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公开(公告)号：US20180238177A1
公开(公告)日：2018-08-23
申请号：US15954910
申请日：2018-04-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew A. Turner , Royce E. Tatton , Kristin V. Wood , Matthew R. Satterwhite
IPC: F01D5/22 , B29C70/70 , B29C70/84 , B29C70/86 , F01D11/00 , B29C70/68 , F01D5/02 , B29K707/04 , B29K627/12 , B29K619/00 , B29K309/08 , B29L31/08
Abstract: A fan blade platform is provided. The fan blade platform may include a wall, a first sidewall extending from the flowpath to a circular member, and a second sidewall extending from the flowpath to the circular member. A stiffening member may also extend from the circular member to the flowpath and be formed integrally with the first sidewall, the second sidewall, and the flowpath.
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公开(公告)号：US10018048B2
公开(公告)日：2018-07-10
申请号：US14761360
申请日：2013-12-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Andrew G. Alarcon , Christopher M. Quinn , James Glaspey , Matthew A. Turner
CPC classification number: F01D5/02 , F01D5/025 , F01D5/30 , F01D5/3053 , F01D11/008 , F05D2220/10 , F05D2220/36 , F05D2230/60 , F05D2240/80 , F05D2260/30 , Y02T50/671 , Y02T50/673 , Y10T29/49334
Abstract: Anti-rotation tabs for the platforms in the fan section of a gas turbine engine are provided. The anti-rotation tabs interface with the trailing edge of the spinner, thereby preventing the platform from rotating and twisting.
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公开(公告)号：US09976426B2
公开(公告)日：2018-05-22
申请号：US14805081
申请日：2015-07-21
Applicant: United Technologies Corporation
Inventor： Matthew A. Turner , Royce E. Tatton , Kristin Wood , Matthew Satterwhite
IPC: F01D5/22 , F01D11/00 , B29C70/68 , B29C70/70 , B29C70/84 , B29C70/86 , F01D5/02 , B29K309/08 , B29K619/00 , B29K627/12 , B29K707/04 , B29L31/08
CPC classification number: F01D5/225 , B29C70/682 , B29C70/70 , B29C70/84 , B29C70/865 , B29K2309/08 , B29K2619/00 , B29K2627/12 , B29K2707/04 , B29L2031/082 , F01D5/02 , F01D11/008 , F05D2220/36 , F05D2230/23 , F05D2300/431 , F05D2300/432 , F05D2300/603 , Y02T50/672
Abstract: A fan blade platform is provided. The fan blade platform may include a wall, a first sidewall extending from the flowpath to a circular member, and a second sidewall extending from the flowpath to the circular member. A stiffening member may also extend from the circular member to the flowpath and be formed integrally with the first sidewall, the second sidewall, and the flowpath.
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公开(公告)号：US20160281737A1
公开(公告)日：2016-09-29
申请号：US14850438
申请日：2015-09-10
Applicant: United Technologies Corporation
Inventor： Matthew A. Turner , Colin J. Kling , David A. Topol
CPC classification number: F04D29/526 , F01D5/02 , F01D21/045 , F02C3/04 , F02C7/045 , F04D29/321 , F04D29/325 , F05D2220/32 , F05D2220/36 , F05D2230/23 , F05D2230/30 , F05D2240/35 , F05D2300/17 , F05D2300/43 , Y02T50/671
Abstract: A gas turbine engine impact liner is disclosed. The impact liner may include a base sheet, a plurality of stanchions extending from the base sheet, and a plurality of supports, each being operatively associated with one of the plurality of stanchions.
Abstract translation: 公开了一种燃气涡轮发动机冲击衬垫。 冲击衬垫可以包括基片，从基片延伸的多个支柱，以及多个支撑件，每个支撑件与多个支柱中的一个可操作地相关联。
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15.发明申请GAS TURBINE ENGINE INCLUDING VANE STRUCTURE AND SEAL TO CONTROL FLUID LEAKAGE 有权气体涡轮发动机，包括叶片结构和密封，以控制流体泄漏公开(公告)号：US20150226130A1
公开(公告)日：2015-08-13
申请号：US14428379
申请日：2013-02-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Keith T. Salamon , Matthew A. Turner , Christopher M. Quinn
CPC classification number: F02C7/28 , F01D9/02 , F01D11/001 , F02C3/10 , F05D2220/36
Abstract: A gas turbine engine includes a core engine, a fan coupled to be driven by the core engine, a first case structure around the core engine and a second case structure around the fan. The first case structure and the second case structure define a bypass passage there between. A vane structure includes an airfoil extending radially between the first case structure and the second case structure. A seal is configured to control leakage between the bypass passage and a core engine.
Abstract translation: 燃气涡轮发动机包括核心发动机，联接成由发动机驱动的风扇，围绕铁芯发动机的第一壳体结构和围绕风扇的第二壳体结构。 第一壳体结构和第二壳体结构在其间限定旁路通道。 叶片结构包括在第一壳体结构和第二壳体结构之间径向延伸的翼型件。 密封件构造成控制旁通通道和核心发动机之间的泄漏。
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Patent Agency Ranking
公开(公告)号：US10519784B2
公开(公告)日：2019-12-31
申请号：US15954910
申请日：2018-04-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew A. Turner , Royce E. Tatton , Kristin V. Wood , Matthew R. Satterwhite
IPC: B29C70/68 , F01D5/22 , F01D11/00 , B29C70/70 , B29C70/84 , B29C70/86 , F01D5/02 , B29K105/08 , B29K309/08 , B29K619/00 , B29K627/12 , B29K707/04 , B29L31/08
Abstract: A fan blade platform is provided. The fan blade platform may include a wall, a first sidewall extending from the flowpath to a circular member, and a second sidewall extending from the flowpath to the circular member. A stiffening member may also extend from the circular member to the flowpath and be formed integrally with the first sidewall, the second sidewall, and the flowpath.
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公开(公告)号：US10113559B2
公开(公告)日：2018-10-30
申请号：US14850438
申请日：2015-09-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew A. Turner , Colin J. Kling , David A. Topol
Abstract: A gas turbine engine impact liner is disclosed. The impact liner may include a base sheet, a plurality of stanchions extending from the base sheet, and a plurality of supports, each being operatively associated with one of the plurality of stanchions.
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公开(公告)号：US20180195402A1
公开(公告)日：2018-07-12
申请号：US15116713
申请日：2014-12-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew A. Turner , Andrew G. Alarcon , Shari L. Bugaj
CPC classification number: F01D11/008 , F01D25/005 , F02K3/06 , F04D29/329 , F05D2220/323 , F05D2220/36 , F05D2230/20 , F05D2230/31 , F05D2230/80 , F05D2240/80 , F05D2300/434 , F05D2300/436 , F05D2300/603 , Y02T50/672
Abstract: A fan assembly for a gas turbine engine is disclosed. The fan assembly may include a rotor, a plurality of airfoils extending radially from the rotor, and a platform surrounding the rotor and including a surface that defines a flow path between the plurality of airfoils. The platform may be configured to be disposable during a life of the gas turbine engine.
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公开(公告)号：US20180163743A1
公开(公告)日：2018-06-14
申请号：US15372885
申请日：2016-12-08
Applicant: United Technologies Corporation
Inventor： Matthew A. Turner
CPC classification number: F04D29/388 , F01D5/147 , F01D5/20 , F01D11/122 , F02K3/06 , F04D29/325 , F04D29/526 , F05D2220/36 , F05D2230/23 , F05D2240/307
Abstract: A fan blade includes a tip assembly that is disposed on a blade body. The tip assembly has a leading edge wall disposed proximate a leading edge of the blade body, a trailing edge wall disposed proximate a trailing edge of the blade body, a suction side wall that extends between the leading edge wall and the trailing edge wall, a pressure side wall disposed opposite the suction side wall and extends between the leading edge wall and the trailing edge wall, and a tip wall that extends between the leading edge wall, the trailing edge wall, the suction side wall, and the pressure side wall and is disposed parallel to the tip.
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公开(公告)号：US09909503B2
公开(公告)日：2018-03-06
申请号：US14428379
申请日：2013-02-22
Applicant: United Technologies Corporation
Inventor： Keith T. Salamon , Matthew A. Turner , Christopher M. Quinn
CPC classification number: F02C7/28 , F01D9/02 , F01D11/001 , F02C3/10 , F05D2220/36
Abstract: A gas turbine engine includes a core engine, a fan coupled to be driven by the core engine, a first case structure around the core engine and a second case structure around the fan. The first case structure and the second case structure define a bypass passage there between. A vane structure includes an airfoil extending radially between the first case structure and the second case structure. A seal is configured to control leakage between the bypass passage and a core engine.
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