Components for gas turbine engines and methods of making the same, the components including a component body having an external side wall and an internal side wall and defining at least a first cooling cavity and a second cooling cavity between the external side wall and the internal side wall, at least one segmented rib extending within the component body and separating the first cooling cavity from the second cooling cavity, wherein the first and second cooling cavities, the at least one segmented rib comprising at least two rib segments separated by a segment gap, and a discharge hole formed in the external side wall fluidly connected the segment gap to an exterior surface of the component body.

A method for manufacturing a titanium aluminide blade of a turbine engine, including production of a titanium aluminide ingot, extrusion of the ingot through an opening in a die having one main arm and at least one side arm, such as to obtain a extruded ingot having the shape of a bar with a cross-section having one main arm and at least one side arm substantially perpendicular to the main arm, transverse cutting of the extruded ingot such as to obtain sections of extruded ingot, forging of each section of extruded ingot such as to obtain a turbine engine blade.

A method for manufacturing a titanium aluminide blade of a turbine engine, including production of a titanium aluminide ingot, extrusion of the ingot through an opening in a die having one main arm and at least one side arm, such as to obtain a extruded ingot having the shape of a bar with a cross-section having one main arm and at least one side arm substantially perpendicular to the main arm, transverse cutting of the extruded ingot such as to obtain sections of extruded ingot, forging of each section of extruded ingot such as to obtain a turbine engine blade.

An airflow mask tool incudes a pressure side mask portion to seal at least a portion of a pressure side of a component having an array of internal passageways and a suction side mask portion to seal at least a portion of a suction side of the component, at least one of the suction side mask portion and the pressure side mask portion comprising at least one opening to expose at least one exit from the array of internal passageways.

An airflow mask tool incudes a pressure side mask portion to seal at least a portion of a pressure side of a component having an array of internal passageways and a suction side mask portion to seal at least a portion of a suction side of the component, at least one of the suction side mask portion and the pressure side mask portion comprising at least one opening to expose at least one exit from the array of internal passageways.

A method machines or tests a blade for a turbomachine. The method includes: clamping the blade in a clamp such that a point contact or a line contact forms between the blade and the clamp as clamping partners. One of the clamping partners has a lower strength than the other clamping partner and plasticizes in the region of the point contact or the line contact.

A method machines or tests a blade for a turbomachine. The method includes: clamping the blade in a clamp such that a point contact or a line contact forms between the blade and the clamp as clamping partners. One of the clamping partners has a lower strength than the other clamping partner and plasticizes in the region of the point contact or the line contact.

A turbine airfoil apparatus includes: an airfoil including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and at a trailing edge; an endwall that projects laterally outwardly from the airfoil at one spanwise end thereof, the endwall having an outer surface facing the airfoil and an opposing inner surface; a plenum defined within the endwall between the inner and outer surfaces wherein the plenum is forked in plan view, with at least two branches, each branch terminating at a closed end, each branch having a throat disposed at its upstream end, wherein each throat has a relatively constricted flow area for increasing flow velocity; and at least one film cooling hole passing through the outer surface and communicating with the plenum.

A turbine airfoil apparatus includes: an airfoil including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and at a trailing edge; an endwall that projects laterally outwardly from the airfoil at one spanwise end thereof, the endwall having an outer surface facing the airfoil and an opposing inner surface; a plenum defined within the endwall between the inner and outer surfaces wherein the plenum is forked in plan view, with at least two branches, each branch terminating at a closed end, each branch having a throat disposed at its upstream end, wherein each throat has a relatively constricted flow area for increasing flow velocity; and at least one film cooling hole passing through the outer surface and communicating with the plenum.

A method of additive manufacturing includes additively manufacturing a first section for a component, wherein the first section is provided with a position feature, additively manufacturing a second section for the component on the first section, and, in case that a build failure occurs during the additive manufacture of the second section, machining back a present buildup until the position feature is revealed, additively manufacturing the second section separately from the first section, thereby providing the second section with a corresponding position feature, and connecting the first section and the second section to provide the component.