Brian J Shoemaker

US Patent:

20200080426, Mar 12, 2020

Filed:

Sep 24, 2019

Appl. No.:

16/580784

Inventors:

- Indianapolis IN, US
Bruce Varney - Greenwood IN, US
Brian Shoemaker - Indianapolis IN, US
Charles Bulgrin - Plainfield IN, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN

International Classification:

F01D 5/18
F01D 9/06
F01D 9/04

Abstract:

An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.

US Patent:

20190032493, Jan 31, 2019

Filed:

Jul 31, 2017

Appl. No.:

15/664996

Inventors:

- Indianapolis IN, US
Bruce Varney - Greenwood IN, US
Brian Shoemaker - Indianapolis IN, US
Charles Bulgrin - Plainfield IN, US

International Classification:

F01D 5/18
F01D 9/06

Abstract:

An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.

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:

20170370240, Dec 28, 2017

Filed:

Aug 9, 2017

Appl. No.:

15/672991

Inventors:

- Indianapolis IN, US
- Cypress CA, US
- London, GB
Brian J. Shoemaker - Indianapolis IN, US
Steven Hillier - Manchester, GB

International Classification:

F01D 11/00
F01D 5/22
F01D 9/04
F01D 25/24
F01D 25/26
F01D 5/24

Abstract:

A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.

US Patent:

20160348521, Dec 1, 2016

Filed:

May 28, 2015

Appl. No.:

14/723909

Inventors:

- Indianpolis IN, US
- Indianapolis IN, US
- Huntington Beach CA, US
Joseph P. Lamusga - Indianapolis IN, US
Brian J. Shoemaker - Indianapolis IN, US

International Classification:

F01D 11/00
F01D 25/26

Abstract:

A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.