A nosecone for a turbine engine includes a nosecone body and a nosecone mount. The nosecone body extends along an axis between a tip end and a base end. The nosecone body is configured from or otherwise includes thermoplastic material. The nosecone body includes a shell and an arrangement of ribs, which structurally support at least a portion of the shell. A thickness of the arrangement of ribs is greater than or substantially equal to approximately one half of a thickness of the shell. The nosecone mount is adapted to connect the nosecone body to a component of the turbine engine.

A single-unit nose cone for a ram air including: a dome portion located at a forward end of the single unit nose cone; a dome stand portion adjacent to the dome portion; a seat portion adjacent to the dome stand portion; and a stem portion adjacent to the seat portion and located at an aft end of the single-unit nose cone, wherein the dome portion, the dome stand portion, the seat portion, and the stem portion are composed from a single piece of material having a density of about 0.286 pound/cubic inch (7916 kilogram/cubic meter).

Disclosed is an assembly for a gas turbine engine, the assembly includes: a spinner or nosecone comprising a threaded rear portion, an engine structure comprising a threaded front portion, the nosecone being threadingly connected to the engine structure, wherein rotation of the spinner or nosecone about the engine structure in a first direction secures the spinner or nosecone to the engine structure and rotation of the spinner or nosecone about the engine structure in a second direction releases the spinner or nosecone from the engine structure; and a lock ring slidingly connected to the engine structure to slide between: a forward position to engage the spinner or nosecone and block rotation of the spinner or nosecone in the second direction, and a rearward position, where the lock ring is spaced from the spinner or nosecone.

Disclosed is an assembly for a gas turbine engine, the assembly includes: a spinner or nosecone comprising a threaded rear portion, an engine structure comprising a threaded front portion, the nosecone being threadingly connected to the engine structure, wherein rotation of the spinner or nosecone about the engine structure in a first direction secures the spinner or nosecone to the engine structure and rotation of the spinner or nosecone about the engine structure in a second direction releases the spinner or nosecone from the engine structure; and a lock ring slidingly connected to the engine structure to slide between: a forward position to engage the spinner or nosecone and block rotation of the spinner or nosecone in the second direction, and a rearward position, where the lock ring is spaced from the spinner or nosecone.

A tiltrotor controls shield having a blade or wire substructure under a fragile spinner fairing improves bird strike durability. The present disclosure discloses a spinner wind fairing with a shield structure disposed thereunder for providing protection to the proprotor assembly components. The shield structure can segment a projectile, such as a bird, that penetrates the spinner fairing into a series of smaller and lower energy elements spread across a wider area, such that the rotor components can withstand the impact of the smaller elements without damage.

A tiltrotor controls shield having a blade or wire substructure under a fragile spinner fairing improves bird strike durability. The present disclosure discloses a spinner wind fairing with a shield structure disposed thereunder for providing protection to the proprotor assembly components. The shield structure can segment a projectile, such as a bird, that penetrates the spinner fairing into a series of smaller and lower energy elements spread across a wider area, such that the rotor components can withstand the impact of the smaller elements without damage.

A propeller component, for example a propeller blade airfoil, includes an external surface exposed in use to an oncoming airstream (A), and a protective polymeric film applied over substantially the entire exposed external surface of the component.

A structure adapted to traverse a fluid environment includes an elongate body having a root, a wingtip, a leading edge and a trailing edge; and a rigid winglet associated with the wingtip and having a winglet body extending substantially normal to one of a suction side and a pressure side of the elongate body to a termination point that is rearward of the trailing edge. In an embodiment, the structure is a rotor blade that may be incorporated into a wind turbine.

A structure adapted to traverse a fluid environment includes an elongate body having a root, a wingtip, a leading edge and a trailing edge; and a rigid winglet associated with the wingtip and having a winglet body extending substantially normal to one of a suction side and a pressure side of the elongate body to a termination point that is rearward of the trailing edge. In an embodiment, the structure is a rotor blade that may be incorporated into a wind turbine.

A gas turbine engine including: a tail cone; a low pressure compressor; a low pressure turbine; a low speed spool interconnecting the low pressure compressor and the low pressure turbine; and an electric generator located within the tail cone, the electric generator being operably connected to the low speed spool; a structural support housing at least partially enclosing the electric generator, the structural support housing being located within the tail cone; and a temperature control device located within the tail cone between the structural support housing and the tail cone, wherein the temperature control device is in thermal communication with at least one of the structural support housing and the tail cone.