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公开(公告)号：WO2015073097A2
公开(公告)日：2015-05-21
申请号：PCT/US2014/052924
申请日：2014-08-27
Applicant: UNITED TECHNOLOGIES CORPORATION
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面板段的方法。 冰面板材料可以缠绕在心轴上。 冰面板材料可以包括内玻璃纤维层，多个KEVLAR层和外玻璃纤维层。 冰块材料可以装袋并固化成刚性模制圆筒。 刚性模制圆柱体可以径向切割成冰面板圆筒。 冰面板圆柱体可以轴向切割成冰块段。 冰面板段可以结合到风扇壳体的内表面。
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公开(公告)号：WO2014055105A1
公开(公告)日：2014-04-10
申请号：PCT/US2013/027229
申请日：2013-02-22
Applicant: UNITED TECHNOLOGIES CORPORATION
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.
Abstract translation: 刀片容纳系统包括多个周向布置的可旋转刀片。 每个刀片具有刀片顺应性。 围绕可旋转叶片设置环形容纳结构。 密封结构包括具有衬垫柔顺性的衬垫。 叶片顺应性和衬套顺应性被构造成使得在与衬套撞击时在相应的一个叶片上引起的应变小于阈值临界应变，超过该临界应变可旋转叶片断裂。
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公开(公告)号：WO2014093290A1
公开(公告)日：2014-06-19
申请号：PCT/US2013/074024
申请日：2013-12-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： COSTA, Mark W. , ROBERTSON, Thomas J. , LUSSIER, Darin S.
CPC classification number: F01D21/045 , F05D2300/121 , F05D2300/431 , F05D2300/501 , F05D2300/502 , Y02T50/672
Abstract: A fan section of a gas turbine engine includes a fan containment case assembly includes an outer case of an aluminum alloy. The outer case extends circumferentially around an axial centerline. A thermally conforming liner assembly is located inwardly of the outer case. The thermally conforming liner assembly includes a circumferential liner of an aluminum alloy. A ballistic liner is located between the outer case and the thermally conforming liner assembly.
Abstract translation: 燃气涡轮发动机的风扇部分包括具有铝合金外壳的风扇收容箱组件。 外壳围绕轴向中心线周向延伸。 热适应衬套组件位于外壳的内侧。 热适应衬套组件包括铝合金的圆周衬套。 弹道衬套位于外壳和热适应衬套组件之间。
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公开(公告)号：WO2014197053A2
公开(公告)日：2014-12-11
申请号：PCT/US2014/024618
申请日：2014-03-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： ROBERTSON, JR., Thomas J. , COSTA, Mark W. , WELCH, David A.
CPC classification number: F02C7/045 , B64D33/02 , B64D2033/0206 , B64D2033/0286 , F01D11/125 , F05D2250/283 , F05D2300/173 , F05D2300/433 , F05D2300/44 , F05D2300/5021 , Y02T50/671
Abstract: A cartridge for a fan case of a gas turbine engine includes an inlet acoustic liner section integrated with a thermally conforming liner section.
Abstract translation: 用于燃气涡轮发动机的风扇壳体的盒包括与热适应衬套部分一体化的入口声学衬垫部分。
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公开(公告)号：WO2013191850A1
公开(公告)日：2013-12-27
申请号：PCT/US2013/042444
申请日：2013-05-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： ROBERTSON, Thomas J. , LUSSIER, Darin S. , COSTA, Mark W.
CPC classification number: F01D25/24 , F01D25/005 , F05D2300/501 , F05D2300/603 , Y02T50/672 , Y10T29/49982
Abstract: A composite fan case has a generally cylindrical composite shell, at least one band of sacrificial composite material circumscribing an outer surface of the composite shell, and a metallic rail mounted on the band of sacrificial material. Also disclosed is a method of construction the aforementioned case.
Abstract translation: 复合风扇壳体具有大致圆柱形的复合壳体，至少一个围绕复合壳体的外表面的牺牲复合材料带，以及安装在牺牲材料带上的金属导轨。 还公开了构造上述情况的方法。
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Patent Agency Ranking
公开(公告)号：EP3477062A1
公开(公告)日：2019-05-01
申请号：EP18203530.3
申请日：2018-10-30
Applicant: United Technologies Corporation
Inventor： KLING, Colin J. , LUSSIER, Darin S. , COSTA, Mark W.
IPC: F01D21/04
Abstract: A gas turbine engine (20) is provided. The gas turbine engine comprising: a fan section (22) having a fan; and a containment zone (100) encircling the fan, the containment zone comprising: a ballistic liner (200; 300; 400) composed of a plurality of ring segments (220a-e; 320a-f) located radially outward of the fan; wherein each of the plurality of ring segments include two opposing circumferential ends (230a, 230b; 330a, 330b), and wherein the plurality of ring segments are arranged circumferentially around the fan section and the circumferential ends of each of the plurality of ring segments meet at joints (240; 330) to form the ballistic liner.
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公开(公告)号：EP3447306B1
公开(公告)日：2020-07-22
申请号：EP18190743.7
申请日：2018-08-24
Applicant: United Technologies Corporation
Inventor： COSTA, Mark W.
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公开(公告)号：EP2932052B1
公开(公告)日：2019-07-24
申请号：EP13862300.4
申请日：2013-12-10
Applicant: United Technologies Corporation
Inventor： COSTA, Mark W. , ROBERTSON, Thomas J. , LUSSIER, Darin S.
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公开(公告)号：EP2904214B1
公开(公告)日：2019-08-07
申请号：EP13844100.1
申请日：2013-02-22
Applicant: United Technologies Corporation
Inventor： ROBERTSON, Thomas J. , VOLETI, Sreenivasa R. , COSTA, Mark W. , CLARKSON, Steven
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公开(公告)号：EP2861848B1
公开(公告)日：2018-07-18
申请号：EP13806653.5
申请日：2013-05-23
Applicant: United Technologies Corporation
Inventor： ROBERTSON, Thomas J. , LUSSIER, Darin S. , COSTA, Mark W.
CPC classification number: F01D25/24 , F01D25/005 , F05D2300/501 , F05D2300/603 , Y02T50/672 , Y10T29/49982
Abstract: A composite fan case has a generally cylindrical composite shell, at least one band of sacrificial composite material circumscribing an outer surface of the composite shell, and a metallic rail mounted on the band of sacrificial material. Also disclosed is a method of construction the aforementioned case.
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