CRAIG WILLIAM HIGGINS
Pilots at Cyn Rdg Dr, Hamilton, OH

8608436, Dec 17, 2013

Aug 31, 2010

12/872376

Daniel Edward Wines - Cincinnati OH, US
James Hamilton Grooms - Hamilton OH, US
Craig William Higgins - Liberty Township OH, US

General Electric Company - Schenectady NY

F01D 5/02, F01D 11/00

4151742, 416221

A connection between an annular sleeve on a gas turbine engine first rotor component includes an annular tapered conical slot extending axially inwardly into the sleeve from an annular opening and tapers axially into the sleeve from the opening. An annular rim of a second rotor component is received within the conical slot and includes a rim inner conical surface mating with and contacting a sleeve inner conical surface in part bounding the conical slot. A sleeve cylindrical outer surface in part bounds the conical slot in the sleeve and a rim outer cylindrical surface on the annular rim contacts the sleeve cylindrical outer surface. An annular lip may extend radially inwardly from the sleeve and sleeve inner conical surface at the annular opening to the conical slot. The connection may be used between a first stage disk and an interstage seal.

8172506, May 8, 2012

Nov 26, 2008

12/324324

Rafal Piotr Pieczka - Wodzislaw Slaski, PL
Craig William Higgins - Liberty Township OH, US
Piotr Edward Kobek - Warsaw, PL
Jan Franciszek Sikorski - Warsaw, PL
Edward Donald Michaels - Mason OH, US

General Electric Company - Schenectady NY

F03B 11/00, F01D 5/14, F03D 11/00, F04D 31/00

415115

A method and system for a rotatable member of a turbine engine are provided. The rotatable member includes a substantially cylindrical shaft rotatable about a longitudinal axis, and a hub coupled to the cylindrical shaft through a conical shaft portion wherein the conical shaft portion includes a plurality of circumferentially-spaced air passages and wherein at least one of the plurality of air passages includes a non-circular cross section.

7578656, Aug 25, 2009

Dec 20, 2005

11/306224

Craig William Higgins - Liberty Township OH, US
Charles Chris England - Covington KY, US
Joeseph Charles Kulesa - West Chester OH, US
Andrew John Lammas - Maineville OH, US

General Electric Company - Schenectady NY

F01D 5/02

416244A, 416248

A gas turbine engine disk that includes a centrally disposed disk hub having an integrally-formed, radially outwardly extending web terminating at an outer end. The disk hub has a radially-displaced annular hub surface exposed to high pressure, high temperature discharge gases during engine operation. The radially-displaced annular hub surface acts as an axial free surface mitigating the formation undesirable axial stress in the disk hub.

7458774, Dec 2, 2008

Dec 20, 2005

11/306227

Craig William Higgins - Liberty Township OH, US

General Electric Company - Schenectady NY

F01D 5/02

416 1, 416248, 416198 A

A first stage turbine disk section for a gas turbine engine, including a centrally disposed disk hub having an integrally-formed, radially outwardly extending web terminating at an outer end. The disk hub has a convex, curved hub surface exposed to high pressure, high temperature compressor bleed and discharge gases during engine operation, and the convex, curved hub surface acts to reduce the axial constraint at the location of peak axial stress, thereby mitigating the formation of undesirable axial stress in the disk hub and allows separation of the peak axial and hoop stresses, thereby reducing the magnitude of the peak hub surface effective stress.

7331763, Feb 19, 2008

Dec 20, 2005

11/306226

Craig William Higgins - Liberty Township OH, US
Matthew Lee Krumanaker - Cincinnati OH, US

General Electric Company - Schenectady NY

F01D 25/08

416115, 4151995, 415176

A gas turbine section of a gas turbine engine, including a first stage turbine disk, a forward outer seal carried on the turbine disk and a forward shaft cooperating with the first stage turbine disk for transmitting torque generated by the turbine section to a compressor section of the engine. The forward shaft intersects the first stage turbine disk at a non-perpendicular angle in the area of the disk hub for directing sufficient hot air against the disk hub to balance the thermal response rate of the disk hub to the thermal expansion rate of the forward outer seal.

6860722, Mar 1, 2005

Jan 31, 2003

10/356238

James Michael Forrester - Springboro OH, US
Emily Anne Clausing - Cincinnati OH, US
Robert Russell Grant - Mason OH, US
John Gregory Cargill - West Chester OH, US
Craig William Higgins - Hamilton OH, US

General Electric Company - Schenectady NY

F01D005/30

416219R, 416193 A, 416248

A gas turbine engine blade root shim includes a dovetail shim portion with a dovetail shape and a longitudinally extending substantially flat base and distal first and second longitudinally spaced apart forward and aft ends. Transversely spaced apart first and second walls extend upwardly from the base which includes at least two longitudinally extending elongated base apertures. Each of the base apertures includes a main region and longitudinally spaced apart rounded end regions. Dog-bone-shaped base apertures or rounded end base apertures having semi-circular rounded end regions may be used. The shim is designed for a blade dovetail root with a root slot formed in a bottom of the dovetail root. The dovetail shim portion with the dovetail shape substantially conforms to at least a portion of a cross-sectional dovetail shape of the dovetail root through the root slot. The base is disposed within the root slot.