MONTY LEE SHELTON
Pilots at Gentlewind Ct, Loveland, OH

6422821, Jul 23, 2002

Jan 9, 2001

09/756902

Chander Prakash - Cincinnati OH
Monty Lee Shelton - Loveland OH
John Howard Starkweather - Cincinnati OH
Hardev Singh - Mason OH
Gerard Anthony Rinck - Cincinnati OH

General Electric Company - Schenectady NY

F01D 518

416224, 416228, 416236 R, 416 92, 416 97 R

A rotor blade for a gas turbine engine including a tip region that facilitates reducing operating temperatures of the rotor blade is described. The tip region includes a first tip wall and a second tip wall extending radially outward from a tip plate of an airfoil. The tip walls extend from adjacent a leading edge of the airfoil to connect at a trailing edge of the airfoil. A notch is defined between the first and second tip walls at the airfoil leading edge. At least a portion of the second tip wall is recessed to define a tip shelf.

6340285, Jan 22, 2002

Jun 8, 2000

09/590590

Craig Alan Gonyou - Blanchester OH
Roger Lee Doughty - Cincinnati OH
Monty Lee Shelton - Loveland OH

General Electric Company - Cincinnati OH

F04D 3100

415116, 415138, 415139, 415176

A segmented turbine cooling component, such as shroud segment for the high pressure and low pressure turbine sections of a gas turbine engine, useful in providing preferential cooling to the side rails or panels of the turbine component through the combination of cooling air fed into the intermediate pressure cavity between the discourager and primary seals and then through recesses in the bottom wall of the lower discourager seal slot that impinges air on the portion of the side panel below the discourager seal. The side panels of the turbine component have an upper primary seal slot and a lower discourager seal slot with a bottom wall having a plurality of alternating lands and recesses along the length thereof and a plurality of cooling air passages having outlets exiting into the lower slot above the lands. The subassembly can be formed from a plurality of such turbine components where the spacing of the lands and recesses of the lower discourager slots of the adjacent side panels are staggered such that the lands of the lower slot of one adjacent panel are opposite the recesses of the lower slot of the other adjacent side panel. This subassembly also has primary and discourager seals received by the respective upper and lower slots that are positioned in the gap between the adjacent panels which define the intermediate pressure cavity therebetween and trench below the discourager seal that is purged by spent cooling air from the recesses in the lower slot.

6629817, Oct 7, 2003

Jul 5, 2001

09/899305

Monty Lee Shelton - Loveland OH
Thomas Tracy Wallace - Maineville OH
Robert Alan Frederick - West Chester OH

General Electric Company - Schenectady NY

F01D 518

415115, 416 97 R, 29889721

An airfoil for a gas turbine engine including an inflection that facilitates enhancing film cooling of the airfoil, without adversely affecting aerodynamic efficiency of airfoil is described. The airfoil includes a generally concave first sidewall and a generally convex second sidewall joined at a leading edge and at a trailing edge of the airfoil. A plurality of cooling openings extend between an internal cooling chamber and an external surface of the first sidewall. One cooling opening extends from the cooling chamber into the inflection at a relatively shallow injection angle with respect the airfoil external surface.

6540477, Apr 1, 2003

May 21, 2001

09/862039

Christopher Charles Glynn - Hamilton OH
Thomas Tracy Wallace - Maineville OH
Ronald Arthur Dickman - Indian Springs OH
Monty Lee Shelton - Loveland OH

General Electric Company - Schenectady NY

F01D 514

415115, 4151745, 416 96 R

A turbine cooling circuit includes a flow sleeve having an aft end for adjoining the rim of a turbine disk. A seal rotor is spaced from the aft end adjacent a row of inlet holes. An inducer has an outlet disposed radially outwardly from the sleeve inlet holes. And, a seal stator surrounds the seal rotor to define a rotary seal disposed radially inwardly from the inducer outlet.

6398487, Jun 4, 2002

Jul 14, 2000

09/616257

Thomas Tracy Wallace - Maineville OH
Christopher Charles Glynn - Hamilton OH
Monty Lee Shelton - Loveland OH
Jeffrey Donald Clements - Mason OH
Dean Thomas Lenahan - Cincinnati OH
Barry John Kalb - Cincinnati OH

General Electric Company - Schenectady NY

F01D 514

415115, 415191, 415202, 4152082

A gas turbine engine rotor assembly includes a plurality of aerodynamic devices to direct airflow radially inward. The gas turbine engine rotor assembly includes a rotor shaft that includes a plurality of openings. The aerodynamic devices include a pair of vane segments and a pair of sidewalls. A contoured outer surface includes an opening and permits the aerodynamic device to be positioned against an inner surface of the rotor shaft, and a flange ring defines a pocket. The aerodynamic device fits within the pocket to concentrically align the openings.

6325593, Dec 4, 2001

Feb 18, 2000

9/507407

Toby G. Darkins - Loveland OH
Monty L. Shelton - Loveland OH
Roger L. Doughty - Cincinnati OH
Mark E. Noe - Morrow OH

General Electric Company - Cincinnati OH

F01D 514

415115

A gas turbine engine hollow turbine airfoil, such as a first stage vane of a high pressure turbine of a gas turbine engine includes an outer wall surrounding a hollow interior. The outer wall extends radially outwardly in a spanwise direction from an airfoil base to an airfoil tip and has chordwise spaced apart leading and trailing edges and widthwise spaced apart pressure and suction side portions extending chordwise between the leading edge and a trailing edge block which terminates at the trailing edge. A plurality of trailing edge cooling air ducts extend chordwise through the trailing edge block aftwardly from the hollow interior and a plurality of trailing edge film cooling holes extend from the ducts through the trailing edge block. The cooling air ducts are preferably centered near a neutral axis of chordwise and spanwise bending of the trailing edge block. The trailing edge cooling air ducts converge aftwardly from the hollow interior and preferably converge in width with a substantially constant spanwise height.

5931636, Aug 3, 1999

Aug 28, 1997

8/919520

Joseph W. Savage - Maineville OH
Ely E. Halila - Cincinnati OH
Robert J. Orlando - West Chester OH
Valentine R. Boehm - Cincinnati OH
James A. Martus - West Chester OH
Thomas T. Wallace - Maineville OH
Monty L. Shelton - Loveland OH

General Electric Company - Cincinnati OH

F01D 1716

415115

A variable area turbine nozzle includes a plurality of circumferentially adjoining nozzle segments. Each nozzle segment includes outer and inner bands, with a plurality of first vane segments fixedly joined therebetween. A plurality of second vane segments adjoin respective ones of the first vane segments to define therewith corresponding vanes which are spaced apart to define respective throats of minimum flow area for channeling therethrough combustion gas. The second vane segments are pivotable to selectively vary the throat area.