Anthony B Swift

US Patent:

20200386105, Dec 10, 2020

Filed:

Jun 7, 2019

Appl. No.:

16/434630

Inventors:

- Farmington CT, US
Paul M. Lutjen - Kennebunkport ME, US
Richard K. Hayford - Cape Neddick ME, US
Anthony B. Swift - Waterboro ME, US

International Classification:

F01D 5/20

Abstract:

A blade outer air seal segment including a radially outward surface, a radially inward surface oriented away from the radially outward surface, and a cooling channel located between the radially outward surface and the radially inward surface. The blade outer air seal segment also including a stress-relief boss extending into the cooling channel and an inlet orifice fluidly coupled to the cooling channel through the stress-relief boss. The blade outer air seal segment further including a stress-relief recess. The stress-relief boss being located within the stress relief recess.

US Patent:

20190226406, Jul 25, 2019

Filed:

Apr 4, 2019

Appl. No.:

16/375064

Inventors:

- Farmington CT, US
Anthony B. Swift - North Waterboro ME, US

International Classification:

F02C 7/18
F02C 7/05
F01D 11/12
F01D 25/12

Abstract:

An air-driven particle pulverizer for a gas turbine engine includes an array of fingers arranged about an axis. Each of the fingers comprises a base and a terminal end. Each terminal end extends away from the axis and canted toward one side. The terminal ends are configured to pulverize particles in a fluid directed onto the terminal ends.

US Patent:

20180119560, May 3, 2018

Filed:

Oct 31, 2016

Appl. No.:

15/339581

Inventors:

- Farmington CT, US
Ken F. Blaney - Middleton NH, US
Daniel S. Rogers - Arundale ME, US
Anthony B. Swift - North Waterboro ME, US
Thomas E. Clark - Sanford ME, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Farmington CT

International Classification:

F01D 11/10
F01D 9/02
F01D 25/24

Abstract:

A seal assembly includes a blade outer air seal, a downstream vane, and a pressure wall, according to various embodiments. The blade outer air seal may include a radially outer surface and the downstream vane may be coupled to the blade outer air seal via a fluid sealing engagement. The pressure wall may be coupled to the blade outer air seal and may define a metering orifice. In various embodiments, the metering orifice of the pressure wall is configured to meter air flow from a first plenum upstream of the pressure wall to a second plenum downstream of the pressure wall. In various embodiments, at least a preponderance of the radially outer surface of the blade outer air seal at least partially defines the first plenum and the fluid sealing engagement at least partially defines the second plenum.

US Patent:

20170204735, Jul 20, 2017

Filed:

Jan 15, 2016

Appl. No.:

14/997323

Inventors:

- Hartford CT, US
PAUL M. LUTJEN - KENNEBUNKPORT ME, US
KEN F. BLANEY - MIDDLETON NH, US
ANTHONY B. SWIFT - NORTH WATERBORO ME, US
NEIL L. TATMAN - BRENTWOOD NH, US
CHRISTOPHER M. JAROCHYM - OGUNQUIT ME, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Hartford CT

International Classification:

F01D 11/08
F01D 5/12

Abstract:

A gas turbine engine component is provided. The gas turbine engine component comprises a main body having a leading edge and a leading edge wall including an elongated transition portion extending between the leading edge and a proximate flowpath surface of the main body. The elongated transition portion has an axial length that is greater than a radial height. A gas turbine engine is also provided.

US Patent:

20160169016, Jun 16, 2016

Filed:

Oct 12, 2015

Appl. No.:

14/880403

Inventors:

- Hartford CT, US
Anthony B. Swift - North Waterboro ME, US
Neil L. Tatman - Brentwood NH, US
Paul M. Lutjen - Kennebunkport ME, US
Christopher M. Jarochym - Ogunquit ME, US

International Classification:

F01D 9/06
B22C 9/10
F01D 11/08

Abstract:

A casting core for a Blade Outer Air Seal includes a heat exchange cavity core section in communication with a first plenum section and a second plenum section, the first plenum and the second plenum section are of a thickness greater than the heat exchange cavity section.

US Patent:

20160032835, Feb 4, 2016

Filed:

Jul 21, 2015

Appl. No.:

14/804926

Inventors:

- Hartford CT, US
Anthony B. Swift - North Waterboro ME, US

International Classification:

F02C 7/05

Abstract:

A cooling fluid system for a gas turbine engine includes a structure that provides a fluid passageway. The structure has a wall with an aperture that is in fluid communication with the fluid passageway. The aperture is configured to provide a fluid in a flow direction. Fingers are arranged in the fluid passageway facing into flow direction. The fluid passageway includes a cooling cavity immediately downstream from the fingers and it is configured to receive fluid having passed over or through the fingers.

US Patent:

20160010482, Jan 14, 2016

Filed:

Feb 5, 2014

Appl. No.:

14/766469

Inventors:

- Hartford CT, US
Mark Broomer - Boston MA, US
Craig R McGarrah - Southington CT, US
Timothy M Davis - Kennebunk ME, US
Anthony B Swift - North Waterboro ME, US
Russell E Keene - Arundel ME, US
Carson A. Roy Thill - South Berwick ME, US
Timothy A. Dunbar - Limington ME, US

International Classification:

F01D 11/08

Abstract:

An interface within a gas turbine engine includes a multiple of segmented components, each with a segment flange with a multiple of apertures, at least one of the multiple of apertures a first slot aperture. A full ring component with a ring flange that defines a multiple ring of apertures, at least one of the multiple of ring apertures a second slot aperture, the second slot aperture transverse to the first slot aperture.

US Patent:

20150226132, Aug 13, 2015

Filed:

Feb 2, 2015

Appl. No.:

14/611920

Inventors:

- Hartford CT, US
Mark Broomer - Boston MA, US
Timothy M. Davis - Kennebunk ME, US
Craig R. McGarrah - Southington CT, US
Mark J. Rogers - Kennebunk ME, US
Russell E. Keene - Arundel ME, US
Anthony B. Swift - Waterboro ME, US

International Classification:

F02C 7/28
F01D 25/24
F02C 3/04

Abstract:

A seal assembly for a gas turbine engine includes an engine static structure. First and second members fluidly separate cavities from one another. A seal assembly is captured by the engine structure. The seal assembly includes a carrier and a seal that engages the first member. The second member is captured by the carrier.