| 摘要 |
A gas turbine engine component (2), especially an aerofoil-sectioned nozzle guide vane (NGV), having at least one internal cooling chamber (130F) for passage therethrough of cooling air, the said chamber (103F) including a leading edge portion (80) and at least one inlet portion (90) via which cooling air may enter the chamber (103F) from a feed source (130a, 130b),
wherein the component (2) comprises a partitioning element (100), e.g. a curved or scoop-shaped partitioning plate or wall, provided in at least the chamber inlet portion (90) and defining within at least the inlet portion (90) a sub-chamber (150) adjacent the leading edge portion (80),
and wherein the partitioning element (100) is configured such that the cooling air velocity in the sub-chamber (150) is less than the cooling air velocity in the remainder (160) of the inlet portion (90). The reduction in velocity of the cooling air in the sub-chamber (150) adjacent the leading edge serves to increase the pressure therein, thereby maintaining a desired backflow pressure margin between the feed pressure of the cooling air delivered to the showerhead holes (20) and the gas-path from the combustor. Thus ingestion of hot gas into the component (NGV) can be better assured, leading e.g. to improved engine performance. |
