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公开(公告)号：US10145268B2
公开(公告)日：2018-12-04
申请号：US14400929
申请日：2014-02-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James R. Murdock
IPC: F01D25/28 , F01D11/00 , F01D5/22 , F01D5/28 , B29C45/00 , B29K77/00 , B29K79/00 , B29K105/12 , B29L31/08
Abstract: A fan platform for a gas turbine engine may include an outer flow path surface extending between a first side and a second side. An inner surface extends between the first side and the second side, and faces radially oppositely the outer flow path surface. A plurality of platform hooks may extend radially inwardly from the inner surface.
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公开(公告)号：US20160053636A1
公开(公告)日：2016-02-25
申请号：US14506830
申请日：2014-02-21
Applicant: United Technologies Corporation
Inventor： James R. Murdock
CPC classification number: F01D25/28 , B29C45/0005 , B29K2077/00 , B29K2079/085 , B29K2105/12 , B29L2031/08 , F01D5/225 , F01D5/282 , F01D11/008 , F05D2220/32 , F05D2220/36 , F05D2240/90 , F05D2260/30 , F05D2260/36 , F05D2300/43 , F05D2300/603
Abstract: A fan platform for a gas turbine engine may include an outer flow path surface extending between a first side and a second side. An inner surface extends between the first side and the second side, and faces radially oppositely the outer flow path surface. A plurality of platform hooks may extend radially inwardly from the inner surface.
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公开(公告)号：US20150369582A1
公开(公告)日：2015-12-24
申请号：US14767864
申请日：2013-12-18
Applicant: United Technologies Corporation
Inventor： Thomas H. Rogers , Randall W. Joyner , James R. Murdock , Andrew J. Brinks , Michael A. Morden
CPC classification number: G01B5/008 , F01D5/005 , F01D5/141 , F01D5/288 , F01D9/02 , F01D21/003 , F05D2220/32 , F05D2230/90 , F05D2260/83 , G01B11/03 , G01M13/00
Abstract: A method of inspecting components between a pre-coated state and a post-coated state is provided. The method entails providing at least first and second datum points onto the component in the pre-coated state, where each of the at least first and second datum points have a substantially hemi-spherical shape and a center point. The center points of each of the at least first and second datum points are utilized for measurement of a selected portion on the component in the pre-coated state. Then, the component is coated. Next, the center points of each of the at least first and second datum points are utilized for measurement of the selected portion on the component in the post-coated state. The pre-coated state measurements and the post-coated state measurements are then correlated for inspection purposes.
Abstract translation: 提供了一种在预涂状态和后涂状态之间检查部件的方法。 该方法需要在预涂覆状态下将至少第一和第二基准点提供到部件上，其中至少第一和第二基准点中的每一个具有基本上半球形的形状和中心点。 所述至少第一和第二基准点中的每一个的中心点被用于测量预包装状态下的部件上的选定部分。 然后，涂覆该组分。 接下来，使用至少第一和第二基准点中的每一个的中心点来测量后涂覆状态下的部件上的选定部分。 然后将预涂层状态测量和后涂状态测量相关以进行检查。
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公开(公告)号：US20150226231A1
公开(公告)日：2015-08-13
申请号：US14515184
申请日：2014-10-15
Applicant: United Technologies Corporation
Inventor： James R. Murdock
CPC classification number: F04D29/403 , F02K3/06 , F04D29/526 , F04D29/644 , F05D2220/36 , F05D2230/70 , Y02T50/672 , Y10T29/49318
Abstract: A fan section of a gas turbine engine is disclosed. The fan section may comprise a fan having a hub and a plurality of blades extending radially from the hub. The fan section may further comprise a fan case surrounding the fan and an inlet structure located upstream of the fan and defining at least a portion of an airflow path leading to the fan. The inlet structure may have at least one panel removably connected to at least one structural element of the gas turbine engine, and an opening may be exposed when the panel is disconnected from the gas turbine engine. The opening may provide clearance for removal of at least one of the plurality of blades from the hub.
Abstract translation: 公开了一种燃气涡轮发动机的风扇部分。 风扇部分可以包括具有轮毂和从轮毂径向延伸的多个叶片的风扇。 风扇部分还可以包括围绕风扇的风扇壳体和位于风扇上游的入口结构，并且限定通向风扇的气流路径的至少一部分。 入口结构可以具有可移除地连接到燃气涡轮发动机的至少一个结构元件的至少一个面板，并且当面板与燃气涡轮发动机断开时可以暴露出开口。 开口可以提供用于从轮毂移除多个叶片中的至少一个的间隙。
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公开(公告)号：US10724379B2
公开(公告)日：2020-07-28
申请号：US14767180
申请日：2013-12-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James R. Murdock
Abstract: A sheath, for protecting the leading edge of airfoils used in gas turbine engines, may have a solid member, a pressure side flank and a suction side flank. The solid member may form an outer edge, which may include a main portion and a projecting portion. The projecting portion may have a variable dimension. The pressure side flank and suction side flank may project from the solid member opposite the outer edge. The pressure side flank and suction side flank may form a receiving cavity for receiving an airfoil.
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Patent Agency Ranking
公开(公告)号：US10792771B2
公开(公告)日：2020-10-06
申请号：US15702531
申请日：2017-09-12
Applicant: United Technologies Corporation
Inventor： Michael F. Machinchick , Luke H. Rettberg , Andrew L. Haynes , Janet M. Stanley , Vasisht Venkatesh , David Ulrich Furrer , James R. Murdock , Daniel Gynther , Michael J. Linden
IPC: F01D5/30 , B23P15/00 , F01D5/34 , C22F1/18 , C21D1/00 , F01D5/28 , B23K101/00 , B23K20/12 , B21K1/36
Abstract: Disclosed is a method of making an integrally bladed rotor. According to the method, a rotor disk comprising a radially outer rim surface is provided. A portion of the disk outer rim surface is removed, leaving a protrusion on the rotor disk outer rim surface. The disk with material removed is subjected to thermal processing. A blade comprising an airfoil and a base is positioned such that a base surface is in contact with the protrusion, and heat, pressure, and motion are applied between the blade and the disk to friction weld the base surface to the protrusion.
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公开(公告)号：US10605101B2
公开(公告)日：2020-03-31
申请号：US15702486
申请日：2017-09-12
Applicant: United Technologies Corporation
Inventor： Michael F. Machinchick , Luke H. Rettberg , Andrew L. Haynes , Janet M. Stanley , Vasisht Venkatesh , David Ulrich Furrer , James R. Murdock , Daniel Gynther , Michael J. Linden
IPC: B23P6/04 , F01D5/30 , B23K20/12 , C22F1/18 , C22C14/00 , B23P15/00 , B23K20/233 , C22F1/00 , F01D5/34 , B23K20/24 , F01D5/14 , F04D29/34 , F04D29/38 , B23K103/14 , B23K101/00 , B23K103/18
Abstract: Disclosed is a method of making an integrally bladed rotor. According to the method, a titanium alloy rotor disk with 15-50% by volume of primary alpha grains with a grain size less than 10 μm and secondary alpha grains comprising widmanstatten grains with a grain size less than 1.0 μm is subjected to thermal processing. After thermal processing, a blade having an airfoil and a base is positioned such that a base surface is in contact with an outer rim surface of the disk. Heat, pressure, and motion are applied between the blade and the disk to friction weld the base surface to the disk outer rim surface.
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公开(公告)号：US10385703B2
公开(公告)日：2019-08-20
申请号：US14770256
申请日：2013-12-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James R. Murdock
Abstract: Light weight fan blades for turbofan jet engines are disclosed. The fan blades may be fabricated from an aluminum alloy. To enhance the hardness of the leading edge of the fan blade, a titanium sheath may be attached to the leading edges of the fan blades. To prevent galvanic coupling between the titanium and the aluminum, a polymeric liner may be disposed between the protective titanium sheath and the aluminum fan blade. The liner may be fabricated from a polymer material, such as a polyimide or another high performance polymer.
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公开(公告)号：US20190078449A1
公开(公告)日：2019-03-14
申请号：US15702486
申请日：2017-09-12
Applicant: United Technologies Corporation
Inventor： Michael F. Machinchick , Luke H. Rettberg , Andrew L. Haynes , Janet M. Stanley , Vasisht Venkatesh , David Ulrich Furrer , James R. Murdock , Daniel Gynther , Michael J. Linden
Abstract: Disclosed is a method of making an integrally bladed rotor. According to the method, a titanium alloy rotor disk with 15-50% by volume of primary alpha grains with a grain size less than 10 μm and secondary alpha grains comprising widmanstatten grains with a grain size less than 1.0 μm is subjected to thermal processing. After thermal processing, a blade having an airfoil and a base is positioned such that a base surface is in contact with an outer rim surface of the disk. Heat, pressure, and motion are applied between the blade and the disk to friction weld the base surface to the disk outer rim surface.
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公开(公告)号：US20150322805A1
公开(公告)日：2015-11-12
申请号：US14646158
申请日：2013-02-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James R. Murdock
IPC: F01D5/30
CPC classification number: F01D5/3007 , F01D5/3092 , F05D2220/32 , F05D2230/70 , F05D2300/43 , Y02T50/672 , Y10T29/4932
Abstract: A rotor for use in a gas turbine engine has rotor slots receiving a blade. The blades have an airfoil extending from a dovetail, and the dovetail is received by a rotor slot. A spacer is positioned between an inner wall of the dovetail and an outer wall of the slot, and the spacer is formed with a removal slot. A spacer, a gas turbine engine, and a method are also disclosed.
Abstract translation: 用于燃气涡轮发动机的转子具有容纳叶片的转子槽。 叶片具有从燕尾形延伸的翼型件，燕尾座由转子槽容纳。 间隔件定位在燕尾的内壁和槽的外壁之间，并且间隔件形成有移除槽。 还公开了间隔件，燃气涡轮发动机和方法。
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