STEVEN R WARD, PA
Physician Assistant at Goodman St, Cincinnati, OH

5233822, Aug 10, 1993

Jan 31, 1991

7/648769

Steven D. Ward - Cincinnati OH
Harold R. Hansel - Mason OH

General Electric Company - Cincinnati OH

F02G 300, F02C 720

60 3902

An apparatus and method for effecting the disassembly of an annular combustor for the maintenance of very large power generation gas generators such as those used in military aircraft engines, commercial aircraft engines, and smaller power generation turbines. The apparatus utilizes rollers which are attachable to a lower half outer casing. An inversion ring located radially inward from the lower half outer casing is supported by the rollers. By disconnecting a removable upper half outer casing, the combustor segments of a first section of the combustor can be removed. Supports connected to the first section of the combustor are secured by pins to a tool ring which is in turn secured to the inversion ring so as to create a closed path. By removing pins which secure the inversion ring and lower half outer casing to supports connected to a second section of combustor segments, the combustor can be rotated so that the second section of formerly inaccessible segments can be easily removed.

6283712, Sep 4, 2001

Sep 7, 1999

9/391305

Aaron M. Dziech - Cincinnati OH
Daniel E. Reisenauer - West Chester OH
William Z. Bolt - Fairfield OH
Richard W. Albrecht - Fairfield OH
Steven D. Ward - Cincinnati OH

General Electric Company - Cincinnati OH

B63H 116, F01D 514

416179

A preferred embodiment of the present invention is a gas turbine engine rotor assembly having axially spaced apart forward and aft disks circumferentially disposed about an axis. The forward disk has an aftwardly extending annular forward arm and the aft disk has a forwardly extending annular aft arm. Forward and aft flanges are located at forward and aft ends of the forward and aft arms respectively. Forward and aft pluralities of aligned forward and aft bolt holes extending axially through the forward and aft flanges respectively. A scalloped annular ring having a plurality of circumferentially spaced apart tabs with spaces therebetween is disposed between the flanges. A plurality of ring bolt holes extend axially through the plurality of circumferentially spaced apart tabs such that corresponding ones of the ring, forward, and aft bolt holes are axially aligned. Forward and aft pluralities of apertures extend axially through the forward and aft flanges and the spaces are in fluid flow communication with corresponding forward and aft ones of the apertures. A plurality of bolts are preferably used to attach the forward and aft flanges together and each of the bolts is disposed through corresponding ones of the ring, forward and aft bolt holes.

5327727, Jul 12, 1994

Apr 5, 1993

8/042953

Steven D. Ward - Cincinnati OH

General Electric Company - Cincinnati OH

F23R 316

60757

A gas turbine engine hot section combustor liner is provided a non-film cooled portion of a heat transfer wall having a hot surface and a plurality of longitudinally extending micro-grooves disposed in the portion of the wall along the hot surface in a direction parallel to the direction of the hot gas flow. The depth of the micro-grooves is very small and on the order of magnitude of a predetermined laminar sublayer of a turbulent boundary layer. The micro-grooves are sized so as to inhibit heat transfer from the hot gas flow to the hot surface of the wall while reducing NOx emissions of the combustor relative to an otherwise similar combustor having a liner wall portion including film cooling apertures. In one embodiment the micro-grooves are about 0. 001 inches deep and have a preferred depth range of from about 0.

6261054, Jul 17, 2001

Jan 25, 1999

9/235914

Ronald Scott Bunker - Niskayuna NY
James William Bartos - Wilmington OH
Nicholas Damlis - Cincinnati OH
Mark Eugene Noe - Hamilton OH
Steven Douglas Ward - Cincinnati OH

General Electric Company - Schenectady NY

F01D 518

415115

An apparatus and method including a closed-circuit coolable airfoil assembly for use and exposure in a hot fluid flow of a machine portion. The assembly includes a first flange configured to be connected with a casing of the machine portion. A second flange is configured to be connected with the casing. An airfoil is connected with and between the first flange and the second flange, the airfoil including a peripheral portion surrounding a medial portion. At least one channel is disposed in the peripheral portion, the channel extending between the first flange and the second flange and being in flow communication with each. A closed flow path is formed from the casing and through the first flange, the second flange and the channel in which a coolant fluid can pass to cool the airfoil assembly.

5813827, Sep 29, 1998

Apr 15, 1997

8/843414

Raymond Scott Nordlund - Orlando FL
Kent Goran Hultgren - Winter Park FL
Robert Kenmer Scott - Geneva FL
Zachary Sinnott - Winter Park FL
William Edward North - Winter Springs FL
Steven Douglas Ward - Cincinnati OH

Westinghouse Electric Corporation - Pittsburgh PA

F01D 518

415115

An apparatus for cooling the trailing edge portion of a gas turbine vane. Two radially extending passages connected to the outer shroud direct cooling fluid to a plenum formed about mid-span adjacent the trailing edge. Two arrays of cooling fluid passages extend from the plenum. One array extends radially outward toward the outer shroud while the other array extends radially inward toward the inner shroud. The plenum distributes the cooling fluid to the two arrays of passages so that it flows radially inward and outward to manifolds formed in the inner and outer shrouds. The manifolds direct the spent cooling fluid to a discharge passage.