Abstract: A combustor wall louver for ducting a flow of compressed air through an inlet opening in the combustor wall from a source of compressed air outside the combustor where the louver is a circumferentially extending member, mounted to an interior surface of the combustor wall and covering the inlet opening with outlet openings fed by a channel in flow communication between each outlet opening and the inlet opening. Preferably, the circumferential member is made of arcuate segments of cast metal removably mounted to the interior surface of the combustor wall with threaded studs.

Abstract: A gas turbine engine comprising an annular reverse-flow combustor having a sheet metal combustor wall between a long exit duct portion and a small exit duct portion of the combustor. An exit duct portion of the combustor forms a sliding joint with a downstream turbine vane assembly and has at least two discrete sheet metal walls fastened to the sheet metal combustor wall at a common intersection region.

Abstract: A simplified floating collar is provided comprising an collar with opposed flanges. The arrangement offers reduced cost, and simplicity, and therefore facilitates manufacturing.

Abstract: A method of making a gas turbine engine combustor using the steps of: providing a combustor; providing a circumferentially extending louver member for ducting a flow of compressed air through at least one inlet opening in a combustor wall from a source of compressed air outside the combustor; and mounting the louver member in a non-destructive manner for releasable connection and disconnection to an interior surface of the combustor wall and at least partially covering the at least one inlet opening, the louver having a number of outlet openings in flow communication with an inlet opening.