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1. 发明授权

US08845284B2 Apparatus and system for sealing a turbine rotor 有权
标题翻译：用于密封涡轮转子的装置和系统
公开(公告)号：US08845284B2
公开(公告)日：2014-09-30
申请号：US12829632
申请日：2010-07-02
申请人： Thomas Raymond Farrell , Gary Charles Liotta , Ian David Wilson
发明人： Thomas Raymond Farrell , Gary Charles Liotta , Ian David Wilson
IPC分类号： F01D11/00
CPC分类号： F01D11/005 , F01D11/001 , F05D2240/11
摘要： An apparatus for restricting fluid flow in a turbo-machine is disclosed. The apparatus includes: a first inter-stage sealing member configured to be located between a first rotating airfoil stage and a second rotating airfoil stage attached to a rotor shaft, the first inter-stage sealing member including a segmented structure that includes a plurality of segments forming a circumferential surface, the first inter-stage sealing member including: a first base portion including a securing mechanism configured to at least substantially radially and tangentially secure the inter-stage sealing member to an inter-stage support structure; a first axial retention mechanism; and a first axially extending sealing portion configured to be outwardly radially loaded against at least one of the first rotating airfoil stage and the second rotating airfoil stage.
摘要翻译：公开了一种用于限制涡轮机中的流体流动的装置。该装置包括：第一级间密封构件，其构造成位于第一旋转翼型段和附接到转子轴的第二旋转翼型段之间，第一级间密封构件包括分段结构，其包括多个段形成圆周表面，所述第一级间密封构件包括：第一基部，包括固定机构，所述固定机构构造成至少基本上径向地并且切向地将所述级间密封构件固定到阶段式支撑结构; 第一轴向保持机构; 以及第一轴向延伸的密封部分，其构造成相对于所述第一旋转翼型段和所述第二旋转翼型段中的至少一个向外径向加载。

2. 发明申请

US20120087799A1 AXIAL RETENTION DEVICE FOR TURBINE SYSTEM 审中-公开
标题翻译：用于涡轮机系统的轴向保持装置
公开(公告)号：US20120087799A1
公开(公告)日：2012-04-12
申请号：US12902561
申请日：2010-10-12
申请人： Thomas Raymond Farrell , Gary Charles Liotta
发明人： Thomas Raymond Farrell , Gary Charles Liotta
IPC分类号： F04D29/34
CPC分类号： F01D5/3007 , F01D5/326 , F01D11/02
摘要： An axial retention device for a turbine is disclosed. The axial retention device includes a latch associated with a mating surface of one of a turbine component and a support structure. The latch has an outward bias and includes an axial load surface. The axial retention device further includes a pocket defined in a mating surface of the other of the turbine component and the support structure. The pocket is configured to accept the latch therein and includes a mating axial load surface. Engagement of the latch and the pocket allows the axial load surface and the mating axial load surface to interact, preventing axial movement of the turbine component with respect to the support structure in at least one direction.
摘要翻译：公开了一种用于涡轮机的轴向保持装置。轴向保持装置包括与涡轮机部件和支撑结构之一的配合表面相关联的闩锁。闩锁具有向外偏压并且包括轴向载荷表面。轴向保持装置还包括限定在涡轮机部件和支撑结构中的另一个的配合表面中的凹部。该口袋被配置为在其中接受闩锁并且包括配合的轴向负载表面。闩锁和凹口的接合允许轴向载荷表面和配合轴向载荷表面相互作用，从而防止涡轮机部件在至少一个方向上相对于支撑结构的轴向移动。

3. 发明申请

US20100178160A1 DEVICE AND SYSTEM FOR REDUCING SECONDARY AIR FLOW IN A GAS TURBINE 有权
标题翻译：用于减少气体涡轮机中二次空气流量的装置和系统
公开(公告)号：US20100178160A1
公开(公告)日：2010-07-15
申请号：US12353305
申请日：2009-01-14
申请人： Gary Charles Liotta , Thomas Raymond Farrell
发明人： Gary Charles Liotta , Thomas Raymond Farrell
IPC分类号： F01D11/08
CPC分类号： F01D11/001 , F01D5/066 , F01D11/006
摘要： A device for reducing secondary airflow in a gas turbine is disclosed. The device includes an inter-stage sealing member located between a plurality of first turbine buckets attached to a first rotor disk, and a plurality of second turbine buckets attached to a second rotor disk. The first rotor disk and the second rotor disk are rotatable about a central axis. The inter-stage sealing member is configured to be attached in a fixed position relative to the first rotor disk and the second rotor disk, and to contact the plurality of first buckets and the plurality of second buckets in a sealing engagement.
摘要翻译：公开了一种用于减少燃气轮机中二次气流的装置。该装置包括位于附接到第一转子盘的多个第一涡轮叶片和附接到第二转子盘的多个第二涡轮叶片之间的级间密封构件。第一转子盘和第二转子盘可围绕中心轴线旋转。所述级间密封构件被构造成相对于所述第一转子盘和所述第二转子盘被固定在固定位置，并且以密封接合方式接触所述多个第一铲斗和所述多个第二铲斗。

4. 发明授权

US08221062B2 Device and system for reducing secondary air flow in a gas turbine 有权
标题翻译：用于减少燃气轮机中的二次空气流量的装置和系统
公开(公告)号：US08221062B2
公开(公告)日：2012-07-17
申请号：US12353305
申请日：2009-01-14
申请人： Gary Charles Liotta , Thomas Raymond Farrell
发明人： Gary Charles Liotta , Thomas Raymond Farrell
IPC分类号： F01D11/08
CPC分类号： F01D11/001 , F01D5/066 , F01D11/006
摘要： A device for reducing secondary airflow in a gas turbine is disclosed. The device includes an inter-stage sealing member located between a plurality of first turbine buckets attached to a first rotor disk, and a plurality of second turbine buckets attached to a second rotor disk. The first rotor disk and the second rotor disk are rotatable about a central axis. The inter-stage sealing member is configured to be attached in a fixed position relative to the first rotor disk and the second rotor disk, and to contact the plurality of first buckets and the plurality of second buckets in a sealing engagement.
摘要翻译：公开了一种用于减少燃气轮机中二次气流的装置。该装置包括位于附接到第一转子盘的多个第一涡轮叶片和附接到第二转子盘的多个第二涡轮叶片之间的级间密封构件。第一转子盘和第二转子盘可围绕中心轴线旋转。所述级间密封构件被构造成相对于所述第一转子盘和所述第二转子盘被固定在固定位置，并且以密封接合方式接触所述多个第一铲斗和所述多个第二铲斗。

5. 发明授权

US06726448B2 Ceramic turbine shroud 有权
标题翻译：陶瓷涡轮罩
公开(公告)号：US06726448B2
公开(公告)日：2004-04-27
申请号：US10144851
申请日：2002-05-15
申请人： Edward Lee McGrath , Gregory S. Corman , Anthony J. Dean , Mark Stewart Schroder , Chris Basil Jiomacas , Thomas Raymond Farrell , Kenneth Lorenzo Parks
发明人： Edward Lee McGrath , Gregory S. Corman , Anthony J. Dean , Mark Stewart Schroder , Chris Basil Jiomacas , Thomas Raymond Farrell , Kenneth Lorenzo Parks
IPC分类号： F01O1116
CPC分类号： F01D11/12 , F01D25/246 , F05D2260/30 , Y02T50/67 , Y02T50/672
摘要： A gas turbine having a metallic outer shroud and a ceramic inner shroud. The ceramic inner shroud being secured to the outer shroud by hooks carried on the outer shroud. The hooks on the outer shroud being coated with TBC. A pin and spring system being provided to hold the ceramic inner shroud against the forward hook of the outer shroud. An anti-rotation pin being provided to trap the aft bend of the ceramic inner shroud against the aft hook of the outer shroud. The gas turbine further including a damping spring and pin system, disposed between a heat shield, within the outer shroud, and the ceramic inner shroud, to provide damping of the inner shroud.
摘要翻译：一种具有金属外护罩和陶瓷内护罩的燃气轮机。陶瓷内护罩通过承载在外护罩上的钩固定到外护罩上。外护罩上的钩子涂有TBC。提供销和弹簧系统以将陶瓷内护罩抵靠外护罩的前钩保持。设置有防旋转销，以将陶瓷内罩的后弯部夹紧到外护罩的后钩上。所述燃气轮机还包括阻尼弹簧和销系统，其设置在所述外护罩内的隔热罩和所述陶瓷内护罩之间，以提供所述内护罩的阻尼。

6. 发明授权

US08371815B2 Apparatus for cooling an airfoil 有权
标题翻译：用于冷却翼型的装置
公开(公告)号：US08371815B2
公开(公告)日：2013-02-12
申请号：US12725660
申请日：2010-03-17
申请人： Thomas Raymond Farrell
发明人： Thomas Raymond Farrell
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2260/202
摘要： An apparatus for cooling an airfoil is provided. The airfoil includes an upper airfoil section, a lower airfoil section, at least one cooling passage, and a transition section. The at least one cooling passage is defined at least partially within the lower airfoil section. The at least one cooling passage is configured to flow a cooling medium therethrough, cooling at least a portion of the airfoil. The transition section is disposed between the upper airfoil section and the lower airfoil section and has an outer surface. The outer surface defines at least one cooling hole. The at least one cooling hole is fluidly connected to the at least one cooling passage. At least a portion of the cooling medium is exhausted through the at least one cooling hole.
摘要翻译：提供一种用于冷却翼型的装置。翼型件包括上部翼型部分，下部翼型部分，至少一个冷却通道和过渡部分。至少一个冷却通道至少部分地限定在下翼型部分内。至少一个冷却通道构造成使冷却介质流过其中，冷却翼型的至少一部分。过渡部分设置在上翼部和下翼部之间，并具有外表面。外表面限定至少一个冷却孔。至少一个冷却孔流体地连接到至少一个冷却通道。冷却介质的至少一部分通过至少一个冷却孔排出。

7. 发明申请

US20090005951A1 Systems and Methods for Using a Combustion Dynamics Tuning Algorithm with a Multi-Can Combustor 失效
标题翻译：使用多罐燃烧器的燃烧动力学调整算法的系统和方法
公开(公告)号：US20090005951A1
公开(公告)日：2009-01-01
申请号：US11768751
申请日：2007-06-26
申请人： Garth Frederick , Thomas Raymond Farrell , Timothy Andrew Healy , John Carver Maters , Jonathan Carl Thatcher
发明人： Garth Frederick , Thomas Raymond Farrell , Timothy Andrew Healy , John Carver Maters , Jonathan Carl Thatcher
IPC分类号： G06F19/00
CPC分类号： G05B17/02 , F02C9/28 , F05D2270/13 , F05D2270/70 , F23N1/002 , F23N5/022 , F23N5/184 , F23N2025/04 , F23N2025/08 , F23N2041/20 , F23R2900/00013
摘要： Embodiments of the invention can provide systems and methods for using a combustion dynamics tuning algorithm with a multi-can combustor. According to one embodiment of the invention, a method for controlling a gas turbine engine with an engine model can be implemented for an engine comprising multiple cans. The method can include obtaining operating frequency information associated with multiple cans of the engine. In addition, the method can include determining variation between operating frequency information of at least two cans. Furthermore, the method can include determining a median value based at least in part on the variation. Moreover, the method can include inputting the median value to an engine model, wherein based at least in part on the median value, the engine model determines an engine control action. In addition, the method can include outputting a control command to implement the engine control action.
摘要翻译：本发明的实施例可以提供使用具有多罐燃烧器的燃烧动力学调节算法的系统和方法。根据本发明的一个实施例，可以对于包括多个罐的发动机来实现用于利用发动机模型控制燃气涡轮发动机的方法。该方法可以包括获得与发动机的多个罐相关联的操作频率信息。另外，该方法可以包括确定至少两个罐的工作频率信息之间的变化。此外，该方法可以包括至少部分地基于变化来确定中值。此外，该方法可以包括将中值输入到发动机模型，其中至少部分地基于中值，引擎模型确定发动机控制动作。此外，该方法可以包括输出控制命令以实现发动机控制动作。

8. 发明授权

US07238002B2 Damper seal system and method 失效
标题翻译：阻尼密封系统和方法
公开(公告)号：US07238002B2
公开(公告)日：2007-07-03
申请号：US11265384
申请日：2005-11-03
申请人： Ronald Ralph Cairo , Kevin Leon Bruce , Thomas Raymond Farrell
发明人： Ronald Ralph Cairo , Kevin Leon Bruce , Thomas Raymond Farrell
IPC分类号： F01D5/20
CPC分类号： F01D25/005 , F01D11/005 , F01D11/08 , F01D25/04 , F05D2240/11 , F05D2260/30 , F05D2300/603
摘要： A damper and seal system for a stage of a turbine that includes inner shrouds disposed circumferentially of a hot gas path through the turbine stage and shroud body(s) for supporting the inner shroud(s). A damper block engages a backside surface of the inner shroud and a damping mechanism is carried by the shroud body and connected to the damper block for applying a load to the damper block and inner shroud through the engagement of the block with the backside surface of the inner shroud, thereby damping vibratory movement of the inner shroud. The seal system includes at least one primary, integral seal and at least one secondary, non-integral seal to limit axial and radial hot gas leakage through the stage.
摘要翻译：一种用于涡轮级的阻尼器和密封系统，其包括设置在通过涡轮级的热气路径周向设置并且用于支撑内护罩的护罩体的内护罩。阻尼器块接合内护罩的后侧表面，并且阻尼机构由护罩主体承载并且连接到阻尼器块，用于通过块与其后侧表面的接合来向阻尼块和内护罩施加负载内护罩，从而阻止内护罩的振动运动。密封系统包括至少一个主要的，整体的密封件和至少一个次要的，非整体的密封件，以限制通过该台阶段的轴向和径向的热气体泄漏。

9. 发明授权

US5934687A Gas-path leakage seal for a turbine 失效
标题翻译：涡轮机气道泄漏密封
公开(公告)号：US5934687A
公开(公告)日：1999-08-10
申请号：US888823
申请日：1997-07-07
申请人： Bharat Sampathkumaran Bagepalli , Mahmut Faruk Aksit , Thomas Raymond Farrell
发明人： Bharat Sampathkumaran Bagepalli , Mahmut Faruk Aksit , Thomas Raymond Farrell
IPC分类号： F01D11/00 , F16J15/12 , F16J15/02
CPC分类号： F01D11/005 , F16J15/122 , F23M2900/05005 , F23R2900/00012
摘要： A gas-path leakage seal for generally sealing a gas-path leakage-gap between spaced-apart first and second members of a turbine (such as combustor casing segments of a gas turbine). The seal includes a flexible and generally imperforate metal sheet assemblage having opposing first and second surfaces and two opposing raised edges extending a generally identical distance above and below the surfaces. A first cloth layer assemblage has a thickness generally equal to the previously-defined identical distance and is superimposed on the first surface between the raised edges. A second cloth layer assemblage is generally identical to the first cloth layer assemblage and is superimposed on the second surface between the raised edges.
摘要翻译：一种用于通常密封涡轮机间隔开的第一和第二构件（例如燃气轮机的燃烧器壳体段）之间的气体路径泄漏间隙的气体路径泄漏密封件。密封件包括具有相对的第一和第二表面的柔性和通常无孔的金属板组合件，以及在表面上方和下方延伸大致相同距离的两个相对的凸缘。第一布层组合具有大致等于先前确定的相同距离的厚度，并且叠加在凸起边缘之间的第一表面上。第二布层组合件通常与第一布层组合相同，并且叠置在凸起边缘之间的第二表面上。

10. 发明授权

US07620461B2 Systems and methods for using a combustion dynamics tuning algorithm with a multi-can combustor 失效
标题翻译：使用具有多罐燃烧器的燃烧动力学调谐算法的系统和方法
公开(公告)号：US07620461B2
公开(公告)日：2009-11-17
申请号：US11768751
申请日：2007-06-26
申请人： Garth Frederick, II , Thomas Raymond Farrell , Timothy Andrew Healy , John Carver Maters , Jonathan Carl Thatcher
发明人： Garth Frederick, II , Thomas Raymond Farrell , Timothy Andrew Healy , John Carver Maters , Jonathan Carl Thatcher
IPC分类号： G06F19/00 , F02C9/00
CPC分类号： G05B17/02 , F02C9/28 , F05D2270/13 , F05D2270/70 , F23N1/002 , F23N5/022 , F23N5/184 , F23N2025/04 , F23N2025/08 , F23N2041/20 , F23R2900/00013
摘要： Embodiments of the invention can provide systems and methods for using a combustion dynamics tuning algorithm with a multi-can combustor. According to one embodiment of the invention, a method for controlling a gas turbine engine with an engine model can be implemented for an engine comprising multiple cans. The method can include obtaining operating frequency information associated with multiple cans of the engine. In addition, the method can include determining variation between operating frequency information of at least two cans. Furthermore, the method can include determining a median value based at least in part on the variation. Moreover, the method can include inputting the median value to an engine model, wherein based at least in part on the median value, the engine model determines an engine control action. In addition, the method can include outputting a control command to implement the engine control action.
摘要翻译：本发明的实施例可以提供使用具有多罐燃烧器的燃烧动力学调节算法的系统和方法。根据本发明的一个实施例，可以对于包括多个罐的发动机来实现用于利用发动机模型控制燃气涡轮发动机的方法。该方法可以包括获得与发动机的多个罐相关联的操作频率信息。另外，该方法可以包括确定至少两个罐的工作频率信息之间的变化。此外，该方法可以包括至少部分地基于变化来确定中值。此外，该方法可以包括将中值输入到发动机模型，其中至少部分地基于中值，引擎模型确定发动机控制动作。此外，该方法可以包括输出控制命令以实现发动机控制动作。

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