The present invention is related to an improved thermal insulation of an exhaust tube (8) for use in a rocket engine. The thermal insulation is provided for as a layered structure wherein respective layers comprises a composite material, and wherein domina...

A gas turbine engine augmentor includes an inter-liner cavity (84) including an axially extending annular gap (62) separating augmentor and tailpipe liners (116, 118). A purge flow cavity (226) is in fluid communication with a fan bypass duct and with the ...

A method of assembling a heat exchanger (602) in a gas turbine engine assembly is provided. The method includes providing a structural body (520) including a wall having an elongated slot (524), providing a heat exchanger (602) operably associated with a b...

A mounting assembly for a heat exchanger for a gas turbine engine. The heat exchanger assembly includes a plurality of arcuate manifolds each supporting an array of fins extending from a radial inner surface. A plurality of circumferentially extending spac...

A combination for connecting a hot sheet (30) and a cold sheet (34) of a nozzle liner (25) in spaced relationship apart includes a stud (60) having a main body wherein the stud (60) is attached to the hot sheet (30) and a portion of the stud (60) extends t...