Abstract: A guide vane assembly for a gas turbine engine includes: a strut having: a root, a tip, a leading edge, a trailing edge wall, and opposed sidewalls extending between the leading edge and the trailing edge wall; and a pair of spaced-apart prongs extending axially aft from the trailing edge wall, each prong having an outer wall that is flush with a respective one of the sidewalls; and a flap positioned axially aft of the strut, the flap having a root, a tip, a leading edge, a trailing edge, and opposed sides extending between the leading and trailing edge, wherein a portion of the leading edge is disposed between the prongs, and wherein a disk-like flap button is disposed at the tip of the flap adjacent its leading edge, the flap button including a pair of spaced-apart notches formed therein.

Abstract: An article made of constituent elements is prepared by furnishing at least one nonmetallic precursor compound, wherein all of the nonmetallic precursor compounds collectively contain the constituent elements. The constituent elements include a titanium-base metallic composition, boron present at a level greater than its room-temperature solid solubility limit, and, optionally, a stable-oxide-forming additive element present at a level greater than its room-temperature solid solubility limit. The precursor compounds are chemically reduced to produce a material comprising a titanium-base metallic composition having titanium boride particles therein, without melting the titanium-base metallic composition. The titanium-base metallic composition having the titanium boride particles therein is consolidated without melting.

Abstract: A FLADE fan assembly includes radially inner and outer airfoils extending radially inwardly and outwardly respectively from an annular shroud circumferentially disposed about a centerline. Inner and outer chords extend between inner and outer leading and trailing edges of inner and outer airfoil cross-sections of the radially inner and outer airfoils respectively. Inner and outer stagger angles between the inner and outer chords respectively at the shroud and the centerline are different. The radially outer airfoils may outnumber the radially inner airfoils and particularly by a ratio in a range of 1.5:1 to about 4:1. Load paths or radii may extend radially through the inner and outer airfoils and through the rotating shroud between the inner and outer airfoils and may pass near or through the inner and outer leading edges and through the inner and outer trailing edges.

Abstract: Including a disk, a plurality of circumferentially spaced apart airfoils extending radially outwardly from the disk, a plurality of shroud segments being disposed circumferentially between the plurality of airfoils and configured to attach to a corresponding airfoil of the plurality of airfoils and a plurality of wear surfaces, where at least one wear surface of the plurality of wear surfaces is configured and disposed to prevent excessive wear between the adjacent shroud segments. Each shroud segment of the plurality of shroud segments may be attached to a corresponding airfoil by weld connections to permit clearance during translation friction welding of the airfoil to the disk hub are located to avoid high stress areas.

Abstract: A FLADE fan assembly includes radially inner and outer airfoils extending radially inwardly and outwardly respectively from an annular shroud circumferentially disposed about a centerline. Inner and outer chords extend between inner and outer leading and trailing edges of inner and outer airfoil cross-sections of the radially inner and outer airfoils respectively. Inner and outer stagger angles between the inner and outer chords respectively at the shroud and the centerline are different. The radially outer airfoils may outnumber the radially inner airfoils and particularly by a ratio in a range of 1.5:1 to about 4:1. Load paths or radii may extend radially through the inner and outer airfoils and through the rotating shroud between the inner and outer airfoils and may pass near or through the inner and outer leading edges and through the inner and outer trailing edges.

Abstract: An article made of constituent elements is prepared by furnishing at least one nonmetallic precursor compound, wherein all of the nonmetallic precursor compounds collectively contain the constituent elements. The constituent elements include a titanium-base metallic composition, boron present at a level greater than its room-temperature solid solubility limit, and, optionally, a stable-oxide-forming additive element present at a level greater than its room-temperature solid solubility limit. The precursor compounds are chemically reduced to produce a material comprising a titanium-base metallic composition having titanium boride particles therein, without melting the titanium-base metallic composition. The titanium-base metallic composition having the titanium boride particles therein is consolidated without melting.

Abstract: An article made of constituent elements is prepared by furnishing at least one nonmetallic precursor compound, wherein all of the nonmetallic precursor compounds collectively contain the constituent elements. The constituent elements include a titanium-base metallic composition, boron present at a level greater than its room-temperature solid solubility limit, and, optionally, a stable-oxide-forming additive element present at a level greater than its room-temperature solid solubility limit. The precursor compounds are chemically reduced to produce a material comprising a titanium-base metallic composition having titanium boride particles therein, without melting the titanium-base metallic composition. The titanium-base metallic composition having the titanium boride particles therein is consolidated without melting.

Abstract: Including a disk, a plurality of circumferentially spaced apart airfoils extending radially outwardly from the disk, a plurality of shroud segments being disposed circumferentially between the plurality of airfoils and configured to attach to a corresponding airfoil of the plurality of airfoils and a plurality of wear surfaces, where at least one wear surface of the plurality of wear surfaces is configured and disposed to prevent excessive wear between the adjacent shroud segments. Each shroud segment of the plurality of shroud segments may be attached to a corresponding airfoil by weld connections to permit clearance during translation friction welding of the airfoil to the disk hub are located to avoid high stress areas.

Abstract: A method for assembling an articulated fan front frame for a gas turbine engine facilitates improving engine performance. The method includes forming a strut including a pair of sidewalls connected at a leading edge and a trailing edge, forming a flap including a first sidewall and a second sidewall connected at a leading edge and a trailing edge, and extending in radial span between a root endwall and a tip endwall, wherein each endwall extends between the first and second sidewalls, and wherein at least one of the root endwall and the tip endwall is contoured in a radial direction extending between the flap leading and trailing edges, and pivotally coupling the flap downstream from the strut such that a gap is defined between the flap and the strut.

Abstract: A method for assembling an articulated fan front frame for a gas turbine engine facilitates improving engine performance. The method includes forming a strut including a pair of sidewalls connected at a leading edge and a trailing edge, forming a flap including a first sidewall and a second sidewall connected at a leading edge and a trailing edge, and extending in radial span between a root endwall and a tip endwall, wherein each endwall extends between the first and second sidewalls, and wherein at least one of the root endwall and the tip endwall is contoured in a radial direction extending between the flap leading and trailing edges, and pivotally coupling the flap downstream from the strut such that a gap is defined between the flap and the strut.