FIELD: aviation.
SUBSTANCE: aviation turbine blade (10) differs in that it contains at least first trough cavity (C2) and first back cavity (C3), each of which is located adjacent to first through cavity (C1) and to second through cavity (C4). In this case, first back cavity (C3) is adjacent to back wall (24), first trough cavity (C2) is adjacent to trough wall (22). At the same time, each of the specified first and second through cavities (C1, C4) passes from trough wall (22) to back wall (24). In this case, second through cavity (C4) contains first inner wall (P1) passing from back wall (24) to first through cavity (C1) and second inner wall (P2) passing from trough wall (22) to first through cavity (C1). At the same time, the specified first inner wall (P1) and second inner wall (P2) are separated from each other.
EFFECT: optimization of blade cooling is achieved.
6 cl, 3 dwg
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