Abstract: A method for orienting cooling holes of a nozzle singlet for a turbine engine is provided. The method includes providing a nozzle singlet having an inner band, an outer band, and at least one airfoil extending therebetween. The method also includes orienting at least one first row of cooling holes an angle with respect to at least one second row of cooling holes. The orientation of the at least one first row and the at least one second row provides a cooling hole pattern that accommodates a change in the airfoil angle without reorienting the cooling hole pattern.

Abstract: A method for orienting cooling holes of a nozzle singlet for a turbine engine is provided. The method includes providing a nozzle singlet having an inner band, an outer band, and at least one airfoil extending therebetween. The method also includes orienting at least one first row of cooling holes an angle with respect to at least one second row of cooling holes. The orientation of the at least one first row and the at least one second row provides a cooling hole pattern that accommodates a change in the airfoil angle without reorienting the cooling hole pattern.

Abstract: A method is provided for making, from a plurality of members brazed together, an article including an environmental resistant surface coating and a wear resistant surface portion. Prior to brazing, the members are assembled with at least one preform including the wear resistant material in a matrix including a first brazing alloy having a brazing temperature in a brazing temperature range. The assembly of members includes a second brazing alloy having a brazing temperature in the brazing temperature range. The assembly of members and wear resistant preform is heated in the brazing temperature range to provide a brazed article preform. Then the article preform is machined to a selected geometry and can be coated with the environmental coating.

Abstract: A gas turbine engine arcuate segment has an arcuate band segment, at least one tab and an arcuate rail segment spaced axially apart from the tab and located along an axial end of the band segment. The tab and the arcuate rail segment extend radially away from the band segment and a space is located between the tab and the rail segment. A tab aperture extends entirely through the tab. The rail segment has a rail aperture entirely therethrough. A leaf seal and a spring are disposed within the space to bias the leaf seal against the aft rail. In an exemplary embodiment, a spring aperture extends entirely through the spring, a seal aperture extends entirely through the leaf seal, and a headless pin is disposed in the apertures such that the leaf seal and the spring are radially restrained by the pin.

Abstract: A turbine nozzle includes outer and inner bands between which extend a plurality of vanes for channeling combustion gases. Each of the vanes includes leading and trailing edges, and pressure and suction sides extending therebetween, and also a bow along the trailing edge to increase pressure in the gases adjacent the inner band. The vanes also include a thermal barrier coating (TBC) selectively disposed solely along the suction side between the leading and trailing edges.

Abstract: A turbine nozzle includes outer and inner bands between which extend a plurality of vanes for channeling combustion gases. Each of the vanes includes leading and trailing edges, and pressure and suction sides extending therebetween, and also a bow along the trailing edge to increase pressure in the gases adjacent the inner band. The vanes also include a thermal barrier coating (TBC) selectively disposed solely along the suction side between the leading and trailing edges.

Abstract: A method of forming a thermal barrier coating system on an article subjected to a hostile thermal environment, such as the hot gas path components of a gas turbine engine. The coating system is generally composed of a ceramic layer and preferably a bond coat that adheres the ceramic layer to the component surface. Surface features such as grooves are cast directly into the surface of the component. If the bond coat is present, the grooves in the component surface cause the bond coat to also have grooves that generally correspond to the grooves in the component surface.

Abstract: A turbine engine vane segment, including spaced apart band or platform members and at least one airfoil member carried at metallic bonds between the platform members, is improved by providing at least one, but not necessarily all, of the segment members as an improved member having a directionally oriented Ni base superalloy microstructure with a stress rupture strength greater than the stress rupture strength of the balance of the segment members, which have a conventional generally equiaxed microstructure. For example, the balance of the members are conventionally cast from a Co base alloy. The coefficient of thermal expansion of the improved member is different from that of the balance of the members. A metallic bond including a brazed structure is provided between the improved member and the balance of the members, possessing strength sufficient to carry the stresses caused by differences in coefficients of thermal expansion of the dissimilar materials.