| 摘要 |
This invention relates to a blade of a turbomachine, more particularly an axial-flow high-pressure turbine, having at least one integrated cooling air duct issuing at the downstream back of the blade root when viewed in the direction of the working gas conducted by the blade. This invention also relates to a rotor disk of a turbomachine having several blades designed in accordance with the present invention. The cooling air duct in accordance with this invention branches off from a cooling air chamber provided in the blade root, from which chamber a cooling air duct issuing at the surface of the blade conducting the working gas is supplied with cooling air, where the cooling air duct issuing at the back of the blade root deflects the cooling air flow through it and provides an essentially continuous passage. The cooling air-duct is preferably made to converge in the direction from the cooling air chamber toward its outlet port and is shaped in accordance with design rules for axial-flow reaction turbines. On a rotor disk of a turbomachine having several such blades, the cooling air duct can continue through a lock-plate that is provided at the back of the blades and attached to the rotor disk.
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