According to the invention, a drive device for an aircraft is provided, which has a shaft turbine coupled to an impeller via a shaft. The impeller has an intake side and a thrust side. The shaft turbine is mounted in the area of the intake side of the impeller. The drive device is also designed for mounting externally on an aircraft fuselage and/or inside an aircraft fuselage and/or in a casing on a wing.

An inlet barrier filter system for a tiltrotor aircraft comprising a filter duct extending from a filter to a filter outlet, a ram air duct extending from a ram air inlet to an engine where the filter duct connects to the ram air duct at the filter outlet, and a closure member movable between a first position blocking the ram air duct and a second position blocking the filter outlet. In use, the inlet barrier filter system provides for two mutually exclusive air flow paths, one for introducing ram air to the engine while closing off the filter and another air flow path for introducing filtered air to the engine while closing off the ram air duct.

An aircraft intake duct for channeling a flow of ambient air toward an annular engine compressor inlet of a gas turbine engine having a compressor reference axis and a reference plane that extends from such compressor reference axis. The aircraft intake duct includes an oblong air intake inlet for receiving the flow of ambient air, the air intake inlet being offset radially outwardly relative to the compressor reference axis and located on a first side of the reference plane. Two distal intake channels fluidly link distal extremities of the oblong air intake inlet to a segment of the annular engine compressor inlet located on a second side of the reference plane. A central channel fluidly links a central section of the oblong air intake inlet to a segment of the annular engine compressor inlet located on a first side of the reference plane. The distal channels are blended together by the central channel so that a single intake duct is formed.

An aircraft includes a fuselage and an engine housed in the fuselage. A ram-air engine inlet is formed on an exterior of the fuselage. The ram-air engine inlet is defined, at least in part, by a cowling door. The cowling door is moveable between a closed position and an open position. An intake duct fluidly couples the ram-air engine inlet to the engine. A filter is disposed across the intake duct. A bypass duct is formed in the ram-air engine inlet aft of the intake duct. The bypass duct is operable to be selectively opened and closed.

A system and method of an airflow control system for a vehicle is described herein. The airflow control system (100) includes an airflow housing (120) defining an airflow passageway (125) extending between a bypass opening (122) and an intake outlet (124). The airflow housing also defines a duct opening (126) positioned between the bypass opening (122) and the intake outlet (124). The intake outlet (124) may be in fluid communication with an engine intake (12) of the vehicle such that air passes from the bypass opening (122) and/or the duct opening (126) to the engine intake (12). The airflow control system (100) also includes a movable duct (160) movably connected to the airflow housing (120) to selectively allow or prevent air passage through the duct opening (126) and into the engine intake (12), and further includes a bypass door (140) movably connected to the airflow housing (120) to selectively allow or prevent air passage through the bypass opening (122) and into the engine intake (12).

A turbine engine module including an upstream propulsive unit including a propellers doublet that are upstream and downstream, respectively mounted around an axis, a power turbine shaft with axis of rotation intended for rotating the propellers doublet, a speed reducer connected to the propellers doublet and driven by the shaft, and, a pitch-changing system including a cylinder that controls the pitch of the blades of the upstream propeller the rotational axis of the propellers doublet is shifted in relation to that of the shaft. The cylinder is placed downstream of the reducer, and the pitch-changing system includes a shaft for controlling the pitch of the blades that connect the cylinder to the blades of the upstream propeller.

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.

A turboprop engine system for an aircraft includes an engine, a propeller, and a gear train coupled to and configured to provide power from the engine to the propeller at a predetermined gear reduction. The engine system also includes a gearbox that houses at least part of the gear train. The gearbox includes a gearbox flow structure and an inlet flow structure that is removably attached to the gearbox. The inlet flow structure and the gearbox flow structure cooperate to define an inlet flow passage to the engine. The inlet flow passage has an upstream end and a downstream end that are cooperatively defined by the inlet flow structure and the gearbox flow structure. The upstream end is configured to receive an airstream that is directed along the inlet flow passage to the downstream end and toward the engine.

A system for delivering a flow stream of a gas to a compressor. A shroud extends from an inlet to the compressor and defines a main inlet passage configured to direct the flow stream from the inlet to the compressor. A communication plenum is separated from the main inlet passage. A port system includes first and second port subsystems that each provide an opening between the main inlet passage and the communication plenum. The first port subsystem is disposed further from the compressor than the second port subsystem. The port system is configured so that a portion of the gas enters or exits the compressor through the second port subsystem, depending on operating conditions of the compressor.

The invention relates to a torque limiting device in a torque bearing connecting structure between a gearbox and a stationary structure in a gas turbine engine, wherein the torque limiting device comprises a mechanical fuse in the connection structure comprising an at least partially circumferential weakening of the material. The invention also relates to a gas turbine engine.