Curtis Lee Stover

US Patent:

56851588, Nov 11, 1997

Filed:

Mar 31, 1995

Appl. No.:

8/414699

Inventors:

Dean Thomas Lenahan - Cincinnati OH
Poul D. Pedersen - Cincinnati OH
Larry Wayne Plemmons - Fairfield OH
Christopher Charles Glynn - Hamilton OH
Frederick M. Miller - Cincinnati OH
Curtis W. Stover - Mason OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 100

US Classification:

60726

Abstract:

In a gas turbine including a compressor having a bore and a rotor comprised of multiple stages extending between a first stage at a forward end of the compressor and a last stage at an aft end of the compressor, each stage including a rotor disk having a peripheral rim and multiple blades secured to the peripheral rim, a combustion system comprising a plurality of combustors utilizing discharge air from the compressor for combustion, and multiple turbine stages driven by combustion gases from the combustion system, the improvement comprising means for supplying cooling air at least to a peripheral rim of the last stage of the compressor.

US Patent:

20180038243, Feb 8, 2018

Filed:

Aug 5, 2016

Appl. No.:

15/229466

Inventors:

- SCHENECTADY NY, US
Andrew Martin - Blue Ash OH, US
Curtis Walton Stover - Mason OH, US
Jared Matthew Wolfe - West Chester OH, US
Mohammed El Hacin Sennoun - West Chester OH, US

International Classification:

F01D 25/14
F01D 17/10
F01D 17/14
F04D 29/54
F04D 19/00
F02K 3/06
F01D 25/12
F01D 17/16

Abstract:

A heat exchanger assembly for a gas turbine engine that includes an outer engine case. The heat exchanger assembly includes at least one cooling channel, the at least one cooling channel is configured to receive a flow of fluid to be cooled. At least one first coolant flow duct that is configured to receive a flow of a first coolant, wherein the at least one cooling channel is disposed between a first inlet and a first outlet. The heat exchanger assembly further include at least one second coolant flow duct that is configured to receive a flow of a second coolant, wherein the at least one cooling channel is disposed between a second inlet and a second outlet.

US Patent:

20170335716, Nov 23, 2017

Filed:

Oct 28, 2015

Appl. No.:

15/522854

Inventors:

- Schenectady NY, US
Jason Randolph ALLEN - Loveland OH, US
Robert David BRIGGS - West Chester OH, US
Kevin Robert FELDMANN - Mason OH, US
Curtis Walton STOVER - Mason OH, US
Zachary Daniel WEBSTER - Mason OH, US
Fernando REITER - Reading OH, US

International Classification:

F01D 25/12
F01D 11/08
F23R 3/04
F02C 7/18
F01D 5/18
F23R 3/00
F01D 9/04
F02C 3/04

Abstract:

An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface with at least one cavity. A second engine component is spaced from the cooling surface, and includes at least one cooling aperture. The cooling aperture is arranged such that cooling fluid impinges on the cooling surface at an angle.

US Patent:

20170191417, Jul 6, 2017

Filed:

Jan 6, 2016

Appl. No.:

14/989290

Inventors:

- Schenectady NY, US
Robert Frederick Bergholz - Loveland OH, US
Jason Randolph Allen - Loveland OH, US
Robert David Briggs - West Chester OH, US
Kevin Robert Feldmann - Mason OH, US
Curtis Walton Stover - Mason OH, US
Zachary Daniel Webster - Mason OH, US
Fernando Reiter - Reading OH, US
Michael Alan Meade - Liberty Township OH, US

International Classification:

F02C 7/12
F23R 3/00
F01D 5/14
F01D 25/24
F01D 25/08
F01D 9/04

Abstract:

An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, and a second engine component having a first surface in fluid communication with a cooling fluid flow and a second surface spaced from the cooling surface to define a space. A cooling aperture extends through the second engine component. A cooling feature extends from the cooling surface of the first engine component, and is oriented relative to the cooling aperture such that the cooling fluid flow is orthogonal and non-orthogonal to different portions of the cooling feature.

US Patent:

20170101896, Apr 13, 2017

Filed:

May 28, 2015

Appl. No.:

15/314341

Inventors:

- Schenectady NY, US
Timothy Deryck STONE - West Chester OH, US
Jared Peter BUHLER - Tewksbury MA, US
Victor Hugo Silva CORREIA - Milton Mills NH, US
Gregory Michael LASKOWSKI - Lynn MA, US
Robert Carl MURRAY - Niskayuna NY, US
Jonathan Russell RATZLAFF - West Chester OH, US
Robert PROCTOR - Cincinnati OH, US
John Howard STARKWEATHER - Cincinnati OH, US
Curtis Walton STOVER - West Chester OH, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F01D 25/32
F02C 7/18
B04C 3/06
F01D 5/08
F02C 9/18
B01D 45/16
F02C 3/04
F01D 25/12

Abstract:

A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser configured to increase the angular velocity of a fluid stream, a flow splitter configured to split the fluid stream to form a concentrated-particle stream and a reduced-particle stream, and an exit conduit configured to receive the reduced-particle stream. An inducer assembly for a turbine engine includes an inducer with a flow passage having an inducer inlet and an inducer outlet in fluid communication with a turbine section of the engine, and a particle separator, which includes a particle concentrator that receives a compressed stream from a compressor section of the engine and a flow splitter. A turbine engine includes a cooling air flow circuit which supplies a fluid stream to a turbine section of the engine for cooling, a particle separator located within the cooling air flow circuit, and an inducer forming a portion of the cooling air flow circuit in fluid communication with the particle separator. A method of cooling a rotating blade of a turbine engine having an inducer includes directing a cooling fluid stream from a portion of turbine engine toward the rotating blade, separating particles from the cooling fluid stream by passing the cooling fluid stream through a inertial separator, accelerating a reduced-particle stream emitted from the inertial separator to the speed of the rotating blade, and orienting the reduced-particle stream by emitting the reduced-particle stream from the inertial separator into a cooling passage in the inducer.

US Patent:

20160186605, Jun 30, 2016

Filed:

Oct 9, 2015

Appl. No.:

14/879277

Inventors:

- Schenectady NY, US
Gulcharan Singh BRAINCH - West Chester OH, US
Curtis Walton STOVER - West Chester OH, US

International Classification:

F01D 25/12
F01D 9/02

Abstract:

A shroud assembly for a turbine section of a turbine engine includes a shroud plate in thermal communication with a hot combustion gas flow and a baffle overlying the shroud plate to define a region. One or more shaped cooling features are located along the region such that a cooling fluid flow passing through the region encounters the shaped cooling features to increase the turbulence of the cooling fluid flow.

US Patent:

20160040552, Feb 11, 2016

Filed:

Mar 14, 2014

Appl. No.:

14/777331

Inventors:

- Schenectady NY, US
Daniel John FUSINATO - Cincinnati OH, US
Scott David HUNTER - Seattle OH, US
Joel Francis KIRK - Middleton OH, US
Michael Robert MELZAK - Cincinnati OH, US
Curtis Walton STOVER - Mason OH, US

International Classification:

F01D 25/12
F01D 5/02
F01D 25/14

Abstract:

A flow transfer apparatus for transferring cooling flow from a primary gas flowpath to a turbine rotor. The apparatus includes a first supply plenum communicating with the primary gas flowpath and first inducers, the first inducers configured to accelerate a first fluid flow from the first supply plenum and discharge it toward the rotor with a tangential velocity; a second supply plenum communicating with the primary gas flowpath and second inducers , the second inducers configured to accelerate a second fluid flow from the second supply plenum towards the rotor with a tangential velocity; and a cooling modulation valve operable to selectively permit or block the second fluid flow from the primary gas flowpath to the second supply plenum. The valve includes a flow control structure disposed in the primary gas flowpath and an actuation structure extending to a location radially outside of a casing defining the primary gas flowpath.

US Patent:

20150345305, Dec 3, 2015

Filed:

May 14, 2015

Appl. No.:

14/712287

Inventors:

- Schenectady NY, US
Robert David Briggs - West Chester OH, US
Gulcharan Singh Brainch - West Chester OH, US
Curtis Walton Stover - West Chester OH, US

International Classification:

F01D 5/18
F28F 1/40

Abstract:

A structure for disrupting the flow of a fluid, the structure comprising: (a) a first lateral wall and a second lateral wall spaced apart from one another, yet joined, by a floor and a ceiling; and, (b) a vorticor pin extending incompletely between the first lateral wall and the second lateral wall in a direction parallel to an X-axis, the vorticor pin concurrently rising above and extending away from the floor to a height, in a direction parallel to a Y-axis, to provide a gap between the vorticor pin and the ceiling, the vorticor pin comprising: (i) a front surface extending incompletely between the first lateral wall and the second lateral wall, the front surface extending above the floor and having an arcuate portion that is transverse with respect to a Z-axis, which is perpendicular to the X-axis and the Y-axis, and (ii) a rear surface extending between the first lateral wall and the second lateral wall, the rear surface extending between the front surface and the floor, the rear surface having an inclining section that tapers in height, taken parallel to the Y-axis, in a direction parallel to the Z-axis.