An air direction arrangement for an aircraft. The air direction arrangement contains an inlet opening and an inlet channel connected thereto and which is at least partially surrounded by an outer wall. The inlet channel is configured to guide air to an engine of the aircraft. The outer wall contains at least one outlet channel and at least one outlet element. The outlet element is configured to selectively release or close the outlet channel for an air flow from the inlet channel into the environment of the aircraft. The air direction arrangement contains a heat exchanger in the outlet channel to discharge thermal energy to the air flow which is flowing from the inlet channel into the environment of the aircraft.

Drag modification systems for aircraft and related methods. An example system for modifying drag on an aircraft includes a boundary layer intake plenum and an eductor. The eductor defines a primary inlet to receive a primary fluid, a secondary inlet in fluid communication with the intake plenum to receive a secondary fluid entrained from the intake plenum, and an outlet to exhaust a mixed flow including the primary fluid and the secondary fluid. The primary fluid is a motive fluid having flow parameters to generate a suction at the secondary inlet.

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.

The invention relates to an air system for an aircraft, that includes air consumers; air sources and a network of ducts and associated control valves controlled by a control unit. The air system is characterized in that: the network of ducts and associated valves includes at least one isolation valve, arranged between an air bleed device and an air duct connecting an air conditioning pack and an auxiliary power unit; the control unit is configured to be able to determine an ideal configuration of the control valves according to the identified requirements of each consumer and a degraded configuration that makes it possible to supply air to predetermined air consumers from the available air sources when the ideal configuration is not attainable.

An aircraft air conditioning pack assembly including an air conditioning pack configured to discharge heat, and an exterior panel positioned in close proximity to the air conditioning pack. The exterior panel includes an opening defined therein, a first side facing towards the air conditioning pack, and a second side defining an exterior surface configured to be in communication with a free stream airflow. At least a portion of the air conditioning pack is disposed within the opening to facilitate transferring heat from the air conditioning pack to the free stream airflow.

An air direction arrangement for an aircraft. The air direction arrangement contains an inlet opening and an inlet channel connected thereto and which is at least partially surrounded by an outer wall. The inlet channel is configured to guide air to an engine of the aircraft. The outer wall contains at least one outlet channel and at least one outlet element. The outlet element is configured to selectively release or close the outlet channel for an air flow from the inlet channel into the environment of the aircraft. The air direction arrangement contains a heat exchanger in the outlet channel to discharge thermal energy to the air flow which is flowing from the inlet channel into the environment of the aircraft.

An aircraft air conditioning pack assembly including an air conditioning pack configured to discharge heat, and an exterior panel positioned in close proximity to the air conditioning pack. The exterior panel includes an opening defined therein, a first side facing towards the air conditioning pack, and a second side defining an exterior surface configured to be in communication with a free stream airflow. At least a portion of the air conditioning pack is disposed within the opening to facilitate transferring heat from the air conditioning pack to the free stream airflow.

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.

An aircraft including an aft-mounted boundary layer energisation system is shown. The system comprises a nacelle arranged around a tailcone of the aircraft which thereby defines a duct, the duct having, in axial flow series, an intake, a heat exchanger, and a nozzle, and no turbomachinery therein, whereby the system energises a boundary layer of the aircraft by means of Meredith effect.

A laminar flow control surface having a foraminous section (also referred to below as a foraminous portion, 251) of a skin (250) of a vehicle to permit low temperature fluid to flow through the foraminous section to a heat exchanger (236), to reduce drag of the vehicle and to dissipate heat from the heat exchanger. The foraminous section (251) and the heat exchanger (236) synergistically reduce drag and transfer heat from the heat exchanger. The vehicle may be an aircraft with a laminar flow control system including a foraminous portion on a leading edge of the aircraft. While the aircraft is in flight, a portion of air impinging near the foraminous portion may flow laminarly about the leading edge, and another portion of the impingingair may flow through the foraminous portion to a heat exchanger to transfer heat from the heat exchanger to the air.