Abstract:
A blade outer air seal for a gas turbine engine includes a first side surface, a second side surface, and a wall. The wall extends between the first side surface and the second side surface and has one or more holes formed therein. The holes are spaced from the first side surface and/or the second side surface and have areas between about 0.005% and 0.450% of a surface area of the blade outer air seal.
Abstract:
An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a multiple of rotary ramps. Each of the multiple of rotary ramps is associated with one of the multiple of blade outer air seal assemblies. A method of active blade tip clearance control for a gas turbine engine is provided. The method includes rotating a multiple of rotary ramps to control a continuously adjustable radial position for each of a respective multiple of blade outer air seal assemblies.