Patent ID: 9157329
Filing Date: 2015-10-13
Classification: F01D,F05D,Y02T

Abstract:
1. An airfoil for a gas turbine engine comprising: spaced apart pressure and suction walls at leading and trailing edges to provide an airfoil, intermediate walls interconnecting the pressure and suction walls to provide cooling passageways, the cooling passagways having interior pressure and suction surfaces respectively provided on the pressure and suction walls; and trip strips including a chevron-shaped trip strip that is provided on at least one of the interior pressure and suction surfaces, wherein the airfoil includes first, second and third span regions extending along a span that extends in the radial direction from 0% span near the platform to 100% span near the tip, the first span region extending 0-20% the span +/−5%, the second span region extending 20-60% the span +/−5%, and the third span region extending 60-100% the span +/−5%, wherein the first, second and third span regions have different average P/E ratios, wherein P is a pitch of the trip strips, and E is a height of the trip strip with respect to a support surface of the trip strip.