A turbine engine blade having an aerodynamic surface extending a first direction between a leading edge and a trailing edge and in a second direction, perpendicular to the first direction, between a root of the blade and a tip of the blade, the aerodynamic surface being made of a fiber-reinforced organic matrix composite material, and a metallic structural reinforcement bonded by an adhesive joint to the leading edge whose shape it follows and which has over its entire height a substantially V-shaped section with a base extended by two lateral flanks having a thinned profile at free ends directed toward the trailing edge, the adhesive joint being locally supplemented below the free ends of the lateral flanks by an elastomeric polymer introduced in the form of solid particles into the adhesive joint and adhered to the aerodynamic surface and/or the free ends of the lateral flanks during a polymerization phase.

A fan platform for gas turbine engine is provided. The fan platform incudes a body portion and a flow path surface coupled to the body portion. The body portion and the flow path surface define at least a portion of a flow path extending through the engine. The body portion and/or the flow path surface include an impact region including hybrid composite plies including one or more metallic tows. A gas turbine engine including the fan platform and methods for forming the fan platform are also disclosed.

A method for treating a surface of a contoured titanium substrate used for adhesively bonded engine components. The method including applying energy from a fiber laser system to a contoured surface of a titanium substrate, the laser energy is distributed to the contoured titanium surface by at least one of direct light of sight, reflection, or scattering of one or more laser beam.

An engine bi-material joint includes a first flange composed of a first material and defining a first coefficient of thermal expansion, and a second flange composed of a second material and defining a second coefficient of thermal expansion. The second flange is different from the first material. An interface flange is engaged with the first flange and with the second flange. The interface flange defines a third coefficient of thermal expansion being equal to or less than the first coefficient of thermal expansion of the first flange. The third coefficient of thermal expansion is less than the second coefficient of thermal expansion of the second flange. The first coefficient of thermal expansion of the first flange is less than the second coefficient of thermal expansion of the second flange.

A blade has an attachment root and an airfoil, the airfoil having a proximal end and a distal end. The blade has a compositional variation along the airfoil.

A method for forming a blade for a gas turbine engine may include forming a suction side sheath and a pressure side sheath, a first cavity and a second cavity established on opposed sides of a rib, forming a structural core configured for positioning in an interior section of the blade between the suction side sheath and the pressure side sheath, the structural core including a first core member, a second core member and a root interconnecting the first and second core members, assembling the suction side sheath and the pressure side sheath with the structural core such that the first core member is positioned in the first cavity and such that the second core member is positioned in the second cavity, and securing the suction side sheath to the pressure side sheath to form the blade.

A compression ring for a shrouded compressor including a radially inner surface having one or more areas configured to mate flush with one or more portions of a radially outward surface of a shroud of the shrouded compressor, a radially outer surface located opposite the radially inner surface, a labyrinth seal located on the radially outer surface, a groove located within the radially inner surface, and a load ring located within the groove.

A compressor assembly includes a compressor including a central shaft including an external surface, a shroud extending circumferentially around the central shaft. The shroud including a radially inward surface and radially outward surface located opposite the radially inward surface. The external surface of the central shaft and the radially inward surface of the shroud are in a facing spaced relationship forming a core flow path therebetween. The compressor also includes a plurality of blades extending from the central shaft to the shroud. The compressor assembly also includes a compression ring extending circumferentially around the shroud, the compression ring being in an interference fit with the shroud. The compression ring is configured to apply a radially inward compressive force along one or more portions of the radially outward surface of the shroud, the radially inward compressive is configured to compress the shroud and the plurality of blades into the central shaft.

An impeller for a centrifugal compressor, the impeller rotatable about a central axis, has: an outer hub body including a first material and extending around the central axis, the outer hub body defining a gaspath face extending from an inlet to an outlet, the gaspath face extending radially away from the central axis from the inlet to the outlet; blades protruding from the gaspath face and circumferentially distributed around the central axis; and an inner hub body extending around the central axis, the inner hub body secured to the outer hub body, the outer hub body axially overlapping and extending around the inner hub body, the inner hub body made of a second material being more cold dwell resistant than the first material.

A control ring for controlling discharge gates for an aircraft turbine engine extends around a casing of the turbine engine and includes a connector for connecting to the gates. The control ring includes metal sectors and composite material sectors. The metal sectors may be connected to one another by the composite material sectors and the connector may be carried by the metal sectors.