Abstract: Hybrid turbine airfoil components containing a ceramic material, in which detailed features of the components are formed of materials other than ceramic materials. The components include a first component formed of a ceramic-based material and a second component formed of a metallic material. The first component comprises an airfoil portion and a nub, and the second component is separately formed and attached to the first component by casting the metallic material around the nub of the first component. The second component includes a platform portion between the airfoil portion and the nub of the first component and a dovetail portion on the nub of the first component. Each of the platform and dovetail portions has at least one off-axis geometric feature that results in the second component having a more complex geometry than the first component.

Abstract: A ceramic shroud assembly includes a tip shroud having an outer platform supporting at least one seal tooth, a shroud cap less brittle than the outer platform and including a shroud cap base on the outer platform, and clockwise and counter-clockwise facing clockwise and counter-clockwise contact surfaces located at clockwise and counter-clockwise distal ends respectively of the base. A rotor assembly may include a circumferential row of turbine blades made of a ceramic material and extending radially outwardly from a disk of a turbine rotor. The turbine blades include airfoils having the airfoil tip shrouds and the shroud caps at blade tips. The clockwise and counter-clockwise contact surfaces of circumferentially adjacent ones of the shroud caps contact each other. The shroud and the platform may be made of a ceramic or ceramic matrix composite material and the shroud cap may be made of a metallic material.

Abstract: A hybrid turbine airfoil component containing a ceramic material, in which detailed features of the component are formed of materials other than ceramic materials, yet result in a robust mechanical attachment of the ceramic and non-ceramic portions of the component. The component includes a first subcomponent formed of a ceramic-based material, and a second subcomponent formed of a metallic material. The first subcomponent has an airfoil portion and a nub, and the second subcomponent is separately formed and attached to the first subcomponent by casting the metallic material around the nub of the first subcomponent. The second subcomponent includes a blade tip shroud portion having at least one off-axis geometric feature that results in the second subcomponent having a more complex geometry than the first subcomponent.

Abstract: Hybrid components containing a ceramic material, in which detailed features of the components are formed of materials other than ceramic materials, yet result in a robust mechanical attachment of the ceramic and non-ceramic portions of the components. The components includes a first subcomponent formed of a ceramic-based material and a second subcomponent formed of a metallic material. The first subcomponent has a nub and the second subcomponent is separately formed and attached to the first subcomponent by casting the metallic material around the nub of the first subcomponent. The second subcomponent is attached to the first subcomponent by a compression fit and encapsulation of the second subcomponent on the nub of the first subcomponent. The nub has a compliant coating system that provides thermal expansion compliance between the metallic material of the second subcomponent and the ceramic-based material of the first subcomponent.

Abstract: Processes for producing a component containing a ceramic-based material and having detailed features formed from materials other than ceramic materials. Such a process entails producing the component to include a first subcomponent and at least a second subcomponent having at least one off-axis geometric feature that results in the second subcomponent having a more complex geometry than the first subcomponent. The first subcomponent is formed of a ceramic-based material, and the second subcomponent and its off-axis geometric feature are separately formed of a metallic material and attached to the first subcomponent to yield a robust mechanical attachment. The component may be, for example, a gas turbine airfoil component.

Abstract: A ceramic shroud assembly includes a tip shroud having an outer platform supporting at least one seal tooth, a shroud cap less brittle than the outer platform and including a shroud cap base on the outer platform, and clockwise and counter-clockwise facing clockwise and counter-clockwise contact surfaces located at clockwise and counter-clockwise distal ends respectively of the base. A rotor assembly may include a circumferential row of turbine blades made of a ceramic material and extending radially outwardly from a disk of a turbine rotor. The turbine blades include airfoils having the airfoil tip shrouds and the shroud caps at blade tips. The clockwise and counter-clockwise contact surfaces of circumferentially adjacent ones of the shroud caps contact each other. The shroud and the platform may be made of a ceramic or ceramic matrix composite material and the shroud cap may be made of a metallic material.

Abstract: Hybrid components containing a ceramic material, in which detailed features of the components are formed of materials other than ceramic materials, yet result in a robust mechanical attachment of the ceramic and non-ceramic portions of the components. The components includes a first subcomponent formed of a ceramic-based material and a second subcomponent formed of a metallic material. The first subcomponent has a nub and the second subcomponent is separately formed and attached to the first subcomponent by casting the metallic material around the nub of the first subcomponent. The second subcomponent is attached to the first subcomponent by a compression fit and encapsulation of the second subcomponent on the nub of the first subcomponent. The nub has a compliant coating system that provides thermal expansion compliance between the metallic material of the second subcomponent and the ceramic-based material of the first subcomponent.

Abstract: Processes for producing a component containing a ceramic-based material and having detailed features formed from materials other than ceramic materials. Such a process entails producing the component to include a first subcomponent and at least a second subcomponent having at least one off-axis geometric feature that results in the second subcomponent having a more complex geometry than the first subcomponent. The first subcomponent is formed of a ceramic-based material, and the second subcomponent and its off-axis geometric feature are separately formed of a metallic material and attached to the first subcomponent to yield a robust mechanical attachment. The component may be, for example, a gas turbine airfoil component.

Abstract: A hybrid turbine airfoil component containing a ceramic material, in which detailed features of the component are formed of materials other than ceramic materials, yet result in a robust mechanical attachment of the ceramic and non-ceramic portions of the component. The component includes a first subcomponent formed of a ceramic-based material, and a second subcomponent formed of a metallic material. The first subcomponent has an airfoil portion and a nub, and the second subcomponent is separately formed and attached to the first subcomponent by casting the metallic material around the nub of the first subcomponent. The second subcomponent includes a blade tip shroud portion having at least one off-axis geometric feature that results in the second subcomponent having a more complex geometry than the first subcomponent.

Abstract: Hybrid turbine airfoil components containing a ceramic material, in which detailed features of the components are formed of materials other than ceramic materials. The components include a first component formed of a ceramic-based material and a second component formed of a metallic material. The first component comprises an airfoil portion and a nub, and the second component is separately formed and attached to the first component by casting the metallic material around the nub of the first component. The second component includes a platform portion between the airfoil portion and the nub of the first component and a dovetail portion on the nub of the first component. Each of the platform and dovetail portions has at least one off-axis geometric feature that results in the second component having a more complex geometry than the first component.

Abstract: A rotor blade may include a tip shroud having at least one seal tooth disposed at an angle that may be relative to the engine centerline when in an assembled condition, the leading edge of the tip shroud and/or the trailing edge of the tip shroud.

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.

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.

Abstract: A turbine nozzle includes segments of outer and inner bands supporting corresponding vane pairs. The bands adjoin each other at corresponding ends along splitlines, with each band having a forward land, an opposite aft land, and a middle land extending therebetween. The forward lands have a nominal aft-facing step, the aft lands have a nominal forward-facing step and the middle lands are nominally flush.

Abstract: A turbine nozzle includes segments of outer and inner bands supporting corresponding vane pairs. The bands adjoin each other at corresponding ends along splitlines, with each band having a forward land, an opposite aft land, and a middle land extending therebetween. The forward lands have a nominal aft-facing step, the aft lands have a nominal forward-facing step and the middle lands are nominally flush.

Abstract: The present invention provides a method of repairing a turbine nozzle segment having one or more vanes disposed between outer and inner bands. The method includes separating at least one of the outer and inner bands from the vanes. The vanes are cut through in close proximity to the band being replaced. A newly manufactured replacement band including protruding vane stubs is provided for each one of the original bands being replaced. The replacement band is attached to the vanes by welding.

Abstract: An airfoil for a gas turbine engine, the airfoil having a core body with an airfoil body, an integral partial height squealer tip, and an integral tip cap between the airfoil body and the integral partial height squealer tip; and a squealer tip extension bonded to the partial height squealer tip. A method for manufacture and repair of an airfoil.

Abstract: A gas turbine engine includes a blade including a leading edge, a trailing edge, a first sidewall extending in radial span between a blade root and blade tip, and a second sidewall connected to the first sidewall at the leading edge and at the trailing edge. The first and second sidewalls each include an outer surface and an inner surface. A cooling cavity is defined by the first sidewall inner surface and the second sidewall inner surface. At least a portion of the cooling cavity is coated with an oxidation resistant environmental coating that has a thickness less than 0.0015 inches.

Abstract: An airfoil for a gas turbine engine, the airfoil having a core body with an airfoil body, an integral partial height squealer tip, and an integral tip cap between the airfoil body and the integral partial height squealer tip; and a squealer tip extension bonded to the partial height squealer tip. A method for manufacture and repair of an airfoil.

Abstract: A gas turbine engine includes a blade including a leading edge, a trailing edge, a first sidewall extending in radial span between a blade root and blade tip, and a second sidewall connected to the first sidewall at the leading edge and at the trailing edge. The first and second sidewalls each include an outer surface and an inner surface. A cooling cavity is defined by the first sidewall inner surface and the second sidewall inner surface. At least a portion of the cooling cavity is coated with an oxidation resistant environmental coating that has a thickness less than 0.0015 inches.