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1.发明授权公开(公告)号：US10752557B2
公开(公告)日：2020-08-25
申请号：US15979079
申请日：2018-05-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin T. Fisk , Grant O. Cook, III
IPC: B23K20/00 , C04B37/02 , B23K20/02 , B23K20/16 , B23K20/233 , B23K20/04 , B32B7/04 , B32B15/04 , B23K103/16
Abstract: A means for attaching a metallic component to a non-metallic component using a compliant material having thermal properties intermediate those of the metallic component to a non-metallic component is provided. The method can accommodate CTE mismatches and wear-type problems common to many assemblies of dissimilar materials. In particular, the method provides a sufficient wear surface to accommodate relative motion and provide a durable wear surface that does not excessively wear/gall/mico-weld itself together and provides the necessary damping and motion for proper operation in aeronautical applications.
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公开(公告)号：US10525525B2
公开(公告)日：2020-01-07
申请号：US14904991
申请日：2014-07-02
Applicant: UNITED TECHNOLOGIES CORPORATION
IPC: B22C9/04 , B22F3/105 , B33Y10/00 , F01D5/18 , F01D9/04 , F01D11/08 , F01D25/12 , F01D5/14 , F01D5/28 , B22F5/00 , B33Y80/00 , B22F3/24 , C04B35/64
Abstract: A method of preparing a casting article for use in manufacturing a gas turbine engine part according to an exemplary aspect of the present disclosure includes, among other things, communicating a powdered material to an additive manufacturing system and preparing a casting article that includes at least one trunk and a skin core that extends from the at least one trunk out of the powdered material.
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公开(公告)号：US10151204B2
公开(公告)日：2018-12-11
申请号：US15042840
申请日：2016-02-12
Applicant: United Technologies Corporation
Inventor： David P. Houston , Tracy A. Propheter-Hinckley , Benjamin T. Fisk , Anita L. Tracy
IPC: F01D5/16 , B22F3/105 , B22F5/04 , F01D9/04 , F01D25/04 , F04D29/38 , F04D29/54 , F04D29/66 , B22F5/10
Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge between a radially outer end and a radially inner end. The first sidewall and the second sidewall at least partially define a cavity extending radially in the airfoil body. A damper member has a free radially inner end in the cavity and a free radially outer end in the cavity. The damper member is free-floating in the cavity.
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公开(公告)号：US20160160651A1
公开(公告)日：2016-06-09
申请号：US15042840
申请日：2016-02-12
Applicant: United Technologies Corporation
Inventor： David P. Houston , Tracy A. Propheter-Hinckley , Benjamin T. Fisk , Anita L. Tracy
CPC classification number: F01D5/16 , B22F3/1055 , B22F5/04 , B22F5/10 , F01D9/041 , F01D25/04 , F04D29/38 , F04D29/542 , F04D29/668 , F05D2220/32 , F05D2230/21 , F05D2240/50 , F05D2250/232 , Y02P10/295
Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge between a radially outer end and a radially inner end. The first sidewall and the second sidewall at least partially define a cavity extending radially in the airfoil body. A damper member has a free radially inner end in the cavity and a free radially outer end in the cavity. The damper member is free-floating in the cavity.
Abstract translation: 翼型件包括具有前缘和后缘的翼型件主体和与第一侧壁间隔开的第一侧壁和第二侧壁。 第一侧壁和第二侧壁将前缘和后缘连接在径向外端和径向内端之间。 第一侧壁和第二侧壁至少部分地限定在翼型件本体中径向延伸的空腔。 阻尼器构件在空腔中具有自由的径向内端，并且在空腔中具有自由的径向外端。 阻尼器构件在空腔中自由浮动。
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公开(公告)号：US20160053625A1
公开(公告)日：2016-02-25
申请号：US14853059
申请日：2015-09-14
Applicant: United Technologies Corporation
Inventor： Benjamin T. Fisk , Tracy A. Propheter-Hinckley
CPC classification number: F01D11/122 , B23P15/02 , F01D1/02 , F01D5/147 , F01D5/20 , F01D9/04 , F05D2220/32 , F05D2240/307 , F05D2240/55 , F05D2250/283 , F05D2300/177 , Y10T29/49337
Abstract: A gas turbine engine includes a plurality of airfoils that are circumferentially arranged to rotate about an engine central axis. Each of the airfoils includes a base and a free tip end. The tip end includes first and second porous abradable elements that are axially spaced apart. The first porous abradable elements of the airfoils circumferentially align with each other, and the second porous abradable elements of the airfoils circumferentially align with each other.
Abstract translation: 燃气涡轮发动机包括沿圆周布置成围绕发动机中心轴线旋转的多个翼型件。 每个翼型件包括底座和自由尖端。 尖端包括轴向间隔开的第一和第二多孔耐磨元件。 翼型件的第一多孔耐磨元件彼此周向对准，并且翼型件的第二多孔耐磨元件彼此周向对准。
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Patent Agency Ranking
6.发明申请公开(公告)号：US20180297900A1
公开(公告)日：2018-10-18
申请号：US15979079
申请日：2018-05-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin T. Fisk , Grant O. Cook, III
Abstract: A means for attaching a metallic component to a non-metallic component using a compliant material having thermal properties intermediate those of the metallic component to a non-metallic component is provided. The method can accommodate CTE mismatches and wear-type problems common to many assemblies of dissimilar materials. In particular, the method provides a sufficient wear surface to accommodate relative motion and provide a durable wear surface that does not excessively wear/gall/mico-weld itself together and provides the necessary damping and motion for proper operation in aeronautical applications.
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7.发明授权公开(公告)号：US09969654B2
公开(公告)日：2018-05-15
申请号：US14601520
申请日：2015-01-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin T. Fisk , Grant O. Cook, III
IPC: B23K31/02 , C04B37/02 , B23K20/02 , B23K20/16 , B23K20/233 , B32B7/04 , B32B15/04 , B23K103/16
CPC classification number: C04B37/026 , B23K20/02 , B23K20/021 , B23K20/16 , B23K20/2333 , B23K2103/16 , B32B7/04 , B32B15/04 , B32B2311/24 , B32B2315/02 , B32B2605/18 , C04B2237/121 , C04B2237/60
Abstract: A means for attaching a metallic component to a non-metallic component using a compliant material having thermal properties intermediate those of the metallic component to a non-metallic component is provided. The method can accommodate CTE mismatches and wear-type problems common to many assemblies of dissimilar materials. In particular, the method provides a sufficient wear surface to accommodate relative motion and provide a durable wear surface that does not excessively wear/gall/mico-weld itself together and provides the necessary damping and motion for proper operation in aeronautical applications.
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公开(公告)号：US20160245090A1
公开(公告)日：2016-08-25
申请号：US15025784
申请日：2014-04-17
Applicant: United Technologies Corporation
Inventor： Grant O. Cook , Benjamin T. Fisk
CPC classification number: F01D5/147 , B23K20/023 , B23K2101/001 , C04B37/026 , C04B2237/38 , C04B2237/385 , C04B2237/62 , C04B2237/84 , F01D5/282 , F01D5/284 , F01D5/30 , F01D5/3084 , F01D9/02 , F04D29/324 , F04D29/325 , F04D29/542 , F05D2220/32 , F05D2230/236 , F05D2230/237 , F05D2300/10 , F05D2300/50212 , F05D2300/6033 , Y02T50/672
Abstract: An airfoil is disclosed. The airfoil may comprise a body portion having a leading edge, a trailing edge, a pressure side, and a suction side. The airfoil may further comprise a compliant attachment bonded to the body portion and the compliant attachment may be configured to connect to a support structure. The compliant attachment may have a coefficient of thermal expansion intermediate between a coefficient of the thermal expansion of the body portion of the airfoil and a coefficient of thermal expansion of the support structure.
Abstract translation: 公开了一种翼型件。 翼型件可以包括具有前缘，后缘，压力侧和吸力侧的主体部分。 翼型件还可以包括结合到主体部分的柔顺附件，并且柔性附件可被配置成连接到支撑结构。 柔性附件可以具有在翼型件的主体部分的热膨胀系数与支撑结构的热膨胀系数之间的中间热膨胀系数。
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公开(公告)号：US20160208708A1
公开(公告)日：2016-07-21
申请号：US15022653
申请日：2014-09-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Evan Butcher , Benjamin T. Fisk , Wendell V. Twelves , Caitlin Oswald , Andre Herman Troughton , Bryan P. Conway
Abstract: A fuel/oil manifold includes first and second manifold flanges and a manifold tube. The first and second manifold flanges are located in non-parallel planes with respect to one another. The manifold tube is connected at a first end to the first manifold flange and at a second end to the second manifold flange and includes at least one turn between the first and the second end that includes a non-zero tube bend radius defined as the ratio of a turn radius to a diameter of the manifold tube.
Abstract translation: 燃料/油歧管包括第一和第二歧管凸缘和歧管管。 第一和第二歧管凸缘相对于彼此位于非平行平面中。 歧管在第一端连接到第一歧管凸缘，第二端连接到第二歧管凸缘，并且包括在第一和第二端之间的至少一个匝，其包括非零管弯曲半径，其定义为比率 的转弯半径相对于歧管管的直径。
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公开(公告)号：US10513983B2
公开(公告)日：2019-12-24
申请号：US15022653
申请日：2014-09-26
Applicant: United Technologies Corporation
Inventor： Evan Butcher , Benjamin T. Fisk , Wendell V. Twelves , Caitlin Oswald , Andre Herman Troughton , Bryan P. Conway
Abstract: A fuel/oil manifold includes first and second manifold flanges and a manifold tube. The first and second manifold flanges are located in non-parallel planes with respect to one another. The manifold tube is connected at a first end to the first manifold flange and at a second end to the second manifold flange and includes at least one turn between the first and the second end that includes a non-zero tube bend radius defined as the ratio of a turn radius to a diameter of the manifold tube.
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