DAVID M LEO
Engineering in Leominster, MA
License number
Massachusetts 36184
Issued Date
Aug 9, 1991
Expiration Date
Jun 30, 2008
Type
Mechanical Engineer
Address
Address
Leominster, MA 01453
Professional information
Cooling Circuit Within A Turbine Nozzle And Method Of Cooling A Turbine Nozzle
US Patent:
2005003, Feb 10, 2005
Filed:
Aug 4, 2003
Appl. No.:
10/632851
Inventors:
Michael Pothier - Leominster MA, US
John Seymour - Harvard MA, US
David Leo - Leominster MA, US
John Seymour - Harvard MA, US
David Leo - Leominster MA, US
International Classification:
F01D025/08
US Classification:
415114000
Abstract:
A cooling circuit is provided within a turbine nozzle to help increase turbine efficiency. The turbine nozzle includes first, second and third cavities, an outer band, and an inner band. The cooling circuit contains an inlet receiving cooling medium flow, and a first duct insert disposed in the second cavity. The first duct insert receives the cooling medium flow via the inlet and duct flows the cooling medium flow to a bottom of the second cavity. An impingement insert is disposed in the first cavity that receives the cooling medium flow from the first duct insert. A first impingement plate is disposed within the outer band defining an outer band cooling path within the outer band. The outer band cooling path receives the cooling medium flow from the first cavity. A second cavity cooling path is defined between the first duct insert and a second cavity wall, where the second cavity cooling path receives the cooling medium flow from the outer band cooling path. A second impingement plate is disposed within the inner band and defines an inner band cooling path within the inner band. The inner band cooling path receives the cooling medium flow from second cavity cooling path. Finally, a second duct insert is disposed in the third cavity and defines a third cavity cooling path between the second duct insert and a third cavity wall. The third cavity cooling path receives the cooling medium flow from the inner band cooling path.
Airfoil For Nozzle And A Method Of Forming The Machined Contoured Passage Therein
US Patent:
8246306, Aug 21, 2012
Filed:
Apr 3, 2008
Appl. No.:
12/062123
Inventors:
Margaret Jones Schotsch - Greer SC, US
Randall Gill - Greenville SC, US
Peter Stevens - Simpsonville SC, US
David Leo - Leominster MA, US
John Seymour - Harvard MA, US
Randall Gill - Greenville SC, US
Peter Stevens - Simpsonville SC, US
David Leo - Leominster MA, US
John Seymour - Harvard MA, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 5/08
US Classification:
416 96R, 415115
Abstract:
A nozzle in which an airfoil includes a pressure surface and a suction surface that join at substantially opposing chordal ends of the airfoil to form a leading edge of the airfoil and a trailing edge of the airfoil. A trailing edge passage is defined through the airfoil through which coolant flows. The trailing edge passage is proximate to the trailing edge of the airfoil and has a contoured shape that conforms to that of the trailing edge.