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1. 发明申请

US20120272522A1 GAS TURBINE ENGINE SYSTEMS AND RELATED METHODS INVOLVING THERMALLY ISOLATED RETENTION 有权
标题翻译：气体涡轮发动机系统和涉及热隔离保持的相关方法
公开(公告)号：US20120272522A1
公开(公告)日：2012-11-01
申请号：US13539621
申请日：2012-07-02
申请人： Andreas Sadil , Claude I. Barnett, JR. , Ricky A. Daigle
发明人： Andreas Sadil , Claude I. Barnett, JR. , Ricky A. Daigle
IPC分类号： B23Q3/00
CPC分类号： F02K3/10 , F05D2260/30 , Y10T29/49234 , Y10T29/4932 , Y10T29/53996
摘要： Gas turbine engine systems and related methods involving thermally isolated retention are provided. In this regard, a representative method for attaching a gas turbine engine component includes using a fastener, varying in diameter along a length thereof, to prevent a portion of a component from being crimped between surfaces to which the component is attached such that the component moves relative to the surfaces responsive to thermal cycling of a gas turbine engine of which the surfaces and the component are constituent parts.
摘要翻译：提供了燃气涡轮发动机系统和涉及热隔离保持的相关方法。在这方面，用于附接燃气涡轮发动机部件的代表性方法包括使用沿其长度改变直径的紧固件，以防止部件的一部分在部件附接的表面之间被卷曲，使得部件移动相对于响应于其表面和部件是组成部件的燃气涡轮发动机的热循环的表面。

2. 发明申请

US20130327847A1 TURBINE ENGINE EXHAUST NOZZLE FLAP 有权
标题翻译：涡轮发动机排气喷嘴
公开(公告)号：US20130327847A1
公开(公告)日：2013-12-12
申请号：US13493664
申请日：2012-06-11
申请人： Francis R. Moon , Claude I. Barnett, JR. , Jeffrey M. Jacques
发明人： Francis R. Moon , Claude I. Barnett, JR. , Jeffrey M. Jacques
IPC分类号： F02K1/12
CPC分类号： F02K1/1223
摘要： An exhaust nozzle flap for a turbine engine may include an exhaust nozzle flap linkage, an exhaust nozzle flap panel and a mounting pin. The linkage may include a first linkage segment that extends longitudinally from a linkage end to a second linkage segment, and a mounting aperture that extends transversely through the second linkage segment. The panel may include a first panel segment that extends longitudinally from a panel end to a second panel segment. The first panel segment may be pivotally engaged with the first linkage segment. The mounting pin may extend through and move transversely within the mounting aperture, and may be connected to the second panel segment.
摘要翻译：用于涡轮发动机的排气喷嘴挡板可包括排气喷嘴挡板连接件，排气喷嘴挡板和安装销。连接件可以包括从连接端纵向延伸到第二连杆段的第一连杆段和横向延伸穿过第二连杆段的安装孔。面板可以包括从面板端部纵向延伸到第二面板区段的第一面板区段。第一面板片段可以与第一连接片段枢转地接合。安装销可以延伸穿过并且在安装孔内横向移动，并且可以连接到第二面板段。

3. 发明授权

US08572979B2 Gas turbine combustor liner cap assembly 有权
标题翻译：燃气轮机燃烧器衬套组件
公开(公告)号：US08572979B2
公开(公告)日：2013-11-05
申请号：US12822607
申请日：2010-06-24
申请人： Craig F. Smith , Hannes A. Alholm , Jonathan J. Eastwood , Dennis J. Duhamel , David A. Burns , Claude I. Barnett, Jr. , Randy J. Danburg , Jeffrey D. Melman , David R. Wiley , Monica Pacheco-Tougas
发明人： Craig F. Smith , Hannes A. Alholm , Jonathan J. Eastwood , Dennis J. Duhamel , David A. Burns , Claude I. Barnett, Jr. , Randy J. Danburg , Jeffrey D. Melman , David R. Wiley , Monica Pacheco-Tougas
IPC分类号： F02C1/00
CPC分类号： F23R3/002 , F23R2900/00017 , F23R2900/00018
摘要： A combustor liner cap assembly is provided for use in a multiple fuel nozzle combustor of a gas turbine. The combustor liner cap assembly includes a tube plate having a plurality of fuel nozzle openings and a plurality of open ended premix tubes extending aft from the tube plate. Each premix tube has a forward end having a forward edge, the forward end being received in a corresponding one of the fuel nozzle openings. Each premix tube is secured to the tube plate aft of the forward edge of the forward end of the premix tube, for example, metallurgically bonded, such as by welding or brazing, to the tube plate or threaded into the tube plate.
摘要翻译：提供燃烧器衬套盖组件以用于燃气轮机的多燃料喷嘴燃烧室。燃烧器衬套组件包括具有多个燃料喷嘴开口的管板和从管板向后延伸的多个开放式预混合管。每个预混管具有前端具有前缘，前端被接收在对应的一个燃料喷嘴开口中。每个预混合管被固定到预混合管前端的前边缘的管板上，例如通过焊接或钎焊冶金结合到管板或螺纹连接到管板中。

4. 发明申请

US20110314823A1 GAS TURBINE COMBUSTOR LINER CAP ASSEMBLY 有权
标题翻译：气体涡轮搅拌机衬管总成
公开(公告)号：US20110314823A1
公开(公告)日：2011-12-29
申请号：US12822607
申请日：2010-06-24
申请人： Craig F. Smith , Hannes A. Alholm , Jonathan J. Eastwood , Dennis J. Duhamel , David A. Burns , Claude I. Barnett, JR. , Randy J. Danburg , Jeffrey D. Melman , David R. Wiley , Monica Pacheco-Tougas
发明人： Craig F. Smith , Hannes A. Alholm , Jonathan J. Eastwood , Dennis J. Duhamel , David A. Burns , Claude I. Barnett, JR. , Randy J. Danburg , Jeffrey D. Melman , David R. Wiley , Monica Pacheco-Tougas
IPC分类号： F02C7/22
CPC分类号： F23R3/002 , F23R2900/00017 , F23R2900/00018
摘要： A combustor liner cap assembly is provided for use in a multiple fuel nozzle combustor of a gas turbine. The combustor liner cap assembly includes a tube plate having a plurality of fuel nozzle openings and a plurality of open ended premix tubes extending aft from the tube plate. Each premix tube has a forward end having a forward edge, the forward end being received in a corresponding one of the fuel nozzle openings. Each premix tube is secured to the tube plate aft of the forward edge of the forward end of the premix tube, for example, metallurgically bonded, such as by welding or brazing, to the tube plate or threaded into the tube plate.
摘要翻译：提供燃烧器衬套盖组件以用于燃气轮机的多燃料喷嘴燃烧室。燃烧器衬套组件包括具有多个燃料喷嘴开口的管板和从管板向后延伸的多个开放式预混合管。每个预混管具有前端具有前缘，前端被接收在对应的一个燃料喷嘴开口中。每个预混合管被固定到预混合管前端的前边缘的管板上，例如通过焊接或钎焊冶金结合到管板或螺纹连接到管板中。

5. 发明授权

US08833721B2 Gas turbine engine systems and related methods involving thermally isolated retention 有权
标题翻译：燃气涡轮发动机系统和涉及热隔离保持的相关方法
公开(公告)号：US08833721B2
公开(公告)日：2014-09-16
申请号：US13539621
申请日：2012-07-02
申请人： Andreas Sadil , Claude I. Barnett, Jr. , Ricky A. Daigle
发明人： Andreas Sadil , Claude I. Barnett, Jr. , Ricky A. Daigle
IPC分类号： F16M13/00 , F16B15/00 , F02K3/10
CPC分类号： F02K3/10 , F05D2260/30 , Y10T29/49234 , Y10T29/4932 , Y10T29/53996
摘要： Gas turbine engine systems and related methods involving thermally isolated retention are provided. In this regard, a representative method for attaching a gas turbine engine component includes using a fastener, varying in diameter along a length thereof, to prevent a portion of a component from being crimped between surfaces to which the component is attached such that the component moves relative to the surfaces responsive to thermal cycling of a gas turbine engine of which the surfaces and the component are constituent parts.
摘要翻译：提供了燃气涡轮发动机系统和涉及热隔离保持的相关方法。在这方面，用于附接燃气涡轮发动机部件的代表性方法包括使用沿其长度改变直径的紧固件，以防止部件的一部分在部件附接的表面之间被卷曲，使得部件移动相对于响应于其表面和部件是组成部件的燃气涡轮发动机的热循环的表面。

6. 发明授权

US08235345B2 Gas turbine engine systems and related methods involving thermally isolated retention 有权
标题翻译：燃气涡轮发动机系统和涉及热隔离保持的相关方法
公开(公告)号：US08235345B2
公开(公告)日：2012-08-07
申请号：US12112470
申请日：2008-04-30
申请人： Andreas Sadil , Claude I. Barnett, Jr. , Ricky A. Daigle
发明人： Andreas Sadil , Claude I. Barnett, Jr. , Ricky A. Daigle
IPC分类号： A47B97/00 , F16M13/00 , D06F79/02 , A47G23/02 , B65D63/00 , B64D13/00
CPC分类号： F02K3/10 , F05D2260/30 , Y10T29/49234 , Y10T29/4932 , Y10T29/53996
摘要： Gas turbine engine systems and related methods involving thermally isolated retention are provided. In this regard, a representative method for attaching a gas turbine engine component includes using a fastener, varying in diameter along a length thereof, to prevent a portion of a component from being crimped between surfaces to which the component is attached such that the component moves relative to the surfaces responsive to thermal cycling of a gas turbine engine of which the surfaces and the component are constituent parts.
摘要翻译：提供了燃气涡轮发动机系统和涉及热隔离保持的相关方法。在这方面，用于附接燃气涡轮发动机部件的代表性方法包括使用沿其长度改变直径的紧固件，以防止部件的一部分在部件附接的表面之间被卷曲，使得部件移动相对于响应于其表面和部件是组成部件的燃气涡轮发动机的热循环的表面。

7. 发明申请

US20090272123A1 Gas Turbine Engine Systems and Related Methods Involving Thermally Isolated Retention 有权
标题翻译：燃气轮机发动机系统及相关方法涉及隔热保温
公开(公告)号：US20090272123A1
公开(公告)日：2009-11-05
申请号：US12112470
申请日：2008-04-30
申请人： Andreas Sadil , Claude I. Barnett, JR. , Ricky A. Daigle
发明人： Andreas Sadil , Claude I. Barnett, JR. , Ricky A. Daigle
IPC分类号： F02C7/20 , B23P11/00
CPC分类号： F02K3/10 , F05D2260/30 , Y10T29/49234 , Y10T29/4932 , Y10T29/53996
摘要： Gas turbine engine systems and related methods involving thermally isolated retention are provided. In this regard, a representative method for attaching a gas turbine engine component includes using a fastener, varying in diameter along a length thereof, to prevent a portion of a component from being crimped between surfaces to which the component is attached such that the component moves relative to the surfaces responsive to thermal cycling of a gas turbine engine of which the surfaces and the component are constituent parts.
摘要翻译：提供了燃气涡轮发动机系统和涉及热隔离保持的相关方法。在这方面，用于附接燃气涡轮发动机部件的代表性方法包括使用沿其长度改变直径的紧固件，以防止部件的一部分在部件附接的表面之间被卷曲，使得部件移动相对于响应于其表面和部件是组成部件的燃气涡轮发动机的热循环的表面。

8. 发明授权

US08607574B1 Turbine engine exhaust nozzle flap 有权
标题翻译：涡轮发动机排气喷嘴阀瓣
公开(公告)号：US08607574B1
公开(公告)日：2013-12-17
申请号：US13493664
申请日：2012-06-11
申请人： Francis R. Moon , Claude I. Barnett, Jr. , Jeffrey M. Jacques
发明人： Francis R. Moon , Claude I. Barnett, Jr. , Jeffrey M. Jacques
IPC分类号： F02K1/00
CPC分类号： F02K1/1223
摘要： An exhaust nozzle flap for a turbine engine may include an exhaust nozzle flap linkage, an exhaust nozzle flap panel and a mounting pin. The linkage may include a first linkage segment that extends longitudinally from a linkage end to a second linkage segment, and a mounting aperture that extends transversely through the second linkage segment. The panel may include a first panel segment that extends longitudinally from a panel end to a second panel segment. The first panel segment may be pivotally engaged with the first linkage segment. The mounting pin may extend through and move transversely within the mounting aperture, and may be connected to the second panel segment.
摘要翻译：用于涡轮发动机的排气喷嘴挡板可包括排气喷嘴挡板连接件，排气喷嘴挡板和安装销。连接件可以包括从连接端纵向延伸到第二连杆段的第一连杆段和横向延伸穿过第二连杆段的安装孔。面板可以包括从面板端部纵向延伸到第二面板区段的第一面板区段。第一面板片段可以与第一连接片段枢转地接合。安装销可以延伸穿过并且在安装孔内横向移动，并且可以连接到第二面板段。

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