Honeywell International Inc.

Hamdullah Ozogul

Rodolphe Dudebout

Atul Verma

Sunil James

John Gintert

Michael Ryan Wedig

Bradley Culbertson

Amy Kujala

Ryan Meyer

Michael Wedig

A combustor for a gas turbine engine includes an outer liner having a first end interconnected to an opposite second end by an outer liner wall composed of a plurality of outer segments. The inner liner has a first inner end interconnected to an opposite second inner end by an inner liner wall composed of a plurality of inner segments. The outer liner wall and the inner liner wall define a combustion chamber, and each of the outer wall segments extend at an angle of at least 40 degrees relative to a longitudinal axis. The outer wall segments includes a first segment, a second segment that extends at a second angle relative to the first segment, which is less than a third angle defined between the second segment and a third segment and is substantially the same as a fourth angle defined between the third segment and a fourth segment.

Combustor for gas turbine engine and method of manufacture

A hot section part of a turbine engine configured to be exposed to hot gases includes a first wall, a second wall, a plurality of pedestals, a plurality of impingement cooling holes, and a plurality of effusion cooling passages. The walls are spaced apart to form an intervening cavity, and each pedestal extends through the intervening cavity. The impingement cooling holes extend through the second wall to admit a flow of cooling air into the intervening cavity. Each effusion cooling passage is associated with a different one of the plurality of pedestals and is disposed at a predetermined angle relative to its associated principal axis. A portion of the flow of cooling air admitted to the intervening cavity is directed through at least a portion of each of the plurality of pedestals and onto the first wall inner surface.

Gas turbine engine dual-wall hot section structure

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Phoenix, AZ, United States of America

Hamdullah Ozogul