Brian F Merry, 7355 Blake Rd, Upper Stepney, CT 06468

6672836, Jan 6, 2004

Dec 11, 2001

10/014952

Brian D. Merry - Andover CT

United Technologies Corporation - Hartford CT

F01D 518

416 97R, 415178

A coolable rotor blade having an airfoil having two serpentine passages is disclosed. Various construction details are developed for providing cooling to the leading edge region and the trailing edge region of the airfoil. In one detailed embodiment, the airfoil trip strips in the passages having constant height and constant pitch over each leg in most legs of the passages except for the legs closest to the edge regions of the airfoil.

7128535, Oct 31, 2006

Nov 26, 2003

10/720875

Gabriel Sucin - Glastonbury CT, US
Brian Merry - Andover CT, US

United Technologies Corporation - Hartford CT

F01D 5/06
F01D 5/02

416198A, 416201 R, 416244 R, 416213 R, 4151991, 298892

The present invention relates to an improved turbine structure for use in a gas turbine engine. The turbine structure includes a one-piece drum rotor and a plurality of turbine blades attached to the one-piece drum rotor. The one-piece drum rotor includes integrally formed, welded disks for supporting the plurality of turbine blades. A method for installing the turbine structure is also described.

7249929, Jul 31, 2007

Nov 13, 2003

10/713641

Kevin J. Cummings - West Hartford CT, US
Christopher G. Demers - Willington CT, US
James C. Hodgson - Canton CT, US
Gabriel Suciu - Glastonbury CT, US
Brian Merry - Andover CT, US

United Technologies Corporation - Hartford CT

F01D 25/14

415144, 415145, 4152112, 2988922

A gas turbine engine compressor has a number of shroud rings, at least a bleed one of which defines a number of bleed ports. A structural hub is downstream of the shroud rings and secured relative to the shroud rings. A structural hub case extends from an aft joint with the structural hub to a fore joint with a joined one of the shroud rings and has a number of valve ports. At least a portion of the structural case extends structurally between the fore and aft joints. A valve element is shiftable between first and second conditions for respectively blocking and not blocking communication through the valve ports.

7500365, Mar 10, 2009

May 5, 2005

11/122336

Gabriel Suciu - Glastonbury CT, US
Brian Merry - Andover CT, US

United Technologies Corporation - Hartford CT

F02C 6/00

60802, 74DIG 5

Provided is an accessory gearbox for a gas turbine engine that contributes minimally to engine weight and complexity. An accessory gearbox comprises a stationary frame that is circumferentially disposed about a central longitudinal axis of the engine. The frame includes a forward-directed axial face and a rearward-directed axial face for fastening the frame to the engine. A central bore accepts a rotational driving means and an outermost rim circumscribes the outer diameter of the frame. A compartment is located between the bore and the rim. At least one primary accessory is mounted to a face and proximate the compartment, remotely engaging the driving means and able to be driven concurrently therewith.

7594794, Sep 29, 2009

Aug 24, 2006

11/509241

Brian D. Merry - Andover CT, US
Om Parkash Sharma - South Windsor CT, US
Gabriel L. Suciu - Glastonbury CT, US
William E. Alford - Mesa AZ, US

United Technologies Corporation - Hartford CT

F01D 9/00

415161, 4152082

A variable geometry inlet guide vane assembly that reduces stress placed on downstream compressor blades in gas turbine engines. The invention circumferential leans upstream guide vanes, pushing engine core air flow radially. This allows for aerodynamic stresses on the downstream blades to be reduced. The invention overcomes the difference in movement between a unison ring and a vane arm by providing a hinge in conjunction with a spherical bearing that couples to the unison ring.

7631480, Dec 15, 2009

Dec 1, 2004

11/720529

Gabriel L. Suciu - Glastonbury CT, US
Brian Merry - Andover CT, US

United Technologies Corporation - Hartford CT

F02C 3/04

60 3943

A tip turbine engine assembly includes a compressor module () and a fan module () located aft of the compressor module (). The compressor module () and fan module () are fastened together along a mating portion with seals that generally prevent airflow from escaping through the mating portion. The compressor module () and fan module () are independently attachable to each other such that the compressor module () may be attached or detached to or from the fan module () without having to significantly disassemble the fan module (), and verse visa.

7631485, Dec 15, 2009

Dec 1, 2004

11/718429

Gabriel L. Suciu - Glastonbury CT, US
Brian Merry - Andover CT, US

United Technologies Corporation - Hartford CT

F02C 3/073

602261, 60 3983

A liquid-air heat exchanger extracts thermal energy from an engine lubricating fluid system. The liquid-air heat exchanger is located within a tailcone section and is in communication with a portion of the fan bypass airflow which enters the tailcone section through an annular tailcone exhaust nozzle entrance to transfer thermal energy into the combined airflow out of the engine to recover thrust loss ducted from the fan bypass stream.

7845157, Dec 7, 2010

Dec 1, 2004

11/719317

Gabriel Suciu - Glastonbury CT, US
Gary D. Roberge - Tolland CT, US
Brian Merry - Andover CT, US

United Technologies Corporation - Hartford CT

F02K 3/02

602261

A tip turbine engine () according to the present invention provides at least one gear () coupling rotation of a bypass fan () to an axial compressor (), such that the axial compressor () is driven by rotation of the fan () at a rate different from than the rate of the fan. In one embodiment, the rate of rotation of the axial compressor () is increased relative to a rate of rotation of the fan (). By increasing the rotation rate, the compression provided by the axial compressor is increased, while the number of stages of the axial compressor blades may be reduced. As a result, the length of the axial compressor and the overall length of the tip turbine engine are decreased.