Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete airfoil shape.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete airfoil shape.

Abstract: A turbine or compressor blade assembly includes a blade fixed to a dovetail section attachable to a wheel. The dovetail section has a dovetail shaped to fit in a correspondingly shaped slot in the wheel. A dovetail platform serves as an interface between the blade and the dovetail. An undercut fillet radius is formed at an intersection of the dovetail platform and a dovetail pressure surface, where the undercut radius has a multi-part profile shape configured to attenuate edge of contact stresses. An additional feature is the area where the undercut radius transitions into the P-cut area at the forward end (leading edge) of the dovetail.

Abstract: A turbine or compressor blade assembly includes a blade fixed to a dovetail section attachable to a wheel. The dovetail section has a dovetail shaped to fit in a correspondingly shaped slot in the wheel. A dovetail platform serves as an interface between the blade and the dovetail. An undercut fillet radius is formed at an intersection of the dovetail platform and a dovetail pressure surface, where the undercut radius has a multi-part profile shape configured to attenuate edge of contact stresses. An additional feature is the area where the undercut radius transitions into the P-cut area at the forward end (leading edge) of the dovetail.

Abstract: A gas turbine engine fan blade includes an airfoil and dovetail having an integral aluminum core and a fatigue resistant reinforcing sheath.

Abstract: A blade assembly, which may have blisk for a gas turbine engine, includes an annular rim disposed about a rotor axis and a blade assembly disposed around the rim. The blade assembly has circumferentially disposed and radially extending inner and outer rows of inner and outer airfoils, respectively and each airfoil has axially spaced apart leading and trailing airfoil edges. An annular shroud is disposed between and connecting the inner and outer rows of inner and outer airfoils and has axially spaced apart annular leading and trailing shroud edges corresponding to the leading and trailing airfoil edges, respectively. An axially extending cavity is provided in each of the leading and trailing shroud edges for reducing stresses in leading and trailing airfoil edges, respectively and the corresponding airfoil edges are located near the cavities. The cavities preferably extend axially under the corresponding airfoil edges.

Abstract: The present invention provides a composite airfoil, particularly useful as a wide chord fan blade having a high degree of twist in a large high bypass ratio turbofan engine. The composite airfoil of the present invention has a reinforced region of its airfoil that extends a portion of its span from its tip and a portion of its chord from its trailing edge. The region is covered by thin metallic sheathing bonded to trailing edge surfaces of the blade in a manner to reinforce that portion of the composite blade.

Abstract: A fan blade includes a spar having first and second opposite sides. The spar sides include a fatigue-life enhanced surface layer, with the spar first side having a cavity bounded in part by the surface layer. A skin closes the cavity and is bonded to the spar for maintaining the enhanced surface layer inside the cavity.