An engine system has a gas generator, a bi-fi wall surrounding at least a portion of the gas generator, a casing surrounding a fan, and the casing having first and second thrust reverser doors which in a deployed position abut each other and the bi-fi wall.

A fan module for an aircraft turbine engine, this module comprising a fan and an electrical machine, such that the electrical machine is coaxially mounted downstream of the fan and comprises a rotor coupled to rotate with the fan and an annular member with generally C-shaped axial cross-section, the opening of which is axially orientated and receives the rotor, this member comprising a radially outer portion forming a stator, and a radially inner portion forming a support for bearings guiding the rotor.

A fan module for an aircraft turbine engine, this module comprising a fan and an electrical machine, such that the electrical machine is coaxially mounted downstream of the fan and comprises a rotor coupled to rotate with the fan and an annular member with generally C-shaped axial cross-section, the opening of which is axially orientated and receives the rotor, this member comprising a radially outer portion forming a stator, and a radially inner portion forming a support for bearings guiding the rotor.

An environmental control system (ECS) for use with a gas turbine engine has an air cycle system (ACS) and a vapor cycle system (VCS). The VCS has along a vapor compression flowpath: a VCS compressor; a heat donor leg of a VCS condenser; an expansion device; and a heat receiving leg of a VCS evaporator. The ACS has along a bleed flowpath: a bleed air inlet; a primary heat exchanger; an ACS compressor; a secondary heat exchanger; a turbine coupled to the ACS compressor to drive the ACS compressor; a heat donor leg of the VCS evaporator; a water collector; and a heat receiving leg of the VCS condenser.

A powerplant is provided that includes an engine and a water recovery system. The engine includes an engine combustor, an engine turbine, a flowpath and a fluid delivery system. The flowpath extends out of the engine combustor and through the engine turbine. The fluid delivery system includes a hydrogen reservoir and an oxygen reservoir. The hydrogen reservoir is configured to store fluid hydrogen as liquid hydrogen. The oxygen reservoir is configured to store fluid oxygen as liquid oxygen. The fluid delivery system is configured to provide the fluid hydrogen and the fluid oxygen for combustion within the engine combustor to produce combustion products within the flowpath. The water recovery system is configured to extract water from the combustion products. The water recovery system is configured to provide the water to a component of the powerplant.

A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for directing incoming objects towards an outer portion of the turbofan engine in communication with the inlet pre-swirl feature.

A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for directing incoming objects towards an outer portion of the turbofan engine in communication with the inlet pre-swirl feature.

A gas turbine engine defining an axial direction and a radial direction, the gas turbine engine including: a turbomachine; a fan rotatable by the turbomachine, the fan including a plurality of fan blades; a plurality of outlet guide vanes located downstream of the plurality of fan blades of the fan; a casing surrounding the plurality of fan blades or surrounding at least in part the turbomachine, the casing defining an opening at a location upstream of the plurality of outlet guide vanes; and a compressed airflow injection assembly positioned at least partially within the casing and configured to provide a flow of compressed airflow through the opening in a repeating pattern during an operating condition of the gas turbine engine.

A gas turbine engine defining an axial direction and a radial direction, the gas turbine engine including: a turbomachine; a fan rotatable by the turbomachine, the fan including a plurality of fan blades; a plurality of outlet guide vanes located downstream of the plurality of fan blades of the fan; a casing surrounding the plurality of fan blades or surrounding at least in part the turbomachine, the casing defining an opening at a location upstream of the plurality of outlet guide vanes; and a compressed airflow injection assembly positioned at least partially within the casing and configured to provide a flow of compressed airflow through the opening in a repeating pattern during an operating condition of the gas turbine engine.

The invention relates to a fan module having variable-pitch blades for a turbine engine, including a rotor (2) having blades (3), a stationary casing (7), and a system for adjusting and controlling the pitch of the blades (3), the rotor (2) including a central shaft (6) and a ring (9) for supporting the blades surrounding the shaft, a front end of the ring being connected to a front end of the shaft so as to define an annular space between the ring and the shaft which is open towards the rear, said annular space of the rotor (2) housing said system, and the shaft (6) being guided by a first bearing (8) mounted in the stationary casing (7), to the rear of the ring (9), characterised in that the ring (9) is guided by at least one complementary bearing (31) located upstream of the first bearing (8).