Abstract: A high temperature repairable airfoil having a plurality of flow path cover tiles coupled to a single crystal spar member. In one embodiment, the plurality of flow path cover tiles include an attachment portion that is received within a groove formed in the outer surface of the spar. The attachment portion slides into a retaining feature within the groove so as to limit movement of the plurality of flow path cover tiles. Upon rotation of the airfoil, the plurality of flow path cover tiles become centrifugally loaded with a portion of the spar member. In one embodiment, the plurality of flow path cover tiles are formed of a material selected from the group consisting of ceramics, intermetallic, and thermal barrier coated single crystal alloy material.

Abstract: A high temperature repairable airfoil having a plurality of flow path cover tiles coupled to a single crystal spar member. In one embodiment, the plurality of flow path cover tiles include an attachment portion that is received within a groove formed in the outer surface of the spar. The attachment portion slides into a retaining feature within the groove so as to limit movement of the plurality of flow path cover tiles. Upon rotation of the airfoil, the plurality of flow path cover tiles become centrifugally loaded with a portion of the spar member. In one embodiment, the plurality of flow path cover tiles are formed of a material selected from the group consisting of ceramics, intermetallic, and thermal barrier coated single crystal alloy material.

Abstract: An actively cooled component having a plurality of film cooling discharge apertures passing through a heat transfer pedestal. In one embodiment the pedestal is elongated so as to provide good covered turning for the cooling media exiting the cooled component. In one embodiment the discharge aperture has a L/D ratio in the range of about two to three.

Abstract: A fabricated gas turbine engine component and method of manufacturing. In one embodiment the component having a structural member with a cover member metalurgically bonded thereto. The bonding of the cover member being controlled by an apparatus that sequentially applies a substantially non-unifrom bonding load across the components radius of curvature. The patterns utilized in the casting process are formed in one embodiment to a precision preformed geometry by a closed die forming operation.

Abstract: A fabricated gas turbine engine component and method of manufacturing. In one embodiment the component having a structural member with a cover member metalurgically bonded thereto. The bonding of the cover member being controlled by an apparatus that sequentially applies a substantially non-unifrom bonding load across the components radius of curvature. The patterns utilized in the casting process are formed in one embodiment to a precision preformed geometry by a closed die forming operation.

Abstract: A gas turbine engine vane and method of manufacture. In one form of the present invention a vane is non destructively removeable from a vane segment to allow individual components to be replaced. The vane and endwalls are coupled together by a retainer that is formed in place between the vane and the endwall and that can be removed by conventional techniques. In one form the retainer fills a pair of corresponding grooves in the vane and endwall member so as to mechanically couple the components together and minimize fluid leakage therebetween. The retainer being nonmetallurgically coupled to the vane and endwall member. A portion of the vane being allowed to move relative to the endwall in response to thermal conditions.

Abstract: A cooled wall structure including a hot side, a cold side, a linear slot opening through the hot side, a plurality of diffusion chambers below the hot side separated therefrom by relatively thin bridge sections of the wall structure and arrayed in checkerboard fashion on opposite sides of the linear slot and opening into the linear slot through the sidewalls thereof, and a plurality of passages from the cold side to each of the diffusion chambers. The cold side is exposed to coolant gas under pressure and the passages are aimed at the bridge sections so that jet of cooling gas issuing from the passages impinge against the bridge section for convection cooling the hot side. The bridge sections prevent direct penetration of the coolant gas jets into the environment adjacent the hot side. The coolant gas flows from the diffusion chambers into the linear slots and from the linear slots over the hot side to form on the latter a coolant film or blanket.