United Technologies Corporation

Stanley Keysa

Jorge I Farah

Michael Joseph Murphy

Curtis C Cowan

Jeffrey R Lavin

Debora F Kehret

Stephen A Paul

Richard Scott

Michael Murphey

Deborah F Kehret

A cooled exhaust duct for use in gas turbine engines is provided. The cooled exhaust duct includes an axial centerline, a circumference, an annulus, and a plurality of radially expandable bands. The annulus is disposed between a first wall and a second wall, and extends along the axial centerline. The first wall is disposed radially inside of the second wall. Each of the plurality of radially expandable bands extends circumferentially within the annulus. The bands are axially spaced apart from one another. Each band includes a first portion attached to the first wall, a second portion attached to the second wall and an intermediate portion connected to the first and second portions. The bands create circumferentially extending compartments that inhibit axial travel of the cooling air within the annulus.

Cooled duct for gas turbine engine

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Windsor, CT, United States of America

Stanley Keysa