Abstract: An after-fan system for a gas turbine engine includes a variable pitch fan exit guide vane array. An after-fan turbine downstream of the variable pitch fan exit guide vane array and a control operable to vary a pitch of the variable fan exit guide vane array. A method of generating thrust for a gas turbine engine includes rotating a fan section with an array of fan blades; rotating an after-fan turbine downstream of the fan section; and varying a pitch of a variable fan exit guide vane array downstream of the fan section and upstream of the after-fan turbine.

Abstract: An after-fan system for an engine may comprise an after-fan turbine an electrical generator operationally coupled to the after-fan turbine, and an electric motor electrically coupled to the electrical generator. The electrical generator may be configured to generate an electrical current in response to rotation of the after-fan turbine. The electric motor may be configured to generate torque.

Abstract: An after-fan system for an engine may comprise an after-fan turbine an electrical generator operationally coupled to the after-fan turbine, and an electric motor electrically coupled to the electrical generator. The electrical generator may be configured to generate an electrical current in response to rotation of the after-fan turbine. The electric motor may be configured to generate torque.

Abstract: An after-fan system for an engine may comprise an after-fan turbine an electrical generator operationally coupled to the after-fan turbine, and an electric motor electrically coupled to the electrical generator. The electrical generator may be configured to generate an electrical current in response to rotation of the after-fan turbine. The electric motor may be configured to generate torque.

Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil has a leading edge and a trailing edge that define the true chord length. The airfoil includes a first portion near the airfoil base with a first density and a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction. The second portion is in the range of 90% span to 100% span.

Abstract: An after-fan system for a gas turbine engine includes a variable pitch fan exit guide vane array. An after-fan turbine downstream of the variable pitch fan exit guide vane array and a control operable to vary a pitch of the variable fan exit guide vane array. A method of generating thrust for a gas turbine engine includes rotating a fan section with an array of fan blades; rotating an after-fan turbine downstream of the fan section; and varying a pitch of a variable fan exit guide vane array downstream of the fan section and upstream of the after-fan turbine.

Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil has a leading edge and a trailing edge that define the true chord length. The airfoil includes a first portion near the airfoil base with a first density and a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction. The second portion is in the range of 90% span to 100% span.

Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil includes a first portion near the airfoil base with a first density and includes a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction.

Abstract: Airfoils are provided having a body having a leading edge, a trailing edge, a first end surface, and a second end surface opposite the first end surface, wherein (i) a first true chord length is a line extending from a first leading edge point to a first trailing edge point and (ii) a second true chord length is a line extending from a second leading edge point to a second trailing edge point, a first button located on the first end surface of the airfoil body, the first button having a first diameter and a first attachment device extending from the first button to enable rotation of the airfoil body about an attachment device axis. The first diameter is at least 15% of the first true chord length or the attachment device axis is located 10% of the first true chord length from the leading edge point.

Abstract: The present disclosure relates to gas turbine engines, and in particular high pressure turbine vane assemblies and combustor/turbine interface configurations. In one embodiment, a vane assembly includes a plurality of turbine vanes, an inner diameter platform, wherein the leading edge of the inner diameter platform is associated with a first axis, and an outer diameter platform, wherein the leading edge of the outer diameter platform is associated with a second axis. The second axis may be offset from the first axis such that the outer platform extends away from the leading edge of turbine vanes greater than the inner platform extends away from the leading edges. Another embodiment is directed to a gas turbine engine include a combustor and a turbine vane assembly, wherein an inner diameter platform and outer diameter platform of the vane assembly interface with the combustor.

Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil includes a first portion near the airfoil base with a first density and includes a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction.