Patent ID: 6406260
Filing Date: 2002-06-18
Classification: F01D,F05D,F28F

Abstract:
A coolable gas turbine engine airfoil structure having a leading edge, a leading edge internal cooling passage through which a cooling fluid is circulated to convectively cool the airfoil structure, and a heat transfer promotion structure provided within said leading edge internal cooling passage, said heat transfer promotion structure comprising a plurality of trip strips arranged to cause said cooling fluid to flow towards said leading edge in a pair of counter-rotating vortices, thereby promoting heat transfer at said leading edge, wherein the plurality of trip strips includes a first array of trip strips and a second array of trip strips, the first array being disposed generally farther from said leading edge than the second array, the trip strips of the second array being spaced closer to one another than the trip strips of the first array, and wherein the height of the trip strips of the-first array is generally greater than the height of the trip strips of the second array.