A louvre system controls a flow of cooling air to a heat-generating element mounting inside a wing of an aircraft. The louvre system includes a louvre operably connected to the wing and structured to be rotatable to control airflow through an air intake of the wing into an interior of the wing. A louvre actuation mechanism is operably connected to the louvre and configured to control rotation of the louvre. A memory is communicably coupled to a processor and stores a louvre control module configured to autonomously control operation of the louvre actuation mechanism to control rotation of the louvre responsive to a temperature of a heat-generating element mounted in the wing interior.

An aircraft refrigeration system comprises an ambient air line, through which ambient air flows and which is connected to conduct ambient air to an aircraft, an ambient air compressor, arranged in the ambient air line, for compressing the ambient air in the ambient air line, a cabin exhaust air turbine, connected to a cabin exhaust air line and coupled to the ambient air compressor in the ambient air line and configured to expand cabin exhaust air flowing through the cabin exhaust air line and to drive the ambient air compressor, a transmission, configured to couple the cabin exhaust air turbine to the ambient air compressor and to set a speed of the ambient air compressor, and a motor, coupled to the transmission and configured to drive the ambient air compressor.

A primary structural assembly for an aircraft outside-skin heat exchanger, the assembly comprising an outer-skin portion which defines an outer shape of the aircraft and forms a portion of a hull of the aircraft, wherein the outer-skin portion comprises at least one recess, a thermal-transfer fluid connection which is designed to convey a thermal-transfer fluid into the recess, a component which closes the recess, and at least one retaining element which is arranged in or on the recess and is configured to hold the component closing the recess, in the recess. Further, an aircraft including such a primary structural assembly and a method for attaching the aircraft outside-skin heat exchanger are disclosed.

A system for managing thermal transfer in an aircraft includes a fuel stabilization unit, a fuel-air heat exchanger, and a turbine. The fuel-air heat exchanger is located downstream from the fuel stabilization unit. The fuel-air heat exchanger places deoxygenized fuel in a heat exchange relationship with compressor bleed air to produce heated deoxygenized fuel and cooled bleed air. The turbine is operationally connected to the engine compressor and receives cooled bleed air from the fuel-air heat exchanger.

There is provided a gas turbine engine comprising a blower system for supplying pressurised air to an airframe via an airframe port. The blower system comprises a compressor configured to receive air from a bypass duct or a core of the gas turbine engine and to discharge compressed air into a delivery line extending from the compressor to the airframe port. The blower system also comprises a heat exchanger configured to transfer heat from the compressed air to a coolant and a valve arrangement configured to switch between operation of the blower system in a baseline mode and a cooling mode, the valve arrangement being configured to: selectively divert the compressed air within the delivery line to the heat exchanger for operation in the cooling mode; and/or selectively provide the coolant to the heat exchanger for operation in the cooling mode.

A turbomachine including a nozzle extending along an axial direction and configured to convey a hot gas stream; and a mounting pylon for mounting the turbomachme, in which the pylon extends radially from a base arranged in the vicinity of the nozzle, is provided. The turbomachine includes a pylon cooler device having at least one auxiliary gas duct having a gas inlet configured to take cold gas from the outside of the nozzle, and a gas outlet opening out in the vicinity of the base of the pylon.

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 heated leading-edge structure for an aircraft includes a leading-edge panel having an outer surface configured to be contacted by an ambient flow, and an inner surface opposite the outer surface, a rear panel arranged at least partially arranged at a distance to the inner surface, a closed chamber inside the leading-edge structure, a heating device attached inside the chamber, and an air conveying device in fluid communication with the heating device. The air conveying device is configured to convey air from inside the chamber through the heating device to be heated and returned to the chamber, such that a circulating flow of heated air is created inside the chamber.

An apparatus and system are provided to provide transpiration cooling for an airframe. An airframe includes a body that contains circuitry, a phase change material (PCM) that changes phase to a gas when cooling the circuitry, a fluid reservoir that retains the PCM in liquid and gaseous form, a vapor reservoir that retains the gas, a thermal sensor that detects a temperature of an external surface of the body, and a controller that control ejection of the gas from the vapor reservoir based on the temperature to control a thickness of a boundary air layer at the external surface. The controller also controls flow of the gas from the fluid reservoir to the vapor reservoir via a valve based on pressure in the vapor reservoir detected by a pressure sensor.

In an aircraft, a cooling target having a different amount of heat depending on a situation is sufficiently cooled. An aircraft is provided with a cooling facility having a first cooling circuit and a second cooling circuit that are independent of each other. The first cooling circuit includes a first circulation flow path that allows a first cooling medium to sequentially and repeatedly pass through a cooling target. Similarly, the second cooling circuit includes a second circulation flow path that allows a second cooling medium to sequentially and repeatedly pass through the cooling target. Here, the first circulation flow path and the second circulation flow path do not communicate with each other. Therefore, the first cooling medium and the second cooling medium do not merge or split.