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公开(公告)号：US09476322B2
公开(公告)日：2016-10-25
申请号：US13541818
申请日：2012-07-05
CPC分类号： F01D25/26 , F01D9/023 , F05D2250/322 , F05D2250/323 , F05D2250/38 , F05D2250/71
摘要： A transition duct assembly for a turbine engine includes a transition duct with an inner liner removably received therein. The duct is hollow with an inner peripheral surface and an outer peripheral surface. The duct can have an inlet end and an outlet end. The inner peripheral surface of the duct can be convergent along a majority of the length of the duct when moving from the inlet end to the outlet end thereof. The liner is hollow body with an inner peripheral surface and an outer peripheral surface. The outer peripheral surface of the liner can be correspondingly convergent to the inner peripheral surface of the duct. The inner peripheral surface of the liner can define an internal flow passage through the assembly. Such a construction permits the use of different materials for the liner and the duct and can allow the liner to be readily removed and replaced.
摘要翻译： 用于涡轮发动机的过渡管道组件包括具有可拆卸地容纳在其中的内衬管的过渡管道。 管道是中空的，具有内周表面和外周表面。 管道可以具有入口端和出口端。 当从入口端到其出口端移动时，管道的内周表面可以沿着管道的大部分长度会聚。 衬套是具有内周面和外周面的中空体。 衬套的外周表面可以相应地收敛于管道的内周表面。 衬套的内周表面可以限定穿过组件的内部流动通道。 这种结构允许使用不同的材料用于衬管和管道，并且可以允许衬垫容易地移除和更换。
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公开(公告)号：US20140010644A1
公开(公告)日：2014-01-09
申请号：US13541818
申请日：2012-07-05
CPC分类号： F01D25/26 , F01D9/023 , F05D2250/322 , F05D2250/323 , F05D2250/38 , F05D2250/71
摘要： A transition duct assembly for a turbine engine includes a transition duct with an inner liner removably received therein. The duct is hollow with an inner peripheral surface and an outer peripheral surface. The duct can have an inlet end and an outlet end. The inner peripheral surface of the duct can be convergent along a majority of the length of the duct when moving from the inlet end to the outlet end thereof. The liner is hollow body with an inner peripheral surface and an outer peripheral surface. The outer peripheral surface of the liner can be correspondingly convergent to the inner peripheral surface of the duct. The inner peripheral surface of the liner can define an internal flow passage through the assembly. Such a construction permits the use of different materials for the liner and the duct and can allow the liner to be readily removed and replaced.
摘要翻译： 用于涡轮发动机的过渡管道组件包括具有可拆卸地容纳在其中的内衬管的过渡管道。 管道是中空的，具有内周表面和外周表面。 管道可以具有入口端和出口端。 当从入口端到其出口端移动时，管道的内周表面可以沿着管道的大部分长度会聚。 衬套是具有内周面和外周面的中空体。 衬套的外周表面可以相应地收敛于管道的内周表面。 衬套的内周表面可以限定穿过组件的内部流动通道。 这种结构允许使用不同的材料用于衬管和管道，并且可以允许衬垫容易地移除和更换。
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3.发明申请TURBINE TRANSITION COMPONENT FORMED FROM AN AIR-COOLED MULTI-LAYER OUTER PANEL FOR USE IN A GAS TURBINE ENGINE 有权用于气体涡轮发动机的空气冷却多层外板组成的涡轮转换部件公开(公告)号：US20120121381A1
公开(公告)日：2012-05-17
申请号：US12945943
申请日：2010-11-15
申请人： Richard C. Charron , Daniel J. Pierce , Jay A. Morrison , Ching-Pang Lee , Kenneth K. Landis , Walter Marussich
发明人： Richard C. Charron , Daniel J. Pierce , Jay A. Morrison , Ching-Pang Lee , Kenneth K. Landis , Walter Marussich
IPC分类号： F03B11/00
CPC分类号： F01D9/023 , F01D25/12 , F05D2260/201 , F23R2900/03044
摘要： A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane.
摘要翻译： 公开了一种用于将来自燃烧器的气流引导到燃气涡轮发动机中的涡轮部分的第一级的过渡管道的冷却系统。 过渡管道可以具有由内板形成的多面板外壁，该内板具有限定热气路径气室的至少一部分的内表面和从内板径向向外定位的中间板，使得至少一个冷却室 形成在内板和中间板之间。 过渡管还可以包括外板。 内部，中间和外部面板可以包括一个或多个计量孔，用于在冷却室之间通过冷却流体以冷却面板。 中间板和外板可以用连接系统固定到内板上，使得中间板和外板可在平面内移动。
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4.发明授权Turbine transition component formed from an air-cooled multi-layer outer panel for use in a gas turbine engine 有权由用于燃气涡轮发动机的风冷多层外板形成的涡轮转换部件公开(公告)号：US09097117B2
公开(公告)日：2015-08-04
申请号：US12945943
申请日：2010-11-15
申请人： Richard C. Charron , Daniel J. Pierce , Jay A. Morrison , Ching-Pang Lee , Kenneth K. Landis , Walter Marussich
发明人： Richard C. Charron , Daniel J. Pierce , Jay A. Morrison , Ching-Pang Lee , Kenneth K. Landis , Walter Marussich
CPC分类号： F01D9/023 , F01D25/12 , F05D2260/201 , F23R2900/03044
摘要： A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane.
摘要翻译： 公开了一种用于将来自燃烧器的气流引导到燃气涡轮发动机中的涡轮部分的第一级的过渡管道的冷却系统。 过渡管道可以具有由内板形成的多面板外壁，该内板具有限定热气路径气室的至少一部分的内表面和从内板径向向外定位的中间板，使得至少一个冷却室 形成在内板和中间板之间。 过渡管还可以包括外板。 内部，中间和外部面板可以包括一个或多个计量孔，用于在冷却室之间通过冷却流体以冷却面板。 中间板和外板可以用连接系统固定到内板上，使得中间板和外板可在平面内移动。
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公开(公告)号：US08276389B2
公开(公告)日：2012-10-02
申请号：US13096041
申请日：2011-04-28
申请人： Richard C. Charron , Raymond S. Nordlund , Jay A. Morrison , Ernie B. Campbell , Daniel J. Pierce , Matthew D. Montgomery , Jody W. Wilson
发明人： Richard C. Charron , Raymond S. Nordlund , Jay A. Morrison , Ernie B. Campbell , Daniel J. Pierce , Matthew D. Montgomery , Jody W. Wilson
IPC分类号： F02C3/00
CPC分类号： F01D9/023 , F05D2240/40 , F05D2250/121 , F05D2250/141 , F05D2250/322 , F05D2250/323 , F23R3/425 , F23R3/46 , F23R3/60
摘要： An arrangement (10) for conveying combustion gas from a plurality of can annular combustors to a turbine first stage blade section of a gas turbine engine, the arrangement (10) including a plurality of interconnected integrated exit piece (IEP) sections (16) defining an annular chamber (18) oriented concentric to a gas turbine engine longitudinal axis (20) upstream of the turbine first stage blade section. Each respective IEP (16) includes a first flow path section (40) receiving and fully bounding a first flow from a respective can annular combustor along a respective common axis (22) there between, and delivering a partially bounded first flow to a downstream adjacent IEP section (42). Each respective IEP further includes a second flow path section (112) receiving a partially bounded second flow from an upstream adjacent IEP (66) and delivering at least part of the second flow to the turbine first stage blade section.
摘要翻译： 一种用于将燃烧气体从多个罐环形燃烧器输送到燃气涡轮发动机的涡轮机第一级叶片部分的装置（10），所述装置（10）包括多个互连的集成出口件（IEP）部分（16），其限定 与涡轮机第一级叶片部分上游的燃气涡轮发动机纵向轴线（20）同心取向的环形室（18）。 每个相应的IEP（16）包括第一流路部分（40），其沿着相应的公共轴线（22）接收并完全限定来自相应的罐环形燃烧器的第一流动，并且将部分有界的第一流体递送到下游相邻 IEP部分（42）。 每个相应的IEP还包括第二流路部分（112），其接收来自上游相邻的IEP（66）的部分界定的第二流，并将第二流的至少一部分输送到涡轮机第一级叶片部分。
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公开(公告)号：US20110203282A1
公开(公告)日：2011-08-25
申请号：US13096041
申请日：2011-04-28
申请人： Richard C. Charron , Raymond S. Nordlund , Jay A. Morrison , Ernie B. Campbell , Daniel J. Pierce , Matthew D. Montgomery , Jody W. Wilson
发明人： Richard C. Charron , Raymond S. Nordlund , Jay A. Morrison , Ernie B. Campbell , Daniel J. Pierce , Matthew D. Montgomery , Jody W. Wilson
IPC分类号： F02C3/14
CPC分类号： F01D9/023 , F05D2240/40 , F05D2250/121 , F05D2250/141 , F05D2250/322 , F05D2250/323 , F23R3/425 , F23R3/46 , F23R3/60
摘要： An arrangement (10) for conveying combustion gas from a plurality of can annular combustors to a turbine first stage blade section of a gas turbine engine, the arrangement (10) including a plurality of interconnected integrated exit piece (IEP) sections (16) defining an annular chamber (18) oriented concentric to a gas turbine engine longitudinal axis (20) upstream of the turbine first stage blade section. Each respective IEP (16) includes a first flow path section (40) receiving and fully bounding a first flow from a respective can annular combustor along a respective common axis (22) there between, and delivering a partially bounded first flow to a downstream adjacent IEP section (42). Each respective IEP further includes a second flow path section (112) receiving a partially bounded second flow from an upstream adjacent IEP (66) and delivering at least part of the second flow to the turbine first stage blade section.
摘要翻译： 一种用于将燃烧气体从多个罐环形燃烧器输送到燃气涡轮发动机的涡轮机第一级叶片部分的装置（10），所述装置（10）包括多个互连的集成出口件（IEP）部分（16），其限定 与涡轮机第一级叶片部分上游的燃气涡轮发动机纵向轴线（20）同心取向的环形室（18）。 每个相应的IEP（16）包括第一流路部分（40），其沿着相应的公共轴线（22）接收并完全限定来自相应的罐环形燃烧器的第一流动，并且将部分有界的第一流体递送到下游相邻 IEP部分（42）。 每个相应的IEP还包括第二流路部分（112），其接收来自上游相邻的IEP（66）的部分界定的第二流，并将第二流的至少一部分输送到涡轮机第一级叶片部分。
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公开(公告)号：US5317367A
公开(公告)日：1994-05-31
申请号：US3055
申请日：1993-01-11
申请人： Daniel J. Pierce , William P. Reese
发明人： Daniel J. Pierce , William P. Reese
摘要： A reprographic machine having a plurality of operating subsystems employs a setup procedure that prevents use for copying until all subsystems reach operating conditions. To avoid the need for time lost in the setup procedure where a power shut down is short, a bypass system, which senses the duration of the shut down, is utilized to allow prompt return to the copy function. Heated elements, such as fuser rolls, motors, and the like can be utilized to provide a timing function, based on temperature decay characteristics relative to time. The sensed temperature can be used as a control parameter for allowing bypass of the setup procedures.
摘要翻译： 具有多个操作子系统的复印机采用防止用于复制的设置过程，直到所有子系统达到操作状态。 为了避免在电源关闭短暂的设置过程中需要时间丢失，可以使用检测关闭持续时间的旁路系统来允许迅速返回到复制功能。 基于相对于时间的温度衰减特性，加热元件（例如定影辊，电动机等）可用于提供定时功能。 感测到的温度可以用作允许旁路设置过程的控制参数。
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