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公开(公告)号：WO2014081500A3
公开(公告)日：2014-08-21
申请号：PCT/US2013059746
申请日：2013-09-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERTSON THOMAS J , CLARKSON STEVEN , COSTA MARK W
IPC: F16M13/00
CPC classification number: F02C7/32 , F01D21/045 , F02C7/20 , F05D2220/32 , F05D2240/90 , F05D2260/30 , F05D2260/311
Abstract: A mount for mounting a component to a gas turbine engine is disclosed. The mount may include a central portion that attaches to the component, and a flange circumscribing the central portion and extending to the gas turbine engine, the flange including a fusible region that breaks at a predetermined load. A method for protecting a component mounted to a gas turbine engine is also disclosed. The method may include attaching a mount to a casing of the gas turbine engine, the mount including a fusible region that breaks at a predetermined load. The method may further include attaching the component to the mount. The method may further include the fusible region breaking when the mount experiences the predetermined load, detaching the component from the casing of the gas turbine engine.
Abstract translation: 公开了一种用于将部件安装到燃气涡轮发动机的支架。 所述安装件可以包括附接到所述部件的中央部分和限定所述中央部分并且延伸到所述燃气涡轮发动机的凸缘，所述凸缘包括在预定载荷下断裂的可熔区域。 还公开了一种用于保护安装到燃气涡轮发动机的部件的方法。 该方法可以包括将安装件附接到燃气涡轮发动机的壳体，安装件包括在预定负载下断裂的可熔区域。 该方法可以进一步包括将部件附接到安装件。 该方法可进一步包括当安装件经历预定负载时可熔区断裂，从燃气涡轮发动机的壳体分离该部件。
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公开(公告)号：CA2917884A1
公开(公告)日：2015-01-15
申请号：CA2917884
申请日：2014-07-09
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROACH JAMES T , BARNETT BERRY , COOK GRANT O III , WATSON CHARLES R , BUGAJ SHARI L , LEVASSEUR GLENN , TWELVES WENDELL V JR , HERTEL CHRISTOPHER J , KLING COLIN J , TURNER MATTHEW A , XU JINQUAN , CLARKSON STEVEN , CAULFIELD MICHAEL
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：WO2015073097A3
公开(公告)日：2015-07-16
申请号：PCT/US2014052924
申请日：2014-08-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CLARKSON STEVEN , COSTA MARK W
CPC classification number: F01D25/02 , B29C53/56 , B29C65/00 , B29C70/06 , B29C70/32 , B29K2063/00 , B29K2105/12 , B29K2105/256 , B29K2309/08 , B29K2995/0089 , B29L2031/082 , B29L2031/3076 , F01D21/045 , F01D25/24 , F05D2220/36 , F05D2230/30 , Y02T50/672
Abstract: The present disclosure relates to methods of manufacturing ice panel segments for turbofan engines. An ice panel material may be wrapped around a mandrel. The ice panel material may include an inner fiberglass layer, a plurality of KEVLAR® layers, and an outer fiberglass layer. The ice panel material may be bagged and cured into a rigid molded cylinder. The rigid molded cylinder may be radially cut into ice panel cylinders. The ice panel cylinders may be axially cut into ice panel segments. The ice panel segments may be bonded to an inner surface of a fan case.
Abstract translation: 本公开涉及制造用于涡轮风扇发动机的冰块区段的方法。 冰板材料可以缠绕在心轴上。 冰板材料可以包括内部玻璃纤维层，多个KEVLAR层和外部玻璃纤维层。 冰板材料可以装袋并固化成刚性模制圆筒。 刚性模制圆筒可以被径向切割成冰面板圆筒。 冰面板滚筒可以被轴向切割成冰块区段。 冰块区段可以结合到风扇外壳的内表面。
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公开(公告)号：WO2015080787A2
公开(公告)日：2015-06-04
申请号：PCT/US2014055593
申请日：2014-09-15
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CLARKSON STEVEN
IPC: F02K1/78
CPC classification number: F01D25/02 , F01D21/14 , F01D25/24 , F02K1/78 , F02K1/82 , F05D2220/323 , F05D2230/53 , F05D2240/11 , F05D2240/14 , F05D2260/607 , F05D2300/43 , F05D2300/603 , Y02T50/672 , Y02T50/675
Abstract: A jet engine fan case is disclosed. The fan case may comprise an ice liner section and a rear liner section, wherein the ice liner section and the rear liner section are constructed from a constructed from a single, integral material. The ice liner section may comprise fiberglass and the rear liner section comprises fiberglass, such that the combined liner comprises a single piece. The combined liner may comprise a plurality of segments in the range of one segment to nine segments. The ice liner section may comprise a first cross-sectional profile and the rear liner section may comprise a second cross-sectional profile. The ice liner section may comprise a first cross-sectional profile and the rear liner section may comprise a second cross-sectional profile that is less than the first cross-sectional profile. The combined liner may comprise an uninterrupted aerodynamic surface.
Abstract translation: 公开了一种喷气发动机风扇箱。 风扇壳体可以包括冰套和后衬套部分，其中，所述冰套和所述后衬套部分由构成单一的整体材料构成。 冰盖部分可以包括玻璃纤维，并且后衬里部分包括玻璃纤维，使得组合的衬垫包括单件。 组合的衬垫可以包括在一个段到九个段的范围内的多个段。 冰衬层部分可以包括第一横截面轮廓，并且后衬里部分可以包括第二横截面轮廓。 冰衬层部分可以包括第一横截面轮廓，并且后衬里部分可以包括小于第一横截面轮廓的第二横截面轮廓。 组合衬套可以包括不间断的空气动力学表面。
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公开(公告)号：WO2015006433A2
公开(公告)日：2015-01-15
申请号：PCT/US2014045928
申请日：2014-07-09
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROACH JAMES T , BARNETT BARRY , COOK III GRANT O , WATSON CHARLES R , BUGAJ SHARI L , LEVASSEUR GLENN , TWELVES WENDELL V JR , HERTEL CHRISTOPHER J , KLING COLIN J , TURNER MATTHEW A , XU JINQUAN , CLARKSON STEVEN , CAULFIELD MICHAEL
CPC classification number: F04D19/002 , B32B1/00 , B32B1/08 , B32B27/281 , B32B27/285 , B32B27/34 , B32B27/36 , B32B2255/10 , B32B2255/205 , B32B2262/101 , B32B2262/103 , B32B2262/106 , B32B2270/00 , B32B2307/554 , F01D5/147 , F01D5/26 , F01D5/282 , F01D5/286 , F01D9/041 , F01D25/02 , F01D25/24 , F04D29/388 , F04D29/541 , F05D2220/32 , F05D2230/90 , F05D2240/00 , F05D2240/12 , F05D2240/30 , F05D2260/96 , F05D2300/10 , F05D2300/43 , F05D2300/603 , Y02T50/672 , Y02T50/673
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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Patent Agency Ranking
公开(公告)号：EP2904214A4
公开(公告)日：2016-08-31
申请号：EP13844100
申请日：2013-02-22
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERTSON THOMAS J , VOLETI SREENIVASA R , COSTA MARK W , CLARKSON STEVEN
CPC classification number: F01D25/24 , F01D5/021 , F01D5/147 , F01D5/28 , F01D21/045 , F01D25/30 , F05D2220/30 , F05D2240/24 , F05D2250/283 , F05D2300/121 , F05D2300/173 , F05D2300/612 , Y02T50/672
Abstract: A blade containment system includes a plurality of circumferentially-arranged rotatable blades. Each blade has a blade compliance. An annular containment structure is arranged around the rotatable blades. The containment structure includes a liner that has a liner compliance. The blade compliance and the liner compliance are configured such that a strain induced on a respective one of the blades upon impact with the liner is less than a threshold critical strain beyond which the rotatable blades fracture.
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公开(公告)号：EP3084178A4
公开(公告)日：2016-12-28
申请号：EP14871637
申请日：2014-12-08
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CLARKSON STEVEN , BERGETHON RICHARD B
IPC: F02C7/05
CPC classification number: F04D29/526 , F01D21/045 , F02C7/045 , F02C7/05 , F02K3/06 , F04D29/325 , F04D29/38 , F05D2220/32 , F05D2220/36 , F05D2250/283 , F05D2300/43 , F05D2300/603 , Y02T50/672
Abstract: A liner assembly for lining of a gas turbine engine includes a honeycomb core having at least two axially adjacent segments, including a forward segment and an aft segment. An impact resistant layer is disposed against and radially inward of the honeycomb forward segment. A radially interior layer, defining a relatively substantially uninterrupted flowpath over at least a portion of the impact resistant layer and the aft segment, extends against and radially interior of both the impact resistant layer and the honeycomb aft segment.
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公开(公告)号：EP2901067A4
公开(公告)日：2016-05-25
申请号：EP13856339
申请日：2013-09-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERTSON THOMAS J , CLARKSON STEVEN , COSTA MARK W
CPC classification number: F02C7/32 , F01D21/045 , F02C7/20 , F05D2220/32 , F05D2240/90 , F05D2260/30 , F05D2260/311
Abstract: A mount for mounting a component to a gas turbine engine is disclosed. The mount may include a central portion that attaches to the component, and a flange circumscribing the central portion and extending to the gas turbine engine, the flange including a fusible region that breaks at a predetermined load. A method for protecting a component mounted to a gas turbine engine is also disclosed. The method may include attaching a mount to a casing of the gas turbine engine, the mount including a fusible region that breaks at a predetermined load. The method may further include attaching the component to the mount. The method may further include the fusible region breaking when the mount experiences the predetermined load, detaching the component from the casing of the gas turbine engine.
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公开(公告)号：EP3019710A4
公开(公告)日：2017-05-10
申请号：EP14822947
申请日：2014-07-09
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROACH JAMES T , BARNETT BARRY , COOK III GRANT O , WATSON CHARLES R , BUGAJ SHARI L , LEVASSEUR GLENN , TWELVES WENDELL V JR , HERTEL CHRISTOPHER J , KLING COLIN J , TURNER MATTHEW A , XU JINQUAN , CLARKSON STEVEN , CAULFIELD MICHAEL
CPC classification number: F04D19/002 , B32B1/00 , B32B1/08 , B32B27/281 , B32B27/285 , B32B27/34 , B32B27/36 , B32B2255/10 , B32B2255/205 , B32B2262/101 , B32B2262/103 , B32B2262/106 , B32B2270/00 , B32B2307/554 , F01D5/147 , F01D5/26 , F01D5/282 , F01D5/286 , F01D9/041 , F01D25/02 , F01D25/24 , F04D29/388 , F04D29/541 , F05D2220/32 , F05D2230/90 , F05D2240/00 , F05D2240/12 , F05D2240/30 , F05D2260/96 , F05D2300/10 , F05D2300/43 , F05D2300/603 , Y02T50/672 , Y02T50/673
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10.发明公开COMBINED FAN CASE ICE LINER AND REAR LINER 审中-公开HOMTERIERTE EISISOLIERUNG日内瓦ISRIERUNGFÜRVENTILATORGEHÄUSE
公开(公告)号：EP3049643A4
公开(公告)日：2016-10-12
申请号：EP14866210
申请日：2014-09-15
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CLARKSON STEVEN
CPC classification number: F01D25/02 , F01D21/14 , F01D25/24 , F02K1/78 , F02K1/82 , F05D2220/323 , F05D2230/53 , F05D2240/11 , F05D2240/14 , F05D2260/607 , F05D2300/43 , F05D2300/603 , Y02T50/672 , Y02T50/675
Abstract: A jet engine fan case is disclosed. The fan case may comprise an ice liner section and a rear liner section, wherein the ice liner section and the rear liner section are constructed from a constructed from a single, integral material. The ice liner section may comprise fiberglass and the rear liner section comprises fiberglass, such that the combined liner comprises a single piece. The combined liner may comprise a plurality of segments in the range of one segment to nine segments. The ice liner section may comprise a first cross-sectional profile and the rear liner section may comprise a second cross-sectional profile. The ice liner section may comprise a first cross-sectional profile and the rear liner section may comprise a second cross-sectional profile that is less than the first cross-sectional profile. The combined liner may comprise an uninterrupted aerodynamic surface.
Abstract translation: 公开了一种喷气发动机风扇箱。 风扇壳体可以包括冰套和后衬套部分，其中，所述冰套和所述后衬套部分由构成单一的整体材料构成。 冰衬层部分可以包括玻璃纤维，并且后衬里部分包括玻璃纤维，使得组合的衬垫包括单件。 组合衬垫可以包括在一个段到九个段的范围内的多个段。 冰衬层部分可以包括第一横截面轮廓，并且后衬里部分可以包括第二横截面轮廓。 冰衬层部分可以包括第一横截面轮廓，并且后衬里部分可以包括小于第一横截面轮廓的第二横截面轮廓。 组合衬套可以包括不间断的空气动力学表面。
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