Sarah Riley

US Patent:

20140000262, Jan 2, 2014

Filed:

Aug 30, 2012

Appl. No.:

13/598988

Inventors:

Mark A. Boeke - Plainville CT, US
Edwin Otero - Southington CT, US
Jeffrey J. DeGray - Hampden MA, US
Guillermo J. Fernandez - San Juan PR, US
Sarah Riley - Glastonbury CT, US

International Classification:

F01D 9/02
F02C 3/06

US Classification:

60726, 415115

Abstract:

A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an body portion that extends between a leading edge and a trailing edge. At least one of the leading edge and the trailing edge includes at least one discharge slot having a first portion that includes an oval geometry.

US Patent:

20160208627, Jul 21, 2016

Filed:

Jan 16, 2015

Appl. No.:

14/599075

Inventors:

- Farmington CT, US
Kristopher K. Anderson - Manchester CT, US
Jeffrey J. De Gray - Hampden MA, US
Jeffrey R. Levine - Vernon Rockville CT, US
Sarah Riley - Smyrna GA, US

International Classification:

F01D 9/02

Abstract:

An airfoil platform includes a platform body having an arcuate base defining a centerline axis. A rail extends radially outboard from a side of the arcuate base. A feed orifice is defined at least partially in the rail. The inner diameter edge of an axially facing opening of the feed orifice is spaced apart radially outboard of an outer diameter surface of the arcuate base. A method for manufacturing an airfoil platform includes providing an airfoil platform body and forming the feed orifice through the rail. Forming the feed orifice through the rail includes forming the feed orifice radially outboard of and spaced apart from the outer diameter surface of the arcuate base.

US Patent:

20140219778, Aug 7, 2014

Filed:

Sep 28, 2012

Appl. No.:

13/630419

Inventors:

United Technologies Corporation - , US
Shawn J. Gregg - Wethersfield CT, US
Sarah Riley - Glastonbury CT, US
Jeffrey J. DeGray - Hampden MA, US
Richard M. Salzillo - Plantsville CT, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Hartford CT

International Classification:

F01D 5/18
F01D 9/02

US Classification:

415115

Abstract:

A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform. A void is interconnected to at least one of the radially extending passage and the inlet passage.