Provided is an air diffuser and a construction method thereof. The air diffuser is especially applied to the field of civil aircrafts. The air diffuser comprises: an open upper end part; an open lower end part; and an air flow passage defined between the open upper end part and the open lower end part, the air flow passage comprising a first side wall and a second side wall which are connected between the open upper end part and the open lower end part and are symmetrically located with respect to a vertical center plane of the air diffuser; wherein the section outline of each of the first side wall and the second side wall has a curved shape bending inwards, such that in a direction from the open upper end part to the open lower end part, the air flow passage has, in sequence, a contraction portion bending toward the vertical center plane and an expansion portion away from the vertical center plane.

Provided is an air diffuser and a construction method thereof. The air diffuser is especially applied to the field of civil aircrafts. The air diffuser comprises: an open upper end part; an open lower end part; and an air flow passage defined between the open upper end part and the open lower end part, the air flow passage comprising a first side wall and a second side wall which are connected between the open upper end part and the open lower end part and are symmetrically located with respect to a vertical center plane of the air diffuser; wherein the section outline of each of the first side wall and the second side wall has a curved shape bending inwards, such that in a direction from the open upper end part to the open lower end part, the air flow passage has, in sequence, a contraction portion bending toward the vertical center plane and an expansion portion away from the vertical center plane.

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.

An aircraft including: a wing having a leading edge; an electric motor mounted on the wing; and an electric power cable in the wing for providing power to the electric motor, wherein the electric power cable runs through a duct in the wing; the duct comprises an air inlet and an air outlet; and the electric power cable is cooled by air passing through the duct between the air inlet and the air outlet.

An aircraft including a fuselage having a side wall at least partially defining a passenger cabin and a crown section of the aircraft. The passenger cabin includes an overhead zone, a passenger zone, and a floor zone. An air supply duct is positioned within the crown section, and the air supply duct is configured to pressurize the crown section with air. At least one return air outlet is defined in the floor zone. An interior structure is coupled to the side wall and extends between the passenger cabin and the crown section. The interior structure includes a plurality of nozzles oriented to discharge the pressurized air from the crown section along an airflow path that extends downward through the overhead zone, downward through the passenger zone, and then towards the at least one return air outlet.

A propeller system for a tail section of an aircraft includes a propeller hub located at the tail section of the aircraft, a plurality of propeller blades mounted to and extending outwardly from the propeller hub, a propeller shaft coupled to the propeller hub and operable to rotate the propeller hub about an axis of rotation, and a propeller gearbox connected to the propeller shaft. The propeller gearbox is fluidly cooled by an airflow within the tail section. A spinner assembly surrounds the propeller hub. The spinner assembly includes at least one outlet opening formed therein downstream from the propeller hub relative to the airflow. The spinner assembly is rotatable to draw the airflow into at least one cooling flow inlet formed in the tail section and across the propeller gearbox to cool the propeller gearbox and out the at least one outlet opening.

A servo valve for an actuator comprises a housing, a sleeve provided within the housing comprising an axis (A) and having a plurality of metering holes for communication with a cavity within. A metering rod extends within the cavity for metering flow of pneumatic fluid through the metering holes. The metering rod is coupled to a drive unit for axial movement within the cavity, the drive unit comprising a drive unit housing, a solenoid and an adjustable core. The adjustable core comprises a threaded first portion having a thread and a second portion. The thread of the first portion engages a thread extending through the drive unit housing for adjustment of the relative position of the adjustable core with respect to the solenoid.

In some examples, a computing device is configured to monitor an air quality of a vehicle cabin by at least receiving, from a plurality of remote sensors distributed throughout the cabin, signals indicative of one or more air quality parameters for air in the cabin. Based on the received signals, the computing device can determine if values for the one or more air quality parameters are indicative of an air quality event and generate an output in response to such a determination. The output may include, for example, an audio or visual indication of the air quality event or a signal to control another system of the aircraft to take action to remedy the air quality event.

A vehicle includes an internal cabin, a first group of seats within a first row within the internal cabin, a second group of seats within a second row within the internal cabin, and an air curtain system within the internal cabin. The air curtain system is configured to provide one or more air curtains between one or both of (a) the first row and the second row or (b) adjacent seats of one or both of the first group or the second group.

A vehicle includes an internal cabin, a first group of seats within a first row within the internal cabin, a second group of seats within a second row within the internal cabin, and an air curtain system within the internal cabin. The air curtain system is configured to provide one or more air curtains between one or both of (a) the first row and the second row or (b) adjacent seats of one or both of the first group or the second group.