General Electric Company

Harris Daniel Abramson

Robert Paul Czachor

George A Durgin

George Elliott Moore

Christopher George Housley

Andre Christopher Urso

Kwanwoo Kim

Nayan Vinodbhai Patel

Duane Douglas Thomsen

Craig Alan Gonyou

Anquan Wang

Chad Holden Sutton

Robert Andrew Stowers

James A Russo

Shanwu Wang

George Albert Durgin

A combustor assembly for a gas turbine engine defining an axial direction is provided. The combustor assembly generally includes a liner, an annular dome, and a deflector plate. The liner at least partially defines a combustion chamber. The annular dome defines a first cavity and has a plurality of impingement holes, and the deflector plate defines a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate. The annular dome and the deflector plate are positioned together to define a second cavity that is in fluid communication with the first cavity through the plurality of impingement holes. In addition, the second cavity is in fluid communication with the combustion chamber through the plurality of cooling holes.

Sealed conical-flat dome for flight engine combustors

A gas turbine engine component has an annular flange arm, a backing plate mounted to the flange arm and a bypass circuit formed between the flange arm and the backing plate. The bypass circuit includes one or more channels formed in one of the flange arm or the backing plate. When more than one channels are used, at least one connecting slot is provided between the channels. At least one inlet passage extends through the flange arm in fluid communication with the forward-most channel, and at least one outlet slot is formed between the flange arm and the backing plate in fluid communication with the aft-most channel.

Gas turbine engine component having bypass circuit

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Cincinnati, OH, United States of America

Harris Daniel Abramson