Patents by Inventor Patrick James McComb
Patrick James McComb 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: 11118463Abstract: A fan platform for electrically grounding an airfoil of a gas turbine engine includes a flow path surface extending between a first and second side. An inner surface radially opposing the flow path surface also extends between the first and second side, and includes a body portion extending radially inwardly therefrom. At least a first conductive path for grounding travels from the first side via the body portion.Type: GrantFiled: January 15, 2015Date of Patent: September 14, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Sean A. Whitehurst, Patrick James McComb
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Patent number: 10954804Abstract: A hybrid rotor may comprise a rotor disk having a peripheral rim, a plurality of solid rotor blades extending outwardly from the rotor disk, and a plurality of hollow rotor blades extending outwardly from the rotor disk in a blade array with the plurality of solid rotor blades. In various embodiments, the plurality of solid rotor blades may be integrally coupled to the rotor disk. In various embodiments, the plurality of hollow rotor blades may be mechanically retained in the rotor disk.Type: GrantFiled: July 5, 2017Date of Patent: March 23, 2021Assignee: Raytheon Technologies CorporationInventors: Patrick James McComb, Sean A. Whitehurst
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Patent number: 10408068Abstract: A blade according to an exemplary aspect of the present disclosure includes, among other things, a radially inner dovetail supporting a radially outer airfoil; and the dovetail having a radial thickness which is less in a circumferentially center portion of the dovetail than circumferentially opposing outer edges.Type: GrantFiled: February 18, 2014Date of Patent: September 10, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Sean A. Whitehurst, Patrick James McComb, Christopher S. McKaveney
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Patent number: 10323521Abstract: An airfoil for a gas turbine engine is disclosed. The airfoil may include a first portion including a first slot, a second portion including a second slot, and a biscuit disposed within the first slot and the second slot. The first portion and the second portion may be joined by the biscuit. A method for constructing an airfoil is also disclosed. The method may include making a first slot on a sheath, the first slot sized to fit a first part of a biscuit; making a second slot on a body, the second slot sized to fit a second part of the biscuit; and joining the sheath and the body together through a biscuit joint, the biscuit disposed within the first slot and the second slot.Type: GrantFiled: December 16, 2013Date of Patent: June 18, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Patrick James McComb
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Publication number: 20190010812Abstract: A hybrid rotor may comprise a rotor disk having a peripheral rim, a plurality of solid rotor blades extending outwardly from the rotor disk, and a plurality of hollow rotor blades extending outwardly from the rotor disk in a blade array with the plurality of solid rotor blades. In various embodiments, the plurality of solid rotor blades may be integrally coupled to the rotor disk. In various embodiments, the plurality of hollow rotor blades may be mechanically retained in the rotor disk.Type: ApplicationFiled: July 5, 2017Publication date: January 10, 2019Applicant: United Technologies CorporationInventors: Patrick James McComb, Sean A. Whitehurst
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Patent number: 10036261Abstract: A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described.Type: GrantFiled: April 30, 2012Date of Patent: July 31, 2018Assignee: United Technologies CorporationInventors: Sean A. Whitehurst, Christopher S. McKaveney, Patrick James McComb
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Patent number: 9995152Abstract: A fan blade for a turbomachinery fan and methods for fabricating a fan blade for a turbomachinery fan are disclosed. The fan blade for a turbomachinery fan includes an airfoil having a leading edge and a trailing edge in a chordwise direction, a tip and a root in a spanwise direction, a suction side and a pressure side. The fan blade includes a sheath including a solid portion that covers the leading edge of the airfoil, a first wing attached to the suction side of the airfoil, and a second wing attached to the pressure side of the airfoil. Construction of the fan blade includes one or more hollow cavities between the suction side and the pressure side of the airfoil.Type: GrantFiled: December 16, 2013Date of Patent: June 12, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Patrick James McComb
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Patent number: 9896936Abstract: A fan assembly for gas assembly engine is disclosed. The fan assembly includes a rotor that is coupled to at least one fan blade. The fan assembly also includes a spinner that extends towards the rotor and the fan blades so that an edge of the spinner engages the fan blades. The edge of the spinner thereby serves as a grounding element for the fan blade. If the spinner is fabricated from a composite or a plastic material that is not sufficiently conductive for grounding purposes, the edge may be coated with a conductive material. Alternatively, the spinner may be fabricated from a metallic material, which would eliminate the need for a conductive coating on the edge that engages the fan blades.Type: GrantFiled: October 15, 2014Date of Patent: February 20, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Sean A. Whitehurst, Patrick James McComb
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Patent number: 9828864Abstract: A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described.Type: GrantFiled: March 15, 2013Date of Patent: November 28, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Sean A. Whitehurst, Patrick James McComb, Lee Drozdenko
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Patent number: 9810078Abstract: Rotary machines including a hybrid rotor with an integrally bladed rotor portion are provided. The integrally bladed rotor portion for the hybrid rotor comprises a rotor disk portion and a blade portion. The rotor disk portion has a peripheral rim configured to mechanically retain an individual rotor blade. The blade portion comprises an integral rotor blade extending outwardly and integrally from the rotor disk portion. The individual rotor blade is configured to extend outwardly from the rotor disk portion in a blade array with the integral rotor blade. The hybrid rotor is also provided and comprises the integrally bladed rotor portion and a plurality of individual rotor blades extending outwardly from the rotor disk portion in a blade array with a plurality of integral rotor blades.Type: GrantFiled: June 17, 2015Date of Patent: November 7, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Sean A. Whitehurst, Patrick James McComb
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Publication number: 20170058916Abstract: A gas turbine fan fairing platform includes at least one body defining a surface and having an opening receptive to a blade, a protrusion extending outwardly from the surface in a direction that will position the protrusion along a leading edge near a root of the blade.Type: ApplicationFiled: September 1, 2015Publication date: March 2, 2017Inventors: Sean A. Whitehurst, Michael A. Weisse, Jordan J. Franklin, Patrick James McComb
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Publication number: 20160369638Abstract: Rotary machines including a hybrid rotor with an integrally bladed rotor portion are provided. The integrally bladed rotor portion for the hybrid rotor comprises a rotor disk portion and a blade portion. The rotor disk portion has a peripheral rim configured to mechanically retain an individual rotor blade. The blade portion comprises an integral rotor blade extending outwardly and integrally from the rotor disk portion. The individual rotor blade is configured to extend outwardly from the rotor disk portion in a blade array with the integral rotor blade. The hybrid rotor is also provided and comprises the integrally bladed rotor portion and a plurality of individual rotor blades extending outwardly from the rotor disk portion in a blade array with a plurality of integral rotor blades.Type: ApplicationFiled: June 17, 2015Publication date: December 22, 2016Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: SEAN A. WHITEHURST, PATRICK JAMES MCCOMB
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Publication number: 20160017727Abstract: A blade according to an exemplary aspect of the present disclosure includes, among other things, a radially inner dovetail supporting a radially outer airfoil; and the dovetail having a radial thickness which is less in a circumferentially center portion of the dovetail than circumferentially opposing outer edges.Type: ApplicationFiled: February 18, 2014Publication date: January 21, 2016Inventors: Sean A. Whitehurst, Patrick James McComb, Christopher S. McKaveney
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Publication number: 20160003061Abstract: A fan blade for a turbomachinery fan and methods for fabricating a fan blade for a turbomachinery fan are disclosed. The fan blade for a turbomachinery fan includes an airfoil having a leading edge and a trailing edge in a chordwise direction, a tip and a root in a spanwise direction, a suction side and a pressure side. The fan blade includes a sheath including a solid portion that covers the leading edge of the airfoil, a first wing attached to the suction side of the airfoil, and a second wing attached to the pressure side of the airfoil. Construction of the fan blade includes one or more hollow cavities between the suction side and the pressure side of the airfoil.Type: ApplicationFiled: December 16, 2013Publication date: January 7, 2016Inventor: Patrick James McComb
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Publication number: 20150354375Abstract: An airfoil for a gas turbine engine is disclosed. The airfoil may include a first portion including a first slot, a second portion including a second slot, and a biscuit disposed within the first slot and the second slot. The first portion and the second portion may be joined by the biscuit. A method for constructing an airfoil is also disclosed. The method may include making a first slot on a sheath, the first slot sized to fit a first part of a biscuit; making a second slot on a body, the second slot sized to fit a second part of the biscuit; and joining the sheath and the body together through a biscuit joint, the biscuit disposed within the first slot and the second slot.Type: ApplicationFiled: December 16, 2013Publication date: December 10, 2015Inventor: Patrick James McComb
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Publication number: 20150300176Abstract: A fan assembly for gas assembly engine is disclosed. The fan assembly includes a rotor that is coupled to at least one fan blade. The fan assembly also includes a spinner that extends towards the rotor and the fan blades so that an edge of the spinner engages the fan blades. The edge of the spinner thereby serves as a grounding element for the fan blade. If the spinner is fabricated from a composite or a plastic material that is not sufficiently conductive for grounding purposes, the edge may be coated with a conductive material. Alternatively, the spinner may be fabricated from a metallic material, which would eliminate the need for a conductive coating on the edge that engages the fan blades.Type: ApplicationFiled: October 15, 2014Publication date: October 22, 2015Inventors: Sean A. Whitehurst, Patrick James McComb
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Publication number: 20150292338Abstract: A fan platform for electrically grounding an airfoil of a gas turbine engine includes a flow path surface extending between a first and second side. An inner surface radially opposing the flow path surface also extends between the first and second side, and includes a body portion extending radially inwardly therefrom. At least a first conductive path for grounding travels from the first side via the body portion.Type: ApplicationFiled: January 15, 2015Publication date: October 15, 2015Inventors: Sean A. Whitehurst, Patrick James McComb
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Publication number: 20150233259Abstract: A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described.Type: ApplicationFiled: March 15, 2013Publication date: August 20, 2015Inventors: Sean A. Whitehurst, Patrick James McComb, Lee Drozdenko
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Publication number: 20130287578Abstract: A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described.Type: ApplicationFiled: April 30, 2012Publication date: October 31, 2013Inventors: Sean A. Whitehurst, Christopher S. McKaveney, Patrick James McComb