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.

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.

A method of cooling a gas turbine engine case assembly includes moving a fan air valve that is operatively connected to a pre-cooler having a bypass inlet that is configured to receive bypass air that bypasses a gas turbine engine core to facilitate a provision of bypass air through a fan air valve inlet to the bypass inlet to a first open position, in response to a core compartment temperature being greater than a target core compartment temperature. The method further includes bleeding the bypass air through a bypass outlet of the pre-cooler into a core compartment.

An aircraft includes: a cockpit, the inside of which is pressurized; equipment which is at least partially disposed on the outside of the cockpit (external space) where the pressure is lower than the inside of the cockpit (internal space); a forced air delivery mechanism which discharges air from a peripheral space of the equipment on the outside of the cockpit by an exhaust fan to supply a branch flow divided from a main flow of air-conditioning exhaust, which has air-conditioned the inside of the cockpit, as cooling air to the equipment; and a natural air delivery mechanism which uses a differential pressure between the inside of the cockpit and the outside of the cockpit to supply air inside the cockpit as cooling air to the equipment through a ventilation opening putting in communication the peripheral space and the inside of the cockpit with one another.

An aircraft includes: a cockpit, the inside of which is pressurized; equipment which is at least partially disposed on the outside of the cockpit (external space) where the pressure is lower than the inside of the cockpit (internal space); a forced air delivery mechanism which discharges air from a peripheral space of the equipment on the outside of the cockpit by an exhaust fan to supply a branch flow divided from a main flow of air-conditioning exhaust, which has air-conditioned the inside of the cockpit, as cooling air to the equipment; and a natural air delivery mechanism which uses a differential pressure between the inside of the cockpit and the outside of the cockpit to supply air inside the cockpit as cooling air to the equipment through a ventilation opening putting in communication the peripheral space and the inside of the cockpit with one another.

An aircraft air conditioning system, powered solely using electrical energy, to draw bleed air from outside the aircraft and deliver conditioned air to the aircraft's interior, includes at most three motorized rotary machines, which include: independent first and second motorized turbocompressors, each turbocompressor includes a turbine compressor and an electric motor; and a motor compressor interconnected between the turbocompressors via an interconnection pipe. The motor compressor: generates a primary air flow, which drives a secondary air flow, allowing a breathing air flow to be cooled in a first operation phase, corresponding to a ground operation or at relatively low altitude and relatively low aircraft speed; be at shutdown or at low idle in a second phase of operation at relatively low altitude and relatively high aircraft speed; and, provide a top up breathing air flow in a third phase of operation at relatively high altitude and relatively high aircraft speed.

An aircraft air conditioning system, powered solely using electrical energy, to draw bleed air from outside the aircraft and deliver conditioned air to the aircraft's interior, includes at most three motorized rotary machines, which include: independent first and second motorized turbocompressors, each turbocompressor includes a turbine compressor and an electric motor; and a motor compressor interconnected between the turbocompressors via an interconnection pipe. The motor compressor: generates a primary air flow, which drives a secondary air flow, allowing a breathing air flow to be cooled in a first operation phase, corresponding to a ground operation or at relatively low altitude and relatively low aircraft speed; be at shutdown or at low idle in a second phase of operation at relatively low altitude and relatively high aircraft speed; and, provide a top up breathing air flow in a third phase of operation at relatively high altitude and relatively high aircraft speed.

Thermoelectric cooling assemblies, and systems and methods employing such assemblies integrated within an aircraft antennae radome, with the cooling assemblies operating exclusively via electrical power provided by scavenging waste heat from an adjoining antennae array provide thermal protection to heat-sensitive structural components adjoining the antennae array.

Thermoelectric cooling assemblies, and systems and methods employing such assemblies integrated within an aircraft antennae radome, with the cooling assemblies operating exclusively via electrical power provided by scavenging waste heat from an adjoining antennae array provide thermal protection to heat-sensitive structural components adjoining the antennae array.

Systems and methods for cooling a core flow-path of a compressor section of a gas turbine engine are provided. In various embodiments, a cooling system for a gas turbine engine may comprise a valve system located radially outward from an engine case, the valve system being coupled between an air duct and the engine case, the valve system having an actuation device configured to at least one of open or close a valve in response to a command from an electronic engine controller, wherein cooling air from the air duct can pass through the valve system and enter the engine case into a high pressure compressor plenum when the valve system is in an open position.