Alan R Stuart

US Patent:

7146388, Dec 5, 2006

Filed:

Oct 7, 2003

Appl. No.:

10/681558

Inventors:

Christopher John Stakutis - Concord MA, US
William Robert Haselton - Peabody MA, US
Kevin Michael Stearns - Maynard MA, US
Alan L. Stuart - Scarsdale NY, US
Toby Lyn Marek - Santa Clara CA, US

Assignee:

International Business Machines Corporation - Armonk NY

International Classification:

G06F 12/00
G06F 17/30

US Classification:

707204, 707200

Abstract:

Provided are a method, system, and program for archiving files. A hierarchical file system having directories is provided. An archival retention policy is associated with at least one of the directories in the hierarchical file system, wherein the retention policy applies to files included in the associated directory, and wherein the retention policy specifies a retention time indicating a time period during which a file is subject to the retention policy.

US Patent:

7673442, Mar 9, 2010

Filed:

Nov 14, 2006

Appl. No.:

11/559761

Inventors:

Jorge Francisco Seda - Cincinnati OH, US
Thomas Ory Moniz - Loveland OH, US
Robert Joseph Orlando - West Chester OH, US
Alan Roy Stuart - Cincinnati OH, US
Kenneth S. Scheffel - Edgewood KY, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02K 1/54

US Classification:

602262, 60725, 23926531

Abstract:

A method for operating a turbofan engine assembly is provided. The turbofan engine assembly includes a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct having an area defined between the core cowl and a portion of the nacelle, a first cowl and a second cowl that define a portion of the nacelle wherein the second cowl is repositionable with respect to the first cowl, and a thrust reverser assembly wherein the second cowl surrounds the thrust reverser assembly. The method includes varying an operating speed of the fan assembly from a first operating speed to a second operating speed. The method further includes selectively positioning the second cowl between a first operational position and a second operational position to vary the area of the fan nozzle duct to facilitate improving engine efficiency at the second operating speed. The method further includes selectively positioning the second cowl between the second operational position and a third operational position to vary an amount of air flowing through the fan nozzle duct and the thrust reverser assembly, wherein the second operational position substantially prevents airflow from flowing through the thrust reverser assembly to improve the efficiency of the turbofan engine, and wherein the third operational position directs airflow through the thrust reverser assembly.

US Patent:

7765177, Jul 27, 2010

Filed:

Aug 18, 2006

Appl. No.:

11/465594

Inventors:

Christopher John Stakutis - Concord MA, US
William Robert Haselton - Peabody MA, US
Kevin Michael Stearns - Maynard MA, US
Alan L. Stuart - Scarsdale NY, US
Toby Lyn Marek - Santa Clara CA, US

Assignee:

International Business Machines Corporation - Armonk NY

International Classification:

G06F 7/00

US Classification:

707 1, 707203

Abstract:

Provided are a method, system, and program for archiving files. A hierarchical file system having directories is provided. An archival retention policy is associated with at least one of the directories in the hierarchical file system, wherein the retention policy applies to files included in the associated directory, and wherein the retention policy specifies a retention time indicating a time period during which a file is subject to the retention policy.

US Patent:

8469309, Jun 25, 2013

Filed:

Dec 24, 2008

Appl. No.:

12/343833

Inventors:

Alan Roy Stuart - Cincinnati OH, US
Mark Linz - Cincinnati OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

B64D 27/26
F16M 13/00
F02C 7/20

US Classification:

244 54, 248554, 60797

Abstract:

Assembly includes an integral monolithic structure for mounting an engine to an aircraft. The monolithic structure includes a nacelle portion and a support structure. The nacelle portion includes an inlet region and a fan case region defining an annular wall about an axial channel. A ring member disposed in the axial channel is connected through a plurality of radial elements to the annular wall. The support structure portion includes a forward section integral with the nacelle portion and an aft section including at least one aircraft mount region for mounting the monolithic structure to an aircraft. The forward section includes an inlet stiffening region radially outward of the annular wall. When mounted on the aircraft, the nacelle portion and the support structure portion cooperate to form a first load path operable to transmit an applied nacelle maneuvering force directly to the aircraft instead of through the engine core.

US Patent:

8479491, Jul 9, 2013

Filed:

Dec 14, 2011

Appl. No.:

13/325203

Inventors:

Alan Roy Stuart - Cincinnati OH, US
John Robert Fehrmann - Loveland OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

B05B 12/00
F02K 3/02
F02K 1/54
F02C 7/20

US Classification:

602262, 60798, 244110 B

Abstract:

A method and system suitable facilitating the connection and disconnection of a thrust reverser assembly to a fan case of a nacelle of a gas turbine engine. The method and system entail operating a clamping system to simultaneously engage and disengage flanges associated with the fan case and flanges associated with the fixed structure of the thrust reverser assembly. The clamping system includes a plurality of over-center clamping mechanisms, each of which is movable to simultaneously clamp together complementary flanges of the thrust reverser assembly and the fan case.

US Patent:

20080010969, Jan 17, 2008

Filed:

Jul 11, 2006

Appl. No.:

11/456666

Inventors:

Thomas Anthony Hauer - West Chester OH, US
Alan Roy Stuart - Cincinnati OH, US
John Robert Fehrmann - Loveland OH, US

International Classification:

F02K 1/54

US Classification:

60204, 602262

Abstract:

A method for operating a gas turbine engine assembly for an aircraft that includes a wing, wherein the gas turbine engine includes a core gas turbine engine and a fan coupled to the core gas turbine engine, the gas turbine engine assembly extends upstream from the wing and includes a first cowl and a second cowl that is repositionable with respect to the first cowl. The method includes selectively positioning the second cowl in a first operational position such that airflow is channeled from the gas turbine engine across a surface of the wing to facilitate increasing lift, and selectively positioning the second cowl in a second operational position such that the airflow is channeled from the gas turbine engine to effect reverse thrust.

US Patent:

20100192595, Aug 5, 2010

Filed:

Jan 30, 2009

Appl. No.:

12/363427

Inventors:

Robert Joseph Orlando - West Chester OH, US
Thomas Ory Moniz - Loveland OH, US
Alan Roy Stuart - Cincinnati OH, US

International Classification:

F02C 3/10

US Classification:

60792

Abstract:

A turbine engine assembly includes, a core gas turbine engine, a first low-pressure turbine section in serial flow communication with the core gas turbine engine, the first low-pressure turbine section configured to rotate in a first rotational direction, a first gear assembly coupled to the first low-pressure turbine section, a second low-pressure turbine section coupled to the gear assembly, the second low-pressure turbine section configured to rotate in a second rotational direction, and a fan assembly coupled to the second low-pressure turbine section.

US Patent:

20110023450, Feb 3, 2011

Filed:

Jul 31, 2009

Appl. No.:

12/533334

Inventors:

Alan Roy Stuart - Cincinnati OH, US
John Robert Fehrmann - Loveland OH, US

International Classification:

F02K 3/02

US Classification:

602262

Abstract:

Assembly for supporting a gas turbine engine comprises a support member including mounting sites for attachment to an associated aircraft. The support member includes integral slider tracks disposed on opposed sidewalls for selective engagement with a translatable cowl. The translatable cowl is translatable along the slider tracks to selectively cover and expose a cascade thrust-reversing structure. The cascade structure includes arcuate segments mounted in hinged relationship to the support member. Rearward translation of the translatable cowl to a service position permits the cascade structure to be opened for access to the core engine.