Richard J Page

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:

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.

US Patent:

7273353, Sep 25, 2007

Filed:

Aug 14, 2006

Appl. No.:

11/503779

Inventors:

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

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 11/12

US Classification:

416192, 4151736

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 disposed substantially over an axis of the airfoil portion.

US Patent:

7713027, May 11, 2010

Filed:

Aug 28, 2006

Appl. No.:

11/511114

Inventors:

Anthony P. Cherolis - East Hartford CT, US
Richard H. Page - Guilford CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 5/18

US Classification:

416 97R

Abstract:

A gas turbine engine is provided with an airfoil component that is disclosed as a turbine blade. Internal cooling passages circulate air within the blade. An impingement rib separates a cooling air channel from a pedestal array, and includes cross-over holes to meter the flow of air into the pedestal array. A lower end of the impingement rib is split to reduce stress concentrations between the impingement rib and a platform. Further, the pedestals adjacent to the lower end of the impingement rib are formed to be stubs, which do not extend entirely across a width of the blade. The disclosed structure reduces the stress concentration at an area where the impingement rib meets the platform.

US Patent:

8100165, Jan 24, 2012

Filed:

Nov 17, 2008

Appl. No.:

12/271980

Inventors:

Justin D. Piggush - Hartford CT, US
Karl A. Mentz - Hartford CT, US
Richard H. Page - Guilford CT, US
Jesse R. Christophel - Manchester CT, US
Ricardo Trindade - Coventry CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B22C 9/10
B22C 9/04
B22C 7/00

US Classification:

164369, 164 28, 164516, 164361, 164 45, 164235

Abstract:

An investment casting core combination includes a metallic casting core and a ceramic feedcore. A first region of the metallic casting core is embedded in the ceramic feedcore. A mating edge portion of the metallic casting core includes a number of projections. The first region is along at least some of the projections. A number of recesses span gaps between adjacent projections. The ceramic feedcore includes a number of compartments respectively receiving the metallic casting core projections. The ceramic feedcore further includes a number of portions between the compartments and respectively received in the metallic casting core recesses.

US Patent:

8347947, Jan 8, 2013

Filed:

Feb 17, 2009

Appl. No.:

12/372181

Inventors:

Bryan P. Dube - Columbia CT, US
Ryan Shepard Levy - Middletown CT, US
Richard H. Page - Guilford CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B22C 9/10
B28B 7/28

US Classification:

164369, 249175

Abstract:

The present disclosure is directed to a refractory metal core for use in forming varying thickness microcircuits in turbine engine components, a process for forming the refractory metal core, and a process for forming the turbine engine components. The refractory metal core is used in the casting of a turbine engine component. The core is formed by a sheet of refractory metal material having a curved trailing edge portion integrally formed with a leading edge portion.

US Patent:

20090208339, Aug 20, 2009

Filed:

Feb 15, 2008

Appl. No.:

12/032231

Inventors:

Anthony P. Cherolis - East Hartford CT, US
Richard H. Page - Guilford CT, US
Karl A. Mentz - East Hartford CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 5/30
B21K 25/00
B23P 6/00

US Classification:

416219 R, 416193 A, 2988921, 298892

Abstract:

In a gas turbine engine, a stress relief is formed along a blade root and disk slot junction. An exemplary relief is a chamfer along the pressure side of the blade root extending forward from the aft face of the root.