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公开(公告)号：US20170022824A1
公开(公告)日：2017-01-26
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
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.
Abstract translation: 提供风扇叶片平台。 风扇叶片平台可以包括壁，从流动路径延伸到圆形构件的第一侧壁，以及从流动路径延伸到圆形构件的第二侧壁。 加强构件还可以从圆形构件延伸到流动路径并且与第一侧壁，第二侧壁和流动路径一体地形成。
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公开(公告)号：US20160160680A1
公开(公告)日：2016-06-09
申请号：US14540664
申请日：2014-11-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew A. Turner , Andrew G. Alarcon , Shari L. Bugaj , Glenn Levasseur
CPC classification number: F01D25/005 , F01D5/282 , F01D9/041 , F05D2220/36 , F05D2240/12 , F05D2300/434 , F05D2300/436 , F05D2300/44 , F05D2300/603 , F05D2300/614 , Y02T50/672 , Y02T50/673
Abstract: The present disclosure relates generally to the field of guide vanes for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber structural guide vane for a gas turbine engine.
Abstract translation: 本公开一般涉及用于燃气涡轮发动机的导向叶片领域。 更具体地，本公开涉及一种用于燃气涡轮发动机的压缩短切纤维结构导叶。
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公开(公告)号：US20160159488A1
公开(公告)日：2016-06-09
申请号：US14903987
申请日：2014-07-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James T. Roach , Colin J. Kling , Grant O. Cook , James J. McPhail , Shari L. Bugaj , James F. O'Brien , Majidullah Dehlavi , Scott A. Smith , Matthew R. Rader , Matthew A. Turner , JinQuan Xu
CPC classification number: B64D29/00 , B29D22/00 , F01D5/02 , F01D25/28 , F02K3/04 , F05D2220/32 , F05D2230/30 , F05D2230/90 , F05D2300/10 , F05D2300/43 , F05D2300/603 , Y02T50/672
Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.
Abstract translation: 公开了用于制造轻质电镀聚合物燃气涡轮发动机部件的电镀聚合物燃气涡轮发动机部件和方法。 这些部件包括镀有一个或多个金属层的聚合物基材。 聚合物基材的聚合材料可以用可以包括碳，金属或玻璃的材料在结构上加强。 聚合物基底还可以包括多个层以形成复合铺层结构。
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公开(公告)号：US20160032729A1
公开(公告)日：2016-02-04
申请号：US14711192
申请日：2015-05-13
Applicant: United Technologies Corporation
Inventor： Matthew A. Turner
CPC classification number: F01D5/147 , F01D5/282 , F02K3/06 , F05D2220/36 , F05D2300/612 , F05D2300/614 , Y02T50/672
Abstract: A composite fan blade for a gas turbine engine is disclosed. The fan blade may include a core being made of a first material and a shell enclosing the core. The shell may be made of a second material and the second material may have less plasticity than the first material.
Abstract translation: 公开了一种用于燃气涡轮发动机的复合风扇叶片。 风扇叶片可以包括由第一材料制成的芯和封闭芯的外壳。 壳可以由第二材料制成，并且第二材料可以具有比第一材料更少的可塑性。
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公开(公告)号：US11267576B2
公开(公告)日：2022-03-08
申请号：US14903987
申请日：2014-07-09
Applicant: United Technologies Corporation
Inventor： James T. Roach , Colin J. Kling , Grant O. Cook, III , James J. McPhail , Shari L. Bugaj , James F. O'Brien , Majidullah Dehlavi , Scott A. Smith , Matthew R. Rader , Matthew A. Turner , JinQuan Xu
Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.
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Patent Agency Ranking
公开(公告)号：US20150275757A1
公开(公告)日：2015-10-01
申请号：US14430709
申请日：2013-03-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew A. Turner , Keith T. Salamon , Barry M. Ford
CPC classification number: F02C7/04 , B64D33/02 , B64D2033/0226 , F01D17/105 , F02C7/18 , F02K3/075 , F05D2240/12 , F05D2250/52 , F05D2260/606 , Y10T137/0536
Abstract: A disclosed gas turbine engine includes a fan including a plurality of fan blades rotatable about an engine axis and core engine disposed within a core nacelle for driving the fan. A bypass passage is defined between the core nacelle and an outer or fan nacelle. A duct mounted within the core nacelle defines a bleed air flow path for directing bleed air from the core engine into the bypass passage. The bleed air duct includes a plurality of airfoils disposed at a defined chord angle for directing bleed airflow into the bypass passage to minimize disruption to bypass airflow.
Abstract translation: 所公开的燃气涡轮发动机包括：风扇，包括可围绕发动机轴线旋转的多个风扇叶片和设置在用于驱动风扇的核心机舱内的核心发动机。 在核心机舱和外部或风扇机舱之间限定旁路通道。 安装在核心机舱内的管道限定了用于将排气从核心发动机引导到旁路通道中的排气流动路径。 排气管道包括以限定的弦角设置的多个翼型件，用于将排气流引导到旁路通道中以最小化对旁路气流的破坏。
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公开(公告)号：US20150337661A1
公开(公告)日：2015-11-26
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 , 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.
Abstract translation: 提供了用于燃气涡轮发动机的风扇部分中的平台的防旋转突出部。 防旋转翼片与旋转器的后缘接合，从而防止平台旋转和扭转。
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公开(公告)号：US20150204201A1
公开(公告)日：2015-07-23
申请号：US14421645
申请日：2013-03-15
Applicant: United Technologies Corporation
Inventor： Matthew A. Turner , Andrew G. Alarcon , James Glaspey , Brian Green , Barry M. Ford , Renee J. Jurek
CPC classification number: F01D5/30 , F01D5/02 , F01D5/143 , F01D5/145 , F01D11/008 , F05D2220/32 , F05D2240/55 , Y02T50/673
Abstract: A spacer assembly for a rotor assembly of a gas turbine engine includes an endwall segment having a non-axisymmetric flowpath surface, a first depression and a second depression. A perimeter of the flowpath surface includes a forward edge, an aft edge, a suction side edge and a pressure side edge. The first depression is formed along the flowpath surface adjoining the suction side edge, and the second depression is formed along the flowpath surface adjoining the pressure side edge.
Abstract translation: 用于燃气涡轮发动机的转子组件的间隔件组件包括具有非轴对称流路表面的端壁段，第一凹陷和第二凹陷。 流路表面的周边包括前边缘，后边缘，吸力侧边缘和压力侧边缘。 第一凹部沿着与吸力侧边缘相邻的流路面形成，第二凹部沿着与压力侧边缘相邻的流路面形成。
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公开(公告)号：US11268526B2
公开(公告)日：2022-03-08
申请号：US14903996
申请日：2014-07-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James T. Roach , Barry Barnett , Grant O. Cook, III , Charles R. Watson , Shari L. Bugaj , Glenn LeVasseur , Wendell V. Twelves, Jr. , Christopher J. Hertel , Colin J. Kling , Matthew A. Turner , JinQuan Xu , Steven Clarkson , Michael Caulfield
IPC: F01D5/28 , F04D19/00 , F01D5/14 , B32B27/34 , B32B1/08 , B32B1/00 , B32B27/28 , B32B27/36 , F01D5/26 , F01D9/04 , F01D25/02 , F01D25/24 , F04D29/38 , F04D29/54
Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.
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公开(公告)号：US10344601B2
公开(公告)日：2019-07-09
申请号：US14421645
申请日：2013-03-15
Applicant: United Technologies Corporation
Inventor： Matthew A. Turner , Andrew G. Alarcon , James Glaspey , Brian Green , Barry M. Ford , Renee J. Jurek
Abstract: A spacer assembly for a rotor assembly of a gas turbine engine includes an endwall segment having a non-axisymmetric flowpath surface, a first depression and a second depression. A perimeter of the flowpath surface includes a forward edge, an aft edge, a suction side edge and a pressure side edge. The first depression is formed along the flowpath surface adjoining the suction side edge, and the second depression is formed along the flowpath surface adjoining the pressure side edge.
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