Abstract: A blade includes an airfoil section and a root section that extends in a chord-wise direction between leading and trailing root faces and in a radial direction that is perpendicular to the chord-wise direction from an inner root face to the second end of the airfoil section. The root section defines a dovetail cross-section that is perpendicular to the chord-wise direction. The airfoil section and the root section are comprised of a composite material architecture that includes inter-section fiber plies that each extend from the leading to the trailing edge and from the airfoil section into the root section. Wedges extend in the root section and are interleaved with the inter-section fiber plies. Each of the wedges tapers in the chord-wise direction and the radial direction.

Abstract: A method of manufacturing composite blades comprises: laying up a pre-impregnated composite material to form a pre-impregnated composite structure; vacuum bagging the pre-impregnated composite structure between a first pressure plate and a second pressure plate; consolidating and curing the pre-impregnated composite structure to form a fiber-reinforced composite structure; and machining an overlap portion of the fiber-reinforced composite structure to form a first fiber-reinforced composite blade and a second fiber-reinforced composite blade.

Abstract: A platform for an airfoil in a gas turbine engine is provided. The platform includes a top wall configured to connect to an airfoil of the gas turbine engine, a connector configured to receive a pin and secure the platform to a rotor of the gas turbine engine, and a sidewall extending from the top wall to the connector, the sidewall having a first arm and a second arm, wherein the first arm and the second arm are curved such at a bowed sidewall extends from the top wall to the connector.

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 platform for an airfoil in a gas turbine engine is provided. The platform includes a top wall configured to connect to an airfoil of the gas turbine engine, two sidewalls extending downward from the top wall a connector attached to and connecting the two sidewalls, wherein the top wall, the sidewalls, and the connector define an interior volume of the platform, and a single stiffener extending from the connector to the top wall within the interior volume between the two sidewalls. The connector defines two parallel apertures passing through the connector.

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, a fan section for a gas turbine engine, and a method for assembling a fan section of a gas turbine engine are disclosed. The fan section may include a fan hub having a slot, a spinner having a castellated spinner seal, a fan blade including an airfoil extending from a root to a tip, wherein the airfoil has a leading edge and the root is received in the slot, and a platform secured to the fan hub and arranged between adjacent fan blades. The fan section may further include a flap seal having a base secured to a side of the platform, and a flap integral with and extending from the base portion and canted toward the root and engaging the blade, the seal trimmed back from the leading edge of the airfoil.

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 platform for an airfoil in a gas turbine engine is provided. The platform includes a top wall configured to connect to an airfoil of the gas turbine engine, two sidewalls extending downward from the top wall a connector attached to and connecting the two sidewalls, wherein the top wall, the sidewalls, and the connector define an interior volume of the platform, and a single stiffener extending from the connector to the top wall within the interior volume between the two sidewalls. The connector defines two parallel apertures passing through the connector.

Abstract: A platform for an airfoil in a gas turbine engine is provided. The platform includes a top wall configured to connect to an airfoil of the gas turbine engine, a connector configured to receive a pin and secure the platform to a rotor of the gas turbine engine, and a sidewall extending from the top wall to the connector, the sidewall having a first arm and a second arm, wherein the first arm and the second arm are curved such at a bowed sidewall extends from the top wall to the connector.

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, a fan section for a gas turbine engine, and a method for assembling a fan section of a gas turbine engine are disclosed. The fan section may include a fan hub having a slot, a spinner having a castellated spinner seal, a fan blade including an airfoil extending from a root to a tip, wherein the airfoil has a leading edge and the root is received in the slot, and a platform secured to the fan hub and arranged between adjacent fan blades. The fan section may further include a flap seal having a base secured to a side of the platform, and a flap integral with and extending from the base portion and canted toward the root and engaging the blade, the seal trimmed back from the leading edge of the airfoil.

Abstract: A fan section for a gas turbine engine includes a fan blade having an airfoil with an exterior surface. A platform seal is adhered to the airfoil. A fan section for a gas turbine engine includes a fan hub having a slot. A fan blade includes an airfoil extending from a root to a tip. The root is received in the slot. A platform is secured to the fan hub and is arranged between adjacent fan blades. A seal has a base secured to opposing sides of the fan blade and a flap integral with and extending from the base portion and canted toward the root and engaging the platform to provide a sealed inner flow path.

Abstract: An electrical connector includes an electrically insulating body having a base mating surface and a stepped mating surface offset from the base mating surface. The electrical connector either has first and second electrically conducting pins extending from the base and stepped mating surfaces, respectively, or has first and second electrically conducting sockets extending from an interior portion of the electrically insulating body to the base and stepped mating surfaces, respectively.