Joseph A Stevenson

US Patent:

6364616, Apr 2, 2002

Filed:

May 5, 2000

Appl. No.:

09/567553

Inventors:

Joseph Timothy Stevenson - Amelia OH
Wendy Wen-Ling Lin - Niskayuna NY

Assignee:

General Electric Company - Cincinnati OH

International Classification:

B64C 1116

US Classification:

416233, 416224, 416229 R, 416229 A, 416241 A

Abstract:

A fan blade includes a metal airfoil having a pocket disposed in a first side thereof, with the pocket including a filler bonded thereto. The pocket includes a plurality of cells separated by corresponding ribs which are submerged in the filler.

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:

52267849, Jul 13, 1993

Filed:

Sep 25, 1992

Appl. No.:

7/951929

Inventors:

Peter W. Mueller - Morrow OH
Joseph T. Stevenson - Amelia OH
Josef Panovsky - Hamilton OH
Christopher C. Glynn - Hamilton OH
Sang Y. Park - W. Chester OH
Daniel E. Wines - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 510

US Classification:

416248

Abstract:

The present invention provides a phase independent damper and damper assembly capable of damping rotor blade vibrations in the axial, circumferential, and radial directions. One embodiment, particularly useful in an aircraft gas turbine engine compressor rotor, provides a damper and damper assembly including a generally axially extending blade damper operable to fictionally engage a generally axially extending circumferentially facing surface of a disk and axially extending angled surface under the platform of the blade. The invention provides an additional advantage of allowing simple and easy modification of existing engines to incorporate the damper of the present invention.

US Patent:

60331860, Mar 7, 2000

Filed:

Apr 16, 1999

Appl. No.:

9/293383

Inventors:

Jan C. Schilling - Middletown OH
Jay L. Cornell - Hamilton OH
Joseph T. Stevenson - Amelia OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

B63H 126
B64C 1124

US Classification:

416233

Abstract:

A fan blade includes a metal airfoil having first and second opposite sides extending radially between a root and tip, and axially between a leading edge and a trailing edge. The airfoil further includes a plurality of pockets disposed in the first side and separated by corresponding ribs. A filler is bonded in the pocket, and is coextensive with the airfoil first side. Radial and diagonal ribs respectively intersect solely each other for selectively increasing torsional and bending stiffness to increase frequency margin between adjacent torsional and bending resonant modes of vibration.

US Patent:

60395427, Mar 21, 2000

Filed:

Dec 24, 1997

Appl. No.:

8/997832

Inventors:

Jan C. Schilling - Middletown OH
Jay L. Cornell - Hamilton OH
Joseph T. Stevenson - Amelia OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

B64C 1116

US Classification:

416233

Abstract:

A fan blade includes a metal airfoil having first and second opposite sides extending radially between a root and a tip, and axially between a leading edge and a trailing edge. The airfoil further includes a pocket disposed in the first side having an elastomeric filler bonded therein. A panel is bonded to the filler along the pocket for allowing differential movement therebetween for damping vibratory response of the airfoil.

US Patent:

59476885, Sep 7, 1999

Filed:

Dec 22, 1997

Appl. No.:

8/995975

Inventors:

Jan C. Schilling - Middletown OH
Jay L. Cornell - Hamilton OH
Joseph T. Stevenson - Amelia OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

B63H 126
B64C 1124

US Classification:

416233

Abstract:

A fan blade includes a metal airfoil having first and second opposite sides extending radially between a root and tip, and axially between a leading edge and a trailing edge. The airfoil further includes a plurality of pockets disposed in the first side and separated by corresponding ribs. A filler is bonded in the pocket, and is coextensive with the airfoil first side. Radial and diagonal ribs respectively intersect solely each other for selectively increasing torsional and bending stiffness to increase frequency margin between adjacent torsional and bending resonant modes of vibration.

US Patent:

51015579, Apr 7, 1992

Filed:

Nov 14, 1990

Appl. No.:

7/613340

Inventors:

Peter W. Mueller - Morrow OH
Dewey D. Dunkman - Cincinnati OH
Joseph T. Stevenson - Amelia OH
Elbert Stonom - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

B23B 524

US Classification:

298897

Abstract:

A method of using a rotor mountable fixture for guiding a cutting tool powered by a hand held air motor to machine a gas turbine engine rotor without removing the rotor from its mountings in the engine is provided. In one particular embodiment the fixture includes a root having the same contour as a blade root slot of a rotor, a base having a platform attached to the root, and a machining guide in the form of a bushing restrained in a guide slot operable to receive a guide a hand held air motor powered cutting tool for machining the rotor. The present invention provides an accurate means to machine a gas turbine engine rotor without removing the rotor from its mounting. In one particular embodiment a method for machining the rotor in the field is provided using a hand held air motor to power a machining tool to cut a blade damper pocket in the dovetail slot of a pressure compressor rotor.

US Patent:

59136618, Jun 22, 1999

Filed:

Dec 22, 1997

Appl. No.:

8/995979

Inventors:

Josef Panovsky - Hamilton OH
Joseph T. Stevenson - Amelia OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

B63H 126

US Classification:

416229A

Abstract:

A fan blade includes a metal airfoil having first and second opposite sides extending longitudinally between a root and a tip, and laterally between a leading edge and a trailing edge. The airfoil further includes a plurality of fine striations spaced laterally apart between the leading and trailing edges in the airfoil first side, and extending longitudinally between the root and the tip. A viscoelastic filler is bonded in the striations for damping torsional vibrations of the airfoil.