Combustor exit duct cooling

Details Combustor exit duct cooling Combustor exit duct cooling

F - Mech Eng,Light,Heat,Weapons

23

R

F23R 3/42 (2006.01) F01D 25/12 (2006.01) F02C 3/14 (2006.01)

Patent

CA 2579881

A combustor (16) for a gas turbine (10) engine includes a sheet metal combustor wall (22) having a plurality of cooling apertures (34) therein immediately upstream of a corner (24) between two intersecting combustor wall portions (33/32, 33'/32', 33''/32'').

La présente invention a trait à une chambre de combustion (16) pour une turbine à gaz (10) comportant une paroi de chambre de combustion en tôle (22) comprenant une pluralité d'orifices de refroidissement (34) immédiatement en amont d'un angle (24) entre deux portions de paroi d'intersection (33/32, 33'/32', 33''/32'') de la chambre de combustion.

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