Brian K Norton

US Patent:

6554572, Apr 29, 2003

Filed:

May 17, 2001

Appl. No.:

09/859610

Inventors:

Gerard Anthony Rinck - Cincinnati OH
Mark Edward Stegemiller - Franklin OH
Hardev Singh - Mason OH
Brian Alan Norton - Cincinnati OH

Assignee:

General Electric Company - Schnectady NY

International Classification:

F01D 518

US Classification:

416 97R, 415115, 298891, 29889721

Abstract:

A turbine blade for a gas turbine engine. An existing blade was found to exhibit bowing, or a concave configuration facing the pressure side, along its trailing edge. The invention reduces bowing by ( ) changing tilt, ( ) changing lean, ( ) reducing the number of cooling holes, while ( ) changing the diameters of the cooling holes, to maintaining the total cooling flow unchanged.

US Patent:

6561758, May 13, 2003

Filed:

Apr 27, 2001

Appl. No.:

09/844206

Inventors:

Gerard Anthony Rinck - Cincinnati OH
Jonathan Philip Clarke - West Chester OH
Brian Alan Norton - Cincinnati OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 518

US Classification:

415115, 416 97 R

Abstract:

A gas turbine engine includes rotor blades including airfoils that facilitates reducing manufacturing losses due to airfoil trailing edge scarfing. Each airfoil includes a first and second sidewall connected at a leading edge and a trailing edge. The sidewalls define a cooling cavity that includes at least a leading edge chamber bounded by the sidewalls and the airfoil leading edge, and a trailing edge chamber bounded by sidewalls and the airfoil trailing edge. The cooling cavity trailing edge chamber includes a tip region, a throat, and a passageway region connected in flow communication such that the throat is between the tip region and the passageway region. Furthermore, the tip region is bounded by the airfoil tip and extends divergently from the throat, such that a width of the tip region is greater than a width of the throat.

US Patent:

6786696, Sep 7, 2004

Filed:

May 6, 2002

Appl. No.:

10/139534

Inventors:

William Charles Herman - Blue Ash OH
Brian Alan Norton - Cincinnati OH
Brian David Keith - Cincinnati OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 530

US Classification:

416 96R, 416193, 416248

Abstract:

A turbine blade includes an airfoil and dovetail. The dovetail includes a pair of supporting tangs. A rectangular root block bridges the tangs over a majority of the root end thereof. The block terminates short of one endface of the dovetail to form a root notch thereat for preferentially reducing weight.

US Patent:

6793457, Sep 21, 2004

Filed:

Nov 15, 2002

Appl. No.:

10/295185

Inventors:

James Walter Caddell - Milford OH
Matthew Nicklus Miller - Maineville OH
Brian Alan Norton - Cincinnati OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 904

US Classification:

4152094

Abstract:

A method for repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands includes separating the inner band from the nozzle segment, and joining the inner band to a newly manufactured replacement casting having an outer band and at least one vane. The replacement casting includes a mounting platform formed on one end of the vane and a boss formed on the mounting platform. A collar is joined to the inner band and has a slot formed therein. The boss is then inserted into the slot, and the mounting platform is received in a recess formed in the inner band. Joining is completed by joining the boss to the collar and the mounting platform to the inner band. The thickness of the collar is tapered in an axial direction, and a relief is formed in the collar to provide assembly clearance with adjacent components.

US Patent:

6905308, Jun 14, 2005

Filed:

Nov 20, 2002

Appl. No.:

10/300098

Inventors:

Michael Philip Hagle - Mason OH, US
Brian Alan Norton - Cincinnati OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F03B003/16

US Classification:

4152094, 4152101, 416193 A, 416195

Abstract:

A method is provided for repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes separating the inner band from the nozzle segment, and joining the inner band to a newly manufactured replacement casting having an outer band and a vane. The replacement casting includes an airfoil stub. The airfoil stub is received in a recess formed in the inner band. Joining is completed by joining the airfoil stub to the inner band. The replacement casting may be modified from a newly manufactured singlet casting.

US Patent:

7008186, Mar 7, 2006

Filed:

Sep 17, 2003

Appl. No.:

10/664649

Inventors:

Robert John Heeg - Cincinnati OH, US
Brian Alan Norton - Blue Ash OH, US
Scott Joseph Schmid - Cincinnati OH, US
Ganesh Nagab Kumar - Liberty Township OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/18

US Classification:

416 97R, 415115

Abstract:

A turbine blade includes an airfoil having an internal cooling circuit with a first flow passage disposed directly behind the leading edge followed by a second flow passage separated therefrom by a corresponding bridge. The bridge includes a row of impingement apertures for cooling the leading edge. The suction sidewall of the airfoil includes a row of diffusion film cooling first holes extending in flow communication with the first passage. The first holes have a compound inclination angle, with a quadrilateral cross section forming a generally teardrop shaped outlet in the convex contour of the suction sidewall.

US Patent:

7097429, Aug 29, 2006

Filed:

Jul 13, 2004

Appl. No.:

10/889837

Inventors:

Robert Edward Athans - Cincinnati OH, US
William Charles Herman - Blue Ash OH, US
Brian Alan Norton - Cincinnati OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/14

US Classification:

416193A, 416239

Abstract:

A turbine blade includes an airfoil, platform, shank, and dovetail. The shank includes opposite forward and aft faces corresponding with leading and trailing edges of the airfoil, and opposite first and second sides corresponding with pressure and suction sides of the airfoil. The shank further includes lugs extending outwardly from the two sides, with a first lug having an inverted skirt extending outwardly toward the platform to join the shank aft face. The skirt cooperates with a seal body when mounted in the engine for reducing inter-blade leakage.

US Patent:

7121802, Oct 17, 2006

Filed:

Jul 13, 2004

Appl. No.:

10/889838

Inventors:

Robert Edward Athans - Cincinnati OH, US
Brian Alan Norton - Cincinnati OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/16

US Classification:

416193A, 416239, 416500

Abstract:

A turbine blade includes an airfoil, platform, shank, and dovetail. The platform includes a first side disposed along the pressure side of the airfoil, and an opposite second side disposed along the airfoil suction side. The platform second side includes an integral damper keeper disposed below the midchord of the airfoil, and is locally thinner at the forward and aft ends of the platform second side for reducing blade weight.