INTERNAL COOLING OF ENGINE COMPONENTS

摘要

A gas turbine engine component, especially an aerofoil-sectioned nozzle guide vane (NGV), having at least one internal cooling chamber for passage of cooling air, the chamber including leading edge portion and one inlet portion via which cooling air may enter the chamber from feed source, wherein the component includes a partitioning element, e.g. curved or scoop-shaped partitioning plate or wall, provided in the chamber inlet portion and defining within the inlet portion a sub-chamber adjacent the leading edge portion, and wherein partitioning element is configured so the cooling air velocity in the sub-chamber is less than the cooling air velocity in the remainder of inlet portion. The reduced velocity of the cooling air in the sub-chamber adjacent the leading edge serves to increase pressure therein, thereby maintaining desired backflow pressure margin between the feed pressure of the cooling air delivered to the showerhead holes and the gas-path from the combustor.

主权项

1. A gas turbine engine component having at least one internal cooling chamber for passage therethrough of cooling air, the said chamber including a leading edge portion and at least one inlet portion via which cooling air may enter the chamber from a feed source,
wherein the component comprises a partitioning element present in the chamber inlet portion and extending to define a sub-chamber wholly or partly within the chamber which sub-chamber is bounded by the partitioning element and the leading edge portion, the sub-chamber having a sub-chamber inlet arranged to receive cooling air from the feed source and wherein the partitioning element is configured such that the cooling air velocity in the sub-chamber is less than the cooling air velocity in the remainder of the inlet portion.