| 摘要 |
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).
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