Ronald G Tolbert

US Patent:

6478896, Nov 12, 2002

Filed:

Jun 7, 1995

Appl. No.:

08/473798

Inventors:

Swami Ganesh - West Chester OH
Ronald Gene Tolbert - Cincinnati OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

C22C 1905

US Classification:

148428, 148675, 148677, 148902

Abstract:

A turbine disk for a gas turbine engine differentially heat treated so as to produce a dual property disk. The process is applicable to superalloy disks, and achieves substantially uniform yet different temperatures in the rim and hub of the disk during heat treatment, so as to attain specific and different properties for the rim and hub. The process includes the steps of heat treating the entire disk to achieve a uniform structure having a fine grain size and fine precipitates. A device for heating the rim of the disk is then disposed at the disks periphery, such that the rim is maintained at a substantially uniform temperature above the gamma prime solvus temperature of the superalloy so as to dissolve gamma prime precipitates present in the rim and cause grain growth in the rim. The hub is thermally insulated from the heating device and cooled with an apparatus that enables the hub to be maintained at a substantially uniform temperature that is below the gamma prime solvus temperature of the superalloy. This apparatus insulates and cools the hub such that a temperature gradient is established in the web portion of the disk between the rim and hub, yet substantially uniform temperatures are maintained in the rim and hub.

US Patent:

8480368, Jul 9, 2013

Filed:

Feb 5, 2010

Appl. No.:

12/701050

Inventors:

Ronald Gene Tolbert - Cincinnati OH, US
Eric Scott Huron - West Chester OH, US
David Paul Mourer - Beverly MA, US
Douglas Gerard Konitzer - West Chester OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/02

US Classification:

416213R, 416234, 416241 R, 2988923, 148649

Abstract:

A process of fabricating a rotating component and components formed thereby. The process includes fabricating preforms corresponding to portions of the component. Each preform has an interface surface at which the preforms can be joined to locate a first of the portions in a radially outward direction from a second of the portions. The preforms are then inertia welded together to form a profile having a solid-state weld joint containing a finer-grained material than other portions of the profile. The profile is then forged with dies to produce a forging. At least one of the dies has a recess into which the finer-grained material from the weld joint is expelled during forging to purge a joint region of the forging between the forging portions of the finer-grained material. The joint region contains grains distorted in an axial direction of the forging.

US Patent:

55270204, Jun 18, 1996

Filed:

Jun 7, 1995

Appl. No.:

8/473797

Inventors:

Swami Ganesh - West Chester OH
Ronald G. Tolbert - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

C21D 162

US Classification:

266260

Abstract:

Apparatus for differentially heat treating a turbine disk of a gas turbine engine so as to produce a dual property superalloy disk. The apparatus enables a process to achieve substantially uniform yet different temperatures in the rim and hub of the disk during heat treatment, so as to attain specific and different properties for the rim and hub. The process includes the steps of heat treating the entire disk to achieve a uniform structure having a fine grain size and fine precipitates. A device for heating the rim of the disk is then disposed at the disk's periphery, such that the rim is maintained at a substantially uniform temperature above the gamma prime solvus temperature of the superalloy so as to dissolve gamma prime precipitates present in the rim and cause grain growth in the rim. The hub is thermally insulated from the heating device and cooled with an apparatus that enables the hub to be maintained at a substantially uniform temperature that is below the gamma prime solvus temperature of the superalloy. This apparatus insulates and cools the hub such that a temperature gradient is established in the web portion of the disk between the rim and hub, yet substantially uniform temperatures are maintained in the rim and hub.

US Patent:

55274021, Jun 18, 1996

Filed:

Aug 25, 1994

Appl. No.:

8/295980

Inventors:

Swami Ganesh - West Chester OH
Ronald G. Tolbert - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

C22C 1900

US Classification:

148675

Abstract:

A process for differentially heat treating a turbine disk of a gas turbine engine so as to produce a dual property disk. The process is applicable to superalloy disks, and achieves substantially uniform yet different temperatures in the rim and hub of the disk during heat treatment, so as to attain specific and different properties for the rim and hub. The process includes the steps of heat treating the entire disk to achieve a uniform structure having a fine grain size and fine precipitates. A device for heating the rim of the disk is then disposed at the disk's periphery, such that the rim is maintained at a substantially uniform temperature above the gamma prime solvus temperature of the superalloy so as to dissolve gamma prime precipitates present in the rim and cause grain growth in the rim. The hub is thermally insulated from the heating device and cooled with an apparatus that enables the hub to be maintained at a substantially uniform temperature that is below the gamma prime solvus temperature of the superalloy. This apparatus insulates and cools the hub such that a temperature gradient is established in the web portion of the disk between the rim and hub, yet substantially uniform temperatures are maintained in the rim and hub.