James Michael Forrester

US Patent:

6341419, Jan 29, 2002

Filed:

Feb 29, 2000

Appl. No.:

09/515169

Inventors:

James M. Forrester - Springboro OH
Richard A. Wesling - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

B23P 1500

US Classification:

298892, 700279, 416129

Abstract:

A plurality of rotors are individually measured for determining relative eccentricity between forward and aft annular mounting ends thereof. The measured rotor eccentricities are stacked analytically to minimize eccentricity from a centerline axis. The rotors are then assembled axially end-to-end to correspond with the stacked measured eccentricities thereof.

US Patent:

6416280, Jul 9, 2002

Filed:

Nov 27, 2000

Appl. No.:

09/723113

Inventors:

James Michael Forrester - Springboro OH
Joseph Timothy Stevenson - Amelia OH
Jeffrey Clayton Potter - Holand MI
Sean Joel Corrigan - Fairfield OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

B64C 1114

US Classification:

416 94, 416219 R, 416245 R

Abstract:

An exemplary embodiment of the invention is a spinner for a front end of a fan assembly of a gas turbine engine. The spinner includes a single piece substantially conically shaped hollow body circumscribed about a centerline extending aftwardly from a tip to an axially aft spinner end. A plurality of bolt holes extend axially parallel to the centerline through the hollow body at an axial location between the tip and the aft spinner end. The hollow body may include a forward conical section extending aftwardly from the tip to a transition section, an aft conical section extending aftwardly from the transition section to the aft spinner end, and the bolt holes are axially located in the transition section. An aft spinner flange attached to the axially aft spinner end includes a plurality of flange lightening holes axially disposed through the aft spinner flange and the flange lightening holes.

US Patent:

6447250, Sep 10, 2002

Filed:

Nov 27, 2000

Appl. No.:

09/723108

Inventors:

Sean Joel Corrigan - Fairfield OH
Jeffrey Clayton Potter - Holland MI
Joseph Timothy Stevenson - Amelia OH
Jay L. Cornell - Hamilton OH
James Michael Forrester - Springboro OH
Rolf Robert Hetico - Cincinnati OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 522

US Classification:

416193A, 416219 R, 416245 R, 416248

Abstract:

A gas turbine engine rotor disk has a number of annular hubs circumscribed about a centerline and each of the hubs is connected to a disk rim by a web. A plurality of circumferentially spaced apart circular arc dovetail slots are disposed through the rim. Circumferentially extending annular burst slots extend radially through the rim into the dovetail slots between each adjacent pair of the webs. The fan blades have circular arc dovetail roots disposed within the circumferentially spaced apart circular arc dovetail slots. A one piece spinner attached to a forward extension of the disk at a location between a tip and an axially aft spinner end of the spinner. Non-integral platforms circumferentially disposed between the fan blades. A booster spool is connected to the rotor disk by a mounting plate therebetween and the platforms are radially retained to the disk and mounting plates by pins through holes in mounting lugs depending radially inwardly from the platforms. Pairs of circumferentially oppositely facing retaining slots have retainers disposed therein which extend across the dovetail slots to axially retain the dovetail roots in the dovetail slots.

US Patent:

6457942, Oct 1, 2002

Filed:

Nov 27, 2000

Appl. No.:

09/723112

Inventors:

James Michael Forrester - Springboro OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 532

US Classification:

416220R, 416193 A, 416221, 416244 A

Abstract:

An exemplary embodiment of the invention is a gas turbine engine retainer having a block, a retainer slot disposed through the block, and a shelf normal to and extending axially forward of the block below the retainer slot. A retainer wall depending radially inwardly from the block and the retainer wall has a retainer wall thickness smaller than a block thickness of the block. The shelf is disposed along a radially inner edge of the retainer wall and the retainer slot is disposed through the retainer wall along the shelf. The retainer slot is arced or curved sideways and may be rectangular in cross-section. The retainer slot may be rectangular in cross-section and the shelf may be a rectangular shelf that is rectangular in cross-section. The retainer slot may also be skewed sideways with respect to a shelf centerline extending axially down a middle of the shelf. A radially extending shelf aperture is disposed through the shelf.

US Patent:

6481971, Nov 19, 2002

Filed:

Nov 27, 2000

Appl. No.:

09/723110

Inventors:

James Michael Forrester - Springboro OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 532

US Classification:

416221, 416220 R, 416500

Abstract:

A gas turbine engine blade spacer has an axially extending backbone, spaced apart forward, mid and aft dovetail lands, respectively, disposed along the backbone, the backbone and the forward, mid, and aft dovetail lands having bottom curved backbone surfaces. Each of the forward, mid and aft dovetail lands has a riser that extends above the backbone and has a riser flat top. In the exemplary embodiment disclosed herein, a spacer tab extends generally axially forward of the forward land and includes intersecting axially and radially extending tab apertures. A void extends around the backbone and between the forward and aft dovetail lands and the void is filled with an elastomeric material. The spacer has a constant shape and size cross-section between the forward and aft dovetail lands. The spacer has a particular use with circular arc dovetail slots and roots for which the spacer is a circular arc shaped spacer and the backbone, and the forward, mid and aft dovetail lands are curved along a circular arc normal to and about a radial axis. The spacer tab has a rectangular cross-section, extends axially out of a forward face of the forward land, and has a tab flat top that is co-planar with the riser flat tops of the risers.

US Patent:

6520742, Feb 18, 2003

Filed:

Nov 27, 2000

Appl. No.:

09/723109

Inventors:

James Michael Forrester - Springboro OH
Janine Elizabeth Bolt - Fairfield OH
James Edwin Rhoda - Mason OH
Joseph Timothy Stevenson - Amelia OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 532

US Classification:

416220R, 416221, 416244 A, 416245 R

Abstract:

A gas turbine engine rotor disk has a number of annular hubs circumscribed about a centerline and each of the hubs is connected to a disk rim by a web. A plurality of circumferentially spaced apart dovetail slots are disposed through the rim, extending circumferentially between disk posts, extending axially from a forward end to an aft end of the rim, and extending radially inwardly from a disk outer surface of the rim. Circumferentially extending annular burst slots extend radially through the rim into the dovetail slots between each adjacent pair of the webs. In the exemplary embodiment of the disk illustrated herein, the dovetail slots are circular arc dovetail slots. An axially forwardly extending overhang is located radially outwardly on each of the disk posts and a chamfer is on a radially outer corner of the each of the disk posts on a portion of the overhangs. A plurality of post holes extending axially aftwardly into the rim wherein each of the post hole extends axially aftwardly into a corresponding one of the disk posts.

US Patent:

6634863, Oct 21, 2003

Filed:

Nov 27, 2000

Appl. No.:

09/723111

Inventors:

James Michael Forrester - Springboro OH
Joseph Timothy Stevenson - Amelia OH
Jeffrey Clayton Potter - Holland MI
Sean Joel Corrigan - Fairfield OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 532

US Classification:

416220R, 416193 A, 416221, 416244 A, 416245 R, 602261

Abstract:

A gas turbine engine rotor disk has a number of annular hubs circumscribed about a centerline and each of the hubs is connected to a disk rim by a web. A plurality of circumferentially spaced apart circular arc dovetail slots are disposed through the rim. Circumferentially extending annular burst slots extend radially through the rim into the dovetail slots between each adjacent pair of the webs. The fan blades have circular arc dovetail roots disposed within the circumferentially spaced apart circular arc dovetail slots. A one piece spinner attached to a forward extension of the disk at a location between a tip and an axially aft spinner end of the spinner. Non-integral platforms circumferentially disposed between the fan blades. A booster spool is connected to the rotor disk by a mounting plate therebetween and the platforms are radially retained to the disk and mounting plates by pins through holes in mounting lugs depending radially inwardly from the platforms. Pairs of circumferentially oppositely facing retaining slots have retainers disposed therein which extend across the dovetail slots to axially retain the dovetail roots in the dovetail slots.

US Patent:

6860722, Mar 1, 2005

Filed:

Jan 31, 2003

Appl. No.:

10/356238

Inventors:

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

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D005/30

US Classification:

416219R, 416193 A, 416248

Abstract:

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.