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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Publication number: 20160186591Abstract: 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: ApplicationFiled: December 31, 2014Publication date: June 30, 2016Inventors: Michael James Healy, Patrick Daniel Noble, Jeremy Peter Latimer, Brendon James Leary
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Publication number: 20160186593Abstract: 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: ApplicationFiled: December 31, 2014Publication date: June 30, 2016Inventor: Michael James Healy
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Publication number: 20160186592Abstract: 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: ApplicationFiled: December 31, 2014Publication date: June 30, 2016Inventors: Michael James Healy, Jeremy Peter Latimer
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Publication number: 20160186594Abstract: 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: ApplicationFiled: December 31, 2014Publication date: June 30, 2016Inventors: Michael James Healy, Brendon James Leary
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Patent number: 9341071Abstract: Locking spacer assemblies and turbomachines are provided. In one embodiment, a locking spacer assembly includes a spacer, the spacer including a platform and a plurality of legs extending generally radially inward from the platform. The locking spacer assembly further includes a clamp configured to contact and cause elastic deformation of each of the plurality of legs in a generally axial direction towards each other. The locking spacer assembly further includes a locking lug configured to contact and impart a force against each of the plurality of legs in an opposite generally axial direction.Type: GrantFiled: October 16, 2013Date of Patent: May 17, 2016Assignee: General Electric CompanyInventors: Michael James Healy, Brian Denver Potter
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Publication number: 20160032736Abstract: A coating process and coated article are provided. The coating process includes providing a turbine component, applying a coating repellant to a predetermined region of the turbine component, and depositing a coating material on the turbine component. The coating repellant directs the coating material away from the predetermined region of the turbine component, to at least partially form a channel. A coating process for a hot gas path turbine component and coated article are also disclosed.Type: ApplicationFiled: May 15, 2013Publication date: February 4, 2016Applicant: GENERAL ELECTRIC COMPANYInventors: Michael James HEALY, John Wesley HARRIS, JR.
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Publication number: 20150101351Abstract: Locking spacer assemblies and turbomachines are provided. In one embodiment, a locking spacer assembly includes a spacer, the spacer including a platform and a plurality of legs extending generally radially inward from the platform. The locking spacer assembly further includes a clamp configured to contact and cause elastic deformation of each of the plurality of legs in a generally axial direction towards each other. The locking spacer assembly further includes a locking lug configured to contact and impart a force against each of the plurality of legs in an opposite generally axial direction.Type: ApplicationFiled: October 16, 2013Publication date: April 16, 2015Applicant: General Electric CompanyInventors: Michael James Healy, Brian Denver Potter
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Publication number: 20150101350Abstract: A locking spacer assembly for securing adjacent rotor blades includes a first end piece configured to fit into a space between the platforms of adjacent rotor blades. The first end piece comprises an outer surface and an inner surface. The outer surface has a profile that is adapted to project into the attachment slot. A second end piece is configured to fit into a space between the platforms. The second end piece comprises an outer surface and an inner surface. The outer surface has a profile that is adapted to project into the attachment slot. The inner surfaces of the first and second end pieces generally face each other. The first end piece and the second end piece are bonded together either directly or via a spacer block that is inserted between the inner surfaces.Type: ApplicationFiled: October 16, 2013Publication date: April 16, 2015Applicant: General Electric CompanyInventors: Michael James Healy, Brian Denver Potter
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Publication number: 20150101348Abstract: 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: ApplicationFiled: October 16, 2013Publication date: April 16, 2015Applicant: General Electric CompanyInventors: Christian Michael Hansen, Michael James Healy, Brian Denver Potter
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Publication number: 20150101349Abstract: 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: ApplicationFiled: October 16, 2013Publication date: April 16, 2015Applicant: General Electric CompanyInventors: Christian Michael Hansen, Michael James Healy, Brian Denver Potter
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Publication number: 20150101347Abstract: 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: ApplicationFiled: October 16, 2013Publication date: April 16, 2015Applicant: General Electric CompanyInventors: Brian Denver Potter, Michael James Healy, Christian Michael Hansen
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Publication number: 20150101346Abstract: 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: ApplicationFiled: October 16, 2013Publication date: April 16, 2015Applicant: General Electric CompanyInventors: Gregory Thomas Foster, Michael James Healy
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Publication number: 20150096305Abstract: 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: ApplicationFiled: October 4, 2013Publication date: April 9, 2015Applicant: 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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Publication number: 20150044059Abstract: An airfoil includes a main portion formed of a base material. Also included is a trailing edge region of the main portion. Further included is a trailing edge supplement structure comprising at least one pre-sintered preform (PSP) material operatively coupled to the base material proximate the trailing edge region.Type: ApplicationFiled: August 9, 2013Publication date: February 12, 2015Applicant: General Electric CompanyInventors: Stephen Paul Wassynger, John Wesley Harris, JR., Michael James Healy
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Publication number: 20100002719Abstract: An M-CMTS compatible UEQAM device implements circuitry to identify and analyze MAP message in the data stream sent from the M-CMTS Core with respect to timing information embedded in those messages. The improved UEQAM will then create a specific message as an extension to DEPI to communicate that information to the M-CMTS Core. The M-CMTS Core will employ that analysis to automatically adjust MAP message advance time to reduce delay and thus improve system performance. This invention will provide a closed-loop between the M-CMTS Core and the UEQAM where valuable transmission information will periodically be fed back from UEQAM-to-M-CMTS Core in real-time.Type: ApplicationFiled: July 2, 2008Publication date: January 7, 2010Applicant: CISCO TECHNOLOGY, INC.Inventors: Pawel Sowinski, Michael James Healy, John Torrence Chapman, Daniel Wilson Crocker