Turbomachine annular combustion chamber

Details Turbomachine annular combustion chamber Turbomachine annular combustion chamber

F - Mech Eng,Light,Heat,Weapons

23

R

F23R 3/50 (2006.01) F01D 25/12 (2006.01) F02C 7/12 (2006.01) F23R 3/06 (2006.01) F23R 3/54 (2006.01)

Patent

CA 2470928

The invention relates to a turbomachine annular combustion chamber (1) comprising an outer axial wall (2), an inner axial wall (4), and a chamber bottom end (8) connecting the said walls, the chamber bottom end being provided with several passages (34,36,72) enabling initiation of a cooling air film (D2) along the hot inner surface (30) of the outer axial wall and initiation of a cooling air film (D1) along the hot inner surface (32) of the inner axial wall, the outer axial wall and the inner axial wall being multi-perforated roughly over their full length in order to enable reinforcement of the cooling air films. According to the invention, the outer axial wall and the inner axial wall are provided, in an upstream part, with a first zone (54,40) of perforations (38) formed such that cooling air is introduced inside the combustion chamber in reverse flow.

Cette invention traite d'une chambre de combustion annulaire de turbomachine (1) qui comprend les éléments qui suivent. Une paroi axiale extérieure (2); une paroi axiale intérieure (4); et une extrémité de bas de chambre (8) raccordant lesdites parois. L'extrémité de bas de chambre comprend plusieurs passages (34, 36, 72) qui permettent l'admission d'un film d'air de refroidissement (D2) le long de la surface intérieure chaude (30) de la paroi axiale extérieure, et l'admission d'un film d'air de refroidissement (D1) le long de la surface intérieure chaude (32) de la paroi axiale intérieure. La paroi axiale extérieure et la paroi axiale intérieure comportent des perforations multiples à peu près sur leur pleine longueur, afin de renforcer les films d'air de refroidissement. Selon cette invention, la paroi axiale extérieure et la paroi axiale intérieure comprennent, dans une partie amont, une première zone (54, 40) de perforations (38) faisant que l'air de refroidissement est insufflé à l'intérieur de la chambre de combustion en écoulement inversé.

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