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：US08061969B2

公开(公告)日：2011-11-22

申请号：US12325000

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： F01D1/24 ,  F01D13/00 ,  F03D3/02 ,  F04D13/04 ,  F04D25/16

CPC分类号： F01D9/065 ,  F01D21/045 ,  F01D21/08 ,  F01D25/162 ,  F01D25/28

摘要： A gas turbine engine mid turbine frame having an inner case supporting at least one bearing and at least three spokes extending radially outwardly to an outer case, the mid turbine frame having an interturbine duct extending through the mid turbine frame, the interturbine duct spaced axially closer to an upstream turbine disc than a bearing supporting structure of the mid turbine frame and mounted axially slidingly relative to the bearing supporting structure to substantially isolate the bearing supporting structure from axial loads, for example such as disc loads incurred in the unlikely event a turbine disc shaft shears within the engine.

摘要翻译： 一种燃气涡轮发动机中间涡轮机框架，其具有支撑至少一个轴承的内部壳体和至少三个径向向外延伸到外部壳体的轮辐，所述中间涡轮机框架具有延伸穿过所述中间涡轮机框架的涡轮机管道，所述涡轮机管道在轴向上更靠近 到中间涡轮机框架的轴承支撑结构的上游涡轮盘，并相对于轴承支撑结构轴向滑动地安装，以将轴承支撑结构与轴向载荷基本上隔离，例如在不太可能发生的涡轮盘 发动机内的轴剪。

公开(公告)号：US20110081240A1

公开(公告)日：2011-04-07

申请号：US12571802

申请日：2009-10-01

申请人： Eric Durocher ,  Lam Nguyen

发明人： Eric Durocher ,  Lam Nguyen

IPC分类号： F01D9/04

CPC分类号： F01D9/044 ,  F05D2230/232 ,  F05D2230/237

摘要： A static vane ring for gas turbine engines includes a plurality of radial struts extending between and interconnecting outer and inner duct walls which define an annular duct therebetween. A load transfer apparatus is attached to at least one of the outer and inner duct walls to transfer load from vane to ring, and between vanes.

摘要翻译： 用于燃气涡轮发动机的静态叶片环包括在内壁和内壁之间延伸的多个径向支柱，其在其间限定了环形管道。 负载传送装置附接到外管壁和内管壁中的至少一个，以将负载从叶片传递到环，并且在叶片之间。

公开(公告)号：US08469661B2

公开(公告)日：2013-06-25

申请号：US12571802

申请日：2009-10-01

申请人： Eric Durocher ,  Lam Nguyen

发明人： Eric Durocher ,  Lam Nguyen

IPC分类号： F01D9/04

CPC分类号： F01D9/044 ,  F05D2230/232 ,  F05D2230/237

摘要： A static vane ring for gas turbine engines includes a plurality of radial struts extending between and interconnecting outer and inner duct walls which define an annular duct therebetween. A load transfer apparatus is attached to at least one of the outer and inner duct walls to transfer load from vane to ring, and between vanes.

摘要翻译： 用于燃气涡轮发动机的静态叶片环包括在内壁和内壁之间延伸的多个径向支柱，其在其间限定了环形管道。 负载传送装置附接到外管壁和内管壁中的至少一个，以将负载从叶片传递到环，并且在叶片之间。

公开(公告)号：US08245518B2

公开(公告)日：2012-08-21

申请号：US12324984

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

CPC分类号： F01D9/065 ,  F01D21/045 ,  F01D21/08 ,  F01D25/162

摘要： A gas turbine engine has an engine casing component, such as a mid turbine frame system, which may includes an outer case surrounding a spoke or strut casing. Load transfer spokes of the spoke casing extend between the outer case and an inner case of the spoke casing. A bearing housing supported by the engine casing may include a fuse arrangement for isolating bearing seizure loads from the engine casing. A seal arrangement may be provided to centralize the rotors after the fuse fails. The mid turbine frame may be provided to have a desired flexibility through the configuration of the casing and bearings in design.

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发动机外壳部件，其可以包括围绕辐条或支柱壳体的外壳。 轮辐壳体的载荷传递轮辐在外壳和轮辐壳体的内壳之间延伸。 由发动机壳体支撑的轴承壳体可以包括用于隔离发动机壳体的轴承咬合载荷的保险丝装置。 在保险丝故障之后，可以提供密封装置来集中转子。 中间涡轮机框架可以设计成具有通过外壳和轴承的设计而具有期望的柔性。

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。