A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle.

A clutch for a lift fan comprising at least one output shaft lug key positioned in a keyway of at least two output clutch plates and extending axially from one to the other of the two output clutch plates. The output shaft lug key couples the rotation of the output clutch plates to the rotation an output shaft and allows axial movement of the two output clutch plates relative the output shaft lug key. The output shaft has an outer radial surface and an oppositely disposed inner radial surface, and the inner surface of the output shaft lug key extends radially to the seat of the keyway.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an engine wing. This disclosure also relates to an airplane including an engine wing.

An exemplary convertible engine includes an engine housing forming a fan duct extending from a fan inlet to an exhaust; a fan positioned in the fan duct proximate the fan inlet; an engine core located in the fan duct aft of the fan, the engine core coupled to the fan by a fan shaft; a drive shaft mechanically coupled to the engine core and extending exterior of the engine housing; and a dedicated core inflow duct coupled to the core and having a core inlet to capture and direct air into the engine core. An inlet barrier filter may be located in the dedicated core inflow duct. The core inlet may be located inside of the fan duct or exterior to the fan duct. A gearbox may be operationally connected to the fan shaft and may be located inside of the fan duct.

The present vertical lift vehicle system can include a single internal combustion engine, a single propeller, and a plurality of small ducts. The small ducts can connect to a single main duct acting as a combustion chamber, wherein the combustion chamber combines air from the small ducts with propane, wherein when ignited the contents of the main duct produce added thrust to the vehicle as it exits the main duct.

An unducted thrust producing system has a rotating element with an axis of rotation and a stationary element. The rotating element includes a plurality of blades, and the stationary element has a plurality of vanes configured to impart a change in tangential velocity of the working fluid opposite to that imparted by the rotating element acted upon by the rotating element. The system includes an inlet forward of the rotating element and the stationary element.

Provided are flight control mechanisms, such as omnidirectional thrust mechanisms (OTMs), and methods of using such mechanisms. These mechanisms may be positioned in wings, tails, or other components of aircraft. A mechanism may comprise a center member and top and bottom panels. The center member may comprise two curved segments joint at a center edge. The top and bottom panels may be independently pivotable relative to the center member. At high speeds, the top panel and/or the bottom panel may be pivoted outward to change the lift, drag, roll, and/or other flight conditions. The mechanism may also include a gas nozzle to direct compressed gas to the center member. The center member and/or the top and bottom panels redirect this gas resulting in forces in one of four directions, which are used for controlling the aircraft at low speeds, down to hover.

A regulator device for automatically regulating a power plant of a rotary wing aircraft having a turbine engine includes a computer system. The computer system, while implementation of an idling mode of operation of the turbine engine is requested and the aircraft is standing on ground, implements the idling mode of operation and operates the turbine engine in compliance with idling mode of operation as a function of operational and hierarchically ordered conditions either through a first mode of regulation by regulating a speed of rotation (Ng) of a gas generator of the turbine engine or through a second mode of regulation by regulating a speed of rotation (NTL) of a free turbine of the turbine engine.

An exemplary high-speed hybrid propulsion system for a tiltrotor aircraft includes two pivotal nacelles, each nacelle comprising an electric motor coupled to a proprotor; an electric aircraft system; an electric generator; an electrical bus electrically connected to the electric generator, the electric motors, and the electric aircraft system; and a convertible turbofan engine coupled to an electric generator through a drive shaft.

A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle.