申请日：2022-11-07

申请人： The Aerospace Corporation

发明人： Jerome K. FULLER ,  Denise Galindo BURRELL ,  Edward V. WAGNER ,  Andrew C. CORTOPASSI ,  Jeffrey Arthur LANG ,  Robert B. PAN

IPC分类号： F02K1/82

CPC分类号： F02K1/82

摘要： An ablative thruster includes a nozzle configured to control a flow of thrust from the satellite. The ablative thruster also includes an ablative surface inside of the nozzle, configured to deflect the thrust at a predefined angle. The ablative surface is configured to ablate-away, leaving un-deflected thrust for a majority of the burn.

公开(公告)号：US20180058264A1

公开(公告)日：2018-03-01

申请号：US15554256

申请日：2016-02-25

申请人： Sikorsky Aircraft Corporation

发明人： Joseph Lawrence Simonetti ,  Donald William Lamb, Jr. ,  Shyam Neerarambam

IPC分类号： F01D25/30 ,  F02K1/82

CPC分类号： F01D25/30 ,  F02K1/386 ,  F02K1/82 ,  F05D2220/329 ,  F05D2240/125

摘要： A gas turbine exhaust assembly includes an exhaust flow path configured to receive an exhaust flow from a gas turbine engine, the exhaust flow path defined by an inner hub and a radially outer wall. The gas turbine exhaust assembly also includes a plurality of vanes circumferentially spaced from each other and operatively coupled to the radially outer wall of the exhaust flow path, each of the plurality of vanes extending only partially toward the inner hub and terminating at an inner end of the vanes, the inner end defining an open portion.

公开(公告)号：US09890953B2

公开(公告)日：2018-02-13

申请号：US14588471

申请日：2015-01-02

申请人： Jose E. Ruberte Sanchez ,  Timothy J. McAlice ,  Kevin L. Rugg

发明人： Jose E. Ruberte Sanchez ,  Timothy J. McAlice ,  Kevin L. Rugg

IPC分类号： F23R3/00 ,  F23M5/04 ,  F02K1/82 ,  F23R3/60

CPC分类号： F23M5/04 ,  F02K1/82 ,  F23R3/002 ,  F23R3/007 ,  F23R3/60 ,  F23R2900/00017 ,  Y10T29/49231

摘要： A combined liner and panel for use in a gas turbine engine comprise a ceramic matrix composite panel having a plurality of extending members extending away from a face of ceramic matrix composite panel which will face hot products of combustion. A liner includes a plurality of spring members that apply a bias force biasing the extending members. The spring members bias the extending members on the panel in a direction away from the face of the panel which will face the hot products of combustion. A gas turbine engine, and a method of attaching a ceramic matrix composite panel to a liner are also disclosed.

公开(公告)号：US09758254B2

公开(公告)日：2017-09-12

申请号：US14537957

申请日：2014-11-11

申请人： The Boeing Company

发明人： Matthew D. Moore ,  Kelly L. Boren ,  Hao Shen ,  Chester P. Nelson

IPC分类号： B64D33/00 ,  F02K1/34 ,  F02K1/46 ,  F02K1/28 ,  F02K1/48 ,  F02K1/82 ,  F02K1/38 ,  F02K1/36

CPC分类号： B64D33/06 ,  F02K1/28 ,  F02K1/34 ,  F02K1/36 ,  F02K1/38 ,  F02K1/386 ,  F02K1/46 ,  F02K1/48 ,  F02K1/82 ,  F02K1/822 ,  F02K1/827

摘要： A jet noise suppressor including a nozzle having a front end and an opposed rear end, spokes extending radially inward from the nozzle, the spokes defining vents, and a center-body connected to the spokes and in fluid communication with the vents, the center-body being positioned centrally within the nozzle and including a closed front end and an open rear end, wherein the front end of the nozzle entrains a first ambient airflow passing through the nozzle and exiting the rear end of the nozzle proximate a periphery of the nozzle, and wherein the vents entrain a second ambient airflow passing through the center-body and exiting the rear end of the nozzle proximate a center of the nozzle.

公开(公告)号：US09683516B2

公开(公告)日：2017-06-20

申请号：US14363508

申请日：2012-12-04

申请人： SNECMA

发明人： Matthieu Leyko ,  Jean Bertucchi ,  Mathieu Gaillot

IPC分类号： F02K1/00 ,  F02K1/82 ,  F02K3/06

CPC分类号： F02K1/00 ,  F02K1/82 ,  F02K3/06 ,  F05D2250/71

摘要： A turbine engine convergent-divergent nozzle including an annular central element and an annular cap arranged coaxially around the central element to co-operate with the central element to define an annular flow channel for a gas stream from the engine. Between a throat section and an ejection section of the nozzle, the central element and the cap present respective internal profiles in longitudinal section that are modeled by curves having respective radii of curvature that are identical in absolute value.

公开(公告)号：US20170096963A1

公开(公告)日：2017-04-06

申请号：US15382603

申请日：2016-12-17

申请人： The Boeing Company

发明人： Robert E. Grip ,  John J. Brown

IPC分类号： F02K1/80 ,  B64D29/00 ,  F02K1/82 ,  B64C1/12

CPC分类号： F02K1/80 ,  B64C1/12 ,  B64D27/26 ,  B64D29/00 ,  B64D29/06 ,  F01D25/26 ,  F01D25/30 ,  F02K1/82 ,  F02K1/822 ,  F04D29/441 ,  F05D2220/323 ,  F05D2250/40 ,  F05D2260/50 ,  Y02T50/672 ,  Y10T29/49229 ,  Y10T428/249923

摘要： A sandwich structure includes a first skin and a second skin spaced apart from each other and interconnected by a hinge assembly including a first hinge member and a second hinge member. The first hinge member proximal end is coupled to the first skin. The second hinge member proximal end is coupled to the second skin. The first hinge member distal end is coupled to the second member distal end at a member joint. The hinge assembly: prevents movement of the first skin relative to the second skin in an in-plane longitudinal direction of the first skin, allows movement of the first skin relative to the second skin in an in-plane transverse direction of the first skin, and allows movement of the first skin relative to the second skin in an out-of-plane direction that is normal to the in-plane longitudinal direction and the in-plane transverse direction.

公开(公告)号：US20160376893A1

公开(公告)日：2016-12-29

申请号：US14752186

申请日：2015-06-26

申请人： GENERAL ELECTRIC COMPANY

发明人： Canan Uslu HARDWICKE ,  John McConnell DELVAUX ,  Jason Robert PAROLINI ,  Matthew Troy HAFNER

IPC分类号： F01D5/14 ,  B29C65/02 ,  B29C65/00

CPC分类号： F01D5/14 ,  B23P6/005 ,  B28B1/002 ,  B29C65/002 ,  B29C65/02 ,  B29C73/04 ,  B29L2031/7504 ,  C04B37/005 ,  C04B2235/5252 ,  C04B2235/5268 ,  C04B2235/60 ,  C04B2235/606 ,  C04B2237/083 ,  C04B2237/086 ,  C04B2237/78 ,  C04B2237/84 ,  F01D5/005 ,  F01D5/187 ,  F01D5/282 ,  F01D5/284 ,  F01D5/288 ,  F01D9/02 ,  F01D25/246 ,  F01D25/30 ,  F02K1/82 ,  F02K1/822 ,  F02K1/827 ,  F05D2230/40 ,  F05D2230/60 ,  F05D2230/64 ,  F05D2260/36 ,  F05D2300/224 ,  F05D2300/2261 ,  F05D2300/6012 ,  F05D2300/6033 ,  F05D2300/6034 ,  F05D2300/701 ,  Y02T50/675

摘要： A method for treating a field operated component is disclosed which includes providing the component including a ceramic matrix composite and removing a first portion of the component, forming a first exposed surface on the component. The method further includes providing a second portion including the composite, the second portion having a second exposed surface including a conformation adapted to mate with the first exposed surface. The second portion is positioned in association with the component so as to replace the first portion, and the second portion and the component are joined to form a treated component. Another method is disclosed wherein the component is a turbine component which further includes removing an environmental barrier coating from the component, arranging and conforming the first exposed surface and the second exposed surface to define a joint, and applying an environmental barrier coating to the treated component.

摘要翻译： 公开了一种用于处理场致动部件的方法，其包括提供包括陶瓷基体复合材料的部件并且去除部件的第一部分，从而在部件上形成第一暴露表面。 该方法还包括提供包括复合材料的第二部分，第二部分具有包括适于与第一暴露表面配合的构型的第二暴露表面。 第二部分与部件相关联地定位以便替换第一部分，并且第二部分和部件被连接以形成处理的部件。 公开了另一种方法，其中所述部件是涡轮机部件，其进一步包括从所述部件移除环境阻挡涂层，将所述第一暴露表面和所述第二暴露表面布置和配合以限定接头，以及将环境阻挡涂层施加到所述被处理部件 。

公开(公告)号：US20160290360A1

公开(公告)日：2016-10-06

申请号：US15186641

申请日：2016-06-20

申请人： IHI Corporation ,  IHI AEROSPACE CO., LTD.

发明人： Agamu TANAKA ,  Yuji MORI ,  Takashi HARADA ,  lkuo OKUMURA ,  Kenji ISHIMOTO

IPC分类号： F04D29/52

CPC分类号： F04D29/526 ,  F01D25/243 ,  F02K1/64 ,  F02K1/82 ,  F05D2220/323 ,  F05D2230/21 ,  F05D2230/60 ,  F05D2260/36 ,  F05D2300/121 ,  F05D2300/174 ,  F05D2300/603 ,  Y02T50/672

摘要： A cylindrical case body made of a composite material; a linking ring made of Al, which is fitted and fixed to a rear end portion of the case body and has an annular groove which receives a reverse thrust load from a reverse thrust transmission body; and ring constituent bodies made of Ti alloy, each of which is placed in the rear end portion of the case body and has an arcuate groove which undertakes a reverse thrust load larger than that received by the linking ring, are included. The ring constituent bodies are fitted in notches of the linking ring and are brought into contact with, and are fixed to, outward receiving walls of the linking ring, whereby the ring constituent bodies are positioned relative to the case body in the axis direction and in the radial direction respectively, and the annular groove and the arcuate grooves are allowed to continue to each other. The ring constituent bodies made of Ti alloy, which receive a large reverse thrust load, can be placed with high positioning accuracy. Further, it is possible to allow the ring constituent bodies to undertake the reverse thrust load evenly.

摘要翻译： 由复合材料制成的圆柱形壳体; 由铝制成的连接环，其被安装并固定到壳体的后端部，并且具有从反向推力传递体接收反向推力载荷的环形槽; 并且包括由Ti合金制成的环构成体，其各自被放置在壳体的后端部分中并且具有承受比由连接环接收的反推力负载大的反向推力负载的弓形槽。 环形结构体装配在连接环的凹口中，与连接环的外部接收壁接触并固定，由此环形结构体相对于壳体沿轴向方向定位，并且 径向方向，并且环形槽和弧形槽被允许彼此继续。 可以以高定位精度放置接收大反向推力负载的Ti合金制成的环构成体。 此外，可以使环构成体均匀地承受反推力负荷。

公开(公告)号：US20160251272A1

公开(公告)日：2016-09-01

申请号：US14633347

申请日：2015-02-27

申请人： GENERAL ELECTRIC COMPANY

发明人： Jared Hogg WEAVER ,  Badri Narayan RAMAMURTHI

IPC分类号： C04B41/45 ,  C04B41/87 ,  F01D5/28 ,  B32B18/00 ,  B32B7/02 ,  B32B3/26 ,  C04B35/565 ,  C04B41/50

CPC分类号： C04B41/4531 ,  B32B3/263 ,  B32B7/02 ,  B32B18/00 ,  B32B2603/00 ,  C04B35/14 ,  C04B35/5603 ,  C04B35/563 ,  C04B35/565 ,  C04B35/58092 ,  C04B35/583 ,  C04B35/584 ,  C04B35/62844 ,  C04B35/803 ,  C04B35/806 ,  C04B37/008 ,  C04B41/4584 ,  C04B41/5027 ,  C04B41/5035 ,  C04B41/5058 ,  C04B41/5059 ,  C04B41/5064 ,  C04B41/5066 ,  C04B41/5071 ,  C04B41/87 ,  C04B2235/5244 ,  C04B2235/5252 ,  C04B2235/5256 ,  C04B2235/5268 ,  C04B2235/602 ,  C04B2235/608 ,  C04B2235/614 ,  C04B2235/77 ,  C04B2235/775 ,  C04B2237/38 ,  F01D5/282 ,  F01D5/284 ,  F01D9/023 ,  F01D9/041 ,  F01D11/08 ,  F01D25/162 ,  F01D25/24 ,  F02K1/82 ,  F02K9/97 ,  F05D2240/11 ,  F05D2300/6033

摘要： A preform can be subject to chemical vapor infiltration (CVI) to define a ceramic matrix composite (CMC) structure, a supplemental preform can be added to the CMC structure to define an expanded structure and CVI can be performed using the expanded structure. The adding of a supplemental preform and performing CVI using the expanded structure can be repeated.

摘要翻译： 预成型件可能经受化学气相渗透（CVI）以限定陶瓷基体复合材料（CMC）结构，可以将补充预成型件添加到CMC结构中以限定扩展结构，并且可以使用扩展结构执行CVI。 可以重复使用扩展结构添加补充预成型件并执行CVI。

公开(公告)号：US09388740B2

公开(公告)日：2016-07-12

申请号：US13397436

申请日：2012-02-15

申请人： David W. Kwok ,  James P. Huang ,  Jack W. Mauldin

发明人： David W. Kwok ,  James P. Huang ,  Jack W. Mauldin

IPC分类号： F02C6/18 ,  F02K1/82 ,  F02C6/04 ,  H01L35/30 ,  F01D15/10 ,  F02K1/00 ,  F02K3/06 ,  F02C7/32

CPC分类号： F02C6/18 ,  F01D15/10 ,  F02C6/04 ,  F02C7/32 ,  F02K1/00 ,  F02K1/82 ,  F02K3/06 ,  F05D2220/76 ,  H01L35/30 ,  Y02T50/53

摘要： In one embodiment, a gas turbine engine assembly comprises an engine assembly disposed about a longitudinal axis, a core nozzle positioned adjacent the engine assembly to direct a core flow generated by the engine assembly, a fan nozzle surrounding at least a portion of the core nozzle to direct a fan flow, wherein the core nozzle defines a plenum to receive a portion of the core stream flow from the core nozzle and a thermoelectric generator assembly positioned in the plenum. Other embodiments may be described.

摘要翻译： 在一个实施例中，燃气涡轮发动机组件包括围绕纵向轴线设置的发动机组件，邻近发动机组件定位的芯喷嘴以引导由发动机组件产生的芯流;风扇喷嘴，其围绕芯喷嘴的至少一部分 以引导风扇流动，其中所述芯喷嘴限定一个气室，以容纳来自所述芯喷嘴的芯流流的一部分和位于所述气室中的热电发电机组件。 可以描述其他实施例。