Jeffrey M Jacques

US Patent:

20130327847, Dec 12, 2013

Filed:

Jun 11, 2012

Appl. No.:

13/493664

Inventors:

Francis R. Moon - Granby CT, US
Jeffrey M. Jacques - East Hartford CT, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Hartford CT

International Classification:

F02K 1/12

US Classification:

23926539, 23926537

Abstract:

An exhaust nozzle flap for a turbine engine may include an exhaust nozzle flap linkage, an exhaust nozzle flap panel and a mounting pin. The linkage may include a first linkage segment that extends longitudinally from a linkage end to a second linkage segment, and a mounting aperture that extends transversely through the second linkage segment. The panel may include a first panel segment that extends longitudinally from a panel end to a second panel segment. The first panel segment may be pivotally engaged with the first linkage segment. The mounting pin may extend through and move transversely within the mounting aperture, and may be connected to the second panel segment.

US Patent:

20140000282, Jan 2, 2014

Filed:

Jun 29, 2012

Appl. No.:

13/537258

Inventors:

Mark F. Zelesky - Bolton CT, US
Ricardo Trindade - Coventry CT, US
Bret M. Teller - Meriden CT, US
Scott D. Lewis - Vernon CT, US
Jeffrey S. Beattie - South Glastonbury CT, US
Jeffrey Michael Jacques - East Hartford CT, US
Brandon M. Rapp - West Hartford CT, US

International Classification:

F01D 5/18
F02C 7/18
F02C 3/04

US Classification:

60806, 416 97 R, 416 1

Abstract:

A turbine blade for a gas turbine engine includes an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending in a radial direction. The trailing edge is arranged on an aft side of the turbine blade. A root supports a platform from which the airfoil extends and a cooling passage extends within the root in the radial direction to the airfoil. A lower wing is arranged beneath the platform on the aft side and extends in an axial direction to provide a U-shaped channel with the platform that extends in a circumferential direction. An impingement hole extends from the U-channel to the cooling passage.

US Patent:

20140003950, Jan 2, 2014

Filed:

Jun 29, 2012

Appl. No.:

13/537127

Inventors:

Jeffrey S. Beattie - South Glastonbury CT, US
Jeffrey Michael Jacques - East Hartford CT, US

International Classification:

F01D 5/30
B21D 53/78
F01D 5/10

US Classification:

416204 R, 29889

Abstract:

A method of assembling a blade array includes the step of inserting a blade having a platform into a rotor. The blade includes a pocket radially beneath the platform that includes an interference feature. The blade corresponds to one of first and second blades that are scaled versions of one another. The method includes the step of selecting a damper seal, and inserting the damper seal into the pocket. The damper seal corresponds to one of first and second damper seals. The first damper seal cooperates with the interference feature thereby permitting the first damper seal to fully seat within the pocket. The second damper seal is obstructed by the interference feature thereby preventing the second damper seal from fully seating within the pocket.

US Patent:

20200271006, Aug 27, 2020

Filed:

May 13, 2020

Appl. No.:

15/931434

Inventors:

- Farmington CT, US
John R. Farris - Bolton CT, US
Michael G. McCaffrey - Windsor CT, US
Theodore W. Hall - Berlin CT, US
John J. Korzendorfer - Glastonbury CT, US
Elizabeth F. Vinson - Wethersfield CT, US
Jeffrey Michael Jacques - East Hartford CT, US
John E. Paul - Portland CT, US
Edwin Otero - Southington CT, US
Alan W. Stoner - Tullahoma TN, US

Assignee:

RAYTHEON TECHNOLOGIES CORPORATION - Farmington CT

International Classification:

F01D 11/02
F16J 15/44
F16F 15/06
F01D 25/04

Abstract:

A seal for a gas turbine engine includes a full hoop outer ring, a shoe coupled to the full hoop outer ring via an inner beam and an outer beam, and a wave spring in contact with at least one of the inner beam or the outer beam.

US Patent:

20200025293, Jan 23, 2020

Filed:

Jan 9, 2019

Appl. No.:

16/243632

Inventors:

- Farmington CT, US
John R. Farris - Bolton CT, US
Theodore W. Hall - Berlin CT, US
John J. Korzendorfer - Glastonbury CT, US
Elizabeth F. Vinson - Broad Brook CT, US
Jeffrey Michael Jacques - East Hartford CT, US
John E. Paul - Portland CT, US
Ross Wilson - South Glastonbury CT, US
Edwin Otero - Southington CT, US
Alan W. Stoner - Manchester TN, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Farmington CT

International Classification:

F16J 15/44
F01D 11/02

Abstract:

A seal ring system is provided. The seal ring system comprises a segment defining a slot, a pedal along the slot, and an opening offset from the slot. A retention fastener may be disposed in the opening. A seal ring system is also provided comprising a first segment defining a first opening, a second segment defining a second opening, and a retention fastener extending through the first and second openings. The retention fastener configured to allow relative radial movement of the first segment and the second segment. A seal is further provided comprising a seal ring having a central axis, a petal extending radially inward with respect to the central axis of the seal ring, and a sealing disk axially proximate the seal ring. The sealing disk may have a seal shoe configured as a primary seal. The petal may extend toward the seal shoe.

US Patent:

20190331003, Oct 31, 2019

Filed:

Jun 27, 2019

Appl. No.:

16/455093

Inventors:

- Farmington CT, US
Michael G. McCaffrey - Windsor CT, US
John R. Farris - Bolton CT, US
Theodore W. Hall - Berlin CT, US
John J. Korzendorfer - Glastonbury CT, US
Elizabeth F. Vinson - Wethersfield CT, US
Jeffrey Michael Jacques - East Hartford CT, US
John E. Paul - Portland CT, US
Alan W. Stoner - Tullahoma TN, US
Edwin Otero - Southington CT, US

International Classification:

F01D 25/28
F01D 25/24
F01D 11/12
F01D 11/00
F01D 9/04
F01D 9/02
F01D 5/28
F01D 5/24
F01D 5/22
F16J 15/16
F01D 5/26

Abstract:

A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.

US Patent:

20170335698, Nov 23, 2017

Filed:

May 20, 2016

Appl. No.:

15/160216

Inventors:

- Farmington CT, US
Jeffrey Michael Jacques - East Hartford CT, US
Daniel Belotto - Palm Beach Gardens FL, US

International Classification:

F01D 9/02
F02C 3/04
F01D 11/00
F01D 25/24

Abstract:

A turbine vane for a gas turbine engine includes an outer platform including a first side spaced circumferentially apart from a second side, a forward end and an aft end. The first side includes a first gusset extending between the forward end and the aft end. The first gusset defines a first radius beginning at the forward end that transitions into an elliptical curve toward the aft end. An inner platform is also included. An airfoil extends between the outer platform and the inner platform. A gas turbine engine is also disclosed.

US Patent:

20170321560, Nov 9, 2017

Filed:

May 6, 2016

Appl. No.:

15/147954

Inventors:

- Farmington CT, US
Benjamin F. Hagan - Winston-Salem NC, US
Jeffrey Michael Jacques - East Hartford CT, US

International Classification:

F01D 5/30
F01D 9/02

Abstract:

A vane assembly for a gas turbine engine includes an outer platform, an inner platform, a vane, and a seal. The outer platform is disposed proximate a case. The outer platform has a first rail extending towards the case. The first rail has a first face, a second face disposed opposite the first face, and a first opening extending from the first face towards the second face. The inner platform is disposed opposite the outer platform. The vane extends between the inner platform and the outer platform. The seal is received within a slotted region that is disposed between the first face and the second face.