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公开(公告)号：US20110146230A1
公开(公告)日：2011-06-23
申请号：US12827801
申请日：2010-06-30
Applicant: Donald George LaChapelle , Christopher Charles Glynn , Donald Lee Gardner , Stephen Craig Mitchell , Mullahalli Venkataramaniah Srinivas , Edward Atwood Rainous , David Lance Pennekamp
Inventor： Donald George LaChapelle , Christopher Charles Glynn , Donald Lee Gardner , Stephen Craig Mitchell , Mullahalli Venkataramaniah Srinivas , Edward Atwood Rainous , David Lance Pennekamp
CPC classification number: B64D27/26 , B64D27/18 , B64D2027/264 , B64D2027/266 , B64D2027/268
Abstract: An assembly includes a unitary nacelle structure and an integrated fan housing for a gas turbine engine assembly. The unitary nacelle structure includes an inlet region and a fan cowl region, and is configured to at least partially circumscribe the integrated fan housing. The integrated fan housing comprises an integral composite structure and includes a fan case sized and configured for encircling a fan blade assembly of an associated gas turbine engine, a fan hub, and a plurality of fan outlet guide vanes. The unitary nacelle structure cooperates with the integrated fan housing to transfer static and dynamic loads directly to a support structure, rather than through the engine core, to minimize backbone bending.
Abstract translation: 组件包括单一的机舱结构和用于燃气涡轮发动机组件的集成风扇壳体。 整体式机舱结构包括入口区域和风扇整流罩区域，并且被配置为至少部分地围绕集成风扇壳体。 集成风扇壳体包括整体复合结构，并且包括风扇壳体，其尺寸和构造用于环绕相关联的燃气涡轮发动机，风扇轮毂和多个风扇出口导叶的风扇叶片组件。 整体式机舱结构与集成的风扇壳体配合，将静态和动态载荷直接传递到支撑结构，而不是通过发动机芯，以最大限度地减少主干弯曲。
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公开(公告)号：US20090037035A1
公开(公告)日：2009-02-05
申请号：US11833596
申请日：2007-08-03
Applicant: John Erik Hershey , Brock Estel Osborn , Donald Lee Gardner , Rafael Jose Ruiz , William Lee Herron
Inventor： John Erik Hershey , Brock Estel Osborn , Donald Lee Gardner , Rafael Jose Ruiz , William Lee Herron
CPC classification number: F01D11/24 , F02C9/00 , F02C9/26 , F02C9/48 , F05D2270/305 , F05D2270/44 , F05D2270/70
Abstract: A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin adjusting the tip clearance by expanding or contracting the shroud before the engine command and may be based on monitored aircraft and/or aircraft crew data indicative of the engine. The aircraft and/or aircraft crew data may include communications between aircraft crew and air traffic control authorities or air traffic control surrogates. Determining when to begin adjusting the tip clearance may include using learning algorithms which may use the aircraft gas turbine engine's operating experience and/or operating experience of other jet engines on an aircraft containing the aircraft gas turbine engine and/or on other aircraft.
Abstract translation: 一种方法和系统预期在改变发动机转速的发动机命令之前和之前调整旋转飞机燃气涡轮发动机叶片尖端和周围罩之间的叶片顶端间隙。 该方法可以包括通过在发动机命令之前扩展或收缩护罩来确定何时开始调整顶端间隙，并且可以基于指示发动机的受监视的飞行器和/或飞机机组数据。 飞机和/或飞机机组数据可以包括飞机机组人员和空中交通管制机构或空中交通管制代理人之间的通信。 确定何时开始调整尖端间隙可以包括使用学习算法，其可以使用飞机燃气涡轮发动机在包含飞机燃气涡轮发动机的飞机和/或其它飞行器上的其它喷气发动机的操作经验和/或操作经验。
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公开(公告)号：US08876042B2
公开(公告)日：2014-11-04
申请号：US12827801
申请日：2010-06-30
Applicant: Donald George LaChapelle , Christopher Charles Glynn , Donald Lee Gardner , Stephen Craig Mitchell , Mullahalli Venkataramaniah Srinivas , Edward Atwood Rainous , David Lance Pennekamp
Inventor： Donald George LaChapelle , Christopher Charles Glynn , Donald Lee Gardner , Stephen Craig Mitchell , Mullahalli Venkataramaniah Srinivas , Edward Atwood Rainous , David Lance Pennekamp
CPC classification number: B64D27/26 , B64D27/18 , B64D2027/264 , B64D2027/266 , B64D2027/268
Abstract: An assembly includes a unitary nacelle structure and an integrated fan housing for a gas turbine engine assembly. The unitary nacelle structure includes an inlet region and a fan cowl region, and is configured to at least partially circumscribe the integrated fan housing. The integrated fan housing comprises an integral composite structure and includes a fan case sized and configured for encircling a fan blade assembly of an associated gas turbine engine, a fan hub, and a plurality of fan outlet guide vanes. The unitary nacelle structure cooperates with the integrated fan housing to transfer static and dynamic loads directly to a support structure, rather than through the engine core, to minimize backbone bending.
Abstract translation: 组件包括单一的机舱结构和用于燃气涡轮发动机组件的集成风扇壳体。 整体式机舱结构包括入口区域和风扇整流罩区域，并且被配置为至少部分地围绕集成风扇壳体。 集成风扇壳体包括整体复合结构，并且包括风扇壳体，其尺寸和构造用于环绕相关联的燃气涡轮发动机，风扇轮毂和多个风扇出口导叶的风扇叶片组件。 整体式机舱结构与集成的风扇壳体配合，将静态和动态载荷直接传递到支撑结构，而不是通过发动机芯，以最大程度减少主干弯曲。
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公开(公告)号：US20130081270A1
公开(公告)日：2013-04-04
申请号：US13249868
申请日：2011-09-30
Applicant: David Bruce Patterson , Donald Michael Corsmeier , Craig Douglas Young , Donald Lee Gardner , James Edward Thompson , Daniel Dale Brown , Glenn Edward Wiehe
Inventor： David Bruce Patterson , Donald Michael Corsmeier , Craig Douglas Young , Donald Lee Gardner , James Edward Thompson , Daniel Dale Brown , Glenn Edward Wiehe
CPC classification number: F23R3/50 , F23R3/002 , F23R3/60 , Y02E20/16 , Y10T29/49229 , Y10T29/4932
Abstract: A method of assembling a combustion system for a gas turbine engine includes providing a combustion chamber frame, an inner casing structure, and an outer casing structure. The method also includes mounting the combustion chamber frame between the inner casing structure and the outer casing structure such that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure.
Abstract translation: 一种组装燃气涡轮发动机的燃烧系统的方法包括提供燃烧室框架，内壳结构和外壳结构。 该方法还包括将燃烧室框架安装在内壳结构和外壳结构之间，使得燃烧室框架联接到内壳结构和外壳结构。
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公开(公告)号：US08126628B2
公开(公告)日：2012-02-28
申请号：US11833596
申请日：2007-08-03
Applicant: John Erik Hershey , Brock Estel Osborn , Donald Lee Gardner , Rafael Jose Ruiz , William Lee Herron
Inventor： John Erik Hershey , Brock Estel Osborn , Donald Lee Gardner , Rafael Jose Ruiz , William Lee Herron
CPC classification number: F01D11/24 , F02C9/00 , F02C9/26 , F02C9/48 , F05D2270/305 , F05D2270/44 , F05D2270/70
Abstract: A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin adjusting the tip clearance by expanding or contracting the shroud before the engine command and may be based on monitored aircraft and/or aircraft crew data indicative of the engine. The aircraft and/or aircraft crew data may include communications between aircraft crew and air traffic control authorities or air traffic control surrogates. Determining when to begin adjusting the tip clearance may include using learning algorithms which may use the aircraft gas turbine engine's operating experience and/or operating experience of other jet engines on an aircraft containing the aircraft gas turbine engine and/or on other aircraft.
Abstract translation: 一种方法和系统预期在改变发动机转速的发动机命令之前和之前调整旋转飞机燃气涡轮发动机叶片尖端和周围罩之间的叶片顶端间隙。 该方法可以包括通过在发动机命令之前扩展或收缩护罩来确定何时开始调整顶端间隙，并且可以基于指示发动机的受监视的飞行器和/或飞机机组数据。 飞机和/或飞机机组数据可以包括飞机机组人员和空中交通管制机构或空中交通管制代理人之间的通信。 确定何时开始调整尖端间隙可以包括使用学习算法，其可以使用飞机燃气涡轮发动机在包含飞机燃气涡轮发动机的飞机和/或其它飞行器上的其它喷气发动机的操作经验和/或操作经验。
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Patent Agency Ranking
公开(公告)号：US20100329863A1
公开(公告)日：2010-12-30
申请号：US12494610
申请日：2009-06-30
Applicant: Nicholas Joseph Kray , David W. Crall , Daniel E. Mollmann , Donald Lee Gardner , Marcia Boyle Johnson , Howard P. Weaver , Max Robert Farson
Inventor： Nicholas Joseph Kray , David W. Crall , Daniel E. Mollmann , Donald Lee Gardner , Marcia Boyle Johnson , Howard P. Weaver , Max Robert Farson
CPC classification number: F01D5/20 , F01D11/122 , F05D2240/303 , F05D2240/307 , Y02T50/672 , Y10T29/4932
Abstract: A method for reducing tip rub loads in a rotor blade is described having the steps of selecting a location of contact between the rotor blade and a static structure; selecting a location on the blade for incorporating a tip-cutter; selecting a cutter-profile for the tip-cutter; and incorporating the tip-cutter on the selected location on the blade such that tip-cutter is capable of removing a portion of the static structure during a tip rub such that tip rub loads are facilitated to be reduced.
Abstract translation: 描述了一种用于减小转子叶片中的尖端摩擦负荷的方法，其具有选择转子叶片和静态结构之间的接触位置的步骤; 选择刀片上的一个位置以结合尖端切割器; 选择尖端铣刀的刀具轮廓; 并将尖端切割器结合在刀片上的选定位置，使得尖端切割器能够在尖端摩擦期间移除静态结构的一部分，从而有助于降低尖端摩擦载荷。
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公开(公告)号：US08893382B2
公开(公告)日：2014-11-25
申请号：US13249868
申请日：2011-09-30
Applicant: David Bruce Patterson , Donald Michael Corsmeier , Craig Douglas Young , Donald Lee Gardner , James Edward Thompson , Daniel Dale Brown , Glenn Edward Wiehe , Donald Scott Yeager , Mark Willard Marusko , Michael Joseph Zerbe
Inventor： David Bruce Patterson , Donald Michael Corsmeier , Craig Douglas Young , Donald Lee Gardner , James Edward Thompson , Daniel Dale Brown , Glenn Edward Wiehe , Donald Scott Yeager , Mark Willard Marusko , Michael Joseph Zerbe
CPC classification number: F23R3/50 , F23R3/002 , F23R3/60 , Y02E20/16 , Y10T29/49229 , Y10T29/4932
Abstract: A method of assembling a combustion system for a gas turbine engine includes providing a combustion chamber frame, an inner casing structure, and an outer casing structure. The method also includes mounting the combustion chamber frame between the inner casing structure and the outer casing structure such that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure.
Abstract translation: 一种组装燃气涡轮发动机的燃烧系统的方法包括提供燃烧室框架，内壳结构和外壳结构。 该方法还包括将燃烧室框架安装在内壳结构和外壳结构之间，使得燃烧室框架联接到内壳结构和外壳结构。
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公开(公告)号：US20100329875A1
公开(公告)日：2010-12-30
申请号：US12494595
申请日：2009-06-30
Applicant: Nicholas Joseph Kray , David W. Crall , Daniel E. Mollmann , Donald Lee Gardner , Marcia Boyle Johnson , Haward P. Weaver , Max Robert Farson
Inventor： Nicholas Joseph Kray , David W. Crall , Daniel E. Mollmann , Donald Lee Gardner , Marcia Boyle Johnson , Haward P. Weaver , Max Robert Farson
CPC classification number: F01D11/122 , F01D5/20 , F05D2220/36 , F05D2240/303 , F05D2240/307 , Y02T50/672
Abstract: An airfoil for use in a rotor assembly is disclosed, the airfoil having a tip-cutter located on a sidewall near a tip portion, wherein the tip-cutter is capable of removing a portion of an abradable material during a tip rub. In another embodiment, an airfoil has a tip-grinder located on the tip portion, wherein the tip-grinder capable of removing a portion of an abradable material during a tip rub. In another embodiment, an airfoil has a tip-rake that facilitates reducing loading induced to said airfoil during tip rubs.
Abstract translation: 公开了一种用于转子组件的翼型件，翼型件具有位于靠近顶端部分的侧壁上的尖端切割器，其中尖端切割器能够在尖端摩擦期间去除可磨损材料的一部分。 在另一个实施例中，翼型件具有位于尖端部分上的尖端磨床，其中尖端磨床能够在尖端摩擦期间去除可磨损材料的一部分。 在另一个实施例中，翼型件具有尖耙，其有助于减少在尖端摩擦期间引起的所述翼型的载荷。
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公开(公告)号：US08662834B2
公开(公告)日：2014-03-04
申请号：US12494610
申请日：2009-06-30
Applicant: Nicholas Joseph Kray , David W. Crall , Daniel E. Mollmann , Donald Lee Gardner , Marcia Boyle Johnson , Howard P. Weaver , Max Robert Farson
Inventor： Nicholas Joseph Kray , David W. Crall , Daniel E. Mollmann , Donald Lee Gardner , Marcia Boyle Johnson , Howard P. Weaver , Max Robert Farson
IPC: F01D11/12
CPC classification number: F01D5/20 , F01D11/122 , F05D2240/303 , F05D2240/307 , Y02T50/672 , Y10T29/4932
Abstract: A method for reducing tip rub loads in a rotor blade is described having the steps of selecting a location of contact between the rotor blade and a static structure; selecting a location on the blade for incorporating a tip-cutter; selecting a cutter-profile for the tip-cutter; and incorporating the tip-cutter on the selected location on the blade such that tip-cutter is capable of removing a portion of the static structure during a tip rub such that tip rub loads are facilitated to be reduced.
Abstract translation: 描述了一种用于减小转子叶片中的尖端摩擦负荷的方法，其具有选择转子叶片和静态结构之间的接触位置的步骤; 选择刀片上的一个位置以结合尖端切割器; 选择尖端铣刀的刀具轮廓; 并将尖端切割器结合在刀片上的选定位置，使得尖端切割器能够在尖端摩擦期间移除静态结构的一部分，从而有助于降低尖端摩擦载荷。
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公开(公告)号：US08657570B2
公开(公告)日：2014-02-25
申请号：US12494595
申请日：2009-06-30
Applicant: Nicholas Joseph Kray , David W. Crall , Daniel E. Mollmann , Donald Lee Gardner , Marcia Boyle Johnson , Howard P. Weaver , Max Robert Farson
Inventor： Nicholas Joseph Kray , David W. Crall , Daniel E. Mollmann , Donald Lee Gardner , Marcia Boyle Johnson , Howard P. Weaver , Max Robert Farson
IPC: F01D11/12
CPC classification number: F01D11/122 , F01D5/20 , F05D2220/36 , F05D2240/303 , F05D2240/307 , Y02T50/672
Abstract: An airfoil for use in a rotor assembly is disclosed, the airfoil having a tip-cutter located on a sidewall near a tip portion, wherein the tip-cutter is capable of removing a portion of an abradable material during a tip rub. In another embodiment, an airfoil has a tip-grinder located on the tip portion, wherein the tip-grinder capable of removing a portion of an abradable material during a tip rub. In another embodiment, an airfoil has a tip-rake that facilitates reducing loading induced to said airfoil during tip rubs.
Abstract translation: 公开了一种用于转子组件的翼型件，翼型件具有位于靠近顶端部分的侧壁上的尖端切割器，其中尖端切割器能够在尖端摩擦期间去除可磨损材料的一部分。 在另一个实施例中，翼型件具有位于尖端部分上的尖端磨床，其中尖端磨床能够在尖端摩擦期间去除可磨损材料的一部分。 在另一个实施例中，翼型件具有尖耙，其有助于减少在尖端摩擦期间引起的所述翼型的载荷。
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