Rolls-royce Corporation

Peter Fry

Anthony Pidcock

Jagnandan K Bhangu

David Hustler

Stephen M Cooper

A gas turbine engine combustor 20 has a wall structure 22 including an outer wall 24 having a plurality of wall elements 26 attached thereto. Each wall element 26 has a flange 27 around its periphery which defines a chamber 28 between each wall element and the outer wall 24. Holes 30 in the outer wall 24 permit the flow of cooing air into each chamber 28 to provide impingement cooling of the wall elements 26. Holes 30 in the wall elements 26 permit the exhaustion of cooling air from the chambers to provide film cooling of the wall elements 26.

Removable combustor liner for gas turbine engine combustor

A perforate laminated material suitable for use in the manufacture of combustion chambers for gas turbine engines comprises two sheets bonded together, each sheet having a plurality of perforations, the laminated material being formed with internal channels which interconnect the perforations in the abutting sheets, the contact area between the two sheets being in the range 18% to 60% of the surface area of one side of one of the sheets and the ratio between the number of perforations per unit area in the sheets being in the range 2:1 to 10:1 in use the sheet having the larger number of perforations being adjacent a relatively hot gas stream.

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Derby, United Kingdom

Peter Fry