Eleanor D Kaufman

US Patent:

8016546, Sep 13, 2011

Filed:

Jul 24, 2007

Appl. No.:

11/782001

Inventors:

Raymond Surace - Newington CT, US
Eleanor D. Kaufman - Cromwell CT, US
Andrew D. Milliken - Middletown CT, US
William Abdel-Messeh - Middletown CT, US

Assignee:

United Technologies Corp. - Hartford CT

International Classification:

F01D 25/12

US Classification:

415115, 416193 A

Abstract:

Systems and methods for cooling vane platforms are provided. In this regard, a representative method for cooling a vane platform includes: providing a cooling channel on a platform from which a vane airfoil extends, the cooling channel being defined by a cooling surface and a channel cover, the channel wall being spaced from the cooling surface and located such that the cooling surface is positioned between a gas flow path of the vane and the channel cover; and directing a flow of cooling air through the cooling channel such that heat is extracted from the cooling surface of the platform by the flow of cooling air.

US Patent:

8449254, May 28, 2013

Filed:

Mar 29, 2010

Appl. No.:

12/748501

Inventors:

Matthew A. Devore - Cromwell CT, US
Eleanor D. Kaufman - Cromwell CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 5/18

US Classification:

416 1, 415115, 416 97 R

Abstract:

An example airfoil cooling arrangement includes a airfoil wall having a first face and a second face opposite the first face. The airfoil wall establishes a channel that is configured to communicate fluid between an inlet aperture and an outlet aperture. The channel includes secondary portion that branch from a primary portion. An example airfoil cooling method includes receiving a flow of fluid from a airfoil core cavity and communicating the flow of fluid through channel within a wall of the airfoil. The channel has a secondary portion branching from a primary portion.

US Patent:

20070231138, Oct 4, 2007

Filed:

Mar 28, 2006

Appl. No.:

11/391781

Inventors:

Jeffrey Levine - Vernon CT, US
William Abdel-Messeh - Middletown CT, US
Raymond Surace - Newington CT, US
Eleanor Kaufman - Cromwell CT, US

International Classification:

F01D 5/18

US Classification:

41609700R

Abstract:

A cooling passageway for use in an airfoil portion of a turbine engine component having a pressure side wall and a suction side wall is provided. The cooling passageway comprises a serpentine flow passageway through which a cooling fluid flows. The passageway has an inlet through which cooling fluid is introduced into the passageway, an inlet channel for receiving the cooling fluid, an intermediate channel, and an outlet channel. A divider rib extends from a location in the inlet channel to a termination in the intermediate channel to improve the heat transfer coefficients associated with the passageway.

US Patent:

20070297916, Dec 27, 2007

Filed:

Jun 22, 2006

Appl. No.:

11/473893

Inventors:

Jeffrey R. Levine - Vernon CT, US
William Abdel-Messeh - Middletown CT, US
Eleanor Kaufman - Cromwell CT, US

International Classification:

F01D 5/18

US Classification:

416 96 R

Abstract:

A turbine engine component has an airfoil portion having a leading edge, a suction side, and a pressure side and a radial flow leading edge cavity through which a cooling fluid flows for cooling the leading edge. The turbine engine component further has a staggered arrangement of trip strips for generating a vortex in the leading edge cavity which impinges on a nose portion of the leading edge cavity.

US Patent:

20070297917, Dec 27, 2007

Filed:

Jun 22, 2006

Appl. No.:

11/473894

Inventors:

Jeffrey R. Levine - Vernon CT, US
William Abdel-Messeh - Middletown CT, US
Eleanor Kaufman - Cromwell CT, US

International Classification:

F01D 5/18

US Classification:

416 96 R

Abstract:

A turbine engine component has an airfoil portion having a leading edge, a suction side, and a pressure side and a radial flow leading edge cavity through which a cooling fluid flows for cooling the leading edge. The turbine engine component further has a first set of trip strips and a second set of trip strips which meet at the leading edge nose portion of the leading edge cavity to form a plurality of chevron shaped trip strips and for generating a vortex in the leading edge cavity which impinges on the nose portion of the leading edge cavity and enhances convective heat transfer.

US Patent:

20090238695, Sep 24, 2009

Filed:

Mar 18, 2008

Appl. No.:

12/050408

Inventors:

Matthew A. Devore - Manchester CT, US
Eleanor D. Kaufman - Cromwell CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 5/18

US Classification:

416 97 R

Abstract:

A turbine engine component has an airfoil portion with a pressure side wall, a suction side wall, and a trailing edge. The turbine engine component further has at least one first cooling circuit core embedded within the pressure side wall, with each first cooling circuit core having a first exit for discharging a cooling fluid, at least one second cooling circuit core embedded within the suction side wall, with each second cooling circuit core having a second exit for discharging a cooling fluid, and the first and second exits being aligned in a spanwise direction of the airfoil portion.

US Patent:

20100054915, Mar 4, 2010

Filed:

Aug 28, 2008

Appl. No.:

12/200160

Inventors:

Matthew A. Devore - Manchester CT, US
Eleanor D. Kaufman - Cromwell CT, US
Raymond Surace - Newington CT, US
William Abdel-Messeh - Middletown CT, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Hartford CT

International Classification:

F04D 29/58
F01D 25/12
F01D 5/18

US Classification:

415116, 4152081, 416 96 A

Abstract:

An airfoil insert comprises an insert wall, a contact element and a flow director. The insert wall defines an interior extending inside the insert wall from a first end to second end, and an exterior extending outside the insert wall from the first end to the second end. The contact element is formed on the exterior of the insert wall. The flow director is formed on the insert wall at a boundary between the interior and the exterior. The flow director increases a heat transfer coefficient of convective flow along the insert wall by directing the convective flow to the exterior of the insert wall.

US Patent:

20130243575, Sep 19, 2013

Filed:

Mar 13, 2012

Appl. No.:

13/418854

Inventors:

Mark F. Zelesky - Bolton CT, US
Eleanor D. Kaufman - Cromwell CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F04D 31/00

US Classification:

415116

Abstract:

A turbine engine component includes a first surface to be cooled by a flow of cooling air. The first surface includes a pedestal array and a first row of contour bumps. The pedestal array includes first and second rows of pedestals extending from the first surface. The second row of pedestals runs in a direction generally parallel to the first row of pedestals. The first row of contour bumps extends from the first surface between the first row of pedestals and the second row of pedestals and runs parallel to the first row of pedestals. The first row of contour bumps is aligned such that at least one of the contour bumps of the first row of contour bumps is positioned at least one of immediately downstream of a pedestal of the first row of pedestals and immediately upstream of a pedestal of the second row of pedestals.