Michael Andrew Healy

US Patent:

20220349419, Nov 3, 2022

Filed:

Apr 30, 2021

Appl. No.:

17/245005

Inventors:

- Schenectady NY, US
Kevin Michael Barnett - Greenville SC, US
Matthew John McKeever - Greer SC, US
Michael James Healy - Greenville SC, US

International Classification:

F04D 29/32
F02C 3/04

Abstract:

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.

US Patent:

20180087528, Mar 29, 2018

Filed:

Sep 23, 2016

Appl. No.:

15/274352

Inventors:

- Schenectady NY, US
Michael James Healy - Greenville SC, US

International Classification:

F04D 29/54
F04D 29/32
F04D 29/38
F02C 3/04

Abstract:

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.

US Patent:

20160186574, Jun 30, 2016

Filed:

Dec 29, 2014

Appl. No.:

14/583865

Inventors:

- Schenectady NY, US
Michael James Healy - Greenville SC, US

International Classification:

F01D 5/18
F01D 5/14

Abstract:

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.

US Patent:

20160186593, Jun 30, 2016

Filed:

Dec 31, 2014

Appl. No.:

14/587752

Inventors:

- Schenectady NY, US
Michael James Healy - Greenville SC, US

International Classification:

F01D 11/00
F01D 5/32
F01D 5/30

Abstract:

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.

US Patent:

20150101346, Apr 16, 2015

Filed:

Oct 16, 2013

Appl. No.:

14/055082

Inventors:

- Schenectady NY, US
Michael James Healy - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/30

US Classification:

60805, 416220 R

Abstract:

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.

US Patent:

20150101347, Apr 16, 2015

Filed:

Oct 16, 2013

Appl. No.:

14/055091

Inventors:

- Schenectady NY, US
Michael James Healy - Greenville SC, US
Christian Michael Hansen - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/32

US Classification:

60805, 416220 R

Abstract:

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.

US Patent:

20150101348, Apr 16, 2015

Filed:

Oct 16, 2013

Appl. No.:

14/055095

Inventors:

- Schenectady NY, US
Michael James Healy - Greenville SC, US
Brian Denver Potter - Greer SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/30

US Classification:

60805, 416220 R

Abstract:

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.

US Patent:

20150101349, Apr 16, 2015

Filed:

Oct 16, 2013

Appl. No.:

14/055106

Inventors:

- Schenectady NY, US
Michael James Healy - Greenville SC, US
Brian Denver Potter - Greer SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/30

US Classification:

60805, 416220 R

Abstract:

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.