Patents by Inventor John McConnell
John McConnell 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: 11166592Abstract: A food processor for processing food stuffs having a base assembly, a jar assembly, and a blade assembly that can be rotated from a use position to a stored position is disclosed. The food processor includes a lid that is connected to the jar assembly by a hinge and closed by use of a latch. The jar assembly is connected to the base assembly by the use of push pins on the base assembly which engage corresponding holes on the jar assembly.Type: GrantFiled: August 14, 2018Date of Patent: November 9, 2021Assignee: WHIRLPOOL CORPORATIONInventors: Wenkai Wu, John McConnell, David Gushwa, Andria R. Bauman
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Publication number: 20210340874Abstract: A coating is applied to a base material. The coating comprises a viscoelastic layer; and a constraint layer; wherein the viscoelastic layer is disposed on the base material and the constraint layer is disposed on the viscoelastic layer.Type: ApplicationFiled: May 4, 2020Publication date: November 4, 2021Inventors: James Zhang, John McConnell Delvaux
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Publication number: 20210324743Abstract: An article, such as a turbine blade, includes an airfoil. The airfoil includes a body, the body having an elongated internal cavity extending from a tip of the body. The cavity is defined an internal wall within the body. At least one elongated damping element is disposed in the elongated internal cavity and frictionally engages the internal wall. Thus, the least one elongated damping element is capable of damping vibrations in the article.Type: ApplicationFiled: April 17, 2020Publication date: October 21, 2021Inventors: Andrew Clifford Hart, John McConnell Delvaux, Joseph Anthony Weber, James Zhang, Peter de Diego
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Patent number: 11143036Abstract: A turbine blade includes an airfoil body having an outer tip and a platform; and a part-span shroud positioned between the outer tip and the platform of the airfoil body. The part-span shroud has a first opening extending through the airfoil body and having a first inner surface. The airfoil body includes a second opening extending radially from the first opening and having a second inner surface. A first elongated vibration-damping element is disposed in the first opening, and a second elongated vibration-damping element disposed radially in the second opening. The second elongated vibration-damping element includes a free radially outer end and a radially inner end coupled to the first elongated vibration-damping element. The first elongated vibration-damping element frictionally damps vibration, and the second elongated vibration-damping element damps vibration using impact within the second opening.Type: GrantFiled: August 20, 2020Date of Patent: October 12, 2021Assignee: General Electric CompanyInventors: James Zhang, Michael Anthony Wondrasek, John McConnell Delvaux
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Patent number: 11085303Abstract: A blade vibration damping system impacts a pressurized damping fluid on a surface of at least one of a plurality of blades of a turbine in opposition to a vibratory movement thereof to cause damping of vibration of the blade(s) during operation of the turbine. The system includes a fluid injection nozzle in a stationary component adjacent the plurality of blades. A valve selectively admits the pressurized damping fluid to the fluid injection nozzle from a source of pressurized damping fluid, and a control system controls the valve to operate the fluid injection nozzle in response to an operational parameter exceeding a threshold during operation of the turbine. A related turbine casing and method are also provided.Type: GrantFiled: June 16, 2020Date of Patent: August 10, 2021Assignee: General Electric CompanyInventors: John McConnell Delvaux, Claire Fridtjof Lang, Suryarghya Chakrabarti
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Patent number: 11034842Abstract: A coating includes: at least 34.9 percent by mass silicon dioxide; at least 9.1 percent by mass aluminum oxide; and at least 16.1 percent by mass yttrium oxide.Type: GrantFiled: December 14, 2018Date of Patent: June 15, 2021Assignee: General Electric CompanyInventors: Matthew Troy Hafner, John McConnell Delvaux, Jason Robert Parolini, Rajendra Kumar Bordia, Quan Li
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Publication number: 20210140328Abstract: A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.Type: ApplicationFiled: January 19, 2021Publication date: May 13, 2021Inventors: Matthew Troy Hafner, John McConnell Delvaux, Thomas Raymond Farrell, Markus Feigl
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Patent number: 10907484Abstract: A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.Type: GrantFiled: February 7, 2019Date of Patent: February 2, 2021Assignee: General Electric CompanyInventors: Matthew Troy Hafner, John McConnell Delvaux, Thomas Raymond Farrell, Markus Feigl
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Patent number: 10822955Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral base and top portions. The airfoil may include a pin connector connecting the top portion to the base portion. The pin connector may include: a tab extending from the top portion; a complimentary slot for receiving the tab formed in the base portion; an elongated pin cavity formed through an interior region of the airfoil, where the pin cavity intersects the slot to divide the pin cavity into first and second pin cavity segments; a tab aperture formed through the tab, where the tab aperture is positioned so align with the pin cavity upon the tab being received within the slot; and a locking pin that extends continuously through the first segment of the pin cavity, the tab aperture, and the second segment of the pin cavity.Type: GrantFiled: December 28, 2018Date of Patent: November 3, 2020Assignee: General Electric CompanyInventors: John McConnell Delvaux, Markus Feigl, Matthew Troy Hafner, Michael Anthony Wondrasek, James Zhang, Peter de Diego
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Patent number: 10815786Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil is defined between a pressure face and a laterally opposed suction face, the pressure face and the suction face extending axially between opposite leading and trailing edges and radially between an outboard tip and a connection with a root of the rotor blade. The airfoil may include non-integral portions in which: a base portion of the airfoil is made from a first material; and a top portion of the airfoil is made from a second material. The airfoil may include a dovetail joint connecting the top portion to the base portion. The dovetail joint may include a dovetail extending from the top portion being received within a complementary dovetail groove formed in the base portion.Type: GrantFiled: December 28, 2018Date of Patent: October 27, 2020Assignee: General Electric CompanyInventors: Matthew Troy Hafner, John McConnell Delvaux, James Zhang, Jeffrey Clarence Jones, Peter de Diego
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Patent number: 10808575Abstract: A turbine component assembly is disclosed, including a first component, a second component, and a circumferentially oriented flat spring. The first component is arranged to be disposed adjacent to a hot gas path, and includes a ceramic matrix composite composition. The second component is adjacent to the first component and arranged to be disposed distal from the hot gas path across the first component. The circumferentially oriented flat spring is disposed on and directly contacting the second component and directly contacting and supporting the first component as a compliant contact interface between the first component and the second component. The circumferentially oriented flat spring provides a radial spring compliance between the first component and the second component.Type: GrantFiled: June 15, 2017Date of Patent: October 20, 2020Assignee: GENERAL ELECTRIC COMPANYInventors: Glenn Curtis Taxacher, John McConnell Delvaux, Matthew Troy Hafner
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Publication number: 20200256204Abstract: A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.Type: ApplicationFiled: February 7, 2019Publication date: August 13, 2020Inventors: Matthew Troy Hafner, John McConnell Delvaux, Thomas Raymond Farrell, Markus Feigl
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Patent number: 10731471Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral portions in which: a base portion is made from a first material; and a top portion is made from a second material. The airfoil may include a connector securing the base portion to the top portion of the airfoil, wherein the connector comprises a wire-lock connector that includes: a tab extending from one of the base portion and the top portion; a complimentary slot for receiving the tab formed in the other one of the base portion and the top portion; a first groove formed in a side of the tab; a second groove formed in a side of the slot; a retaining aperture formed cooperatively via an alignment of the first and second grooves upon the tab being received into the slot; and a retaining wire housed within the retaining aperture.Type: GrantFiled: December 28, 2018Date of Patent: August 4, 2020Assignee: General Electric CompanyInventors: Stanley Kevin Widener, John McConnell Delvaux, Matthew Troy Hafner, James Zhang, Peter de Diego
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Publication number: 20200217213Abstract: A method of layering ceramic matrix composite (CMC) plies during a build of a component is disclosed. The method may include creating a plurality of CMC plies for creating the component. At least a first plurality of the plurality of the CMC plies each define both an outer portion and an inner portion of the component, each inner portion being defined within the outer portion by one or more openings in the respective CMC ply. The method may also include layering the plurality of CMC plies, and infiltrating the CMC plies with a binder to form the component. In one example, the component can be a turbine nozzle endwall.Type: ApplicationFiled: January 9, 2019Publication date: July 9, 2020Inventors: Peter de Diego, John McConnell Delvaux, John Ellington Greene, David Randall Hobart, James Joseph Murray, III
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Publication number: 20200208526Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil is defined between a pressure face and a laterally opposed suction face, the pressure face and the suction face extending axially between opposite leading and trailing edges and radially between an outboard tip and a connection with a root of the rotor blade. The airfoil may include non-integral portions in which: a base portion of the airfoil is made from a first material; and a top portion of the airfoil is made from a second material. The airfoil may include a dovetail joint connecting the top portion to the base portion. The dovetail joint may include a dovetail extending from the top portion being received within a complementary dovetail groove formed in the base portion.Type: ApplicationFiled: December 28, 2018Publication date: July 2, 2020Applicant: General Electric CompanyInventors: Matthew Troy Hafner, John McConnell Delvaux, James Zhang, Jeffrey Clarence Jones, Peter de Diego
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Publication number: 20200208528Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral base and top portions. The airfoil may include a pin connector connecting the top portion to the base portion. The pin connector may include: a tab extending from the top portion; a complimentary slot for receiving the tab formed in the base portion; an elongated pin cavity formed through an interior region of the airfoil, where the pin cavity intersects the slot to divide the pin cavity into first and second pin cavity segments; a tab aperture formed through the tab, where the tab aperture is positioned so align with the pin cavity upon the tab being received within the slot; and a locking pin that extends continuously through the first segment of the pin cavity, the tab aperture, and the second segment of the pin cavity.Type: ApplicationFiled: December 28, 2018Publication date: July 2, 2020Applicant: General Electric CompanyInventors: John McConnell Delvaux, Markus Feigl, Matthew Troy Hafner, Michael Anthony Wondrasek, James Zhang, Peter de Diego
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Publication number: 20200208527Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral portions in which: a base portion is made from a first material; and a top portion is made from a second material. The airfoil may include a connector securing the base portion to the top portion of the airfoil, wherein the connector comprises a wire-lock connector that includes: a tab extending from one of the base portion and the top portion; a complimentary slot for receiving the tab formed in the other one of the base portion and the top portion; a first groove formed in a side of the tab; a second groove formed in a side of the slot; a retaining aperture formed cooperatively via an alignment of the first and second grooves upon the tab being received into the slot; and a retaining wire housed within the retaining aperture.Type: ApplicationFiled: December 28, 2018Publication date: July 2, 2020Applicant: General Electric CompanyInventors: Stanley Kevin Widener, John McConnell Delvaux, Matthew Troy Hafner, James Zhang, Peter de Diego
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Patent number: 10697326Abstract: A turbine component assembly is disclosed, including a first component, a second component, and a cantilever spring. The first component is arranged to be disposed adjacent to a hot gas path, and includes a ceramic matrix composite composition. The second component is adjacent to the first component and arranged to be disposed distal from the hot gas path across the first component. The cantilever spring is attached directly to the second component as a compliant contact interface between the first component and the second component. The cantilever spring provides a radial spring compliance between the first component and the second component. During operation, the cantilever spring directly contacts and supports the first component.Type: GrantFiled: June 15, 2017Date of Patent: June 30, 2020Assignee: GENERAL ELECTRIC COMPANYInventors: Glenn Curtis Taxacher, John McConnell Delvaux, Matthew Troy Hafner
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Publication number: 20200189985Abstract: A ceramic matrix composite (CMC) component includes at least one seal surface, the at least one seal surface disposed adjacent an interfacing surface for providing a seal therebetween; and a coating disposed on the seal surface. The coating includes an aluminum oxide and/or a silicon dioxide.Type: ApplicationFiled: December 14, 2018Publication date: June 18, 2020Applicant: General Electric CompanyInventors: Matthew Troy Hafner, John McConnell Delvaux, Jason Robert Parolini, Rajendra Kumar Bordia, Quan Li
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Publication number: 20200190333Abstract: A coating includes: at least 34.9 percent by mass silicon dioxide; at least 9.1 percent by mass aluminum oxide; and at least 16.1 percent by mass yttrium oxide.Type: ApplicationFiled: December 14, 2018Publication date: June 18, 2020Applicant: General Electric CompanyInventors: Matthew Troy Hafner, John McConnell Delvaux, Jason Robert Parolini, Rajendra Kumar Bordia, Quan Li