Gas turbine stator vanes

摘要

The invention provides a method of achieving improved cooling of a stator vane in a gas turbine engine comprising the steps of: determining for a desired stator vane location a gas flow pressure gradient in the gas flow facing said stator vane in use, including said gradient's magnitude and position relative to said stator vane; and providing at said position a stator vane having a hollow airfoil, having a leading edge and a trailing edge; a high pressure chamber, disposed within said hollow airfoil, adjacent said leading edge; a standard pressure chamber, disposed within said hollow airfoil, adjacent said leading edge; a supply chamber, disposed within said hollow airfoil, aft of said high and standard pressure chambers, and forward of said trailing edge for receiving cooling air; a plurality of first inlet apertures, extending between said high pressure chamber and said supply chamber, said first inlet apertures having a first cross-sectional area; a plurality of second inlet apertures, extending between said standard pressure chamber and said supply chamber, said second inlet apertures having a second cross-sectional area; a plurality of first exit apertures, extending from said high pressure chamber to outside of said airfoil, each having a third cross-sectional area; and a plurality of second exit apertures, extending from said standard pressure chamber to outside of said airfoil, each having a fourth cross-sectional area; said high pressure chamber along said leading edge being positioned to oppose a high pressure region in said gas flow pressure gradient; and said first and second inlet and exit apertures being such that pressure in said high pressure chamber is greater than pressure in said standard pressure chamber for a given pressure in said supply chamber.