Jason H Elliott, Age 485225 W 500 N, Huntington, IN 46750

8000942, Aug 16, 2011

May 14, 2008

12/120319

Tahany Ibrahim El-Wardany - Bloomfield CT, US
Shaoluo L. Butler - Manchester CT, US
Jason Elliott - Willington CT, US
Adam Cade Wilcox - Provo UT, US
Ryan Clifford Cox - Middletown CT, US

United Technologies Corporation - Hartford CT

G06F 7/50
G06G 7/48

703 1, 703 7

This disclosure relates to a design methodology used in manufacturing a broaching tool for cutting slots in aerospace disk applications. The method includes modeling geometry of the slot and the broach tool, which is based upon an initial minimum tooth rise that is determined empirically for the particular disk material. The number of broach inserts and teeth per insert is calculated, and the broach inserts are modeled. The stresses and deformation of the lug are calculated in a finite elements environment based upon simulated incremental broach tool movements. If the lug is not within specifications based upon design constraints, then the broach tool is revised and the simulations are repeated until the slot is within the desired specifications.

2013000, Jan 10, 2013

Jul 5, 2011

13/176255

Edward J. Gallagher - West Hartford CT, US
Jun Jiang - Glastonbury CT, US
Becky E. Rose - Colchester CT, US
Jason Elliott - Huntington IN, US
Anthony R. Bifulco - Ellington CT, US

F02K 3/00

60 39163

A gas turbine engine includes a spool, a turbine coupled to drive the spool and a propulsor that is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the propulsor and the spool such that rotation of the spool drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. The row includes no more than 16 of the propulsor blades.

2013015, Jun 20, 2013

Dec 15, 2011

13/327730

Gabriel L. Suciu - Glastonbury CT, US
Allan R. Penda - Amston CT, US
Christopher M. Dye - San Diego CA, US
Jason Elliott - Huntington IN, US

F01D 25/24
F01D 1/04

415 1, 4152081

A fan case of a gas turbine engine includes a fan blade containment section defined about an engine axis and a plurality of helical ribs adjacent to the fan blade containment section.

2013019, Aug 1, 2013

Jan 31, 2012

13/362057

James R. Murdock - Tolland CT, US
Christopher S. McKaveney - Rocky Hill CT, US
Jason Elliott - Huntington IN, US

B64C 27/46

416223 R

A fan blade includes a root including a front surface, a rear surface, a first side surface connected to the front surface and the rear surface, and a second side surface connected to the front surface and the rear surface. The front surface engages the first side surface and the second side surface by one or more blunted surfaces, and the rear surface engages the first side surface and the second side surface by one or more blunted surfaces. A blade extends from the root.

2016023, Aug 11, 2016

Feb 9, 2015

14/617614

- Farmington CT, US
William R. Graves - Manchester CT, US
Jason Elliott - Huntington IN, US
David P. Houston - Glastonbury CT, US
Ethan C. Drew - Mansfield CT, US

F01D 5/30
F02C 3/04

A dovetail root of a fan blade configured for operation within the fan assembly of a gas turbine engine. The dovetail root is imparted with a compressive residual stress layer along the outer faces of the dovetail root preventing crack formation within the dovetail root when the gas turbine engine is in operation. To further protect and structurally enhance the dovetail root, a wear covering is disposed on the dovetail root. The wear covering may consist of a composite laminate layer that is bonded to the metallic core of the dovetail root providing additional cracking protection of the dovetail root when the gas turbine engine is in operation.

2016018, Jun 30, 2016

Nov 6, 2015

14/934449

- Hartford CT, US
Jason Elliott - Huntington IN, US

F01D 5/14
F01D 5/02
F01D 5/32
F01D 5/28
F01D 5/30

A turbojet fan blade adapted for securement to an engine rotor includes a titanium sheath that extends continuously over its leading edge from blade tip to blade root. The sheath provides impact protection over the leading edge of the blade, and also incorporates enhanced radial securement of the sheath to the rotor. As such, a radial lock system for the sheath is disclosed that includes a fully integrated sheath portion that extends completely over the frontal face of a fan blade dovetail, providing a radial lock of the sheath to the rotor in the event of failure of any adhesive used to attach the sheath to the leading edge. Because the sheath extends continuously from blade tip to the blade root, lightning strike protection is enhanced by avoidance of any discontinuities otherwise associated with related art sheaths that typically extend over only a flow path portion of the leading edge.