Anthony P Cherolis

US Patent:

7175386, Feb 13, 2007

Filed:

Dec 17, 2003

Appl. No.:

10/738842

Inventors:

Anthony Cherolis - East Hartford CT, US
Wieslaw A. Chlus - Wethersfield CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 5/14

US Classification:

415115, 416 97 R

Abstract:

A blade for a gas turbine engine includes a trailing edge cooling chamber, wherein the pressure and suction sides are connected by an array of spaced pedestals. The pedestals in a region most subject to thermal stresses are formed to be elliptical, such that the thermal stresses are spread over a larger area. Thus, stress concentrations are reduced. Also, various sized cylindrical pedestals may be used at other locations.

US Patent:

7607891, Oct 27, 2009

Filed:

Oct 23, 2006

Appl. No.:

11/585054

Inventors:

Anthony P. Cherolis - East Hartford CT, US
Jesse R. Christophel - Manchester CT, US
William Abdel-Messeh - Middletown CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 5/08
F01D 5/18

US Classification:

416 97R, 415115

Abstract:

A turbine blade for a gas turbine engine is provided with improved cooling at a radially outer portion of the trailing edge. A tip flag path is provided with a first pedestal array to increase the heat transfer at the area. In addition, a second pedestal array replaces the metering holes which has been positioned radially inwardly of the tip strip. The two pedestal arrays provide improved heat transfer at an area which has been subject to burning and spallation in the prior art.

US Patent:

7708525, May 4, 2010

Filed:

Jun 27, 2005

Appl. No.:

11/167445

Inventors:

Anthony Cherolis - East Hartford CT, US
Jesse Christophel - Manchester CT, US
William Abdel-Messeh - Middletown CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 5/08

US Classification:

416 97R, 416193 A

Abstract:

A gas turbine blade assembly includes a neck defining a neck cavity, and has a first end and a second end at an opposite side relative to the first end. A platform has first and second sides. The first side is disposed on and faces the second end of the neck. An airfoil is supported on the second side of the platform. The neck, platform and airfoil define an inner cooling passage extending through the neck, platform and into the airfoil. The neck defines at least one core channel extending between the cooling passage and the neck cavity. The platform defines at least one film cooling channel extending from the first side facing the neck cavity to the second side disposed exterior to the airfoil to permit cooling air to flow through the inner cooling passage into the neck cavity and through the platform exterior to the airfoil.

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:

8113780, Feb 14, 2012

Filed:

May 14, 2009

Appl. No.:

12/465862

Inventors:

Anthony P. Cherolis - Urbana IL, US
Eric P. Letizia - East Hartford CT, US
Matthew A. Devore - Manchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 5/08
F01D 5/20

US Classification:

416 97R

Abstract:

A gas turbine engine component has a leading edge and a trailing edge and a pressure side and a suction side. The pressure side and suction side extend between the leading edge and trailing edge. One or more cooling passageways extend through the airfoil and comprise a trunk extending from an inlet. At the inlet, there is an additional passageway adjacent the trunk and having at least one edge recessed relative to the trunk.

US Patent:

8137068, Mar 20, 2012

Filed:

Nov 21, 2008

Appl. No.:

12/275793

Inventors:

Raymond Surace - Newington CT, US
Justin D. Piggush - Hartford CT, US
Amarnath Ramlogan - Glastonbury CT, US
Yongxiang D. Xue - Glastonbury CT, US
Anthony P. Cherolis - East Hartford CT, US
Matthew A. Devore - Manchester CT, US
Eric P. Letizia - East Hartford CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 5/18

US Classification:

416 97R, 164 44

Abstract:

The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a plurality of metallic casting cores. Each metallic casting core has opposite first and second faces and a respective portion along the trailing edge of the airfoil. At least two of the metallic cores have sections offset between the pressure side and the suction side.

US Patent:

8171978, May 8, 2012

Filed:

Nov 21, 2008

Appl. No.:

12/275777

Inventors:

Justin D. Piggush - Hartford CT, US
Yongxiang D. Xue - Glastonbury CT, US
Amarnath Ramlogan - Glastonbury CT, US
Anthony P. Cherolis - East Hartford CT, US
Matthew A. Devore - Manchester CT, US
Eric P. Letizia - East Hartford CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B22C 9/04
B22C 9/10

US Classification:

164 35, 164 45, 164516, 164246, 164369

Abstract:

The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a metallic casting core and at least one additional casting core. The metallic casting core has opposite first and second faces. The metallic core and at least one additional casting core extend spanwise into the airfoil of the pattern material. In at least a portion of the pattern material outside the airfoil of the pattern material, the metallic casting core is bent transverse to the spanwise direction so as to at least partially surround an adjacent portion of the at least one additional casting core.

US Patent:

20050135936, Jun 23, 2005

Filed:

Dec 17, 2003

Appl. No.:

10/738288

Inventors:

Anthony Cherolis - East Hartford CT, US
Wieslaw Chlus - Wethersfield CT, US

International Classification:

B63H001/16

US Classification:

41619300A

Abstract:

A turbine blade has an undercut beneath its platform at a trailing edge. The undercut has a complex shape to move thermal stress concentration away from the platform. A preferred undercut shape has a pair of curved fillets at upper and lower extents of the undercut with an intermediate straight section. The intermediate straight section is preferably parallel to a principle stress field of the platform.