Adebukola O Benson

US Patent:

20110236220, Sep 29, 2011

Filed:

Mar 25, 2010

Appl. No.:

12/731783

Inventors:

Adebukola Benson - Greenville SC, US
Gary Michael Itzel - Simpsonville SC, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F01D 5/18

US Classification:

416 97 R

Abstract:

An airfoil is provided and includes a body formed to define a substantially radially extending cooling hole therein, which is configured to be receptive of a supply of a coolant for removing heat from the body, and a flag region therein, which is fluidly communicative with the cooling hole and thereby configured to be receptive of a portion of the supply of the coolant such that the coolant portion is directed to form a vortex within the flag region to increase heat removal from the body beyond that provided by the coolant flow through the cooling hole.

US Patent:

20120171047, Jul 5, 2012

Filed:

Jan 3, 2011

Appl. No.:

12/983400

Inventors:

Gary Michael Itzel - Simpsonville SC, US
Adebukola O. Benson - Simpsonville SC, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F01D 5/18

US Classification:

416 97 R

Abstract:

An airfoil component for use in a turbomachine, and method of promoting the heat transfer characteristics within the component. The component includes an airfoil portion having a span-wise direction delimited by an airfoil root and airfoil tip, and a chord-wise direction delimited by leading and trailing edges. A chamber within the airfoil portion contains a permeable foam member. The chamber is fluidically connected to a cooling fluid source and to a cooling hole through first and second passages, respectively, within the airfoil portion. The chamber is located relative to the first and second passages so as to be offset in the chord-wise direction therefrom so that cooling fluid entering the chamber through the first passage is diverted by the foam member in the chord-wise direction before exiting the airfoil portion through the cooling hole.

US Patent:

20130195650, Aug 1, 2013

Filed:

Jan 27, 2012

Appl. No.:

13/359691

Inventors:

Adebukola O. Benson - Greenville SC, US
Xiuzhang James Zhang - Greenville SC, US
Gary Michael Itzel - Greenville SC, US

International Classification:

F01D 5/18

US Classification:

416 1, 416 97 R

Abstract:

A turbine airfoil includes a blade having a leading and trailing edges and an internal cooling circuit, and a plurality of film holes extending between the internal cooling circuit and an exterior of the blade. The plurality of film holes are shaped to generate a swirling flow exiting the film holes adjacent the leading edge to thereby enhance local convection and provide an insulating barrier to gaspath flow.

US Patent:

20140064984, Mar 6, 2014

Filed:

Aug 31, 2012

Appl. No.:

13/600782

Inventors:

Xiuzhang James Zhang - Simpsonville SC, US
Camilo Andres Sampayo - Greer SC, US
Adebukola Oluwaseun Benson - Simpsonville SC, US
Christopher William Kester - Greenville SC, US

International Classification:

F01D 5/18

US Classification:

416 97 R

Abstract:

A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root. The platform may include a pressure side slashface and a suction side slashface. The platform cooling arrangement may include: a cooling channel formed within the interior of the platform, the cooling channel extending from a first end toward one of the pressure side slashface and the suction side slashface. At a second end, the cooling channel may include a pocket. The pocket may include an abrupt increase in cross-sectional flow area just before the cooling channel reaches the slashface.

US Patent:

20180016902, Jan 18, 2018

Filed:

Jul 12, 2016

Appl. No.:

15/207750

Inventors:

- Schenectady NY, US
Adebukola Oluwaseun Benson - Simpsonville SC, US
Melbourne James Myers - Woodruff SC, US
Peter Paul Pirolla - Greer SC, US
William Scott Zemitis - Simpsonville SC, US

International Classification:

F01D 5/14
F01D 25/24

Abstract:

Various embodiments of the invention include turbine blades and systems employing such blades. Various particular embodiments include a turbine blade having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side, wherein the trailing edge defines a radial throat distribution between the airfoil and an adjacent airfoil; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge.

US Patent:

20150252673, Sep 10, 2015

Filed:

Mar 6, 2014

Appl. No.:

14/198659

Inventors:

- Schenectady NY, US
James Ryan Connor - Greenville SC, US
Bryan David Lewis - Mauldin SC, US
Adebukola Oluwaseun Benson - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/08
B23P 15/02

Abstract:

Platform cooling arrangements in a turbine rotor blade include a feedhole that extends from the suction side slash face to the interior cooling passage, and, one or more branch holes that each extends from the feedhole to the suction side slash face such that coolant flows from the interior cooling passage, through the feedhole to the one or more branch holes and exits the platform along the suction side slash face.

US Patent:

20140161625, Jun 12, 2014

Filed:

Dec 11, 2012

Appl. No.:

13/711241

Inventors:

- Schenectady NY, US
Adebukola Oluwaseun Benson - Simpsonville SC, US
Richard Ryan Pilson - Greer SC, US
Stephen William Tesh - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/18

US Classification:

416 96 R

Abstract:

Systems and devices configured to cool turbine components in a turbine by passing a cooling flow through the turbine component via a cooling passage with a variable diameter are disclosed. In one embodiment, a turbine component includes: at least one elongated cooling passage extending from a root of the bucket to a tip of the bucket, wherein the elongated cooling passage has a variable diameter along a length of the bucket.

US Patent:

20140099193, Apr 10, 2014

Filed:

Oct 5, 2012

Appl. No.:

13/645585

Inventors:

- Schenectady NY, US
Adebukola Benson - Simpsonville SC, US
Zhirui Dong - Simpsonville SC, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F01D 5/18
F01D 9/02

US Classification:

415178, 416 96 R

Abstract:

A rotor blade includes an airfoil having a tip plate that extends across an outer radial end. A rim extends radially outward from the tip plate and surrounds at least a portion of the airfoil and includes a concave portion opposed to a convex portion. A plurality of dividers extend between the concave and convex portions to define a plurality of pockets between the concave and convex portions at the outer radial end. A plurality of cooling passages through the tip plate provide fluid communication through the tip plate to the plurality of pockets. A first fluid passage in at least one divider provides fluid communication between adjacent pockets across the at least one divider.