公开(公告)号：US09091175B2

公开(公告)日：2015-07-28

申请号：US13216613

申请日：2011-08-24

申请人： Eric Durocher ,  Maxime Demers

发明人： Eric Durocher ,  Maxime Demers

IPC分类号： F01D5/14 ,  F01D5/20

CPC分类号： F01D5/147 ,  F01D5/20 ,  Y10T29/49339

摘要： A stiffener rib for a non-cooled, hollow core airfoil of a turbine blade is described. The stiffener rib is constituted by an elongated solid metal piece dimensioned for securement in a hollow region of a core portion of the airfoil. The stiffener rib is shaped and oriented upwards from a leading edge of the airfoil at a predetermined calculated angle to minimize mode 2 deformation of the blade at a trailing edge thereof while improving the rigidity of the turbine blade.

摘要翻译： 描述了用于涡轮叶片的未冷却的空心芯翼型的加强肋。 加强肋由细长的固体金属片构成，其尺寸适于固定在翼型的芯部的中空区域中。 加强肋成形并且以预定的计算角度从翼型的前缘向上定向，以最小化叶片在其后缘处的模式2变形，同时提高涡轮叶片的刚度。

公开(公告)号：US20130251508A1

公开(公告)日：2013-09-26

申请号：US13425816

申请日：2012-03-21

申请人： Marc Tardif ,  Sri Sreekanth ,  Eric Durocher

发明人： Marc Tardif ,  Sri Sreekanth ,  Eric Durocher

IPC分类号： F01D9/02 ,  B23P15/00

CPC分类号： F01D5/187 ,  F01D9/02 ,  F05D2240/81 ,  F05D2260/96 ,  Y10T29/4932

摘要： A turbine vane of a gas turbine engine is provided with a hollow core in the leading edge of the outer platform thereof. The core is interconnected with the leading edge core of the airfoil whereby to create a cooling air stream having a dual purpose and cooling both the leading edge of the outer platform and of the airfoil and thereby reducing cooling air consumption. The cooling air enters the core of the outer platform through an inlet port and exits through cooling holes provided in the leading edge of the airfoil.

摘要翻译： 燃气涡轮发动机的涡轮叶片在其外平台的前缘中设置有中空芯。 芯部与翼型件的前缘芯相互连接，从而形成具有双重目的的冷却空气流，同时冷却外部平台和翼型的前缘，从而减少冷却空气的消耗。 冷却空气通过入口进入外平台的核心，并通过设在翼型前缘的冷却孔排出。

公开(公告)号：US08500392B2

公开(公告)日：2013-08-06

申请号：US12572104

申请日：2009-10-01

申请人： Eric Durocher ,  John Pietrobon

发明人： Eric Durocher ,  John Pietrobon

IPC分类号： F01D9/06

CPC分类号： F01D11/00 ,  F01D9/06 ,  F01D25/12

摘要： A seal housing is provided to substantially cover at least one duct wall of vane array duct of a gas turbine engine, and one example arrangement is employed in a mid-turbine frame. The arrangement provides improved sealing of the vane array duct through the provision of a plurality of cavities extending along the duct wall. The arrangement may also include insulation tubes to assist in sealing around load transfer spokes passing through the vane array.

摘要翻译： 设置密封壳体以基本上覆盖燃气涡轮发动机的叶片阵列管道的至少一个管道壁，并且在中涡轮机框架中采用一个示例性布置。 该装置通过设置沿管道壁延伸的多个空腔来提供叶片排放管道的改进的密封。 该布置还可以包括绝缘管，以帮助密封穿过叶片阵列的载荷传递轮辐。

公开(公告)号：US20130111906A1

公开(公告)日：2013-05-09

申请号：US13292289

申请日：2011-11-09

申请人： RICHARD BOUCHARD ,  John Pietrobon ,  Eric Durocher

发明人： RICHARD BOUCHARD ,  John Pietrobon ,  Eric Durocher

IPC分类号： F01N13/00

CPC分类号： F02C7/24 ,  F02K1/04 ,  F02K1/78 ,  F02K1/80 ,  F02K1/827

摘要： A turbine exhaust case for a turbofan engine comprises a plurality of arcuate acoustic panels assembled into a circumferentially extending inner shroud with circumferential gaps between adjacent acoustic panels. An outer shroud extends circumferentially about the inner shroud. The inner shroud and the outer shroud define an annular gaspath therebetween. A plurality of circumferentially spaced-apart exhaust struts extends radially across the annular gaspath and structurally connects the individual acoustic panels forming the inner shroud to the outer shroud.

摘要翻译： 用于涡轮风扇发动机的涡轮机排气箱包括组装成周向延伸的内护罩的多个弓形声波面板，在相邻的声学面板之间具有圆周间隙。 外护罩围绕内护罩周向延伸。 内护罩和外护罩在其间限定了环形气路。 多个周向间隔开的排气支柱径向延伸穿过环形气体路径，并将构成内护罩的各个隔音板结构连接到外护罩上。

公开(公告)号：US20120110849A1

公开(公告)日：2012-05-10

申请号：US13351634

申请日：2012-01-17

申请人： Eric Durocher ,  Anca Mateescu

发明人： Eric Durocher ,  Anca Mateescu

IPC分类号： B23P15/02

CPC分类号： F01D25/285 ,  F01D9/04 ,  F05D2230/60 ,  F05D2230/68 ,  Y10T29/49245 ,  Y10T29/49321 ,  Y10T29/49323 ,  Y10T29/53613 ,  Y10T29/53635

摘要： A method for assembling a vane ring with a vane support of a vane assembly in a gas turbine engine is described, and includes flexing each of the radial loading elements into the resiliently flexed state simultaneously by sliding the radial loading elements against corresponding lead-in tapers. This can be achieved, for example, using a guide tool which includes a plurality of segments bearing the lead-in tapers and which is previously assembled to the vane support.

摘要翻译： 描述了一种在燃气涡轮发动机中组装具有叶片组件的叶片支撑件的叶片环的方法，并且包括通过相对于相应的引入锥形部分滑动径向加载元件来将每个径向加载元件同时弯曲成弹性弯曲状态 。 这可以通过例如使用引导工具来实现，所述引导工具包括多个带有引入锥形部分并且预先组装到叶片支撑件的部分。

公开(公告)号：US08166767B2

公开(公告)日：2012-05-01

申请号：US12905663

申请日：2010-10-15

申请人： Nicolas Grivas ,  Bhawan B. Patel ,  Oleg Morenko ,  Eric Durocher

发明人： Nicolas Grivas ,  Bhawan B. Patel ,  Oleg Morenko ,  Eric Durocher

IPC分类号： F02C7/20 ,  F01D25/26

CPC分类号： F01D9/023 ,  F01D9/042 ,  F01D11/005 ,  F05D2240/80 ,  F05D2250/41 ,  F05D2260/94 ,  F05D2260/941 ,  F23R2900/00005 ,  Y02T50/675

摘要： An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound.

摘要翻译： 用于燃气涡轮发动机的组件包括燃烧器和设置在其下游的叶片组件。 叶片组件的外平台的一部分限定了与燃烧器的轴向滑动接头连接，并且包括位于与燃烧器相对的外周表面中的多个凹陷。 凹陷被布置在围绕外平台的圆周的期望的较高热增长的区域中，使得整个外平台的热生长在其周向基本上均匀。

公开(公告)号：US20120032987A1

公开(公告)日：2012-02-09

申请号：US12871481

申请日：2010-08-30

申请人： Eric Durocher

发明人： Eric Durocher

IPC分类号： G09G5/38

CPC分类号： G06T11/206 ,  G06T11/00 ,  G06T11/20

摘要： A method, system and computer program product for distinguishing superimposed links to a node in a drawing area. Links connected to a side of a node involved in an editing interaction are identified. The order of the identified links to be connected to the side of the node is determined by sorting the identified links based on the coordinates of the links' bend point and/or opposite end point. The connection points of these identified links are repositioned based on this determined order. By only repositioning the connection points to the node involved in the editing interaction instead of rerouting all of the links in the diagram area, the processing time is improved. Furthermore, by repositioning the connection points that were superimposed so that they are spaced apart based on the coordinates of the links' bend point and/or opposite end point, it is easier to distinguish between the different links.

摘要翻译： 一种方法，系统和计算机程序产品，用于将叠加的链接区分到绘图区域中的节点。 识别连接到参与编辑交互的节点的一侧的链接。 通过基于链接的弯曲点和/或相对端点的坐标对所识别的链接进行排序来确定要连接到节点侧面的所识别的链接的顺序。 这些确定的链接的连接点根据这个确定的顺序重新定位。 通过将连接点重新定位到编辑交互中涉及的节点而不是重新路由图区域中的所有链路，处理时间得到改善。 此外，通过基于链接的弯曲点和/或相对端点的坐标重新定位叠加的连接点使得它们间隔开，更容易区分不同的链接。

公开(公告)号：US08099962B2

公开(公告)日：2012-01-24

申请号：US12325009

申请日：2008-11-28

申请人： Eric Durocher ,  John Pietrobon ,  Lam Nguyen

发明人： Eric Durocher ,  John Pietrobon ,  Lam Nguyen

IPC分类号： F02C7/20 ,  F01D25/16

CPC分类号： F01D9/065 ,  F01D25/162 ,  F01D25/243 ,  F01D25/28 ,  F05B2260/301 ,  F05D2230/60 ,  F05D2240/11 ,  F05D2240/55 ,  F05D2260/94 ,  Y10T29/4932

摘要： A gas turbine engine has a casing component, such as a mid turbine frame system, which includes an outer case surrounding a spoke or strut casing. Load transfer spokes of the spoke casing are detachably connected to the outer case and radially extend between the outer case and an inner case of the spoke casing. A bearing housing is supported by the inner case of the spoke casing. An arrangement for radially centring the bearing within the outer case is provided, the arrangement including at least three radial locators mounted to the outer case.

摘要翻译： 燃气涡轮发动机具有诸如中间涡轮机框架系统的壳体部件，其包括围绕辐条或支柱壳体的外壳。 轮辐壳体的负载传送轮辐可拆卸地连接到外壳，并且在外壳和轮辐壳体的内壳之间径向延伸。 轴承壳体由轮辐壳体的内壳体支撑。 提供了用于使轴承在外壳内径向对中的布置，该装置包括安装到外壳的至少三个径向定位器。

公开(公告)号：US08096746B2

公开(公告)日：2012-01-17

申请号：US11955867

申请日：2007-12-13

申请人： Eric Durocher ,  Yves Caron

发明人： Eric Durocher ,  Yves Caron

IPC分类号： F01D9/04 ,  F01D25/04

CPC分类号： F01D9/042 ,  F05D2260/38

摘要： A vane assembly for a gas turbine engine comprising a number of radial loading elements disposed between lugs of the vane ring and the vane support, such as to generate a radial load force against the vane ring. The radial load force prevents unwanted relative movement between the vane ring and the vane support during operation of the gas turbine engine.

摘要翻译： 一种用于燃气涡轮发动机的叶片组件，包括设置在叶片环的叶片和叶片支撑件之间的多个径向加载元件，以产生抵靠叶片环的径向载荷力。 径向负载力防止在燃气涡轮发动机运行期间叶片环和叶片支撑件之间的不必要的相对运动。

公开(公告)号：US20110085895A1

公开(公告)日：2011-04-14

申请号：US12576261

申请日：2009-10-09

申请人： Eric DUROCHER ,  John WATSON

发明人： Eric DUROCHER ,  John WATSON

IPC分类号： F01D5/08 ,  B23P15/26

CPC分类号： F16L59/143 ,  F01D9/065 ,  F01M11/02

摘要： A gas turbine engine has an oil tube for delivering oil through a high temperature zone of the engine to an engine component for cooling and lubrication. An insulation tube surrounds the oil tube and extends in a substantial length of the oil tube. The opposed ends of the insulation tube are integrally and sealingly connected to respective end portions of the oil tube to form a dead air annulus between the oil tube and the insulation tube.

摘要翻译： 燃气涡轮发动机具有用于将油通过发动机的高温区域输送到用于冷却和润滑的发动机部件的油管。 绝缘管围绕油管并在油管的相当长的长度上延伸。 绝缘管的相对端一体地密封地连接到油管的相应端部，以在油管和绝缘管之间形成死空气环。