| 摘要 |
The invention relates to a blade for a turbine engine propeller, comprising: a blade body (15A) solidly connected to a blade root (15B); and at least one flow channel (19) for a hot gas flow (F), which channel extends along the length of the leading edge (15C) thereof. The invention is characterised in that it comprises an end part (20) that at least partially surrounds the upstream edge (15D) of the blade body (15A), such that the flow channel (19) is disposed between the upstream edge of the body and said part, along the length of the blade body from the blade root. |
