Michael R Epstein, 6125 Cross Hill Rd, Portland, ME 04107

6550254, Apr 22, 2003

Aug 17, 2001

09/932585

Robert Proctor - West Chester OH
Julius John Montgomery - Mason OH
Michael Jay Epstein - Mason OH
Roger Owen Barbe - Montgomery OH
Hai Buu Sam - Hamilton OH
James Bernar Ogzewalla - Maysville KY
Andrew David Kemp - Loveland OH
Bryan Keith Doloresco - Cincinnati OH

General Electric Company - Schenectady NY

F02C 608

60785, 415144

A gas turbine engine includes a compressor including a casing and a stator assembly. The casing extends around the stator assembly, the stator assembly including a plurality of stator vanes, and a plurality of bleed scoops. Adjacent stator vanes define a static high-pressure region, the bleed scoops formed at least partially within the high pressure region.

6722137, Apr 20, 2004

Aug 17, 2001

09/932596

Robert Proctor - West Chester OH
John William Hanify - West Chester OH
Debra Lynn Prikkel - Dayton OH
Michael Jay Epstein - Mason OH
Julius John Montgomery - Mason OH

General Electric Co. - Schenectady NY

F16K 122

60782, 60785, 251305, 415178, 123337

A butterfly valve for a gas turbine engine includes a valve shaft and a valve disk. The valve disk has a centerline axis that extends through the valve disk. The valve disk also includes a shaft opening, an outer periphery, an outer surface, a first side, and a second side. The first side is opposite the second side. The shaft opening extends through the valve disk adjacent the centerline axis, and is sized to receive the valve shaft therein. The disk outer surface extends over the first and second sides, and is tapered between the outer periphery and the centerline axis over at least one of the disk first and second sides.

7094020, Aug 22, 2006

Sep 15, 2004

10/941214

Zhifeng Dong - Cincinnati OH, US
Michael J. Epstein - Mason OH, US
William C. Anderson - Springdale OH, US
Jesse Senyo - Williamstown KY, US

General Electric Company - Schenectady NY

F04D 29/08

415112, 415116, 415117, 4151701

A fastener shield for use in a fluid flow path within a gas turbine engine for reducing fluid drag and heating generated by fluid flow over a plurality of circumferentially spaced bolts. The fastener shield has a radially-extending, downstream-facing mounting flange with a plurality of circumferentially spaced bolt holes positioned to receive respective engine mounting bolts therethrough and to attach the mounting flange to elements of the turbine engine. A curved, upstream-facing fastener shield cover is positioned in spaced-apart relation to the mounting flange for at least partially covering and separating an exposed, upstream-facing portion of the bolts from the fluid flow to thereby reduce drag and consequent heating of the bolts. A plurality of closely spaced-apart, spirally-oriented channels are formed in the fastener shield cover for deflecting the fluid flow impinging on the fastener shield cover, thereby increasing the tangential velocity and lowering the relative temperature of the fluid flow.

7165937, Jan 23, 2007

Dec 6, 2004

11/005870

Zhifeng Dong - Cincinnati OH, US
Michael J. Epstein - Mason OH, US
Glen William Royal - Cincinnati OH, US
Robert J. Albers - Park Hills KY, US

General Electric Company - Schenectady NY

F01D 11/08
F03B 11/02

4151732, 415175, 415177, 2988922

A method enables a gas turbine engine to be assembled. The method comprises coupling a rotor assembly including a plurality of circumferentially-spaced rotor blades downstream from, and in flow communication with, a compressor, coupling a casing assembly circumferentially around the rotor assembly such that a clearance is defined between an inner shroud surface of the casing assembly and the rotor blade tips, and coupling a clearance control system to the casing assembly to facilitate maintaining the clearance between the casing assembly and the rotor blade tips, wherein at least a portion of an external surface of the clearance control system is formed with a textured pattern that facilitates increasing the clearance control closure capability during engine operation.

7249463, Jul 31, 2007

Sep 15, 2004

10/941213

William C. Anderson - Springdale OH, US
Jesse Senyo - Williamstown KY, US
Michael J. Epstein - Mason OH, US
Zhifeng Dong - Cincinnati OH, US

General Electric Company - Schenectady NY

F02C 7/20
F01D 25/12

60798, 415112, 415116, 60 3983

A fastener shield for use in a fluid flow path within a gas turbine engine for reducing fluid drag and heating generated by fluid flow over a plurality of circumferentially spaced fasteners. The fastener shield has a radially-extending, downstream-facing mounting flange with a plurality of circumferentially spaced bolt holes positioned to receive respective engine mounting bolts therethrough and to attach the mounting flange to elements of the turbine engine. A curved, upstream-facing fastener shield cover is positioned in spaced-apart relation to the mounting flange for at least partially covering and separating an exposed, upstream-facing portion of the bolts from the fluid flow to thereby reduce drag and consequent heating of the bolts.

2008017, Jul 24, 2008

Sep 20, 2007

11/858831

Michael Epstein - Cambridge MA, US
Matthew Hockenberry - Boston MA, US
Aaron S. Freedman - Cambridge, GB
Ira J. Hochman - Cambridge MA, US

G06F 17/30

7071041, 707E17001

An authoring tool supporting the creation, editing and use of a “Mobile Media Documentary” (MMD) is discussed. An MMD is an interactive tour of physical and virtual locations that is accompanied by multimedia content mapped to spatial data for a known path. The multimedia content includes character-driven audio narrative supplemented by graphics, text, video and interactive content.

2013018, Jul 25, 2013

Sep 30, 2011

13/876738

Michael Jay Epstein - Mason OH, US
Kurt David Murrow - Liberty Township OH, US
Nicholas Rowe Dinsmore - Cincinnati OH, US
Samuel Martin - Cincinnati OH, US
Randy Vondrell - Sharonville OH, US
Robert Harold Weisgerber - Loveland OH, US
Narendra Digamber Joshi - Schenectady NY, US

General Electric Company - Schenectady NY

F02K 9/42

60205, 60257, 60260

A dual fuel propulsion system comprising a gas turbine engine configured to generate a propulsive thrust using a cryogenic liquid fuel.

2014002, Jan 23, 2014

Sep 30, 2011

13/876667

Michael Jay Epstein - Cincinnati OH, US
Randy M. Vondrell - Cincinnati OH, US
Robert Harold Weisgerber - Cincinnati OH, US
Georgia C. Karvountzi - Cincinnati OH, US

GENERAL ELECTRIC COMPANY - Schenectady NY

H01M 8/04

429415, 429513, 429505, 429434, 429429

An aircraft system comprising a fuel storage system comprising a first fuel tank capable of storing a first fuel and a second fuel tank capable of storing a second fuel is disclosed herein. The aircraft system further comprises a fuel cell system comprising a fuel cell capable of producing electrical power using at least one of the first fuel or the second fuel, and a fuel delivery system capable of delivering a fuel from the fuel storage system to the fuel cell system.