Thermal shield arrangement for gas turbine combustion chambers

Details Thermal shield arrangement for gas turbine combustion chambers Thermal shield arrangement for gas turbine combustion chambers

F - Mech Eng,Light,Heat,Weapons

23

R

F23R 3/10 (2006.01) F23R 3/06 (2006.01) F23R 3/28 (2006.01)

Patent

CA 2214691

In order to cool down as efficiently as possible the hot surface of the thermal shield (1) that surrounds the burner of a gas turbine ring-shaped combustion chamber, in particular in the area of the burner outlet (3), a cooling air flow (10) ejected in the direction of the outlet over a continuous web (8) at the edge of the outlet is guided by a guiding rib (9). The guiding rib (9) is substantially parallel to the web (8) and has at the side of the combustion chamber a bent end, so that the cooling air flow that enters the gap between the web and the guiding rib is deflected there towards the hot surface (2b) of the thermal shield (1).

Afin de refroidir aussi efficacement que possible la surface chaude de l'écran thermique (1) qui entoure le brûleur de la chambre de combustion annulaire d'une turbine à gaz, notamment dans la zone de l'orifice (3) du brûleur, un courant d'air de refroidissement (10), évacué en direction de l'orifice de passage par-dessus un élément jointif continu (8) situé au bord de l'orifice de passage, est guidé par une nervure de guidage (9) sensiblement parallèle à l'élément jointif (8). La nervure de guidage (9) comprend du côté de la chambre de combustion une extrémité coudée de sorte que le courant d'air de refroidissement qui pénètre entre l'élément jointif et la nervure de guidage soit dévié à cet endroit en direction de la surface chaude (2b) de l'écran thermique (1).

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