A lubrication system includes a reserve housing configured to retain a lubrication fluid. A supply line in fluid communication with the reserve housing is configured to provide pressurized lubrication fluid to the reserve housing. An overflow tube has an overflow port, the overflow tube being configured to prevent the volume of the lubrication fluid from exceeding a certain amount. A metering jet is configured to allow the lubrication fluid to flow from the reserve housing onto a component, such as a bearing, in the gearbox at a predetermined rate. The metering jet provides flow of the lubrication fluid onto the bearing even when the supply line no longer provides pressurized lubrication fluid to the reserve housing.

A propulsion system comprises a propeller and a driving device coupled with the propeller. The propeller comprises a hub having a receiving hole, a plurality of blades connected to the hub, and a connecting surface. The driving device comprises a body portion, an elastic abutting member disposed on the body portion and configured to abut against the connecting surface, and a lock portion disposed on the body portion and including a first snap-fitting portion. A second snap-fitting portion is arranged on an inner wall of the receiving hole and is configured to snap with the first snap-fitting portion.

The VTOL aircraft of the present invention has fixed-wings which can be monoplane, biplane or tri-plane and tiltable rotors on outriggers which extend from the fuselage and/or wings. The rotors on the outriggers can be driven by engines located in the fuselage or wings via a transmission system such as a shaft, pulley, or pressurized air using pumps. If rotors are driven by jets at the tips, fuel is fed through pipes inside of the outriggers. The rotors and engines can be located at the ends of the outriggers or the rotors may be separate from the engines and tilting only the rotors reduces structural requirements and weight of the aircraft. The rotors can be tilted over ninety degrees from the vertical position forwards and backwards, sideways if needed for lateral movement. The outriggers can be configured in various ways depending upon how many rotors are used and where the engines are located. Placing rotors on outriggers in the spaces least obstructed by the wings and fuselage reduces drag which increases efficiency and also offers a flexible platform for various hybrid designs.

In one embodiment, an apparatus comprises a thermal barrier configured to surround at least a portion of a driveshaft and to protect the driveshaft from heat. The thermal barrier comprises an inner wall forming a cavity in which the driveshaft lies, an outer wall enclosing the inner wall, and a space between the inner wall and the outer wall. The space is evacuated and forms a vacuum.

A bowed rotor prevention system for a gas turbine engine of an aircraft is provided. The bowed rotor prevention system includes a gear train and a bowed rotor prevention motor. The gear train is coupled through an engine accessory to an engine accessory gearbox that is further coupled to a starting spool of the engine. The bowed rotor prevention motor is operable to drive rotation of the starting spool of the gas turbine engine through the gear train upon engine shutdown.

A bowed rotor prevention system for a gas turbine engine of an aircraft is provided. The bowed rotor prevention system includes a gear train and a bowed rotor prevention motor. The gear train is coupled through an engine accessory to an engine accessory gearbox that is further coupled to a starting spool of the engine. The bowed rotor prevention motor is operable to drive rotation of the starting spool of the gas turbine engine through the gear train upon engine shutdown.

An apparatus and system for supporting a planetary carrier within an aircraft gearbox includes a retainer for engaging a rotor mast and for supporting the planetary carrier.

An in-line propeller gearbox of a turboprop gas turbine engine includes an epicyclic gearing arrangement that has a sun gear, a ring gear and at least one planet gear disposed between and meshing with both the sun gear and the ring gear. The propeller gearbox includes a disk brake that can be operated to slow down or stop altogether the rotation of the propeller. The disk brake has an axially extending shaft having at one end a disk and at the opposite end a gear having teeth that engage with one of the gears in the epicyclic gearing arrangement. The disk brake includes an hydraulic caliper or an electric caliper that can be actuated to slow down rotation of the disk to an eventual full stop and to hold the disk at full stop to thereby stop rotation of the propeller.

An aircraft is provided with a gas turbine engine having a plurality of shafts. A first shaft provides power to an electrical generator and a propeller, while a second shaft provides power to a refrigeration system. The refrigeration system may be integrated to the propeller, like a ducted fan, or on the outer skin of the aircraft.

An aircraft is provided with a gas turbine engine having a plurality of shafts. A first shaft provides power to an electrical generator and a propeller, while a second shaft provides power to a refrigeration system. The refrigeration system may be integrated to the propeller, like a ducted fan, or on the outer skin of the aircraft.