Brett Jordan Barker

US Patent:

20210215051, Jul 15, 2021

Filed:

Jan 13, 2020

Appl. No.:

16/741609

Inventors:

- Indianapolis IN, US
Brett Barker - Indianapolis IN, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN

International Classification:

F01D 5/18

Abstract:

A system includes an air foil positionable in a combustion flow path of a combustion turbine. A shank may be integrally formed with the air foil, and the platform may be integrally formed with the shank. The platform includes linear fluid passageways, access ducts penetrating a wedge face surface of the platform, and outlet apertures formed in a radially outward surface of the platform. The outlet apertures are in fluid communication with respective linear fluid passageways such that fluid flowing through the respective linear fluid passageways is discharged from the outlet apertures into the combustion flow path. The platform also includes plugs is disposed in respective access ducts to form a fluid tight seal and be positioned in at least one of the respective linear fluid passageways. Fluid flowing through the respective linear fluid passageways flows away from a respective plug for discharge from a respective outlet aperture.

US Patent:

20200011199, Jan 9, 2020

Filed:

Jul 6, 2018

Appl. No.:

16/028623

Inventors:

- Indianapolis IN, US
Brett Barker - Indianapolis IN, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN

International Classification:

F01D 25/12

Abstract:

A system for a hot section dual wall component in a gas turbine engine is used to avoid blockage by minimizing particulate deposits. The system includes impingement apertures formed in first wall of a cooling passageway of the dual wall component, and posts included on a second wall of the cooling passageway. The impingement apertures and the posts are respectively aligned opposite each other in the cooling passageway in operative cooperation so that working fluid exhausting into the cooling passageway from the impingement apertures in a first direction is directed to flow in a second direction along the cooling passageway to provide a laminar flow of the working fluid through the cooling passageway in order to minimize deposition of particles.

US Patent:

20180266253, Sep 20, 2018

Filed:

Feb 14, 2017

Appl. No.:

15/432599

Inventors:

- Indianapolis IN, US
Brett Barker - Indianapolis IN, US
Jeff Rhodes - Zionsville IN, US

International Classification:

F01D 5/18
F01D 9/04
F01D 25/12

Abstract:

An actively cooled component can be an airfoil, such as an air foil in a jet turbine engine. The component may have a body comprising at least one internal channel adapted for a flow of a cooling media therein. The channel may have two side walls separating a cold inner surface and a hot inner surface. The cold inner surface may have two impingement holes in fluid communication with a cooling media source, allowing for ingress of the cooling media into the internal channel. The hot inner surface may have one angled film hole in fluid communication with a hot outer surface, allowing for egress of the cooling media out of the internal channel. The first and second side walls may enclose a length of the internal channel along which the angled film hole is located between the two impingement holes.

US Patent:

20180202295, Jul 19, 2018

Filed:

Oct 11, 2017

Appl. No.:

15/729861

Inventors:

- Indianapolis IN, US
Tyler C. Gillen - Indianapolis IN, US
Christopher Nash - Indianapolis IN, US
Brian Shoemaker - Indianapolis IN, US
Brett J. Barker - Indianapolis IN, US

International Classification:

F01D 5/18

Abstract:

An airfoil with dual wall cooling for a gas turbine engine comprises a spar having pressure and suction side walls that meet at leading and trailing edges of the airfoil, with a tip extending therebetween. An interior of the spar includes a coolant cavity, and each of the pressure and suction side walls includes an arrangement of pedestals on an outer surface thereof and a plurality of cooling holes in fluid communication with the coolant cavity. A pressure side coversheet overlies the pressure side wall and terminates in a radial direction short of the tip of the spar to form a shelf extending along a chordal direction. Flow channels between the pressure side wall and coversheet are configured to direct coolant from the cooling holes to radial flow outlets adjacent to the shelf. A suction side coversheet overlies the suction side wall, and a coolant circuit between the suction side wall and coversheet does not include radial coolant outlets.

US Patent:

20160053633, Feb 25, 2016

Filed:

Aug 7, 2015

Appl. No.:

14/820686

Inventors:

- Indianapolis IN, US
Brett J. Barker - Indianapolis IN, US
John A. Weaver - Indianapolis IN, US

International Classification:

F01D 25/14
B23P 15/00
F01D 11/00

Abstract:

A seal may be used in a shroud ring of a turbine. The seal includes a first strip, a second strip, and a flow-control band that extends between and interconnects the first and second strips to control the flow of a fluid through the seal.

US Patent:

20150300257, Oct 22, 2015

Filed:

Dec 31, 2013

Appl. No.:

14/145172

Inventors:

- Indianapolis IN, US
Jeffrey F. Rhodes - Zionsville IN, US
Okey Kwon - Indianapolis IN, US
Tab M. Heffernan - Plainfield IN, US
Brett J. Barker - Dublin OH, US

International Classification:

F02C 7/12

Abstract:

A gas turbine engine component is provided that can be cooled with a cooling media such as air using a variety of passages. In one form, cooling fluid is routed through a hole that exits at least partially through a pedestal formed between walls. A plurality of cooling holes can be provided through a trench face and in some forms can include a diffusion through a divergence in the hole exit. J-Hook passages can be provided through a trench face, and, in some forms, multiple trenches can be provided. A cooling hole having a neck portion can be provided, as can a cooling hole with one or more turns to reduce a total pressure. In one form, a corrugated cooling passage can be provided.