Craig Alan Gonyou

US Patent:

6340285, Jan 22, 2002

Filed:

Jun 8, 2000

Appl. No.:

09/590590

Inventors:

Craig Alan Gonyou - Blanchester OH
Roger Lee Doughty - Cincinnati OH
Monty Lee Shelton - Loveland OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F04D 3100

US Classification:

415116, 415138, 415139, 415176

Abstract:

A segmented turbine cooling component, such as shroud segment for the high pressure and low pressure turbine sections of a gas turbine engine, useful in providing preferential cooling to the side rails or panels of the turbine component through the combination of cooling air fed into the intermediate pressure cavity between the discourager and primary seals and then through recesses in the bottom wall of the lower discourager seal slot that impinges air on the portion of the side panel below the discourager seal. The side panels of the turbine component have an upper primary seal slot and a lower discourager seal slot with a bottom wall having a plurality of alternating lands and recesses along the length thereof and a plurality of cooling air passages having outlets exiting into the lower slot above the lands. The subassembly can be formed from a plurality of such turbine components where the spacing of the lands and recesses of the lower discourager slots of the adjacent side panels are staggered such that the lands of the lower slot of one adjacent panel are opposite the recesses of the lower slot of the other adjacent side panel. This subassembly also has primary and discourager seals received by the respective upper and lower slots that are positioned in the gap between the adjacent panels which define the intermediate pressure cavity therebetween and trench below the discourager seal that is purged by spent cooling air from the recesses in the lower slot.

US Patent:

20220268443, Aug 25, 2022

Filed:

May 12, 2022

Appl. No.:

17/663079

Inventors:

- Schenectady NY, US
Craig Alan Gonyou - Blanchester OH, US
Paul Christopher Schilling - Waynesville OH, US
Hojjat Nasr - West Chester OH, US
Ryan Christopher Jones - West Chester OH, US
Donald Lee Gardner - West Chester OH, US

International Classification:

F23R 3/00
F23R 3/10

Abstract:

A combustor assembly for a heat engine is generally provided. The combustor assembly includes a liner wall defining a combustion chamber, and a deflector assembly. The deflector assembly includes a radially extended first wall disposed adjacent to the combustion chamber, and further an axially extended second wall disposed forward of the first wall and adjacent thereto. The second wall is coupled to the liner wall.

US Patent:

20230066740, Mar 2, 2023

Filed:

Aug 30, 2021

Appl. No.:

17/461113

Inventors:

- Schenectady NY, US
Yu-Liang Lin - Mason OH, US
Craig Alan Gonyou - Blanchester OH, US
Scott Alan Schimmels - Miamisburg OH, US
Jeffrey Douglas Rambo - Mason OH, US
Brian Gregg Feie - Cincinnati OH, US

International Classification:

F01D 9/06
F01D 5/08

Abstract:

A passive flow modulation device for a machine defining an axial direction and a radial direction, the passive flow modulation device including: a first ring with a first coefficient of thermal expansion; a second ring disposed coaxially with the first ring and positioned at least partially inward of the first ring along the radial direction, spaced from the first ring along the axial direction, or both, the first ring, the second ring, or both defining at least in part one or more passages, the second ring with a second coefficient of thermal expansion that is less than the first coefficient of thermal expansion to passively modulate a size of the one or more passages during operation.

US Patent:

20230036206, Feb 2, 2023

Filed:

Jul 30, 2021

Appl. No.:

17/389503

Inventors:

- Schenectady NY, US
Jonathan Russell Ratzlaff - Loveland OH, US
Craig Alan Gonyou - Blanchester OH, US

International Classification:

F01D 5/08
F01D 25/12

Abstract:

A gas turbine engine includes a combustion section, a turbine section, and a compressor section. The combustion section includes a combustor casing, a combustor, a cooling duct, and an outer duct. The combustor casing defines at least in part a diffuser cavity and a fluid inlet. The combustor disposed is in the diffuser cavity. The cooling duct is in fluid communication with the fluid inlet in the combustor casing and is configured to transport a flow of cooled air. The outer duct surrounds at least a portion of the cooling duct and extends along a portion of an entire length of the cooling duct. The outer duct defines a gap with the cooling duct and is configured to transport a flow of buffer air. The turbine section is disposed downstream from the combustion section. The cooling duct is in fluid communication with the turbine section.

US Patent:

20210317745, Oct 14, 2021

Filed:

Oct 12, 2020

Appl. No.:

17/068235

Inventors:

- Schenectady NY, US
Ryan Christopher Jones - Cincinnati OH, US
Paul Christopher Schilling - Waynesville OH, US
Craig Alan Gonyou - Blanchester OH, US

International Classification:

F01D 5/18

Abstract:

An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.

US Patent:

20200224539, Jul 16, 2020

Filed:

Jan 16, 2019

Appl. No.:

16/249285

Inventors:

- Schenectady NY, US
Ryan Christopher Jones - Cincinnati OH, US
Paul Christopher Schilling - Waynesville OH, US
Craig Alan Gonyou - Blanchester OH, US

International Classification:

F01D 5/18

Abstract:

An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.

US Patent:

20200182059, Jun 11, 2020

Filed:

Dec 5, 2018

Appl. No.:

16/210314

Inventors:

- Schenectady NY, US
Kirk Douglas Gallier - Liberty Township OH, US
Brandon Wayne Miller - Liberty Township OH, US
Craig Alan Gonyou - Blanchester OH, US
Kevin Robert Feldmann - Mason OH, US
Justin Paul Smith - Montgomery OH, US

International Classification:

F01D 5/08
F01D 5/18

Abstract:

An aspect of the present disclosure is directed to a rotor assembly for a turbine engine. The rotor assembly includes an airfoil assembly and a hub to which the airfoil assembly is attached. A wall assembly defines a first cavity and a second cavity between the airfoil assembly and the hub. The first cavity and the second cavity are at least partially fluidly separated by the wall assembly. The first cavity is in fluid communication with a flow of first cooling fluid and the second cavity is in fluid communication with a flow of second cooling fluid different from the first cooling fluid.

US Patent:

20200063583, Feb 27, 2020

Filed:

Aug 21, 2018

Appl. No.:

16/107227

Inventors:

- Schenectady NY, US
Donald Lee Gardner - West Chester OH, US
Craig Alan Gonyou - Blanchester OH, US
Paul Christopher Schilling - Waynesville OH, US
Hojjat Nasr - West Chester OH, US
Ryan Christopher Jones - Cincinnati OH, US

International Classification:

F01D 11/00
F23R 3/00
F02K 1/82

Abstract:

A combustor assembly for a heat engine is generally provided. The combustor assembly includes a liner wall defining a combustion chamber, and a deflector assembly. The deflector assembly includes a radially extended first wall disposed adjacent to the combustion chamber, and further an axially extended second wall disposed forward of the first wall and adjacent thereto. The second wall is coupled to the liner wall.