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.

Abstract: A fan blade platform is provided. The fan blade platform may include a wall, a first sidewall extending from the flowpath to a circular member, and a second sidewall extending from the flowpath to the circular member. A stiffening member may also extend from the circular member to the flowpath and be formed integrally with the first sidewall, the second sidewall, and the flowpath.

Abstract: A fan blade includes a tip assembly that is disposed on a blade body. The tip assembly has a leading edge wall disposed proximate a leading edge of the blade body, a trailing edge wall disposed proximate a trailing edge of the blade body, a suction side wall that extends between the leading edge wall and the trailing edge wall, a pressure side wall disposed opposite the suction side wall and extends between the leading edge wall and the trailing edge wall, and a tip wall that extends between the leading edge wall, the trailing edge wall, the suction side wall, and the pressure side wall and is disposed parallel to the tip.

Abstract: A spacer assembly for a rotor assembly of a gas turbine engine includes an endwall segment having a non-axisymmetric flowpath surface, a first depression and a second depression. A perimeter of the flowpath surface includes a forward edge, an aft edge, a suction side edge and a pressure side edge. The first depression is formed along the flowpath surface adjoining the suction side edge, and the second depression is formed along the flowpath surface adjoining the pressure side edge.

Abstract: A gas turbine engine impact liner is disclosed. The impact liner may include a base sheet, a plurality of stanchions extending from the base sheet, and a plurality of supports, each being operatively associated with one of the plurality of stanchions.

Abstract: A fan blade platform is provided. The fan blade platform may include a wall, a first sidewall extending from the flowpath to a circular member, and a second sidewall extending from the flowpath to the circular member. A stiffening member may also extend from the circular member to the flowpath and be formed integrally with the first sidewall, the second sidewall, and the flowpath.

Abstract: A fan assembly for a gas turbine engine is disclosed. The fan assembly may include a rotor, a plurality of airfoils extending radially from the rotor, and a platform surrounding the rotor and including a surface that defines a flow path between the plurality of airfoils. The platform may be configured to be disposable during a life of the gas turbine engine.

Abstract: Anti-rotation tabs for the platforms in the fan section of a gas turbine engine are provided. The anti-rotation tabs interface with the trailing edge of the spinner, thereby preventing the platform from rotating and twisting.

Abstract: A fan blade includes a tip assembly that is disposed on a blade body. The tip assembly has a leading edge wall disposed proximate a leading edge of the blade body, a trailing edge wall disposed proximate a trailing edge of the blade body, a suction side wall that extends between the leading edge wall and the trailing edge wall, a pressure side wall disposed opposite the suction side wall and extends between the leading edge wall and the trailing edge wall, and a tip wall that extends between the leading edge wall, the trailing edge wall, the suction side wall, and the pressure side wall and is disposed parallel to the tip.

Abstract: A fan blade platform is provided. The fan blade platform may include a wall, a first sidewall extending from the flowpath to a circular member, and a second sidewall extending from the flowpath to the circular member. A stiffening member may also extend from the circular member to the flowpath and be formed integrally with the first sidewall, the second sidewall, and the flowpath.

Abstract: A gas turbine engine includes a core engine, a fan coupled to be driven by the core engine, a first case structure around the core engine and a second case structure around the fan. The first case structure and the second case structure define a bypass passage there between. A vane structure includes an airfoil extending radially between the first case structure and the second case structure. A seal is configured to control leakage between the bypass passage and a core engine.

Abstract: A fan blade platform is provided. The fan blade platform may include a wall, a first sidewall extending from the flowpath to a circular member, and a second sidewall extending from the flowpath to the circular member. A stiffening member may also extend from the circular member to the flowpath and be formed integrally with the first sidewall, the second sidewall, and the flowpath.

Abstract: The present disclosure relates generally to the field of fan blade platforms for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber fan blade platform for a gas turbine engine.

Abstract: A gas turbine engine impact liner is disclosed. The impact liner may include a base sheet, a plurality of stanchions extending from the base sheet, and a plurality of supports, each being operatively associated with one of the plurality of stanchions.

Abstract: The present disclosure relates generally to the field of guide vanes for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber composite inlet guide vane for a gas turbine engine.

Abstract: A wall assembly includes a wall that extends axially along a centerline, and circumferentially at least partially around the centerline. The wall assembly also includes a plurality of mounting brackets arranged circumferentially around the centerline, and a plurality of wall brackets. Each of the mounting brackets includes a groove that extends axially into the respective mounting bracket. Each of the wall brackets includes a tongue and a base. The tongue extends axially from the base into the groove of a respective one of the mounting brackets. The base is connected to the wall.

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: The present disclosure relates generally to the field of guide vanes for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber structural guide vane for a gas turbine engine.

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.