FRANK A LASTRINA
Engineering in Andover, MA

6519850, Feb 18, 2003

Jul 10, 2002

10/192576

Timothy P. Mc Caffrey - Swampscott MA
Frank A. Lastrina - Andover MA
Joseph D. Monty - Boxford MA
David E. Hrencecin - Peabody MA

General Electric Company - Schenectady NY

B21D 5300

2989001

A combustor liner has a stepped combustor liner surface defining a combustion zone and an overhang portion forming an air cooling slot. A layer of thermal barrier material is applied to the combustor liner such that at least one portion of the combustor liner receives a layer of thermal barrier material with a thickness greater than 0. 01 inches. Thus, the combustor liner absorbs less heat, and the combustor may operate at higher temperatures. As a result, low cycle fatigue and thermal creep are reduced within the combustor and the life cycle for the combustor is extended.

6487861, Dec 3, 2002

Jun 5, 2001

09/874854

Robert Gregory Carita - Needham MA
Irven Charles Ball - West Newbury MA
Frank Anthony Lastrina - Andover MA

General Electric Company - Schenectady NY

F02C 100

60748, 60 3937, 60737, 60805

A combustor for a gas turbine engine includes outer and inner liners defining a combustion chamber and an igniter mounted to the outer liner. A dome plate is disposed between the outer and inner liners and has a plurality of circumferentially spaced openings formed therein. A fuel-air mixer is disposed in each one of the openings; each fuel-air mixer includes a swirler mounted in the corresponding opening and a fuel nozzle received in the corresponding swirler. Two adjacent ones of the swirlers are low air flow swirlers in general circumferential alignment with the igniter and the rest of the swirlers are higher air flow swirlers. Each one of the fuel nozzles provides a similar amount of fuel so that the two fuel-air mixers having low air flow swirlers produce a local region of increased fuel-to-air ratio in the vicinity of the igniter.

6438958, Aug 27, 2002

Feb 28, 2000

09/513943

Timothy P. McCaffrey - Swampscott MA
Frank A. Lastrina - Andover MA
Joseph D. Monty - Boxford MA
David E. Hrencecin - Peabody MA

General Electric Company - Schenectady NY

F23R 300

60752, 60756

A combustor liner has a stepped combustor liner surface defining a combustion zone and an overhang portion forming an air cooling slot. A layer of thermal barrier material is applied to the combustor liner such that at least one portion of the combustor liner receives a layer of thermal barrier material with a thickness greater than 0. 01 inches. Thus, the combustor liner absorbs less heat, and the combustor may operate at higher temperatures. As a result, low cycle fatigue and thermal creep are reduced within the combustor and the life cycle for the combustor is extended.

4685942, Aug 11, 1987

Dec 27, 1982

6/453011

David D. Klassen - Boxford MA
Roy E. Moyer - Danvers MA
Frank A. Lastrina - Andover MA
Robert P. Tameo - Peabody MA

General Electric Company - Lynn MA

B01D 4504

55306

The invention is an improved inlet particle separator for removing extraneous matter from a stream of air directed into the engine's core section. The improved separator utilizes two stages of separation. The first stage is an axial flow separator for initially separating engine inlet air into a first flow of relatively contaminated air and a second flow of relatively clean air. This first stage of separation is accomplished by sharply turning the air flow radially inwardly so that the relatively dense extraneous matter continues in its original direction into a scavenge system. A second stage of separation is accomplished in the scavenge system and comprises a centrifugal separator that separates the first flow of air into third and fourth flows of relatively contaminated air for the purpose of protecting a blower that powers the flow through the scavenge system and which is in flow communication with only the relatively less contaminated fourth flow of air.

4527387, Jul 9, 1985

Nov 26, 1982

6/444570

Frank A. Lastrina - Andover MA
Leslie M. Pommer - Danvers MA
Jeffrey C. Mayer - Seymour CT

General Electric Company - Lynn MA

F02G 300

60 39092

An inlet particle separator for a gas turbine engine is provided with unique vanes distributed around an entrance to a particle collection chamber. The vanes are uniquely constructed to direct extraneous particles that enter the engine into the collection chamber and prevent the particles from rebounding back into the engine's air flow stream. The vanes are provided with several features to accomplish this function, including upstream faces that are sharply angled towards air flow stream direction to cause particles to bounce towards the collection chamber. In addition, throat regions between the vanes cause a localized air flow acceleration and a focusing of the particles that aid in directing the particles in a proper direction.

4309147, Jan 5, 1982

May 21, 1979

6/041217

Walter E. Koster - Topsfield MA
William E. Ludke - Lynn MA
Frank A. Lastrina - Andover MA

General Electric Company - Lynn MA

F01D 518

416 95

A particle separator for the air cooling system of a gas turbine engine is provided in the form of a rotating chamber having an inlet disposed radially outward of the engine centerline at a distance greater than the distance of the chamber outlet from the engine centerline. The rotation of the chamber centrifuges foreign particles away from the chamber outlet to provide for separation of the particles from the air exiting the chamber.