A gas turbine engine is disclosed having a tip clearance control system. The tip clearance control system has a cabin blower system, a casing arranged in use about a rotor of a gas turbine engine and a fluid delivery passage. The cabin blower system having a cabin blower compressor arranged in use to compress fluid used in a cabin of an aircraft and to compress fluid conducted via the fluid delivery passage into heat exchange with the casing.

The object of this disclosure is to cool the brakes of the landing gear of an aircraft. For this, it uses the air of the same air conditioning system of the airplane. The supply to the air conditioning system of the airplane can receive pre-conditioned air from outside by an air inlet in the lower part of the fuselage of the airplane to which an external equipment is connected. This air inlet has a non-return valve inside, which prevents the air from going outside. In order to extract the air from the air conditioning system of the airplane while it is on the ground, it is necessary to overpass the air valve. For this purpose, a tool that overpasses that valve from outside has been designed, and in this way, extracting and directing the air through connectors and tubes to the brakes, cooling them for a new takeoff.

Heat transfer devices and methods for enclosing a heat source and facilitating convective heat transfer from the heat source. A heat transfer device includes an outer wall having an outer surface exposed to an environment of the heat transfer device and defining an outer shape of the heat transfer device, and an inner wall defining a flow passage through the heat transfer device. The outer wall and the inner wall collectively define an internal volume that is configured to house the heat source. The flow passage comprises an inlet configured to receive a fluid from the environment, and an outlet configured to exhaust the fluid from the flow passage that comprises a core region extending between the inlet and the outlet and configured to deliver the fluid from the inlet to the outlet and allow heat to exchange between the fluid within the core region and the internal volume.

An unmanned aerial vehicle (UAV) includes a vehicle body and a flight control circuit. The vehicle body includes a housing and a fan. The housing includes two vents arranged at two ends of the housing and in communication with an internal space of the housing. The two vents and the internal space form a heat dissipation air passage. The fan is arranged at one of the two vents, and is configure to drive external air into the heat dissipation air passage and expel internal air from the heat dissipation air passage. The flight control circuit is arranged inside the housing and is configured to control flight parameters of the UAV. The heat dissipation air passage is configured to dissipate heat generated by the flight control circuit.

An aircraft includes electrical components and a ducted fan with a cooling coil. The aircraft is designed to discharge heat from the electrical components to the cooling coil.

A vertical takeoff and landing aerial vehicle and a cooling system for the aerial vehicle. The vertical takeoff and landing aerial vehicle comprises at least one air inlet provided on the top side of a linear support below a lift propeller, and at least one air outlet provided on the linear support. In the vertical takeoff and landing stage of the aerial vehicle provided by the disclosure, airflow generated by rotation of a lift propeller forms a rapid-flowing spatial flow field, which can achieve efficient heat dissipation of a motor and an electronic speed controller in an arm; and in the vertical takeoff and landing unmanned aerial vehicle provided by the utility, the takeoff weight of the unmanned aerial vehicle cannot be increased, power consumption of airborne equipment cannot be increased, and interior space of the arm cannot be occupied.

Cooling systems include a cold sink thermally coupled to a heat load, a separator configured to separate liquid and vapor portions of a working fluid, and a cooling cycle having a vapor loop and a liquid loop, the cooling cycle having the working fluid configured to pass through both the vapor loop and the liquid loop. The vapor loop includes the separator, a compressor, a condenser, and a valve. A vapor form of the working fluid flows from the separator into the compressor, and the working fluid then flows to the condenser, and then through the valve, and returned to the separator. The liquid loop includes the cold sink, the separator, and a pump. A liquid form of the working fluid flows from the separator into the pump and the working fluid is increased in pressure and supplied to the cold sink and then returned to the separator.

A cabin blower for an aircraft, the system comprising: a cabin blower compressor; an electric machine; and a controller configured to control the cabin blower system so that: in a cabin blower mode of operation, the cabin blower compressor is driven by power extracted from one or more spools of a gas turbine engine of the aircraft and provides a flow of air to a cabin of the aircraft. The controller may be further configured to control the system so that: in a rotor bow mitigation mode of operation, the cabin blower compressor is driven by the electric machine using electrical power from an electrical power source and provides a flow of air through a core of the gas turbine engine to remove heat from the core. A method of operating a cabin blower system of an aircraft is also provided.

A method includes obtaining thermal energy from a structure to be cooled, where the structure includes micro-channels. The method also includes providing the thermal energy to a water-based polymer network, where the water-based polymer network includes a gel formed using a polymer and water. The method further includes generating one or more gases by heating the water-based polymer network, where generating the one or more gases includes releasing the water in the water-based polymer network to produce steam. In addition, the method includes passing the one or more gases through the micro-channels to remove at least some of the thermal energy from the structure.

An outer panel-mediated cooling system includes a heat source chamber; a cooling path that is located between outer and inner panels; a non-cooling path that is located between the outer and inner panels and thermally insulated from a cooling path and the outer panel and through which at least one of pressurized gas and return gas from the heat source chamber passes; a mixing chamber into which cooled gas leaving the cooling path and an uncooled gas leaving the non-cooling path flow, in which the cooled gas and the uncooled gas are mixed to form a mixed gas, and out of which the mixed gas flows toward the heat source chamber; and a flow rate regulating valve that regulates a flow rate of gas flowing toward the mixing chamber.