Abstract: A method of manufacturing a composite guide vane with a metallic leading edge includes receiving a layup of fiber-reinforced composite sheets of continuous, substantially parallel and non-interlaced fibers impregnated with a resin. A vane body is formed from the layup of sheets. The vane body includes a body mid portion for interacting with a fluid and a body end portion. The method includes applying a metallic sheath on part of the vane body. The metallic sheath defines a leading edge of the guide vane. The method includes overmolding a head or a foot of the guide vane onto part of the vane body and onto part of the metallic sheath.

Abstract: A method of manufacturing a composite guide vane with a metallic leading edge includes receiving a layup of fiber-reinforced composite sheets of continuous, substantially parallel and non-interlaced fibers impregnated with a resin. A vane body is formed from the layup of sheets. The vane body includes a body mid portion for interacting with a fluid and a body end portion. The method includes applying a metallic sheath on part of the vane body. The metallic sheath defines a leading edge of the guide vane. The method includes overmolding a head or a foot of the guide vane onto part of the vane body and onto part of the metallic sheath.

Abstract: A method of manufacturing a composite guide vane with a metallic leading edge includes receiving a layup of fiber-reinforced composite sheets of continuous, substantially parallel and non-interlaced fibers impregnated with a resin. A vane body is formed from the layup of sheets. The vane body includes a body mid portion for interacting with a fluid and a body end portion. The method includes applying a metallic sheath on part of the vane body. The metallic sheath defines a leading edge of the guide vane. The method includes overmolding a head or a foot of the guide vane onto part of the vane body and onto part of the metallic sheath.

Abstract: A method of manufacturing a composite guide vane with a metallic leading edge includes receiving a layup of fiber-reinforced composite sheets of continuous, substantially parallel and non-interlaced fibers impregnated with a resin. A vane body is formed from the layup of sheets. The vane body includes a body mid portion for interacting with a fluid and a body end portion. The method includes applying a metallic sheath on part of the vane body. The metallic sheath defines a leading edge of the guide vane. The method includes overmolding a head or a foot of the guide vane onto part of the vane body and onto part of the metallic sheath.

Abstract: A method of manufacturing a composite guide vane with a metallic leading edge includes receiving a layup of fiber-reinforced composite sheets of continuous, substantially parallel and non-interlaced fibers impregnated with a resin. A vane body is formed from the layup of sheets. The vane body includes a body mid portion for interacting with a fluid and a body end portion. The method includes applying a metallic sheath on part of the vane body. The metallic sheath defines a leading edge of the guide vane. The method includes overmolding a head or a foot of the guide vane onto part of the vane body and onto part of the metallic sheath.

Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

Abstract: There is disclosed a shroud for a compressor stator, including: shroud segments extending circumferentially around an axis along portions of a circumference of the shroud. At least one of the shroud segments extending from a first lateral edge to a second lateral edge. The shroud segment has an inner face oriented toward the axis and an opposed outer face oriented away from the axis. At least one opening extends from the inner face to the outer face for receiving a vane of the compressor. A tab protrudes circumferentially from the second lateral edge and away from the first lateral edge. A slot extends circumferentially from the first lateral edge toward the second lateral edge. The tab is matingly received within a slot of an adjacent one of the shroud segments.

Abstract: A gas turbine engine assembly comprises a casing defining a gas path, the casing including a shroud having an annular body having a surface defining a portion of gas path, the shroud having slots configured for receiving inserted vanes. The slots are delimited substantially about their perimeter by respective flanges, the flanges radially offset from the shroud gas path surface so as to be disposed outside of said gas path, the flanges defined by opposed flange surfaces. Vanes received in the slots. Grommets engage the vanes at the slots. Inserts extend between the shroud and the grommets, the inserts having slots configured for engaging both of the opposed flanges, the inserts extending in a radial direction from at least the respective flange to an adjacent said shroud gas path surface to substantially matchingly mate with an inner surface the adjacent shroud gas path surface.

Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

Abstract: A gas turbine engine assembly comprises a casing defining a gas path, the casing including a shroud having an annular body having a surface defining a portion of gas path, the shroud having slots configured for receiving inserted vanes. The slots are delimited substantially about their perimeter by respective flanges, the flanges radially offset from the shroud gas path surface so as to be disposed outside of said gas path, the flanges defined by opposed flange surfaces. Vanes received in the slots. Grommets engage the vanes at the slots. Inserts extend between the shroud and the grommets, the inserts having slots configured for engaging both of the opposed flanges, the inserts extending in a radial direction from at least the respective flange to an adjacent said shroud gas path surface to substantially matchingly mate with an inner surface the adjacent shroud gas path surface.

Abstract: There is disclosed a shroud for a compressor stator, including: shroud segments extending circumferentially around an axis along portions of a circumference of the shroud. At least one of the shroud segments extending from a first lateral edge to a second lateral edge. The shroud segment has an inner face oriented toward the axis and an opposed outer face oriented away from the axis. At least one opening extends from the inner face to the outer face for receiving a vane of the compressor. A tab protrudes circumferentially from the second lateral edge and away from the first lateral edge. A slot extends circumferentially from the first lateral edge toward the second lateral edge. The tab is matingly received within a slot of an adjacent one of the shroud segments.

Abstract: A method of applying a nanocrystalline metal coating to a titanium or titanium alloy blade of a gas turbine engine is described. The method includes selecting an intermediate bond coat from the group consisting of nickel, nickel alloy, P, B, Tl and combinations thereof, and applying the intermediate bond coat to at least a portion of the blade. A nanocrystalline metal coating having an average grain size of between 10 nm and 500 nm is then applied to the portion of the blade overtop of the intermediate bond coat.

Abstract: A fan blade of a gas turbine engine is disclosed which is composed of an airfoil having a leading edge and a trailing edge, and a root with a platform and a blade fixing for engaging a fan hub. The fan blade is composed of a core substrate selected from the group consisting of composites and polymers, and an entirety of the airfoil and the root of the fan blade has a nanocrystalline metal outer layer thereon which forms an outer surface fully enveloping the fan blade. The nanocrystalline metal layer formed of a nanocrystalline metal coating has an average grain size of between 10 nm and 500 nm, and the nanocrystalline metal outer layer forms a structural element of the fan blade.

Abstract: The gas turbine engine vane assembly has a vane having an elongated airfoil body extending to a tip and a grommet disposed around the tip. An insert having a closed loop shape with an inner surface matingly shaped to receive the outer surface of the grommet, and an outer surface matingly shaped to be snugly received in the slot. A method of mounting such a vane assembly is also disclosed.

Abstract: A fan rotor for a gas turbine engine has a fan hub mounted for rotation about a central axis of the engine. A plurality of fan blades are circumferentially distributed about a radially outer surface of an outer rim section of the fan hub. The outer rim section is connected to an inner rim section through an axially facing web section. The web section extends from the outer rim section at a location axially aft of the center of gravity of the fan blades. A ridge formation extends radially inwardly from the outer rim axially forward of the web section.

Abstract: A fan blade of a gas turbine engine, and a method of producing same, is disclosed which is composed of a core substrate and a nanocrystalline metal coating provided on at least a portion of the airfoil of the fan blade. The method includes the steps of providing a fan blade core having an airfoil and then applying a nanocrystalline metal coating over at least a portion of the fan blade core.

Abstract: A fan blade of a gas turbine engine is disclosed which is composed of an airfoil having a leading edge and a trailing edge, and a root with a platform and a blade fixing for engaging a fan hub. The fan blade is composed of a core substrate selected from the group consisting of composites and polymers, and an entirety of the airfoil and the root of the fan blade has a nanocrystalline metal outer layer thereon which forms an outer surface fully enveloping the fan blade. The nanocrystalline metal layer formed of a nanocrystalline metal coating has an average grain size of between 10 nm and 500 nm, and the nanocrystalline metal outer layer forms a structural element of the fan blade.

Abstract: An airfoil blade of a gas turbine engine includes a root configured for mating attachment with a cooperating rotor hub and an airfoil extending away from the root. The root is composed of a first metal and has a nanocrystalline metal coating, composed of a second metal, over at least a portion thereof. A method of protecting such a blade by applying a nanocrystalline metal coating to a portion of the blade root is also disclosed.

Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.