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1. 发明授权

US08166767B2 Gas turbine combustor exit duct and hp vane interface 有权
标题翻译：燃气轮机燃烧器出口管和hp叶片接口
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。

2. 发明授权

US07836702B2 Gas turbine combustor exit duct and HP vane interface 有权
标题翻译：燃气轮机燃烧器出口管道和HP叶片接口
公开(公告)号：US07836702B2
公开(公告)日：2010-11-23
申请号：US11532231
申请日：2006-09-15
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
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。

3. 发明申请

US20060045745A1 Vane attachment arrangement 有权
标题翻译：叶片附件安排
公开(公告)号：US20060045745A1
公开(公告)日：2006-03-02
申请号：US10923680
申请日：2004-08-24
申请人： Remy Synnott , Nicolas Grivas , Alan Juneau , David Glasspoole
发明人： Remy Synnott , Nicolas Grivas , Alan Juneau , David Glasspoole
IPC分类号： F01D5/30
CPC分类号： F01D11/003 , F01D11/005 , F01D25/246 , F05D2230/60 , F05D2240/55 , F05D2240/56 , F05D2240/57 , Y10T29/49323
摘要： A simplified vane mounting arrangement by which a vane ring can be pre-assembled to an inner support ring before being installed in an outer casing.
摘要翻译：一种简化的叶片安装装置，通过该简化的叶片安装装置，在安装在外壳中之前，叶片环可以预先组装到内部支撑环上。

4. 发明授权

US07001152B2 Shrouded turbine blades with locally increased contact faces 有权
标题翻译：带有局部增加接触面的有罩涡轮叶片
公开(公告)号：US07001152B2
公开(公告)日：2006-02-21
申请号：US10681341
申请日：2003-10-09
申请人： René Paquet , Nicolas Grivas , Richard Brandt
发明人： René Paquet , Nicolas Grivas , Richard Brandt
IPC分类号： F01O5/22
CPC分类号： F01D5/225 , Y10T29/49321 , Y10T29/49336
摘要： A one-piece blade for a turbine section of a gas turbine engine, the blade comprising a root, an airfoil and a shroud. The shroud extends generally perpendicularly from a tip of the airfoil and is defined by a pair of opposed bearing faces and a pair of opposed non-bearing faces. The bearing faces each have a contact portion adapted to contact a shroud of an adjacent blade. The shroud has a substantially constant nominal thickness and the bearing faces have a substantially constant face thickness across the contact portion, the face thickness being greater than the nominal thickness. The transition between the face thickness and the nominal thickness is substantially discontinuous.
摘要翻译：一种用于燃气涡轮发动机的涡轮部分的单件叶片，该叶片包括根部，翼型件和护罩。护罩从翼型件的尖端大致垂直地延伸并且由一对相对的支承面和一对相对的非承载面限定。轴承面各自具有适于接触相邻叶片的护罩的接触部分。护罩具有基本上恒定的标称厚度，并且支承面在接触部分上具有基本上恒定的面厚度，表面厚度大于标称厚度。面厚度和标称厚度之间的过渡基本上是不连续的。

5. 发明申请

US20050079058A1 Shrouded turbine blades with locally increased contact faces 有权
标题翻译：带有局部增加接触面的有罩涡轮叶片
公开(公告)号：US20050079058A1
公开(公告)日：2005-04-14
申请号：US10681341
申请日：2003-10-09
申请人： Rene Paquet , Nicolas Grivas , Richard Brandt
发明人： Rene Paquet , Nicolas Grivas , Richard Brandt
IPC分类号： F01D5/20 , F01D5/22 , B63H1/16
CPC分类号： F01D5/225 , Y10T29/49321 , Y10T29/49336
摘要： A one-piece blade for a turbine section of a gas turbine engine, the blade comprising a root, an airfoil and a shroud. The shroud extends generally perpendicularly from a tip of the airfoil and is defined by a pair of opposed bearing faces and a pair of opposed non-bearing faces. The bearing faces each have a contact portion adapted to contact a shroud of an adjacent blade. The shroud has a substantially constant nominal thickness and the bearing faces have a substantially constant face thickness across the contact portion, the face thickness being greater than the nominal thickness. The transition between the face thickness and the nominal thickness is substantially discontinuous.
摘要翻译：一种用于燃气涡轮发动机的涡轮部分的单件叶片，该叶片包括根部，翼型件和护罩。护罩从翼型件的尖端大致垂直地延伸并且由一对相对的支承面和一对相对的非承载面限定。轴承面各自具有适于接触相邻叶片的护罩的接触部分。护罩具有基本上恒定的标称厚度，并且支承面在接触部分上具有基本上恒定的面厚度，表面厚度大于标称厚度。面厚度和标称厚度之间的过渡基本上是不连续的。

6. 发明授权

US08511969B2 Interturbine vane with multiple air chambers 有权
标题翻译：具有多个气室的涡轮叶片
公开(公告)号：US08511969B2
公开(公告)日：2013-08-20
申请号：US12572142
申请日：2009-10-01
申请人： Eric Durocher , Nicolas Grivas
发明人： Eric Durocher , Nicolas Grivas
IPC分类号： F01D9/06
CPC分类号： F01D25/14 , F01D5/18 , F01D11/005 , F01D25/28 , F05D2260/20
摘要： A gas turbine engine has a mid turbine frame disposed between turbine rotor assemblies. The mid turbine frame includes hollow airfoils radially extending through an annular gas path duct. The airfoils each include a double-walled leading edge structure to define a front chamber separated from a rear chamber defined in the remaining space within the airfoil.
摘要翻译：燃气涡轮发动机具有设置在涡轮转子组件之间的中间涡轮机架。中间涡轮机框架包括径向延伸穿过环形气体通道导管的中空翼型件。翼型件各自包括双壁前缘结构，以限定与在翼型内的剩余空间中限定的后室分离的前室。

7. 发明申请

US20110036068A1 GAS TURBINE ENGINE EXHAUST MIXER 有权
标题翻译：气体涡轮发动机排气混合机
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。

8. 发明申请

US20110023499A1 GAS TURBINE COMBUSTOR EXIT DUCT AND HP VANE INTERFACE 有权
标题翻译：气体涡轮机排气管和HP VANE接口
公开(公告)号：US20110023499A1
公开(公告)日：2011-02-03
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
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。

9. 发明申请

US20100236257A1 GAS TURBINE COMBUSTOR EXIT DUCT AND HP VANE INTERFACE 有权
标题翻译：气体涡轮机排气管和HP VANE接口
公开(公告)号：US20100236257A1
公开(公告)日：2010-09-23
申请号：US11532231
申请日：2006-09-15
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： F02C7/28
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。

10. 发明申请

US20050025622A1 Blade inlet cooling flow deflector apparatus and method 有权
标题翻译：叶片入口冷却导流装置及方法
公开(公告)号：US20050025622A1
公开(公告)日：2005-02-03
申请号：US10627970
申请日：2003-07-28
申请人： Toufik Djeridane , Michael Clyde Papple , Nicolas Grivas
发明人： Toufik Djeridane , Michael Clyde Papple , Nicolas Grivas
IPC分类号： F01D5/08 , F01D5/30 , B63H1/14
CPC分类号： F01D5/081 , F01D5/3007
摘要： An internally cooled turbine blade including at least one deflector extending into an air cavity generally from said first wall towards the second wall for diverting cooling air away from the first wall and generally towards the second wall to thereby improve cooling flow distribution among a plurality of cooling path inlets.
摘要翻译：一种内部冷却的涡轮机叶片，包括至少一个偏转器，所述至少一个偏转器通常从所述第一壁向第二壁延伸到空气腔中，用于将冷却空气从第一壁向远离第二壁转移，从而改善多个冷却之间的冷却流量分布路径入口

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