Patent ID: 6029455
Filing Date: 2000-02-29
Classification: F23R

Abstract:
A combustion chamber for a turbojet engine, the combustion chamber comprising:a forward intake;a rear exit;at least one perforated casing between the forward intake and the rear exit; anda thermally protective lining cooperating with the combustion chamber and defining a combustion zone, the lining comprising at least two rows of tiles juxtaposed to form rings such that the two rows extend circumferentially around the combustion chamber in a forward row and a rear row, the forward and rear rows having inner surfaces which are substantially coplanar, the forward and rear rows being a plurality of forward and rear tiles, respectively, the rear tiles in the rear row having forward edge portions with walls which slope away from the inner surfaces and subsequently extend forwardly along the perforated wall, the forward tiles in the forward row having raised surface portions on outer surfaces thereof which are in contact with the perforated casing so as to form a space between the forward tiles and the perforated casing and having tapering rear edge portions which taper toward the inner surfaces and which overlap the forward edge portions with a clearance ""J"" therebetween, the clearance ""J"" being arranged to communicate with the space between the forward tiles and the perforated casing, the tapered rear edge portions of the forward tiles being located adjacent the walls of the forward edge portions of the rear tiles so as to bound a slot having a width therebetween, the slot opening into the combustion chamber so as to communicate between the clearance ""J"" and the combustion chamber and slanting rearwardly such that cooling air passing from the space, through the clearance and through the slot forms a cooling film on the inner surface of the rear row of tiles, the clearance ""J"" being substantially smaller than the width of the slot.