公开(公告)号：US20100132370A1

公开(公告)日：2010-06-03

申请号：US12324993

申请日：2008-11-28

申请人： Eric DUROCHER ,  John PIETROBON

发明人： Eric DUROCHER ,  John PIETROBON

IPC分类号： F02C7/20

CPC分类号： F01D25/246 ,  F01D25/162 ,  F01D25/243 ,  F05B2260/301 ,  F05D2230/642 ,  F05D2230/644 ,  Y10T29/49323 ,  Y10T29/49895 ,  Y10T29/49947 ,  Y10T29/49963

摘要： A gas turbine engine mid turbine frame apparatus includes a an inner case supporting a bearing, an outer case to which the inner case is mounted, and an apparatus for radially positioning one relative to the other, the apparatus including a plurality of radial locators extending outwardly of the outer case and an associated locking apparatus. The locking apparatus is mounted adjacent to but independent of the locators and provides for anti-rotation of the radial locators once installed.

摘要翻译： 燃气涡轮发动机中涡轮机架装置包括支撑轴承的内壳体，安装内壳体的外壳体和用于相对于另一壳体径向定位的装置，该装置包括多个向外延伸的径向定位器 的外壳和相关联的锁定装置。 锁定装置安装在与定位器相邻但独立的位置，并且一旦安装就提供径向定位器的防旋转。

公开(公告)号：US20090155069A1

公开(公告)日：2009-06-18

申请号：US11954320

申请日：2007-12-12

申请人： Eric DUROCHER ,  John PIETROBON ,  Alan JUNEAU ,  Dennis ENGLISH

发明人： Eric DUROCHER ,  John PIETROBON ,  Alan JUNEAU ,  Dennis ENGLISH

IPC分类号： F01D9/04

CPC分类号： F01D9/042 ,  F05D2260/38

摘要： A vane assembly for a gas turbine engine comprising an axial loading element disposed between a mounting element of the vane ring and a cooperating portion of the supporting structure, such as to generate a load force therebetween in an axial direction. The axial load force limits unwanted relative movement between the vane ring and the supporting structure 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安装元件和支撑结构的协作部分之间的轴向加载元件，以便在轴向方向上产生其间的载荷力。 轴向载荷力限制在燃气涡轮发动机运行期间叶片环与支撑结构之间的不必要的相对运动。

公开(公告)号：US20110078902A1

公开(公告)日：2011-04-07

申请号：US12571952

申请日：2009-10-01

申请人： Eric DUROCHER ,  John PIETROBON ,  Nicolas GRIVAS

发明人： Eric DUROCHER ,  John PIETROBON ,  Nicolas GRIVAS

IPC分类号： B23P11/00

CPC分类号： F01D25/28 ,  F01D25/16 ,  F05D2230/64

摘要： A method for centering an engine structure such as a bearing housing is provided which may be used, for example, during assembly of a mid turbine frame or other engine case structure. In one aspect, the method includes using spacers with respective radial spokes which connect inner and outer portions of the case. In another aspect, centring may be provided by machining selected contacting surfaces of selected components.

摘要翻译： 提供了一种用于使诸如轴承壳体的发动机结构对中的方法，其可以例如在中间涡轮机框架或其他发动机壳体结构的组装期间使用。 在一个方面，该方法包括使用具有连接壳体的内部和外部部分的相应径向轮辐的间隔件。 在另一方面，可以通过加工所选择的部件的所选择的接触表面来提供定中心。

公开(公告)号：US20100080699A1

公开(公告)日：2010-04-01

申请号：US12241990

申请日：2008-09-30

申请人： John PIETROBON ,  Eric DUROCHER

发明人： John PIETROBON ,  Eric DUROCHER

IPC分类号： F02C7/28 ,  F16J15/02

CPC分类号： F16J15/062 ,  F01D11/005 ,  F05D2230/642 ,  F05D2240/11 ,  F05D2260/37

摘要： An arrangement for sealing a turbine shroud gas path duct interface of a turbine engine comprises a static shroud surrounding a rotatable airfoil array and an annular duct downstream of the shroud with respect to a gas flow passing through the gas path. The shroud and the duct define a portion of the gas path for directing the gas flow, having an axially extending interface gap between the shroud and duct. An annular seal in use engages both the shroud and the duct, thereby sealing the annular gap.

摘要翻译： 用于密封涡轮发动机的涡轮机护罩气体路径管道接口的装置包括围绕可旋转翼型阵列的静态护罩和相对于穿过气体路径的气流在护罩下游的环形管道。 护罩和管道限定用于引导气流的气体路径的一部分，其在护罩和管道之间具有轴向延伸的界面间隙。 使用的环形密封件接合护罩和管道，从而密封环形间隙。

公开(公告)号：US20130051987A1

公开(公告)日：2013-02-28

申请号：US13222028

申请日：2011-08-31

申请人： Eric DUROCHER ,  Guy LEFEBVRE

发明人： Eric DUROCHER ,  Guy LEFEBVRE

IPC分类号： F01D25/26 ,  B22F3/12 ,  B22F7/00

CPC分类号： B22F5/009 ,  B22F3/004 ,  B22F3/12 ,  B22F3/225 ,  B22F7/06 ,  C22C19/03 ,  C22C19/07 ,  F01D9/02 ,  F01D11/08 ,  F01D25/24 ,  F05D2230/30 ,  F05D2240/11

摘要： A turbine shroud has a plurality of shroud segments disposed circumferentially one adjacent to another. Each segment has a flow restrictor projecting integrally from one end face thereof and overlapping a corresponding end face of a circumferentially adjacent segment. The overlap between the circumferentially adjacent segments restricts gas leakage through the inter-segment gap between adjacent shroud segments.

摘要翻译： 涡轮机护罩具有多个围绕另一个相邻设置的护罩段。 每个段具有从其一个端面一体地突出并与周向相邻的段的对应的端面重叠的限流器。 周向相邻的区段之间的重叠限制了通过相邻护罩区段之间的段间间隙的气体泄漏。

公开(公告)号：US20110081238A1

公开(公告)日：2011-04-07

申请号：US12571731

申请日：2009-10-01

申请人： Eric DUROCHER ,  Jean Fournier

发明人： Eric DUROCHER ,  Jean Fournier

IPC分类号： F01D9/02

CPC分类号： F01D9/02 ,  F05D2230/232 ,  F05D2230/50 ,  F05D2240/12 ,  F05D2240/122 ,  F05D2240/304

摘要： A gas turbine engine stator vane has a sheet metal body with a pressure surface and a suction surface extending chordwise from a leading edge to a trailing edge. The sheet metal body has opposed pressure and suction side trailing end portions that meet at a joint upstream from the trailing edge of the airfoil. The pressure and suction surfaces of the sheet metal body are parallel to one another between the joint and the trailing edge, thereby forming a straight non-tapering trailing edge section from the joint to the trailing edge of the airfoil.

摘要翻译： 燃气涡轮发动机定子叶片具有带有压力表面的金属板体和从前缘向后缘延伸的抽吸表面。 钣金体具有与翼型件的后缘上游相接的相对的压力和吸力侧后端部。 金属板体的压力和吸力表面在接头和后缘之间彼此平行，从而形成从翼缘的接头到后缘的直的非渐缩的后缘部分。

公开(公告)号：US20110081234A1

公开(公告)日：2011-04-07

申请号：US12571909

申请日：2009-10-01

申请人： Eric DUROCHER ,  Guy LEFEBVRE

发明人： Eric DUROCHER ,  Guy LEFEBVRE

IPC分类号： F01D25/26 ,  B23P11/00

CPC分类号： F01D25/243 ,  F01D25/26 ,  F05B2260/301 ,  F05D2260/94 ,  F05D2260/941

摘要： A thermal expansion joint apparatus includes an insert extending passages passing through respective first and second components to loosely restrain the first component between the second component and an enlarged head of the insert thereby allowing thermal expansion of the respective first and second components relative to each other. The insert is secured to the second component by a fastener which can be removed, for example, when the insert is to be removed from the engine.

摘要翻译： 热膨胀接头装置包括插入件，其延伸通过相应的第一和第二部件的通道，以松散地限制第二部件和插入件的扩大头部之间的第一部件，从而允许相应的第一和第二部件相对于彼此的热膨胀。 插入件通过紧固件固定到第二部件上，该紧固件可以例如当插入件从发动机上移除时被去除。

公开(公告)号：US20110036068A1

公开(公告)日：2011-02-17

申请号：US12858313

申请日：2010-08-17

申请人： Guy LEFEBVRE ,  Nicolas GRIVAS ,  Richard BOUCHARD ,  Denis LECLAIR ,  Eric DUROCHER

发明人： Guy LEFEBVRE ,  Nicolas GRIVAS ,  Richard BOUCHARD ,  Denis LECLAIR ,  Eric DUROCHER

IPC分类号： F02K1/38

CPC分类号： F02K1/386 ,  F01D9/04 ,  F02K1/48 ,  F02K1/80 ,  F05D2220/32 ,  F05D2230/642 ,  F05D2240/10 ,  F05D2240/127 ,  Y02T50/671

摘要： An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring. The mixer struts have a radial length at least equal to a width of a main gas path defined between the inner lobes and the exhaust cone such that the mixer struts extend entirely through the main gas path. The stiffener ring being fixed solely to the mixer struts such as to float with respect to the exhaust cone and permit relative movement therebetween.

摘要翻译： 用于燃气涡轮发动机的排气混合器包括具有适于紧固到发动机壳体的上游端的环形壁和形成多个内部和外部混合器凸角的下游端。 支撑构件互连至少多个内裂片，并且包括从内裂片径向向内定位的周向延伸的加强环，以及一系列周向间隔开的从内裂纹到加强环径向延伸的混合器支柱。 混合器支柱具有至少等于限定在内部叶片和排气锥体之间的主气体通道的宽度的径向长度，使得混合器支柱完全延伸穿过主气体路径。 加强环仅被固定到混合器支柱上，以便相对于排气锥体浮动并允许它们之间的相对运动。

公开(公告)号：US20100272566A1

公开(公告)日：2010-10-28

申请号：US12429242

申请日：2009-04-24

申请人： Eric DUROCHER ,  Mohamad SLEIMAN ,  Panagiota TSIFOURDARIS

发明人： Eric DUROCHER ,  Mohamad SLEIMAN ,  Panagiota TSIFOURDARIS

IPC分类号： F01D1/02

CPC分类号： F01D25/14 ,  F01D5/142 ,  F01D5/143 ,  F01D5/146 ,  F01D9/02 ,  F01D9/041 ,  F01D9/06 ,  F01D17/143 ,  F01D25/16 ,  F01D25/24 ,  F01D25/28 ,  F02C7/057 ,  F02C9/22 ,  F04D29/544

摘要： A gas turbine engine is provided having an annular duct having an inner duct wall and an outer duct wall. At least one strut extends between the inner duct wall and the outer duct wall. The strut has an aerodynamic shape. At least one vane located circumferentially adjacent the strut and axially behind a leading edge of the strut, and an aerodynamic deflector located circumferentially between each strut and each vane. The aerodynamic deflector may positioned axially upstream of a flow separation point which would otherwise be caused by the strut.

摘要翻译： 燃气涡轮发动机设置有具有内管壁和外管壁的环形管道。 至少一个支柱在内管道壁和外管壁之间延伸。 支柱具有空气动力学形状。 至少一个叶片周向地邻近支柱并且轴向地在支柱的前缘之后，以及位于每个支柱和每个叶片之间周向的空气动力学偏转器。 空气动力学偏转器可以轴向位于流动分离点的上游，否则将由支柱引起。

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。