The propulsion system have a load change detecting unit detecting a load change and an operating point control unit controlling power operating points defined using a torque T and a rotation number Ne. The operating point control unit calculates target power operating points 44 and 54 corresponding to the load after change for first power operating points 41 and 51 that are current power operating points in a case in which a change in the load is detected by the load change detecting unit. By changing the fuel flow in a range not exceeding a predetermined fuel line, the operating point control unit moves the power operating points from first power operating points 41 and 51 to second power operating points 42 and 52, third power operating points 43 and 53, and target power operating points 44 and 54 in order.

The propulsion system have a load change detecting unit detecting a load change and an operating point control unit controlling power operating points defined using a torque T and a rotation number Ne. The operating point control unit calculates target power operating points 44 and 54 corresponding to the load after change for first power operating points 41 and 51 that are current power operating points in a case in which a change in the load is detected by the load change detecting unit. By changing the fuel flow in a range not exceeding a predetermined fuel line, the operating point control unit moves the power operating points from first power operating points 41 and 51 to second power operating points 42 and 52, third power operating points 43 and 53, and target power operating points 44 and 54 in order.

A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle defining a duct, and a fan located within the duct. The fan comprises a hub arranged to rotate around a rotational axis and a plurality of blades attached to the hub, each of which has a span from a root at the hub defining a 0 percent span position (r.sub.hub) to a tip defining a 100 percent span position (r.sub.tip) and a plurality of span positions therebetween (r∈[r.sub.hub, r.sub.tip]). A plurality of outlet guide vanes are positioned aft of the fan. An afterbody is located aft of the plurality of outlet guide vanes and which tapers to an apex having an apex angle with respect to the rotational axis of between 35 and 45 degrees.

An aircraft propulsion system comprises a propulsor, a motor and a reduction gearbox coupled to a prime mover at an input side, and the propulsor at an output side. The reduction gearbox is configured to provide a reduction ratio between the input and output. The reduction gearbox is configured such that the input side rotates in an opposite direction to the output side, and the prime mover, motor, propulsor and reduction gearbox are configured such that gyroscopic forces of the propulsor, motor, prime mover and reduction gearbox generated during aircraft manoeuvres and/or propulsion system failures are substantially cancelled.

An aircraft propulsion system comprises a propulsor, a motor and a reduction gearbox coupled to a prime mover at an input side, and the propulsor at an output side. The reduction gearbox is configured to provide a reduction ratio between the input and output. The reduction gearbox is configured such that the input side rotates in an opposite direction to the output side, and the prime mover, motor, propulsor and reduction gearbox are configured such that gyroscopic forces of the propulsor, motor, prime mover and reduction gearbox generated during aircraft manoeuvres and/or propulsion system failures are substantially cancelled.

An assembly for mounting an aircraft engine to an aircraft includes an engine casing flange having a first annular wall extending radially to terminate at an annular rim. A second flange of an additional engine component mounted aft of the engine casing includes a second annular wall. An aft mount bracket has an annular body extending uninterrupted about the center axis and a spigot extending axially from the annular body, the spigot extending circumferentially about an entire circumference of the annular body. The aft mount bracket is axially disposed between the engine casing flange and the additional engine component, with corresponding holes in the first annular wall, second annular wall and aft mount bracket being circumferentially aligned, and the spigot radially abutting the annular rim of the engine casing flange.

A diffuser pipe has a tubular body defining a pipe center axis extending therethrough. The tubular body includes a first portion extending in a generally radial direction from an inlet of the tubular body, a second portion extending in a generally axial direction and terminating at a pipe outlet, and a bend portion fluidly linking the first portion and the second portion. The tubular body has a length defined between the inlet and the pipe outlet. The tubular body has cross-sectional profiles defined in a plane normal to the pipe center axis. An area of the cross-sectional profile at the pipe outlet is at least 20% greater than an area of the cross-sectional profile at a point upstream from the pipe outlet a distance corresponding to 10% of the length of the tubular body.

A diffuser pipe has a tubular body defining a pipe center axis extending therethrough. The tubular body includes a first portion extending in a generally radial direction from an inlet of the tubular body, a second portion extending in a generally axial direction and terminating at a pipe outlet, and a bend portion fluidly linking the first portion and the second portion. The tubular body has a length defined between the inlet and the pipe outlet. The tubular body has cross-sectional profiles defined in a plane normal to the pipe center axis. An area of the cross-sectional profile at the pipe outlet is at least 20% greater than an area of the cross-sectional profile at a point upstream from the pipe outlet a distance corresponding to 10% of the length of the tubular body.

A CO2 capture system includes an intake for CO2-rich exhaust gas to a compressor and one or more outlets for compressed, first CO2-rich gas to a manifold to a shell enclosing parts of a combustion chamber. The combustion chamber has burners to burn fuel and compressed air from a fuel line and an air supply pipe, to form a second, CO2 rich gas.

The wall in the combustion chamber has slits to let in the compressed CO2-rich gas to mix with and cool the other CO2-rich gas formed in the combustion chamber of a third CO2-rich exhaust gas. A heat exchanger operates under high pressure and heat exchanges the third, hot CO2-rich exhaust gas from the combustion chamber with returning CO2-poor exhaust gas from a CO2 extraction plant. The returned, heated CO2-poor exhaust gas is led back to an expander driving the compressor and the CO2 extraction plant.

A CO2 capture system includes an intake for CO2-rich exhaust gas to a compressor and one or more outlets for compressed, first CO2-rich gas to a manifold to a shell enclosing parts of a combustion chamber. The combustion chamber has burners to burn fuel and compressed air from a fuel line and an air supply pipe, to form a second, CO2 rich gas.

The wall in the combustion chamber has slits to let in the compressed CO2-rich gas to mix with and cool the other CO2-rich gas formed in the combustion chamber of a third CO2-rich exhaust gas. A heat exchanger operates under high pressure and heat exchanges the third, hot CO2-rich exhaust gas from the combustion chamber with returning CO2-poor exhaust gas from a CO2 extraction plant. The returned, heated CO2-poor exhaust gas is led back to an expander driving the compressor and the CO2 extraction plant.