Patent ID: 9476308
Filing Date: 2016-10-25
CPC Classification: F01D,F05D,Y02T

Claim Text:
1. A gas turbine engine component comprising: a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend; first and second trip strips respectively arranged in the upstream and downstream portion, wherein the first and second trip strips are chevron-shaped and each with an apex, the first trip strips include first apexes arranged at a first spacing from one another, and the second trip strips include second apexes arranged at a second spacing from one another; and a turbulence promoter is chevron-shaped with a third apex and is arranged in the bend at a third spacing from the third apex to the nearest first apex that is different than the first spacing, and the turbulence promoter arranged at a fourth spacing from the third apex to the nearest second apex that is different than the second spacing.