Aspi R Wadia

6561760, May 13, 2003

Aug 17, 2001

09/932595

Aspi Rustom Wadia - Loveland OH
Kenneth Edward Seitzer - Wyoming OH
Harjit Singh Hura - Cincinnati OH
Frank Worthoff - West Chester OH
Raymond Gust Holm - Lebanon OH
Eric Pierre Masse - West Chester OH
Jason Corey Slagle - Liberty Township OH

General Electric Company - Schenectady NY

F01D 2510

415145, 415176, 60 39093

A booster compressor includes inlet guide vanes supported from a shroud. A shell surrounds the shroud and defines a manifold. A splitter nose includes a groove receiving a forward tang of the shroud with a clearance therebetween defining an outlet for the manifold. Hot air is channeled through the manifold and out the splitter nose for deicing thereof.

6672829, Jan 6, 2004

Jul 16, 2002

10/196623

David Glenn Cherry - Loveland OH
Chander Prakash - Cincinnati OH
Aspi Rustom Wadia - Loveland OH
Brian David Keith - Cincinnati OH
Steven Robert Brassfield - Cincinnati OH

General Electric Company - Schenectady NY

F01D 518

415115, 416 97 R

A turbine blade for a gas turbine engine, including an airfoil and integral dovetail for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud. The airfoil further includes: first and second sidewalls joined together at a leading edge and a trailing edge, where the first and second sidewalls extend from a root disposed adjacent the dovetail to a tip plate for channeling combustion gases thereover; and, at least one tip rib extending outwardly from the tip plate between the leading and trailing edges. The tip rib is oriented so that an axis extending longitudinally therethrough is at an angle with respect to the radial axis for at least a designated portion of an axial length of the turbine blade. Such angle may be substantially the same across the designated portion or may vary thereacross. Accordingly, a recirculation zone of the combustion gases is formed adjacent a distal end of the tip rib which reduces a leakage flow of the combustion gases between the airfoil and the shroud for at least the designated portion of an axial length of the turbine blade.

6725645, Apr 27, 2004

Oct 3, 2002

10/264128

Aspi R. Wadia - Loveland OH
Raymond G. Holm - Lebanon OH

General Electric Company - Schnectady NY

F02K 302

602261, 298901

A system and method are provided for preventing the formation of ice on or removing ice from an internal surface of a turbofan engine. A splitter region, associated with a booster compressor of the turbofan engine, is identified. The splitter region has surfaces internal to the turbofan engine subject to inlet icing conditions. A resin is molded along a leading edge of the splitter region, and electric coils are installed within the resin to prevent ice build-up on the splitter region or to remove ice from the splitter region during icing conditions.

6779979, Aug 24, 2004

Apr 23, 2003

10/421286

Aspi R. Wadia - Loveland OH
Rolf Hetico - Cincinnati OH
Robert Bruce Dickman - Cincinnati OH
Hsin-Yi Yen - Mason OH
Peter Wood - Loveland OH

General Electric Company - Schenectady NY

F01D 510

416236R, 416500

An airfoil for a gas turbine engine includes a leading edge, a trailing edge, a tip, a first side wall that extends in radial span between an airfoil root and the tip, wherein the first side wall defines a first side of said airfoil, and a second side wall connected to the first side wall at the leading edge and the trailing edge, wherein the second side wall extends in radial span between the airfoil root and the tip, such that the second side wall defines a second side of the airfoil. The airfoil also includes a rib that extends outwardly from at least one of the first side wall and the second side wall, such that a natural frequency of chordwise vibration of the airfoil is increased to a frequency that is not present within the gas turbine engine during engine operations.

6790005, Sep 14, 2004

Dec 30, 2002

10/334091

David Glenn Cherry - Loveland OH
Chander Prakash - Cincinnati OH
Aspi Rustom Wadia - Loveland OH

General Electric Company - Schenectady NY

F01D 516

416 97R

A gas turbine engine blade includes pressure and suction sidewalls extending between leading and trailing edges and from root to tip. The pressure sidewall includes an inclined tip rib offset therein by a ramp defining a tip notch having compound inclinations.

7097426, Aug 29, 2006

Apr 8, 2004

10/820325

Aspi Rustom Wadia - Loveland OH, US
David Glenn Cherry - Loveland OH, US

General Electric Company - Schenectady NY

F01D 5/18

416 97R, 416 96 R

A turbine blade includes an airfoil having opposite pressure and suction sidewalls joined together at opposite leading and trailing edges and extending longitudinally from root to tip. A plurality of independent cooling circuits are disposed inside the airfoil correspondingly along the pressure and suction sidewalls thereof. Each circuit includes an inlet channel extending through the dovetail. One of the circuits includes multiple longitudinal channels separated by corresponding perforate partitions each including a row of impingement holes for cascade impingement cooling the inner surface of the airfoil.

7217092, May 15, 2007

Apr 14, 2004

10/824283

Aspi Rustom Wadia - Loveland OH, US
Steven Robert Brassfield - Cincinnati OH, US

General Electric Company - Schenectady NY

F01D 5/18

416 97R

An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and a trailing edge, such that a cavity is defined therebetween. A plurality of rib walls extend at least partially between the first and second sidewalls, wherein the plurality of rib walls define at least one cooling circuit having at least three cooling chambers. At least one row of openings extend through at least one of the rib walls, wherein a first of the cooling chambers supplies cooling fluid to the cavity, and the remaining cooling chambers are coupled in flow communication with the first cooling chamber via the openings.

7249933, Jul 31, 2007

Jan 10, 2005

11/035866

Jan Christopher Schilling - Middletown OH, US
Aspi Rustom Wadia - Loveland OH, US

General Electric Company - Schenectady NY

F01D 5/18

416 97R, 416193 A

A turbine stage includes a row of airfoils and their platforms spaced laterally apart to define flow passages therebetween. Each airfoil is integrally joined to its platform at a funnel-shaped fillet along the pressure side of the airfoil which decreases in size from the leading edge towards the trailing edge. A field of film cooling holes extends through the platform along the fillet for discharging film cooling air.