Paul David Vitt from Chandler, AZ, age 60

Paul C. Vitt

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Specialties:

Family Medicine

Work:

Siletz Community Health Clinic
200 Gwee Shut Rd, Siletz, OR 97380
(541)4441030 (phone), (541)4449695 (fax)

Languages:

English

Description:

Dr. Vitt works in Siletz, OR and specializes in Family Medicine. Dr. Vitt is affiliated with Samaritan Pacific Communities Hospital.

Paul C Vitt

License #:

MT001409T - Expired

Category:

Medicine

Type:

Graduate Medical Trainee

Us Patents

Method And System To Facilitate Enhanced Local Cooling Of Turbine Engines
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US Patent:

7611324, Nov 3, 2009
Filed:

Nov 30, 2006
Appl. No.:

11/565273
Inventors:

Eric Alan Estill - Morrow OH, US
James Harvey Laflen - Loveland OH, US
Paul Hadley Vitt - Hamilton OH, US
Michael Elliot Wymore - Madison AL, US
Assignee:

General Electric Company - Schenectady NY
International Classification:

F01D 25/12
US Classification:

415 1, 4151731, 415191, 4151995, 415116
Abstract:

A method of assembling a gas turbine engine is provided. The method includes coupling at least one turbine nozzle segment within the gas turbine engine. The at least one turbine nozzle segment includes at least one airfoil vane extending between an inner band and an outer band that includes an aft flange and a radial inner surface. The method also includes coupling at least one turbine shroud segment downstream from the at least one turbine nozzle segment, wherein the at least one turbine shroud segment includes a leading edge and a radial inner surface, coupling a cooling fluid source in flow communication with the at least one turbine nozzle segment such that cooling fluid channeled to each turbine nozzle outer band aft flange is directed at an oblique discharge angle towards the leading edge of the at least one turbine shroud segment, and channeling the cooling fluid through at least a first group of cooling openings having a larger aggregate cross-sectional area and a second group of cooling openings having a smaller aggregate cross-sectional area to facilitate preferential cooling of the turbine shroud.

Conformal Tip Baffle Airfoil
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US Patent:

7686578, Mar 30, 2010
Filed:

Aug 21, 2006
Appl. No.:

11/507121
Inventors:

Kevin Samuel Klasing - Springboro OH, US
Paul Hadley Vitt - Hamilton OH, US
Brian David Keith - Cincinnati OH, US
Assignee:

General Electric Company - Schenectady NY
International Classification:

F01D 5/20
US Classification:

4151731, 416228
Abstract:

A turbine blade includes an airfoil tip with first and second tip ribs extending from a tip floor. The ribs extend along the opposite pressure and suction sides of the blade and are joined together at opposite leading and trailing edges. A tip baffle is nested transversely between the ribs, and conforms with the second rib to bifurcate the airfoil tip into first and second tip pockets extending along the corresponding pressure and suction sides.

Method And System To Facilitate Preferentially Distributed Recuperated Film Cooling Of Turbine Shroud Assembly
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US Patent:

7722315, May 25, 2010
Filed:

Nov 30, 2006
Appl. No.:

11/565253
Inventors:

Eric Alan Estill - Morrow OH, US
James Harvey Laflen - Loveland OH, US
Paul Hadley Vitt - Hamilton OH, US
Michael Elliot Wymore - Madison AL, US
Assignee:

General Electric Company - Schenectady NY
International Classification:

F01D 25/14
US Classification:

415115, 4151731
Abstract:

A method of assembling a gas turbine engine includes coupling a turbine shroud assembly within the gas turbine engine. The turbine shroud assembly includes a shroud segment having a leading edge defining a forward face and a radial inner surface. A turbine nozzle is coupled to the turbine shroud assembly such that a gap is defined between an aft face of an outer band of the turbine nozzle and the forward face. A plurality of recuperated cooling openings are defined through the leading edge at an oblique inlet angle with respect to a centerline of the gap and between the forward face and the radial inner surface to direct cooling fluid through the leading edge to facilitate preferential cooling of the leading edge.

Method And System To Facilitate Cooling Turbine Engines
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US Patent:

7785067, Aug 31, 2010
Filed:

Nov 30, 2006
Appl. No.:

11/565229
Inventors:

Eric Alan Estill - Morrow OH, US
James Harvey Laflen - Loveland OH, US
Paul Hadley Vitt - Hamilton OH, US
Michael Elliot Wymore - Madison AL, US
Assignee:

General Electric Company - Schenectady NY
International Classification:

F01D 25/12
US Classification:

4151731, 415191, 4151995, 415116
Abstract:

A method of assembling a gas turbine engine is provided. The method includes coupling at least one turbine nozzle segment within the gas turbine engine. The at least one turbine nozzle segment includes at least one airfoil vane extending between an inner band and an outer band that includes an aft flange and a radial inner surface. The method also includes coupling at least one turbine shroud segment downstream from the at least one turbine nozzle segment, wherein the at least one turbine shroud segment includes a leading edge and a radial inner surface, and coupling a cooling fluid source in flow communication with the at least one turbine nozzle segment such that cooling fluid channeled to each turbine nozzle outer band aft flange is directed at an oblique discharge angle towards the leading edge of the at least one turbine shroud segment.

Triforial Tip Cavity Airfoil
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US Patent:

8425183, Apr 23, 2013
Filed:

Nov 20, 2006
Appl. No.:

11/602421
Inventors:

Kevin Samuel Klasing - Springboro OH, US
Paul Hadley Vitt - Hamilton OH, US
Brian David Keith - Cincinnati OH, US
Assignee:

General Electric Company - Schenectady NY
International Classification:

F01D 5/20
US Classification:

4151731, 416 97 R
Abstract:

A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. The tip ribs are spaced apart between the leading and trailing edges of the airfoil to include a trifurcate tip baffle defining a triforial tip cavity.

Cascade Tip Baffle Airfoil
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US Patent:

8500396, Aug 6, 2013
Filed:

Aug 21, 2006
Appl. No.:

11/507120
Inventors:

Kevin Samuel Klasing - Springboro OH, US
Paul Hadley Vitt - Hamilton OH, US
Brian David Keith - Cincinnati OH, US
Assignee:

General Electric Company - Schenectady NY
International Classification:

F01D 5/20
US Classification:

4151731, 416228
Abstract:

A turbine blade includes an airfoil tip with first and second ribs extending along the opposite pressure and suction sides. The ribs extend outwardly from a tip floor and are joined together at opposite leading and trailing edges. A cascade tip baffle transversely bridges the two ribs above the tip floor forward of the maximum width of the tip to partition the tip chordally into corresponding tip pockets on opposite sides of the baffle.

Tip Ramp Turbine Blade
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US Patent:

8512003, Aug 20, 2013
Filed:

Aug 21, 2006
Appl. No.:

11/507116
Inventors:

Kevin Samuel Klasing - Springboro OH, US
Paul Hadley Vitt - Hamilton OH, US
Brian David Keith - Cincinnati OH, US
Assignee:

General Electric Company - Schenectady NY
International Classification:

F01D 5/14
US Classification:

416228
Abstract:

A turbine blade includes first and second tip ribs extending from a tip floor to define a tip cavity. An exit ramp bridges the ribs and rises in elevation aft from the floor.

Flared Tip Turbine Blade
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US Patent:

8632311, Jan 21, 2014
Filed:

Aug 21, 2006
Appl. No.:

11/507119
Inventors:

Kevin Samuel Klasing - Springboro OH, US
Paul Hadley Vitt - Hamilton OH, US
Brian David Keith - Cincinnati OH, US
Assignee:

General Electric Company - Schenectady NY
International Classification:

F01D 5/14
US Classification:

416228, 4151734, 4151744
Abstract:

A turbine blade includes an airfoil terminating in a tip. The tip includes a first rib conforming with a concave pressure side of the airfoil, and a second rib conforming with a convex suction side of the airfoil. The second rib is flared outwardly from the suction side.