A system is provided. The system includes a first medium at a first pressure, a second medium at a second pressure, and a medium conditioning sub-system. The medium conditioning sub-system includes a compressor, a first heat exchanger, a second heat exchanger, and a turbine. The turbine receives the first medium and the second medium.

An aircraft gas turbine engine comprises a fan coupled to a fan drive turbine, the fan being configured to provide a bypass flow (B) and a core flow (A) in use. The engine includes a reduction gearbox which couples the fan to the fan drive turbine and a core compressor arrangement. The core compressor arrangement has a core inlet at an upstream end of a core gas flow passage (A) defined by radially inner and outer walls, and at least a first compressor rotor blade provided at an upstream end of the compressor arrangement. The radially inner wall of the core inlet defines a first diameter (D.sub.INLET), and a root leading edge of the first compressor rotor blade defines a second diameter (D.sub.COMP). A first ratio (D.sub.INLET:D.sub.COMP) of the first diameter (D.sub.COMP) to the second diameter (D.sub.COMP) is greater than or equal to 1.4.

An aircraft gas turbine engine comprises a fan coupled to a fan drive turbine, the fan being configured to provide a bypass flow (B) and a core flow (A) in use. The engine includes a reduction gearbox which couples the fan to the fan drive turbine and a core compressor arrangement. The core compressor arrangement has a core inlet at an upstream end of a core gas flow passage (A) defined by radially inner and outer walls, and at least a first compressor rotor blade provided at an upstream end of the compressor arrangement. The radially inner wall of the core inlet defines a first diameter (D.sub.INLET), and a root leading edge of the first compressor rotor blade defines a second diameter (D.sub.COMP). A first ratio (D.sub.INLET:D.sub.COMP) of the first diameter (D.sub.COMP) to the second diameter (D.sub.COMP) is greater than or equal to 1.4.

A supply duct of a compressor of a turbine engine, formed from internal and external walls of revolution around an axis and opposite one another to define a circulation stream of a fluid, is provided. The stream allows the fluid to be routed from the inlet of the duct to the inlet of the compressor. The radius of the external wall at the inlet of the duct is greater than the radius of the duct at the inlet of the compressor. The duct includes a portion for which the radius of the external wall along the portion is less than the radius of the external wall at the inlet of the compressor, and the radius of the internal wall along the portion of the duct is less than the radius of the internal wall at the inlet of the compressor.

A supply duct of a compressor of a turbine engine, formed from internal and external walls of revolution around an axis and opposite one another to define a circulation stream of a fluid, is provided. The stream allows the fluid to be routed from the inlet of the duct to the inlet of the compressor. The radius of the external wall at the inlet of the duct is greater than the radius of the duct at the inlet of the compressor. The duct includes a portion for which the radius of the external wall along the portion is less than the radius of the external wall at the inlet of the compressor, and the radius of the internal wall along the portion of the duct is less than the radius of the internal wall at the inlet of the compressor.

Efficient energy storage is provided by using a working fluid flowing in a closed cycle including a ganged compressor and turbine, and capable of efficient heat exchange with heat storage fluids on a hot side of the system and on a cold side of the system. This system can operate as a heat engine by transferring heat from the hot side to the cold side to mechanically drive the turbine. The system can also operate as a refrigerator by mechanically driving the compressor to transfer heat from the cold side to the hot side. Heat exchange between the working fluid of the system and the heat storage fluids occurs in counter-flow heat exchangers. In a preferred approach, molten salt is the hot side heat storage fluid and water is the cold side heat storage fluid.

Efficient energy storage is provided by using a working fluid flowing in a closed cycle including a ganged compressor and turbine, and capable of efficient heat exchange with heat storage fluids on a hot side of the system and on a cold side of the system. This system can operate as a heat engine by transferring heat from the hot side to the cold side to mechanically drive the turbine. The system can also operate as a refrigerator by mechanically driving the compressor to transfer heat from the cold side to the hot side. Heat exchange between the working fluid of the system and the heat storage fluids occurs in counter-flow heat exchangers. In a preferred approach, molten salt is the hot side heat storage fluid and water is the cold side heat storage fluid.

Disclosed is a system including a turbine having a plurality of blades being spaced circumferentially around a shaft. Each blade of the plurality of blades is a hemispherical-shaped cup with an open surface. A plurality of dispensers are included, and each dispenser of the plurality of dispensers is positioned facing the open surface of the each blade, and directs discharged fluid toward the open surface of the each blade to drive the turbine. A housing encloses the plurality of blades and a portion of each dispenser of the plurality of dispensers, and has an exhaust pipe extending away from the shaft directing the discharged fluid out of the housing. A controller is in communication with the plurality of dispensers, and controls the plurality of dispensers.

Disclosed is a system including a turbine having a plurality of spokes. The first spoke end is coupled to a shaft and the second spoke end is coupled to a blade of a plurality of blades. Each blade is a cup with an open surface. A dispenser includes a combustion chamber. An air injector is configured to inject air into the combustion chamber. A fuel injector is configured to inject fuel into the combustion chamber. An ignitor is configured to supply a spark for combustion in the combustion chamber. A nozzle directs discharged fluid toward the open surface of the blade to drive the turbine. A housing encloses the second nozzle end and the plurality of blades, and has an exhaust pipe. A controller is configured to control the air injector, the fuel injector and the ignitor.

A cooling device uses siphon circulation whose heat source is an object-to-be-cooled installed in a vehicle to circulate refrigerant to the object-to-be-cooled, the cooling device including: a tank that is disposed above the object-to-be-cooled and stores the refrigerant; an outflow path that opens to the inside of the tank and through which the refrigerant flows out; a passage member that extends from the inside to the outside of the tank, with an open end of an inside section of the passage member positioned inside the tank being positioned above an opening of the outflow path; and identifying means that is provided at an outside section of the passage member positioned outside the tank and by which the position of the open end inside the tank can be identified.