United Technologies Corporation

Raytheon Technologies Corporation

Karl A Mentz

Michael G McCaffrey

Bryan P Dube

Steven D Porter

Mark John Rogers

James Tilsley Auxier

Ricardo Trindade

Bret M Teller

Allan N Arisi

John T Ols

Paul K Sanchez

Justin D Piggush

Richard M Salzillo

Christopher King

Richard H Page

Renee J Jurek

Richard N Allen

Jesse R Christophel

Christopher Cosher

Kevin J Ryan

Christine F McGinnis

Sandra S Pinero

Stephen D Doll

Aurelia Ledbetter

James Tisley Auxier

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&#x2032; 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&#x2032; and Z&#x2032; axis datum of the sacrificial datum system; machining the oversized coating layer to a machined coating layer forming a Y&#x2033; and Z&#x2033; axis datum with respect to the Y&#x2032; and Z&#x2032; axis datum of the sacrificial datum system; fixturing the CMC blade into a machining fixture at the Y&#x2033; and Z&#x2033; axis datum; and machining off the sacrificial datum system removing the V-notches.

Ceramic matrix composite rotor blade attachment and method of manufacture therefor

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.

Turbine airfoil having film cooling hole arrangement

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.

Turbine component including mixed cooling nub feature

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.

Turbine vanes with variable fillets

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.

Investment casting cores and methods

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.

System and method for verifying the dimensions of airfoils

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Reading, MA, United States of America

Karl A Mentz