Abstract: A process for manufacturing a composite rotor blade includes manufacturing an oversized root region of a root region of a composite rotor blade; fixturing the CMC blade into a machining fixture at a primary Y and Z axis datum located at an attachment fillet radii of the root region; machining V-notches into the oversized root region to form a Y? and Z? axis datum of a sacrificial datum system in relation to the primary Y and Z axis datum; applying an oversized coating layer over the attachment fillet radii of the root region; fixturing the CMC blade into a machining fixture at the Y? and Z? axis datum of the sacrificial datum system; machining the oversized coating layer to a machined coating layer forming a Y? and Z? axis datum with respect to the Y? and Z? axis datum of the sacrificial datum system; fixturing the CMC blade into a machining fixture at the Y? and Z? axis datum; and machining off the sacrificial datum system removing the V-notches.

Abstract: A turbine airfoil includes a body that has inner and outer platforms and an airfoil section that extends between the inner and outer platforms. There are film cooling holes that define external breakout points from the body. The external breakout points are located in accordance with Cartesian coordinates of at least points 222 through 256 set forth in Table 1 herein.

Abstract: A process for manufacturing a composite rotor blade includes manufacturing an oversized root region of a root region of a composite rotor blade; fixturing the CMC blade into a machining fixture at a primary Y and Z axis datum located at an attachment fillet radii of the root region; machining V-notches into the oversized root region to form a Y? and Z? axis datum of a sacrificial datum system in relation to the primary Y and Z axis datum; applying an oversized coating layer over the attachment fillet radii of the root region; fixturing the CMC blade into a machining fixture at the Y? and Z? axis datum of the sacrificial datum system; machining the oversized coating layer to a machined coating layer forming a Y? and Z? axis datum with respect to the Y? and Z? axis datum of the sacrificial datum system; fixturing the CMC blade into a machining fixture at the Y? and Z? axis datum; and machining off the sacrificial datum system removing the V-notches.

Abstract: A component for a gas turbine engine includes at least one cooled surface configured to contact a cooling flow, the at least one cooled surface has a base surface and a plurality of cooling nubs disposed about the base surface. The plurality of cooling nubs are distributed about the base surface in a mixed pattern.

Abstract: An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms. A variable fillet merges a facing surface of one of the radially inner and outer platforms into a wall of the airfoil. The variable fillet has a length extending away from a surface of the airfoil and a height extending away from the facing surface of at least one of the radially inner and outer platforms outwardly on to the airfoil. The variable fillet has a greater length at one of the leading edge and the trailing edge. A spaced portion has a shorter length at locations spaced from at least one of the leading and trailing edges. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract: A component for a gas turbine engine includes at least one cooled surface configured to contact a cooling flow, the at least one cooled surface has a base surface and a plurality of cooling nubs disposed about the base surface. The plurality of cooling nubs are distributed about the base surface in a mixed pattern.

Abstract: A seal assembly arrangement for a gas turbine engine includes first and second non-rotating structures respectively that provide first and second faces. A sealing assembly includes first and second sealing rings respectively that engage the first and second faces. The first and second sealing rings slideably engage one another at a sliding wedge interface.

Abstract: An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms. A variable fillet merges a facing surface of one of the radially inner and outer platforms into a wall of the airfoil. The variable fillet has a length extending away from a surface of the airfoil and a height extending away from the facing surface of at least one of the radially inner and outer platforms outwardly on to the airfoil. The variable fillet has a greater length at one of the leading edge and the trailing edge. A spaced portion has a shorter length at locations spaced from at least one of the leading and trailing edges. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract: An investment casting core combination includes a metallic casting core and a ceramic feedcore. A first region of the metallic casting core is embedded in the ceramic feedcore. A mating edge portion of the metallic casting core includes a number of projections. The first region is along at least some of the projections. A number of recesses span gaps between adjacent projections. The ceramic feedcore includes a number of compartments respectively receiving the metallic casting core projections. The ceramic feedcore further includes a number of portions between the compartments and respectively received in the metallic casting core recesses.

Abstract: An investment casting core combination includes a metallic casting core and a ceramic feedcore. A first region of the metallic casting core is embedded in the ceramic feedcore. A mating edge portion of the metallic casting core includes a number of projections. The first region is along at least some of the projections. A number of recesses span gaps between adjacent projections. The ceramic feedcore includes a number of compartments respectively receiving the metallic casting core projections. The ceramic feedcore further includes a number of portions between the compartments and respectively received in the metallic casting core recesses.

Abstract: In a gas turbine engine, a stress relief is formed along a blade root and disk slot junction. An exemplary relief is a chamfer along the pressure side of the blade root extending forward from the aft face of the root.

Abstract: A computer-implemented method for verifying geometries of airfoils includes the steps of providing a part having an airfoil having an intended positional geometry and an intended feature geometry; measuring a first set of points of a primary datum system; determining an actual positional geometry of the airfoil based on the primary datum system measurements; calculating a first deviation between the intended positional geometry and the actual positional geometry of the airfoil; measuring a plurality of sets of points of at least one secondary datum system; determining an actual feature geometry of the airfoil based on the at least one secondary datum system measurement; calculating a second deviation between the intended feature geometry and the actual feature geometry of the airfoil; and performing a verification of the intended positional geometry and the intended feature geometry of the airfoil based upon the first deviation and the second deviation.

Abstract: A computer-implemented method for verifying geometries of airfoils includes the steps of providing a part having an airfoil having an intended positional geometry and an intended feature geometry; measuring a first set of points of a primary datum system; determining an actual positional geometry of the airfoil based on the primary datum system measurements; calculating a first deviation between the intended positional geometry and the actual positional geometry of the airfoil; measuring a plurality of sets of points of at least one secondary datum system; determining an actual feature geometry of the airfoil based on the at least one secondary datum system measurement; calculating a second deviation between the intended feature geometry and the actual feature geometry of the airfoil; and performing a verification of the intended positional geometry and the intended feature geometry of the airfoil based upon the first deviation and the second deviation.