The position of the stabilizer container 7 in the circulation route is not limited. The stabilizer container 7 is preferably disposed between the evaporator and the condenser between which the refrigerant flows in the circulation route as a liquid refrigerant. Specifically, the stabilizer container 7 is preferably disposed between the outdoor heat exchanger 4 and the expansion mechanism 5 or between the indoor heat exchanger 6 and the expansion mechanism 5. During cooling, the outdoor heat exchanger 4 functions as a condenser and the indoor heat exchanger 6 functions as an evaporator. During heating, the outdoor heat exchanger 4 functions as an evaporator and the indoor heat exchanger 6 functions as a condenser. In either case of cooling or heating, the liquid refrigerant is present between the expansion mechanism 5 and the outdoor heat exchanger 4 or between the expansion mechanism 5 and the indoor heat exchanger 6 depending on the refrigerant circulation direction, and the stabilizer container 7 is located where the liquid refrigerant is present (i.e., between the expansion mechanism and whichever heat exchanger 4, 6 serves as the evaporator in the refrigerant circulation direction). Thus, as the liquid refrigerant passes through the stabilizer container 7, oxidation of the refrigerant can be efficiently prevented and acids in the circulation route can be efficiently scavenged.

The position of the stabilizer container 7 in the circulation route is not limited. The stabilizer container 7 is preferably disposed between the evaporator and the condenser between which the refrigerant flows in the circulation route as a liquid refrigerant. Specifically, the stabilizer container 7 is preferably disposed between the outdoor heat exchanger 4 and the expansion mechanism 5 or between the indoor heat exchanger 6 and the expansion mechanism 5. During cooling, the outdoor heat exchanger 4 functions as a condenser and the indoor heat exchanger 6 functions as an evaporator. During heating, the outdoor heat exchanger 4 functions as an evaporator and the indoor heat exchanger 6 functions as a condenser. In either case of cooling or heating, the liquid refrigerant is present between the expansion mechanism 5 and the outdoor heat exchanger 4 or between the expansion mechanism 5 and the indoor heat exchanger 6 depending on the refrigerant circulation direction, and the stabilizer container 7 is located where the liquid refrigerant is present (i.e., between the expansion mechanism and whichever heat exchanger 4, 6 serves as the evaporator in the refrigerant circulation direction). Thus, as the liquid refrigerant passes through the stabilizer container 7, oxidation of the refrigerant can be efficiently prevented and acids in the circulation route can be efficiently scavenged.

A compact cooling and boosting gas turbine system provides combined cooling, heating, and electrical power with high energy efficiency. The system has a pressure booster and a turbo-compressor. The pressure booster includes a fuel inlet, a fuel outlet, and a piston, and is in fluid communication with a gas turbine engine. The pressure booster also includes a coolant inlet, a coolant chamber, and a coolant outlet, and is in fluid communication with a closed pressurized coolant flow. The turbo-compressor includes a compressor and a turbine, and is in fluid communication with a water input flow and with the closed pressurized coolant flow. A coolant flow control valve controls the closed pressurized coolant flow. The system is configured to provide a cold water flow for a first position of the flow control valve and to provide a hot water flow for a second position of the flow control valve.

A turbofan gas turbine engine includes heat exchanger module, fan assembly, compressor, turbine and exhaust modules. The fan includes a plurality of fan blades. The heat exchanger in fluid communicates with the fan assembly by an inlet duct, and the heat exchanger includes a plurality of radially-extending hollow vanes arranged in a circumferential array, with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger is divided between a set of vane airflows and a set of channel airflows. Each vane airflow has a vane mass flow rate Flow.sub.Vane, and each channel air flow has a channel mass flow rate Flow.sub.Chan. Each hollow vane includes, an inlet, heat transfer, and exhaust portions, with the inlet portion comprising a diffuser element and the heat transfer portion including at least one heat transfer element. The diffuser element causes Flow.sub.Vane to be lower than Flow.sub.Chan.

A turbofan gas turbine engine includes heat exchanger module, fan assembly, compressor, turbine and exhaust modules. The fan includes a plurality of fan blades. The heat exchanger in fluid communicates with the fan assembly by an inlet duct, and the heat exchanger includes a plurality of radially-extending hollow vanes arranged in a circumferential array, with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger is divided between a set of vane airflows and a set of channel airflows. Each vane airflow has a vane mass flow rate Flow.sub.Vane, and each channel air flow has a channel mass flow rate Flow.sub.Chan. Each hollow vane includes, an inlet, heat transfer, and exhaust portions, with the inlet portion comprising a diffuser element and the heat transfer portion including at least one heat transfer element. The diffuser element causes Flow.sub.Vane to be lower than Flow.sub.Chan.

A method of operating an environmental control system of an aircraft includes providing a first medium to the environmental control system including a compressor and a turbine, wherein the first medium is provided to the compressor and the turbine sequentially and extracting work from a second medium provided to a power turbine operably coupled to the compressor to drive the compressor. In a first mode of operation, the first medium to be provided to a downstream load is output from the turbine, in a second mode of operation, at least a portion of the first medium to be provided to a downstream load bypasses the turbine, and in a third mode of operation, at least a portion of the first medium output from the compressor is provided to the power turbine.

A method of operating an environmental control system of an aircraft includes providing a first medium to the environmental control system including a compressor and a turbine, wherein the first medium is provided to the compressor and the turbine sequentially and extracting work from a second medium provided to a power turbine operably coupled to the compressor to drive the compressor. In a first mode of operation, the first medium to be provided to a downstream load is output from the turbine, in a second mode of operation, at least a portion of the first medium to be provided to a downstream load bypasses the turbine, and in a third mode of operation, at least a portion of the first medium output from the compressor is provided to the power turbine.

An environmental control system of an aircraft includes a compressing device including a compressor and a turbine configured to receive a flow of first medium sequentially and a second turbine arranged in fluid communication with an outlet of the compressor. The second turbine is configured to receive a flow of second medium distinct from the first medium. A dehumidification system is arranged in fluid communication with the turbine, a first bypass valve is configured to divert at least a portion of the flow of the first medium output from the compressor around the turbine, and a second bypass valve configured to divert at least a portion of the flow of first medium output from the compressor to the second turbine.

An environmental control system of an aircraft includes a compressing device including a compressor and a turbine configured to receive a flow of first medium sequentially and a second turbine arranged in fluid communication with an outlet of the compressor. The second turbine is configured to receive a flow of second medium distinct from the first medium. A dehumidification system is arranged in fluid communication with the turbine, a first bypass valve is configured to divert at least a portion of the flow of the first medium output from the compressor around the turbine, and a second bypass valve configured to divert at least a portion of the flow of first medium output from the compressor to the second turbine.

A system is described herein for repurposing waste heat from a refrigeration cycle to improve the efficiency of the cycle and power electronic devices. The system may include a compressor, a turbine, an accumulator, a condenser, a throttle, and an evaporator. The accumulator may include a high-pressure chamber connected between the turbine and condenser, and a low-pressure chamber connected between the evaporator and the compressor. The high-pressure chamber may be segregated from the low-pressure chamber such that high-pressure refrigerant in the high-pressure chamber is prevented from mixing with low-pressure refrigerant in the low-pressure chamber. The high-pressure chamber and low-pressure chamber may be thermally coupled such that liquid refrigerant in the low-pressure chamber is vaporized by heat exchange with the high-pressure chamber. The turbine may power an electronic component of the refrigerator or may feed electricity back into a community grid power system.