General Electric Company

John Lawrence Vandike

Gilbert Farmer

Allen Michael Danis

Duane Douglas Thomsen

Michael Louis Vermeersch

James Neil Cooper

Marie Ann McMasters

Shaun M Devane

A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, including: an annular dome plate having an inner portion, an outer portion, a forward surface, and a plurality of circumferentially spaced openings formed therein, wherein a radial section defined between each of the openings includes a cooling trough formed therein; an outer cowl connected to the dome plate outer portion at a downstream end thereof; an inner cowl connected to the dome plate inner portion at a downstream end thereof; and, a deflector plate connected to and positioned aft of each opening in the dome plate. Each deflector plate further includes: an annular section at an upstream end thereof having a forward end, an aft end, an inner surface and an outer surface; a substantially planar flange connected to the aft end of the annular section, the planar flange including an outer circumferential surface, an inner circumferential surface, a first radial surface, a second radial surface, and an opening therein sized to the inner surface of the annular section so as to form opposing radial sections; a first flange connected to the outer circumferential surface of the planar flange at a predetermined angle thereto; and, a second flange connected to the inner circumferential surface of the planar flange at a predetermined angle thereto. The first and second radial sections of the deflector plate planar flange are configured so at least a portion of the dome plate cooling trough is in flow communication with a combustion chamber downstream of said dome plate.

Combustor dome assembly of a gas turbine engine having improved deflector plates

An annular one-piece liner for a combustor of a gas turbine engine, including a first end adjacent to an upstream end of the combustor, a second end adjacent to a downstream end of the combustor, and a plurality of corrugations between the first and second ends, each corrugation having an amplitude and a wavelength between an adjacent corrugation, wherein the amplitude of the corrugations and/or the wavelength between adjacent corrugations is variable from the first end to the second end.

Annular one-piece corrugated liner for combustor of a gas turbine engine

Growing community of inventors

Fairfield, OH, United States of America

John Lawrence Vandike