Abstract: A compliant seal assembly for a rotating machine is provided. The seal assembly includes a static member, a movable member and a biasing member. The static member is rigidly fixed to the machine at its fore and aft ends. The movable portion has a first sealing surface configured to seal against a rotating member and a rear surface, which may be exposed to a fluid pressure to urge the first sealing surface toward a sealing position with the rotating member. The static and the movable members further include sealing surfaces at their fore, aft and end faces to seal against leakage of gas between the static and the movable members. The biasing member is configured to support the movable member on the static member and to urge the movable member away from the sealing position so as to reduce force on the rotating member during contact of the rotating member with the first sealing surface of the movable member.

Abstract: A method enables a gas turbine engine blade to be manufactured to include an airfoil, a platform, a shank, and a dovetail. The platform extends between the airfoil and the shank, the shank extends between the dovetail and the platform, and the dovetail includes at least one tang for securing the blade within the engine. The method comprises defining a cooling cavity in the blade that extends through the airfoil, the platform, the shank, and the dovetail, such that a portion of the cavity defined within the dovetail includes a root passage portion having a first width, and a transition portion extending between the root passage and the portion of the cavity defined within the shank, and wherein the portion of the cavity defined within the shank has a second width that is larger than the root passage first width. The blade is then coated with an environmental resistive coating.