Patents by Inventor Michael James Healy
Michael James Healy 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: 11643933Abstract: A stator vane includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in one of TABLE I or TABLE II. The Cartesian coordinate values of X, Y, and Z are defined relative to a point data origin at a base of the airfoil. The Cartesian coordinate values of X, Y, and Z are non-dimensional values that are convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y, and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values are connected by smooth continuing arcs to define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: September 30, 2022Date of Patent: May 9, 2023Assignee: General Electric CompanyInventors: Matthew John McKeever, Kevin Michael Barnett, Michael James Healy
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Patent number: 11629606Abstract: A compressor section includes a compressor casing that has an upper casing portion coupled to a lower casing portion such that a split-line is defined between the upper casing portion and the lower casing portion. A split-line stator vane assembly includes a first split-line stator vane that has a first shank with a first platform portion and a first mounting portion extends radially outward of the first platform portion. A first airfoil extends radially inward of the platform portion. The first platform portion includes a protrusion that extends circumferentially beyond the split-line. A second split-line stator vane having second shank with a second platform portion and a second mounting portion extends radially outward of the second platform portion. A second airfoil extends radially inward of the second platform portion. The second platform portion includes a recess that extends circumferentially away from the split-line.Type: GrantFiled: July 30, 2021Date of Patent: April 18, 2023Assignee: General Electric CompanyInventors: Michael James Healy, Sabarinath Devarajan, Carlos Alberto Cardoza
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Patent number: 11519272Abstract: A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: April 30, 2021Date of Patent: December 6, 2022Assignee: General Electric CompanyInventors: Paul G. Deivernois, Kevin Michael Barnett, Matthew John McKeever, Michael James Healy
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Patent number: 11519273Abstract: A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, or Table IX. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: July 16, 2021Date of Patent: December 6, 2022Assignee: General Electric CompanyInventors: Michael James Healy, Matthew John McKeever, Sabarinath Devarajan, Uday Krishna Pappala, Kevin Michael Barnett, Kumaran Vale Mudaliar, Wilfried Rick, Moorthi Subramaniyan, Karan Ghule, Denis Stankovic, Yu Wang, Marco Micheli, Mariadas Anton Charles Anandarajah, Michael Loetzerich
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Publication number: 20220381150Abstract: A compressor section includes a compressor casing that has an upper casing portion coupled to a lower casing portion such that a split-line is defined between the upper casing portion and the lower casing portion. A split-line stator vane assembly includes a first split-line stator vane that has a first shank with a first platform portion and a first mounting portion extends radially outward of the first platform portion. A first airfoil extends radially inward of the platform portion. The first platform portion includes a protrusion that extends circumferentially beyond the split-line. A second split-line stator vane having second shank with a second platform portion and a second mounting portion extends radially outward of the second platform portion. A second airfoil extends radially inward of the second platform portion. The second platform portion includes a recess that extends circumferentially away from the split-line.Type: ApplicationFiled: July 30, 2021Publication date: December 1, 2022Inventors: Michael James Healy, Sabarinath Devarajan, Carlos Alberto Cardoza
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Publication number: 20220372878Abstract: A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, or Table IX. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.Type: ApplicationFiled: July 16, 2021Publication date: November 24, 2022Inventors: Michael James Healy, Matthew John McKeever, Sabarinath Devarajan, Uday Krishna Pappala, Kevin Michael Barnett, Kumaran Vale Mudaliar, Wilfried Rick, Moorthi Subramaniyan, Karan Ghule, Denis Stankovic, Yu Wang, Marco Micheli, Mariadas Anton Charles Anandarajah, Michael Loetzerich
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Publication number: 20220349419Abstract: A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.Type: ApplicationFiled: April 30, 2021Publication date: November 3, 2022Inventors: Paul G. Deivernois, Kevin Michael Barnett, Matthew John McKeever, Michael James Healy
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Patent number: 11459892Abstract: A stator vane includes an airfoil having an airfoil shape. The airfoil shape having has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, Table IX, Table X, Table XI, or Table XII. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: November 9, 2021Date of Patent: October 4, 2022Assignee: General Electric CompanyInventors: Matthew John McKeever, Michael James Healy, Wilfried Rick, Rozila Nausheen, Sabarinath Devarajan, Moorthi Subramaniyan, Vsevolod Yuriyevich Ostrovskiy, Kumaran Vale Mudaliar, Damir Novak, Thomas Sommer, Aditya Rajeshbhai Shah, Uday Krishna Pappala, Kevin Michael Barnett, Josip Galic, Gurulakshmi Polisetty, Paul G. Deivernois, Dejan Mikasinovic
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Patent number: 11414996Abstract: A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, Table IX, Table X, Table XI, or Table XII. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: April 30, 2021Date of Patent: August 16, 2022Assignee: General Electric CompanyInventors: Matthew John McKeever, Michael James Healy, Robin Charles Payne, Damir Novak, Bruce Clark Busbey, Wilfried Rick, Thomas Peter Sommer, Ervin Alimani, Kevin Michael Barnett, Carlos Alberto Cardoza, Gerrit Ruch, Dejan Mikasinovic, Denis Stanković, Josip Galic, Olivier Anthony Bron
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Patent number: 11326620Abstract: A stator vane includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, Table IX, Table X, Table XI, or Table XII. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: April 30, 2021Date of Patent: May 10, 2022Assignee: General Electric CompanyInventors: Matthew John McKeever, Michael James Healy, Bruce Clark Busbey, Damir Novak, Robin Charles Payne, Thomas Peter Sommer, Olivier Anthony Bron, Carlos Alberto Cardoza, Lukasz Marcin Maczka, Damir Fanjak, Lance William Smith, Alex David Hollanshead, Wilfried Rick, Yu Wang
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Patent number: 10087952Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.Type: GrantFiled: September 23, 2016Date of Patent: October 2, 2018Assignee: General Electric CompanyInventors: Michael James Dutka, Michael James Healy
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Publication number: 20180087528Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.Type: ApplicationFiled: September 23, 2016Publication date: March 29, 2018Inventors: MIchael James Dutka, Michael James Healy
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Patent number: 9777586Abstract: A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a first axial section of an inner boundary of the flowpath; a second rotor wheel supporting a second rotor blade having a platform that defines a second axial section of the inner boundary of the flowpath; and an annulus filler that includes an outboard surface that defines at least part of a third axial section of the inner boundary of the flowpath occurring between the first axial section and the second axial section of the inner boundary of the flowpath. The first rotor wheel may include an axial connector for axially engaging a mating surface formed on a radially innermost face of the first rotor blade and a mating surface formed on a radially innermost face of the annulus filler.Type: GrantFiled: December 31, 2014Date of Patent: October 3, 2017Assignee: General Electric CompanyInventors: Michael James Healy, Brendon James Leary
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Patent number: 9664058Abstract: A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a first axial section of an inner boundary of the flowpath; a second rotor wheel supporting a second rotor blade having a platform that defines a second axial section of the inner boundary of the flowpath; and an annulus filler that includes an outboard surface that defines at least part of a third axial section of the inner boundary of the flowpath occurring between the first axial section and the second axial section of the inner boundary of the flowpath. The first rotor wheel may include an axial connector for axially engaging a mating surface formed on a radially innermost face of the first rotor blade and a mating surface formed on a radially innermost face of the annulus filler.Type: GrantFiled: December 31, 2014Date of Patent: May 30, 2017Assignee: General Electric CompanyInventors: Michael James Healy, Patrick Daniel Noble, Jeremy Peter Latimer, Brendon James Leary
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Patent number: 9518471Abstract: Locking spacer assemblies, rotor assemblies and turbomachines are provided. In one embodiment, a locking spacer assembly includes a first end piece and a second end piece each configured to fit into a space between platforms of adjacent rotor blades, the first end piece and second end piece each comprising an outer surface and an inner surface, the outer surface having a profile adapted to project into an attachment slot, wherein the inner surfaces of the first and second end pieces generally face each other. The locking spacer assembly further includes an actuator movable between the inner surfaces, the actuator comprising a projection, the projection comprising a first surface and a second surface formed on the projection and configured to engage the inner surfaces, the first and second surfaces generally perpendicular to radial.Type: GrantFiled: October 16, 2013Date of Patent: December 13, 2016Assignee: General Electric CompanyInventors: Christian Michael Hansen, Michael James Healy, Brian Denver Potter
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Patent number: 9512732Abstract: A locking spacer assembly for securing adjacent rotor blades includes a first end piece having a platform portion and a root portion that define an angled first inner surface of the first end piece. The root portion defines a first projection adapted to project into a recess portion of the attachment slot. A second end piece fits between the first inner surface and a sidewall portion of the attachment slot and includes a platform portion and a root portion that define a second projection adapted to project into a recess portion of the attachment slot. The platform portion and the root portion define an angled second inner surface and that is configured to mate with the first inner surface. A borehole extends through the platform portion of the first end piece and the root portion of the second end piece and a fastener extends through the borehole.Type: GrantFiled: October 16, 2013Date of Patent: December 6, 2016Assignee: GENERAL ELECTRIC COMPANYInventors: Brian Denver Potter, Michael James Healy, Christian Michael Hansen
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Patent number: 9464531Abstract: Locking spacer assemblies, rotor assemblies and turbomachines are provided. In one embodiment, a locking spacer assembly includes a first end piece and a second end piece each configured to fit into a space between platforms of adjacent rotor blades, the first end piece and second end piece each comprising an outer surface and an inner surface, the outer surface having a profile adapted to project into an attachment slot, wherein the inner surfaces of the first and second end pieces generally face each other. The locking spacer assembly further includes an actuator movable between the inner surfaces, the actuator comprising a projection configured to engage the inner surface, the actuator further comprising a plurality of locating protrusions extending from the projection, the locating protrusions configured to fit within locating channels defined in the first end piece and the second end piece.Type: GrantFiled: October 16, 2013Date of Patent: October 11, 2016Assignee: General Electric CompanyInventors: Christian Michael Hansen, Michael James Healy, Brian Denver Potter
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Patent number: 9458725Abstract: A method and system for providing cooling of a turbine component that includes a region to be cooled is provided. A recess is defined within the region to be cooled, and includes an inner face. At least one support projection extends from the inner face. The at least one support projection includes a free end. A cover is coupled to the region to be cooled, such that an inner surface of the cover is coupled to the free end of the at least one support projection, such that at least one cooling fluid passage is defined within the region to be cooled.Type: GrantFiled: October 4, 2013Date of Patent: October 4, 2016Assignee: General Electric CompanyInventors: Victor John Morgan, John Wesley Harris, Jr., Michael James Healy, Aaron Ezekiel Smith, Brian Gene Brzek, Donald Earl Floyd, II
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Patent number: 9416670Abstract: A locking spacer assembly for securing adjacent rotor blades includes a first end piece having a platform portion and a root portion that define a first inner surface of the first end piece. The root portion defines a first projection and an opposing second projection of the first end piece. The first projection has an outer profile adapted to project into a first lateral recess of the attachment slot. The second projection has an outer profile adapted to project into a second lateral recess of the attachment slot. A second end piece fits between the first inner surface of the first end piece and a sidewall portion of the attachment slot and includes a platform portion and a root portion. A borehole extends continuously through the first end piece and the second end piece. A fastener configured to engage with a sidewall portion of the attachment slot extends through the borehole.Type: GrantFiled: October 16, 2013Date of Patent: August 16, 2016Assignee: GENERAL ELECTRIC COMPANYInventors: Gregory Thomas Foster, Michael James Healy
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Publication number: 20160186574Abstract: A blade for a turbine of a gas turbine engine that includes an airfoil, the airfoil having a leading edge, a trailing edge, an outboard tip, and an inboard end. The airfoil may further include a cooling configuration that includes a plurality of cooling channels for receiving and directing a coolant. The cooling channels may include a linear cooling channel and a curved cooling channel. The blade may also include a contoured shape defined by the airfoil between the inboard end and the outboard tip, with the contoured shape being configured so to include a target area inaccessible to a linear reference line extending radially from a position at the inboard end of the airfoil. The curved cooling channels may be configured to extend between an upstream end and a downstream end so to intersect the target area therebetween.Type: ApplicationFiled: December 29, 2014Publication date: June 30, 2016Inventors: Joseph Anthony Weber, Michael James Healy