A system for providing active flow control in an aircraft having a gas turbine engine. The system includes an environmental control system that includes a cabin blower system having a compressor operable to compress a fluid delivered by a fan section of the gas turbine engine to generate a pressurised fluid for use by the environmental control system. The environmental control system is fluidicly connected to an active flow control system via a fluid supply line, for allowing the pressurised fluid generated by the compressor to be supplied to the active flow control system so that it can be ejected from the aircraft across an exterior surface of a movable control element of the aircraft.

A leading-edge device for an aircraft, the device comprising a flow body having a front skin, a back skin, a spar and an air inlet. The front skin is curved around a spanwise axis to form a bottom section and a top section.

A leading edge of the flow body is arranged between the bottom section and the top section. The spar extends from the bottom section to the top section. The front skin, the back skin and the spar enclose at least one air chamber that is in fluid communication with the air inlet. An outlet portion is arranged at least directly adjacent to the bottom section of the front skin. The outlet portion comprises a plurality of air outlets for letting air from the at least one air chamber exhaust through the air outlets.

An aircraft includes an environmental control system having a bleed air inlet, a gas turbine engine having a low pressure bleed air supply and a high pressure bleed air supply, and a turbo air cycle machine. The turbo air cycle machine includes a compressor fluidly coupled to the low pressure bleed air supply, as well as a turbine fluidly coupled to at least one of the low pressure bleed air supply or the high pressure bleed air supply.

A thermal management system for a gas turbine engine includes a primary vapor compression system including a primary evaporator defining thermal communication between a primary refrigerant and a flow of fuel to cool the fuel. A boost vapor compression system includes a boost heat exchanger defining thermal communication between the primary refrigerant. A boost refrigerant cools the primary refrigerant and a boost condenser in thermal communication with an air stream cools the boost refrigerant.

An aircraft propulsion system including a turbojet and a heat exchanger system including a main heat exchanger, a hot air supply pipe and a regulating valve, a first pipe bleeding high pressure stage hot air through a first valve, a second pipe bleeding intermediate pressure stage hot air through a second valve, a transfer pipe transferring the hot air to an air management system, a main supply pipe supplying cold fan duct air via a main regulating valve, an evacuation pipe expelling air to the outside, a sub heat exchanger, wherein the first pipe goes through the sub heat exchanger, a sub supply pipe supplying cold fan duct air and including a sub regulating valve, a sub evacuation pipe expelling air to the fan duct, a temperature sensor measuring a hot air temperature exiting the main heat exchanger, and a controller controlling the valves according to the measured temperature.

Apparatus and methods for providing air to pneumatic loads such as an environmental control system for a passenger cabin of an aircraft or an ice protection device of the aircraft are disclosed. In one embodiment, the apparatus comprises: a compressor configured to produce a first quantity of compressed air onboard the aircraft; and a heat exchanger configured to facilitate heat transfer from the first quantity of compressed air to a quantity of cooling air. The heat exchanger can be operatively connected to supply the cooled first quantity of compressed air to a cabin of the aircraft and supply the heated quantity of cooling air to an ice protection device of the aircraft. In some embodiments, the apparatus and methods disclosed herein can reduce or eliminate the need for the extraction of compressed bleed air from an engine of the aircraft.

An aircraft propulsion system including a turbojet and heat exchanger system including a heat exchanger. A supply connection and evacuation connection are forward, and aft are a transfer connection and a scoop connection, a supply pipe connected to the supply connection, and which bleeds hot air from the compression stages. A transfer pipe connected to the transfer connection transfers hot air to an air management system. A scoop connected to a scoop connection bleeds cold air from a fan duct and an evacuation pipe, including an inlet connected to the evacuation connection and an outlet, which emerges on the outside, where hot air through the heat exchanger from the supply pipe to the transfer pipe passes along a first transfer direction and cold air passes through the heat exchanger from each scoop to the inlet along a second transfer direction parallel to the first transfer direction in the opposite direction.

An aircraft fuel system can include a fuel line configured to transport fuel therein, an exposed aircraft structure in direct or indirect thermal communication with the fuel in the fuel line to receive heat from the fuel to provide a deicing or anti-icing heat to the exposed aircraft structure. The exposed aircraft structure can include at least one internal fuel channel in fluid communication with the fuel line for direct thermal communication with the fuel. The system can include a fuel/fluid heat exchanger in fluid communication with the fuel line to transfer heat from the fuel to a fluid to provide indirect thermal communication between the fuel and the exposed aircraft structure.

A manifold assembly configured for integration with a joint cover apparatus in a ducting system to detect leaking gas comprises an elastomeric manifold block having a substantially circular inlet aperture and one or more gas passages fluidly coupled to the inlet aperture. The assembly includes a flow control valve configured to maintain a closed state in which a component of the flow control valve sealingly engages with the inlet aperture to preclude gas at the inlet aperture from flowing into the one or more gas passages until said gas reaches a pressure corresponding to a pressure threshold. The assembly also includes at least one aperture control plate disposed substantially proximate to a lower end of the manifold block and including a substantially circular opening. The aperture control plate is adapted to maintain the substantial circularity of the inlet aperture, so as to ensure a substantially fluid-tight seal.

A vane assembly for distribution of a stratified fluid in an aircraft is taught herein. The vane assembly includes a housing including a housing inlet and a housing outlet. The housing inlet is configured to receive the stratified fluid with the stratified fluid including a first portion and a second portion. The housing outlet is configured to exhaust the stratified fluid. The housing defines an interior housing volume between the housing inlet and the housing outlet. The vane assembly further includes a vane disposed within the interior housing volume and bisecting the interior housing volume. The vane includes a leading edge adjacent the housing inlet and a trailing edge adjacent the housing outlet. The trailing edge is angularly offset from the leading edge.