Darrell G Senile

6658854, Dec 9, 2003

Feb 1, 2002

10/061629

Darrell Senile - Oxford OH
Bernard J. Renggli - Cincinnati OH

General Electric Co. - Schenectady NY

F02K 112

60771, 23926539

A method for assembling a flap and seal system for a gas turbine engine exhaust nozzle including a plurality of backbone assemblies facilitates attaching a basesheet to a backbone. The method includes attaching an attachment system including at least one strap to a basesheet, and coupling the basesheet to a backbone using the attachment system strap.

6739050, May 25, 2004

Oct 13, 2003

10/684275

Darrell Senile - Oxford OH
Bernard J. Renggli - Cincinnati OH

General Electric Company - Schenectady NY

B21D 5300

2989001

A method for assembling a flap and seal system for a gas turbine engine exhaust nozzle including a plurality of backbone assemblies facilitates attaching a basesheet to a backbone. The method includes attaching an attachment system including at least one strap to a basesheet, and coupling the basesheet to a backbone using the attachment system strap.

6745570, Jun 8, 2004

Feb 1, 2002

10/061618

Bernard J. Renggli - Cincinnati OH
Darrell Senile - Oxford OH

General Electric Co. - Schenectady NY

F02K 100

60771, 60228, 60233, 60269, 23926519, 23939143, 2989001, 2989009, 29904

A method for assembling a flap system for a gas turbine engine exhaust nozzle including a plurality of backbone assemblies facilitates extending a useful life of the exhaust nozzle. The method includes providing a flap basesheet having a width defined between a pair of side edges that are coupled together by a leading edge and a trailing edge, and including at least one stiffener that extends between the basesheet side edges and includes an intermediate portion that has a width that is smaller than that of the basesheet and is at least one of bonded to and formed integrally with the basesheet, and coupling the basesheet to the gas turbine engine with a backbone assembly.

6983602, Jan 10, 2006

Apr 21, 2004

10/828643

Darrell Glenn Senile - Oxford OH, US

General Electric Company - Schenectady NY

F02K 1/12

60771, 23926541

A gas turbine engine exhaust nozzle includes a divergent section located aft of a convergent section and a throat therebetween. An exterior fairing is spaced radially outwardly of the divergent section. An ejector cooling air flowpath leads from an ejector cooling air inlet in an aft portion of the fairing to a cooling air ejector in the nozzle. An annular nozzle plenum may be disposed between the divergent section of the nozzle and the external fairing and be part of the ejector cooling air flowpath between the ejector cooling air inlet and the ejector. A plurality of divergent flaps and divergent seals in the divergent section may employ cooling air passages, such as slots, to serve as the ejector. The fairing may include a plurality of circumferentially adjacent exterior flaps and exterior seals and employ truncated ends of or apertures in the exterior seals as the ejector cooling air inlet.

7302793, Dec 4, 2007

Oct 29, 2003

10/696319

Darrell Glenn Senile - Oxford OH, US
Christina Marie Burke - Hamilton OH, US
Bernard J. Renggli - Cincinnati OH, US
John Sigfrid Amneus - Cincinnati OH, US

General Electric Company - Schenectady NY

F02K 1/12

60232, 60771, 23926539, 23926541

A method facilitates assembling a flap system for a gas turbine engine exhaust nozzle including at least one backbone assembly. The method comprises providing a basesheet including a pair of circumferentially-spaced sides coupled together by an upstream side and a downstream side, forming at least one relief cut in the basesheet that extends at least partially across the basesheet from at least one of the circumferentially-spaced sides, and coupling the basesheet to the backbone assembly.

8122722, Feb 28, 2012

Feb 29, 2008

12/040324

Darrell Glenn Senile - Oxford OH, US
Bernard James Renggli - Cincinnati OH, US

General Electric Company - Schenectady NY

F02K 1/00

60770, 60771, 23926519, 277637

An aircraft engine exhaust nozzle basesheet includes longitudinally extending plurality of basesheet segments having panel bodies between segment leading and trailing edges and slidable sealing joints with slidingly un-restrained center surfaces between adjacent segment leading and trailing edges. Segmented first and second basesheet side edges include first and second segment side edges of the basesheet segments respectively. Slidably sealingly engaged overlapping flanges at the segment leading and trailing edges include tacked together transversely spaced apart first and second distal ends of the overlapping flanges. A basesheet assembly includes a frame includes first and second side rails supporting the first and second basesheet side edges. An aircraft gas turbine engine exhaust nozzle includes divergent seals with the basesheet assemblies in sealing engagement against divergent flaps along the first and second side rails.

8156745, Apr 17, 2012

Feb 29, 2008

12/040286

Darrell Glenn Senile - Oxford OH, US
Bernard James Renggli - Cincinnati OH, US

General Electric Company - Schenectady NY

F02K 1/00
B63H 11/10
F16J 15/02

60770, 60771, 23926519, 277637

An aircraft gas turbine engine exhaust nozzle basesheet includes longitudinally extending plurality of basesheet segments. Each of the basesheet segments includes a panel body between segment leading and trailing edges and slidable sealing joints with slidingly un-restrained center surfaces between adjacent segment leading and trailing edges. Segmented first and second basesheet side edges first and second segment side edges of the basesheet segments respectively. Slidably sealingly engaged overlapping flanges at the segment leading and trailing edges include tacked together transversely spaced apart first and second distal ends of the overlapping flanges. Leading and trailing edge ribs supporting the overlapping flanges are clipped together with longitudinally spaced apart and transversely extending forward and aft slits in retainers. A spine includes transverse stiffeners with first and second stiffener distal ends attached to longitudinally spaced apart sets of transversely extending first and second spine tabs of the spine.

8226361, Jul 24, 2012

Jul 8, 2009

12/499377

Ian Francis Prentice - Cincinnati OH, US
Darrell Glenn Senile - Oxford OH, US

General Electric Company - Schenectady NY

F01D 9/02

415191, 4152093, 4152094, 4152101, 4152112

A support frame includes a rail engaging a hook of a composite article having plys. The rail included a rail contact surface generally conformal to and contacting a hook contact surface of the hook. The rail and hook contact surfaces being substantially normal to the plys beneath the hook contact surface. One embodiment of the article is a composite nozzle segment including one or more airfoils extending radially between arcuate radially outer and inner band segments having plys curved about a centerline axis and the rail engages a hook of the radially inner band segment. The hook and the rail may be straight or arcuate. The frame includes a central body extending axially aftwardly from the rail to an aft frame flange. A frame pin may be mounted on the frame, engage the inner band segment or one of the airfoils, and may extend into a cavity in the airfoil.