Colin D Craig

US Patent:

7837199, Nov 23, 2010

Filed:

Nov 3, 2005

Appl. No.:

11/266454

Inventors:

Colin D. Craig - West Hartford CT, US
Enzo Dibenedetto - Torrington CT, US
Christopher P. Kmetz - Amston CT, US
Jonathan L. Miller - East Hampton CT, US
Mark R. Sondeen - West Hartford CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F16J 15/00

US Classification:

277377, 277370, 277375

Abstract:

A face seal includes a seal seat and a seal element carried by a seal housing. The seal element cooperates with the seal seat to establish a seal. The housing includes a support for the seal element and a shroud for effecting a gradual transition between a normal condition and a deteriorated condition. The shroud may have a tip whose properties differ in lubricity, hardness or abradability relative to other portions of the seal housing.

US Patent:

20100264601, Oct 21, 2010

Filed:

Jun 29, 2010

Appl. No.:

12/826629

Inventors:

Colin D. Craig - West Hartford CT, US
Enzo Dibenedetto - Torrington CT, US
Christopher P. Kmetz - Amston CT, US
Jonathan L. Miller - East Hampton CT, US
Mark R. Sondeen - West Hartford CT, US

International Classification:

F16J 15/34

US Classification:

277399, 277358, 277404

Abstract:

One embodiment of the face seal described herein includes a seal seat and a seal element carried by a seal housing. The seal element cooperates with the seal seat to establish a seal. The housing includes a seal element support and a shroud. The seal housing is made of a parent material and the shroud has a tip impregnated with a second material.

US Patent:

61321680, Oct 17, 2000

Filed:

Dec 23, 1998

Appl. No.:

9/220467

Inventors:

Stanley K. Kovaleski - South Windsor CT
Donald J. Kovaleski - South Windsor CT
Colin D. Craig - West Hartford CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 1100

US Classification:

415113

Abstract:

A gas turbine engine includes a plurality of seal stages minimizing leakage of high pressure air from a high pressure cavity into a low pressure cavity. The plurality of seal stages includes an upstream seal stage, substantially adjacent to the high pressure cavity, and a downstream seal stage, substantially adjacent to the low pressure cavity. Each seal stage includes a seal plate and at least one seal. The downstream seal plate includes a plurality of bleeding holes for metering higher pressure air into the low pressure cavity, thereby balancing a pressure drop between the seal stages. Substantial equalization of the pressure drop among the seal stages reduces wear of the downstream seal and therefore, increases useful life an effectiveness thereof.

US Patent:

20220275760, Sep 1, 2022

Filed:

May 18, 2022

Appl. No.:

17/747158

Inventors:

- Farmington CT, US
Colin D. Craig - West Hartford CT, US
Michael M. Davis - North Granby CT, US

International Classification:

F02C 7/28
F02C 3/04
F02C 7/06
F02C 7/36
B64D 27/10
B64D 35/02
F16J 15/34

Abstract:

A bearing is mounted to a static structure outwardly of the shaft, and supporting the shaft. A bearing compartment is defined by face seal arrangements on each of two axial sides of a bearing. Each face seal arrangement includes a seal seat rotating with the shaft and a non-rotating sealing ring. The seal housing is exposed to high pressure air outward of the bearing compartment. A coil spring biases the seal housing towards the seal seat, such that the sealing face is biased into contact with the seal seat by a bias force including a net fluid force acting on the seal housing and the coil spring. The sealing face is defined by a contact portion contacting the seal seat and a feed portion recessed from the seal seat. The feed portion includes a plurality of circumferentially spaced feed slots fluidly connected to at least one annular groove.

US Patent:

20200256211, Aug 13, 2020

Filed:

Feb 7, 2019

Appl. No.:

16/269637

Inventors:

- Farmington CT, US
Colin D. Craig - West Hartford CT, US

International Classification:

F01D 25/18
F01D 25/20
F02C 7/06

Abstract:

A gas turbine engine includes an engine static structure. A rotating structure is configured to rotate relative to the engine static structure. The rotating structure has a target area with first and second directions. The first direction is greater than the second direction. A lubrication system includes a nozzle having a non-circular exit aimed at the target area. The exit provides a width and a height. The width is greater than the height. The width is oriented in the first direction.

US Patent:

20190178381, Jun 13, 2019

Filed:

Dec 13, 2017

Appl. No.:

15/840632

Inventors:

- Farmington CT, US
Colin D. Craig - West Hartford CT, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Farmington CT

International Classification:

F16J 15/16
F16J 15/34

Abstract:

A force balanced face seal may comprise a seal housing comprising an annular extrusion, a seal support, wherein the annular extrusion is disposed within the seal support, and a primary seal coupled to the seal housing, wherein the primary seal comprises a sealing face and a base opposite the sealing face and proximate the seal housing.

US Patent:

20190040957, Feb 7, 2019

Filed:

Aug 1, 2017

Appl. No.:

15/666136

Inventors:

- Farmington CT, US
Colin D. Craig - West Hartford CT, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Farmington CT

International Classification:

F16J 15/34
F01D 11/00

Abstract:

A carbon seal assembly may comprise a seal support, a seal housing coupled to the seal support, and a carbon seal adjacent an aft portion of the seal housing. The carbon seal may comprise a nose defined by an axial surface of the carbon seal, a first radial surface of the carbon seal, and a second radial surface of the carbon seal radially inward of the first radial surface. The first radial surface and the second radial surface may extend forward from the axial surface. A first axial length of the first radial surface may be greater than a second axial length of the second radial surface.

US Patent:

20190017605, Jan 17, 2019

Filed:

Jul 14, 2017

Appl. No.:

15/650171

Inventors:

- Farmington CT, US
Joseph G. Colucci - Milford CT, US
Colin D. Craig - West Hartford CT, US
Aneil S. Hegde - Mansfield Center CT, US
Michael M. Davis - North Granby CT, US

International Classification:

F16J 15/3296
F16J 15/3268

Abstract:

A ring seal in a gas turbine engine includes a ring seal body, an axial sealing dam, a radial sealing dam, and at least one bleed slot. The ring seal body is annular in shape and has a first axial side, a second axial side, a radially outer side, and a radially inner side. The axial sealing dam is on the first axial side and is configured to provide a first sealing surface with a first component. The radial sealing dam is on the radially outer side and is configured to provide a second sealing surface with a second component radially outward from the radially outer side. The at least one bleed slot is on the second axial side and configured to allow fluid to pass through when the ring seal is incorrectly oriented such that the at least one bleed slot is adjacent to the first component.