Patents by Inventor James R. Murdock
James R. Murdock has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 10792771Abstract: 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.Type: GrantFiled: September 12, 2017Date of Patent: October 6, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: 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
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Patent number: 10724379Abstract: 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.Type: GrantFiled: December 16, 2013Date of Patent: July 28, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventor: James R. Murdock
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Patent number: 10605101Abstract: 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 ?m and secondary alpha grains comprising widmanstatten grains with a grain size less than 1.0 ?m 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.Type: GrantFiled: September 12, 2017Date of Patent: March 31, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: 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
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Patent number: 10563666Abstract: A fan for a gas turbine engine is provided. The fan having: a rotor; a hollow fan blade having a cavity, the hollow fan blade secured to the rotor; a cover covering the cavity; a platform independent of the hollow fan blade and secured to the rotor, wherein a portion of the cover is located below a peripheral edge of the platform and the peripheral edge retains the portion of the cover in a desired location.Type: GrantFiled: November 2, 2016Date of Patent: February 18, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: James R. Murdock
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Patent number: 10415402Abstract: A blade assembly comprises a blade (120) and one or more wear pads (170, 172). The blade has an airfoil (122) having a leading edge (126), a trailing edge (128), a pressure side (130), a suction side (132), and extending from an inboard end to a tip (125). The blade further includes an attachment root (124). The one or more wear pads are along the attachment root. The one or more wear pads have a plurality of slits (228, 230 242).Type: GrantFiled: December 20, 2013Date of Patent: September 17, 2019Assignee: United Technologies CorporationInventors: James R. Murdock, Kwan Hui
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Patent number: 10385703Abstract: 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.Type: GrantFiled: December 18, 2013Date of Patent: August 20, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: James R. Murdock
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Patent number: 10280759Abstract: A blade assembly may be configured to rotate about an axis of a gas turbine engine. The blade assembly may include a blade and a blade cover. A blade may include a first surface defining a perimeter of a cavity in the blade. A first portion of the perimeter of the cavity includes a lip. A blade cover disposed over the cavity in the blade, such that the cavity is disposed between the blade and the blade cover, and under the lip, such that blade cover is between a portion of the blade and the cavity.Type: GrantFiled: May 25, 2016Date of Patent: May 7, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: James R. Murdock
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Publication number: 20190078449Abstract: 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 ?m and secondary alpha grains comprising widmanstatten grains with a grain size less than 1.0 ?m 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.Type: ApplicationFiled: September 12, 2017Publication date: March 14, 2019Inventors: 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
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Publication number: 20190076970Abstract: 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.Type: ApplicationFiled: September 12, 2017Publication date: March 14, 2019Inventors: 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
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Patent number: 10145268Abstract: 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.Type: GrantFiled: February 21, 2014Date of Patent: December 4, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: James R. Murdock
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Publication number: 20180202299Abstract: A blade for a gas turbine engine. The blade having: an airfoil formed from a first material; a protective sheath disposed on a leading edge of the airfoil, the protective sheath being formed from a second material, the first material being galvanically incompatible with the second material and the first material being less noble than the second material; a non-conductive material disposed between the protective sheath and the airfoil so that they are electrically isolated from each other; a sacrificial anode in contact with the blade, wherein the sacrificial anode is formed from a third material that is less noble than the first material such that it will corrode before the first material if the non-conductive material disposed between the protective sheath and the airfoil is compromised and the first material and the second material are no longer electrically isolated from each other.Type: ApplicationFiled: January 18, 2017Publication date: July 19, 2018Inventors: James R. Murdock, James H. Moffitt, Scot A. Webb, Jay Thomas Abraham, Maria C. Kirejczyk
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Publication number: 20180119707Abstract: A fan for a gas turbine engine is provided. The fan having: a rotor; a hollow fan blade having a cavity, the hollow fan blade secured to the rotor; a cover covering the cavity; a platform independent of the hollow fan blade and secured to the rotor, wherein a portion of the cover is located below a peripheral edge of the platform and the peripheral edge retains the portion of the cover in a desired location.Type: ApplicationFiled: November 2, 2016Publication date: May 3, 2018Inventor: James R. Murdock
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Patent number: 9927220Abstract: 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.Type: GrantFiled: December 18, 2013Date of Patent: March 27, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas H. Rogers, Randall W. Joyner, James R. Murdock, Andrew J. Brinks, Michael A. Morden
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Publication number: 20170343007Abstract: A blade assembly may be configured to rotate about an axis of a gas turbine engine. The blade assembly may include a blade and a blade cover. A blade may include a first surface defining a perimeter of a cavity in the blade. A first portion of the perimeter of the cavity includes a lip. A blade cover disposed over the cavity in the blade, such that the cavity is disposed between the blade and the blade cover, and under the lip, such that blade cover is between a portion of the blade and the cavity.Type: ApplicationFiled: May 25, 2016Publication date: November 30, 2017Applicant: UNITED TECHNOLOGIES CORPORATIONInventor: James R. Murdock
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Patent number: 9810077Abstract: A fan blade includes a root including a front surface, a rear surface, a first side surface connected to the front surface and the rear surface, and a second side surface connected to the front surface and the rear surface. The front surface engages the first side surface and the second side surface by one or more blunted surfaces, and the rear surface engages the first side surface and the second side surface by one or more blunted surfaces. A blade extends from the root.Type: GrantFiled: January 31, 2012Date of Patent: November 7, 2017Assignee: United Technologies CorporationInventors: James R. Murdock, Christopher S. McKaveney, Jason Elliott
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Patent number: 9376924Abstract: A fan rotor includes a fan blade for use in a gas turbine engine includes a sheath formed of a material that is more conductive than a main fan blade body. A grounding element provides a grounding path from the sheath into a rotor receiving the fan blade. A gas turbine engine incorporating the fan blade is also disclosed.Type: GrantFiled: December 14, 2011Date of Patent: June 28, 2016Assignee: United Technologies CorporationInventors: James R. Murdock, Kwan Hui
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Publication number: 20160053636Abstract: 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.Type: ApplicationFiled: February 21, 2014Publication date: February 25, 2016Inventor: James R. Murdock
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Publication number: 20160024947Abstract: A blade assembly comprises a blade (120) and one or more wear pads (170, 172). The blade has an airfoil (122) having a leading edge (126), a trailing edge (128), a pressure side (130), a suction side (132), and extending from an inboard end to a tip (125). The blade further includes an attachment root (124). The one or more wear pads are along the attachment root. The one or more wear pads have a plurality of slits (228, 230 242).Type: ApplicationFiled: December 20, 2013Publication date: January 28, 2016Applicant: United Technologies CorporationInventors: James R. Murdock, Kwan Hui
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Publication number: 20160003062Abstract: 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.Type: ApplicationFiled: December 18, 2013Publication date: January 7, 2016Applicant: United Technologies CorporationInventor: James R. Murdock
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Publication number: 20150377030Abstract: 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.Type: ApplicationFiled: December 16, 2013Publication date: December 31, 2015Inventor: James R. MURDOCK