Robert L Manning

US Patent:

6398488, Jun 4, 2002

Filed:

Sep 13, 2000

Appl. No.:

09/660572

Inventors:

Robert Barry Solda - Peabody MA
Robert Francis Manning - Newburyport MA
David Gellman - Peabody MA

Assignee:

General Electric Company - Schenectady NY

International Classification:

F03B 1100

US Classification:

415115, 4151737

Abstract:

A turbine nozzle includes a seal pad mounted to a seal support from an inner band thereof. The seal pad is provided for cooperating with seal teeth in an interstage seal. A bypass aperture extends through the seal support to bypass cooling air around the seal pad for providing relatively cool air aft of the seal teeth for improving cooling of the interstage seal in this region.

US Patent:

6402471, Jun 11, 2002

Filed:

Nov 3, 2000

Appl. No.:

09/706387

Inventors:

Daniel Edward Demers - Ipswich MA
Robert Francis Manning - Newburyport MA
Paul Joseph Acquaviva - Newburyport MA

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 518

US Classification:

416 97R, 416 96 R, 416193 A, 415115

Abstract:

A turbine blade includes a platform having an internal cavity formed therein and an airfoil extending radially from the platform. An internal cooling circuit is formed in the airfoil for circulating a coolant therethrough, and at least one supply passage extends between the internal cooling circuit and the internal platform cavity for diverting coolant to the internal platform cavity. The coolant is expelled from holes located in the forward and aft edges of the platform for purging the forward and aft disk wheel spaces and impingement cooling adjacent nozzle bands.

US Patent:

6416284, Jul 9, 2002

Filed:

Nov 3, 2000

Appl. No.:

09/706403

Inventors:

Daniel Edward Demers - Ipswich MA
Robert Francis Manning - Newburyport MA
Paul Joseph Acquaviva - Newburyport MA

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 518

US Classification:

416 97R, 416 96 R, 416193 A, 415115

Abstract:

A turbine blade includes a platform and an airfoil extending radially from the platform. An internal cooling circuit is formed in the airfoil for circulating a coolant therethrough to cool the airfoil. At least one supply passage is provided to direct some of the coolant that has passed at least partially through the internal cooling circuit onto the platform for cooling the platform.

US Patent:

6422819, Jul 23, 2002

Filed:

Dec 9, 1999

Appl. No.:

09/457652

Inventors:

Gene C. F. Tsai - Lexington MA
Sung Tung - Lexington MA
Terence C. Flaherty - Marblehead MA
Robert F. Manning - Newburyport MA

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 508

US Classification:

416 97R, 416235

Abstract:

An airfoil for use in a gas turbine engine includes a pressure side and a suction side joined at a trailing edge wall that defines a trailing edge. The airfoil includes at least one cooling hole extending through the trailing edge wall so as to pass cooling fluid from the pressure side of the airfoil to the suction side.

US Patent:

6530744, Mar 11, 2003

Filed:

May 29, 2001

Appl. No.:

09/867294

Inventors:

Gary Charles Liotta - Beverly MA
Robert Francis Manning - Newburyport MA

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 514

US Classification:

415115, 415189

Abstract:

A gas turbine engine component including a nozzle outer band, a plurality of nozzle vanes extending inward from the outer band, and an inner band extending circumferentially around inner ends of the vanes. Further, the component has a shroud integral with the outer band adapted for surrounding a plurality of blades mounted in the engine for rotation about a centerline thereof.

US Patent:

6585482, Jul 1, 2003

Filed:

Jun 20, 2000

Appl. No.:

09/597183

Inventors:

Gary Charles Liotta - Beverly MA
Robert Francis Manning - Newburyport MA
Robert John Parks - Ipswich MA

Assignee:

General Electric Co. - Schenectady NY

International Classification:

F01D 100

US Classification:

415116, 415144, 415 1

Abstract:

A gas turbine engine includes a compressor rotor assembly which directs air at a sufficient pressure and temperature to a downstream turbine for cooling. The compressor assembly includes a compressor including an impeller and a cooling circuit. The impeller includes an exit, an inlet, and a body extending therebetween. The impeller body includes a first opening positioned a distance from the impeller exit. The cooling circuit extends between the compressor and the turbine and is in flow communication with the impeller opening.

US Patent:

6746209, Jun 8, 2004

Filed:

May 31, 2002

Appl. No.:

10/160548

Inventors:

Thomas Edward DeMarche - Boxford MA
Robert Francis Manning - Newburyport MA

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 906

US Classification:

416 97R

Abstract:

A method for fabricating a nozzle for a gas turbine engine facilitates extending a useful life of the nozzles. The nozzle includes an airfoil. The method includes forming the airfoil to include a suction side and a pressure side connected at a leading edge and a trailing edge such that a cooling cavity and a cooling circuit are defined within the airfoil, wherein the suction side and the pressure side extend radially between a tip and a root. The method also includes forming a plurality of cooling slots within the airfoil that extend from the cooling circuit towards the airfoil trailing edge, and forming a control vane within the cooling circuit to facilitate maintaining a substantially constant cooling effectiveness within the cooling circuit.

US Patent:

6779597, Aug 24, 2004

Filed:

Jan 16, 2002

Appl. No.:

10/053534

Inventors:

Thomas Edward DeMarche - Boxford MA
Robert Francis Manning - Newburyport MA

Assignee:

General Electric Company - Schenectady NY

International Classification:

F28F 312

US Classification:

165169, 165908, 415115

Abstract:

A multiple impingement cooled structure is provided having two or more stages of impingement cooling wherein the stages are arranged so as to have substantially constant cooling effectiveness.