An aircraft defining a longitudinal direction and a lateral direction is provided. The aircraft includes: a fuselage; an engine mounted at a location spaced from the fuselage of the aircraft, the engine comprising a plurality of rotor blades; and a fuselage shield attached to or formed integrally with the fuselage at a location in alignment with the plurality of rotor blades along the lateral direction, the fuselage shield comprising a first layer defining a first density and a second layer defining a second density, the first density being different than the second density.

An axial turbine (100) with two supply levels for the expansion phase of a working fluid in a thermodynamic vapor cycle or in an organic Rankine cycle comprising a shaft (2), a plurality of rotor blade arrays (R1-Rn) and corresponding support disks (21, 22), a plurality of stator blade arrays (S1-Sn), further comprising a first inlet opening (5) and a second inlet opening (7′). The second volute (4) is positioned inside the first volute (3), the working fluid of the second supply level reaching upstream of a stator blade (S2,Sn) that is are immediately upstream of one of the rotor blade arrays that extends radially into both of the first and second supply levels.

A rotor blade is provided for a gas turbine engine. This rotor blade includes a rotor blade pair including a mount, a first airfoil and a second airfoil. The mount includes a forked body with a first leg and a second leg. The first airfoil is connected to the first leg. The second airfoil is connected to the second leg and arranged circumferentially next to the first airfoil.

Various embodiments of an airfoil and machines with airfoils are disclosed. The airfoils include a thicker leading airfoil portion and a thinner trailing airfoil portion. In one embodiment, the leading airfoil portion is formed by bending a body of the airfoil back toward itself. In another embodiment, the leading airfoil portion has a solid geometry and includes two elliptic surfaces. To prevent detachment of airflow, the leading airfoil portion includes at least two arc portions or surfaces that act to direct the airflow down to the trailing airfoil portion in a manner that stabilizes vortexes that may form in the region of changing thickness.

An airfoil assembly for a turbine engine comprising an outer band, an inner band radially spaced inwardly from the outer band to define an annular region, and multiple airfoils circumferentially spaced within the annular region. Each corresponding airfoil of the multiple airfoils can project from a surface at a root and can further include an outer wall defining a pressure side and a suction side. A projection can extend upwardly from the surface on the pressure side and a valley can extend into the surface on the suction side to define a contour in the surface.

A fluid machine has: first and second walls; a gaspath defined between the first wall and the second wall; a rotor having blades rotatable about the central axis; and a tandem having: a first row of first vanes having first airfoils including first leading edges, first trailing edges, first pressure sides and first suction sides opposed the first pressure sides, and a second row of second vanes downstream of the first vanes and having second airfoils including second leading edges, second trailing edges, second pressure sides and second suction sides opposed the second pressure sides, the first vanes being circumferentially offset from the second vanes; and depressions defined in the first wall, a depression of the depressions located circumferentially between a pressure side of the first pressure sides and a suction side of the second suction sides, the depressions axially overlapping the first airfoils and the second airfoils.

A propulsion system is provided including a first vane extended along the radial direction. The first vane is configured to rotate relative to a vane axis extended along the radial direction. A second vane is extended along the radial direction. The second vane is positioned aft along the axial direction of the first vane. The second vane forms an inlet opening proximate to a second vane leading edge, and the second vane forms an outlet opening proximate to a second vane trailing edge. The inlet opening and the outlet opening together allow a flow of fluid through the second vane. A heat exchanger is positioned within the second vane. The inlet opening and the outlet opening allow the flow of fluid in fluid communication with the heat exchanger.

A single unducted rotor engine includes a power source; a casing surrounding the power source; an unducted rotor assembly driven by the power source having a single row of rotor blades; and an outlet guide vane assembly having a plurality of pairs of outlet guide vanes, each pair of the plurality of pairs of outlet guide vanes including a first outlet guide vane extending from the casing at a location downstream from the single row of rotor blades of the unducted rotor assembly and a second outlet guide vane also positioned downstream from the single row of rotor blades of the unducted rotor assembly. The first outlet guide vane of each pair of outlet guide vanes defines a first geometry. The second outlet guide vane of each pair of outlet guide vanes defines a second geometry. The first geometry is not equal to the second geometry.

A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade. The tandem rotor disk apparatus may include two separate rotor disk bodies.

Axial turbine (100) with two supply levels for the expansion phase of a working fluid in a thermodynamic vapor cycle or in an organic Rankine cycle comprising a shaft (2), a plurality of rotor blade arrays (R1-Rn) and corresponding support disks (21, 22), a plurality of stator blade arrays (S1-Sn), further comprising a first inlet opening (5) and a second inlet opening (7′). The second volute (4) is positioned inside the first volute (3), the working fluid of the second supply level reaching upstream of a stator blade (S2, S3 . . . Sn) any subsequent to the first stage, and the vapor flow of the first supply level and that of the second supply level are conveyed so as to be substantially parallel to each other according to an axial direction upstream of a stator blade (S2, S3 . . . Sn).