Bryan P Dube

US Patent:

6607355, Aug 19, 2003

Filed:

Oct 9, 2001

Appl. No.:

09/973222

Inventors:

Frank J. Cunha - Avon CT
Young H. Chon - Manchester CT
Bryan P. Dube - Middletown CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 518

US Classification:

416 97R

Abstract:

A turbine airfoil section having an internal cavity and a plurality of indentations on the inner surface of the internal cavity is described. The indentations provide enhanced heat transfer for cooling the internal cavity of an airfoil thereby improving the life of the airfoil and optimizing the efficiency of the engine by minimizing the amount of compressor bleed air required. Advantageously, this cooling scheme also does not restrict the cooling flow within the internal cavity. The indentations may have varying patterns and alternative geometric configurations.

US Patent:

6884023, Apr 26, 2005

Filed:

Sep 27, 2002

Appl. No.:

10/260083

Inventors:

Bryan Dube - Columbia CT, US
Andrew D. Milliken - Middletown CT, US
John H. Mosley - Portland CT, US
Conan Cook - Norwich VT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F04D031/00

US Classification:

415116, 415115, 415117, 4151735, 4151745

Abstract:

The present invention relates to a system for delivering cooling air to a seal arrangement in a turbine stage of a gas turbine engine. The system comprises at least one vane having a passageway extending from an outer platform of the at least one vane to an inner platform of the at least one vane. A tube insert is positioned within the passageway. The tube insert has an inlet at one end for receiving cooling air from a source of cooling air and an outlet at a second end. A cover assembly is attached to the second end of the tube for receiving cooling air from the tube and delivering the cooling air to the seal arrangement. In a preferred embodiment, the cooling air is pre-swirled in the direction of rotation of a rotor stage of the turbine stage.

US Patent:

6929054, Aug 16, 2005

Filed:

Dec 19, 2003

Appl. No.:

10/741710

Inventors:

James T. Beals - West Hartford CT, US
Samuel D. Draper - Kohler WI, US
Jose A. Lopes - Glastonbury CT, US
Stephen D. Murray - Marlborough CT, US
Brandon W. Spangler - Rocky Hill CT, US
Michael K. Turkington - Manchester CT, US
Bryan P. Dube - Columbia CT, US
Keith A. Santeler - Middletown CT, US
Jacob A. Snyder - Southington CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B22C009/10

US Classification:

164369, 164397, 164365

Abstract:

A sacrificial core for forming an interior space of a part includes a ceramic core element and a first core element including a refractory metal element. The ceramic core element may be molded over the first core element or molded with assembly features permitting assembly with the first core element.

US Patent:

6932571, Aug 23, 2005

Filed:

Feb 5, 2003

Appl. No.:

10/358646

Inventors:

Frank Cunha - Avon CT, US
Bryan Dube - Columbia CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D005/18

US Classification:

416 97R

Abstract:

An improved cooling design and method for cooling airfoils within a gas turbine engine is provided which includes an embedded microcircuit that traverses a tip between a suction sidewall and a pressure sidewall of the airfoil. The microcircuit includes at least on inlet disposed proximate to the tip and one of the sidewalls for receiving cooling air from an internal cooling cavity of the airfoil and at least outlet disposed proximate to the tip through which the cooling air ejects into a region outside the airfoil.

US Patent:

6997675, Feb 14, 2006

Filed:

Feb 9, 2004

Appl. No.:

10/774989

Inventors:

Bryan P. Dube - Columbia CT, US
William Abdel-Messeh - Middletown CT, US
Daniel Herrera - East Hartford CT, US
Richard Page - Guilford CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 5/08

US Classification:

415115, 416 96 R, 416 97 R

Abstract:

A turbine blade having improved cooling has an airfoil with a root end and a tip end and at least one cooling passageway in the airfoil. Each cooling passageway extends from the root end to the tip end and has a circular cross-section. A plurality of turbulation promotion devices are arranged in each cooling passageway. Each of the turbulation promotion devices is arcuate in shape and circumscribes an arc less than 180 degrees.

US Patent:

7066713, Jun 27, 2006

Filed:

Jan 31, 2004

Appl. No.:

10/770323

Inventors:

Bryan P. Dube - Columbia CT, US
Eric D. Gray - Wallingford CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 11/08

US Classification:

4151735, 416190, 416191, 416192

Abstract:

A rotor blade having a wing and beam construction for a tip shroud is disclosed. Various construction details are developed for providing a transition zone that extends from the suction side and pressure side of the airfoil to provide a flow path surface of the shroud. In one detailed embodiment, the transition zone is contoured under the beam differently than a portion under the rear portions of the wings.

US Patent:

7094023, Aug 22, 2006

Filed:

Feb 9, 2004

Appl. No.:

10/774824

Inventors:

Bryan P. Dube - Columbia CT, US
Richard Page - Guilford CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 11/08

US Classification:

4151731, 4151736, 416189, 416191, 416192

Abstract:

A turbine blade for use in a gas turbine engine is provided. The turbine blade includes an airfoil portion having a tip end, a shroud attached to the tip end, which shroud has an outer surface, and a knife edge attached to an outer surface of the shroud. The knife edge has a pair of cutter blades protruding outwardly from the knife edge.

US Patent:

7114916, Oct 3, 2006

Filed:

Feb 9, 2004

Appl. No.:

10/774822

Inventors:

Bryan P. Dube - Columbia CT, US
William Abdel-Messeh - Middletown CT, US
Daniel Herrera - East Hartford CT, US
Richard Page - Guilford CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F03D 11/00

US Classification:

415115, 416 95, 416 96 R

Abstract:

A turbine blade having improved cooling characteristics is provided. The turbine blade has an airfoil portion having a span, and at least one cooling passageway in the airfoil portion extending from a root portion of the airfoil portion to a tip portion of the airfoil portion. A plurality of turbulation promotion devices are placed in the at least one cooling passageway. The turbulation promotion devices have a P/e ratio which varies along the span of the airfoil portion, where P is the pitch between adjacent turbulation promotion devices and e is the height of the turbulation promotion devices.