Duane A Busch

US Patent:

7588412, Sep 15, 2009

Filed:

Jul 28, 2005

Appl. No.:

11/161275

Inventors:

Glenn Herbert Nichols - Mason OH, US
Duane Allan Busch - Loveland OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 9/06

US Classification:

415 1, 415116, 4151731

Abstract:

A cooled shroud assembly for a gas turbine engine having a longitudinal centerline includes at least one arcuate shroud segment surrounding a row of rotating turbine blades. The shroud segment has a forward flange, an aft flange defining an axially-facing aft edge, and an inwardly-facing flowpath surface, and the shroud segment lacks cooling holes for cooling the aft flange or the aft edge. At least one stationary turbine nozzle is disposed axially next to the shroud segment and includes an airfoil-shaped airfoil and an arcuate outer band disposed at a radially outer end of the airfoil and positioned axially adjacent to the shroud. At least one cooling hole is formed in the outer band in fluid communication with a source of cooling air. The cooling hole is positioned so as to direct a flow of cooling air against the shroud segment.

US Patent:

7762761, Jul 27, 2010

Filed:

Nov 30, 2005

Appl. No.:

11/290010

Inventors:

Duane Busch - Loveland OH, US
Andrew Charles Powis - Madeira OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 9/00

US Classification:

415 1, 415191, 4152093

Abstract:

A method for assembling a turbine nozzle for a gas turbine engine. The method includes providing a turbine nozzle including a plurality of airfoil vanes extending between an inner band and an outer band, wherein the outer band includes a forward hook assembly having a rail and at least one hook, providing at least one scalloped recessed area within the forward hook assembly at least one hook to facilitate reducing stresses induced to the turbine nozzle, and coupling the turbine nozzle into the gas turbine engine using the forward hook assembly such that the turbine nozzle is at least partially supported by the forward hook assembly.

US Patent:

20050135921, Jun 23, 2005

Filed:

Dec 17, 2003

Appl. No.:

10/738514

Inventors:

Duane Busch - Loveland OH, US
Melissa Starkweather - Cincinnati OH, US
Andrew Powis - Madeira OH, US

International Classification:

F01D005/14

US Classification:

415115000

Abstract:

A turbine nozzle includes outer and inner bands integrally joined to a doublet of hollow vanes extending radially therebetween. Each of the vanes includes opposite pressure and suction sidewalls extending between opposite leading and trailing edges, and spaced apart to define an internal plenum extending radially between the bands for receiving an air coolant. The vanes are spaced apart from each other to define a flow passage for channeling hot combustion gases which are bound by corresponding pressure and suction sidewalls of the vanes facing inboard toward each other, with the remaining suction and pressure sidewalls of the vanes facing outboard. The vanes include different cooling configurations to bias more of the coolant to the inboard sidewalls than to the outboard sidewalls.

US Patent:

20200024951, Jan 23, 2020

Filed:

Jul 17, 2018

Appl. No.:

16/037662

Inventors:

- Schenectady NY, US
Jacob Romeo Rendon - Cedar Park TX, US
Duane Allan Busch - Loveland OH, US
Ryan Christopher Jones - Cincinnati OH, US
Paul Christopher Schilling - Waynesville OH, US
Zachary Daniel Webster - Mason OH, US
Tingfan Pang - West Chester OH, US
Gregory Terrence Garay - West Chester OH, US
Steven Robert Brassfield - Cincinnati OH, US

International Classification:

F01D 5/08

Abstract:

An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a passage. The cooling hole can include a laid back section where a coating can be applied. The method can include forming the cooling hole in the component and applying the coating to the component to maintain a specific geometry.