A composite power generating device of the present invention includes an engine (110), a first flow line (121), a turbocharger (130), a second flow line (122), a third flow line (123), a compressor (211), a first medium line (221), a medium turbine (212), a second medium line (222), a working medium cooler (213), a recuperator (215), a power generating unit (214), a cross-line (233), a first heat exchanger (251), a second heat exchanger (252), and a third heat exchanger (253).

A low friction inlet nozzle for a turbo expander including a nozzle cover ring, wherein the nozzle cover ring includes a face, a set of nozzle blades, wherein each nozzle blade includes a face, a set of pressure springs, and a set of axial loading bolts is provided. The axial loading bolts may be configured to accept all or at least a portion of the force which the set of pressure springs induces between the nozzle cover ring and the face of the nozzle blades, thereby locating the first face of the nozzle blade at a predetermined distance away from the face of the nozzle cover ring. The predetermined distance may be between 0.02 and 0.04 mm.

Apparatus, systems, and methods store energy by liquefying a gas such as air, for example, and then recover the energy by regasifying the liquid and combusting or otherwise reacting the gas with a fuel to drive a heat engine. The process of liquefying the gas may be powered with electric power from the grid, for example, and the heat engine may be used to generate electricity. Hence, in effect these apparatus, systems, and methods may provide for storing electric power from the grid and then subsequently delivering it back to the grid.

The invention relates to an aircraft propulsion system, comprising a main transmission unit (12) and at least two turbojet engines connected to the main transmission unit (12), respectively a first turbojet engine (14a) and a second turbojet engine (14b), each turbojet engine comprising a free turbine (24a, 24b), characterized in that the first turbojet engine (14a) comprises a heat exchanger (30) configured to recover some of the thermal energy from the exhaust gas at the outlet of the free turbine, and in that the propulsion system comprises at least one computer (28a, 28b) configured to control the two turbojet engines and to limit the acceleration and the deceleration of the first turbojet engine (14a) when neither of the turbojet engines is broken down, in order to limit the reactor power transients at the heat exchanger (30).

An aircraft incorporating a cabin air recovery system in which the aircraft comprises a pressurizable cabin, main turbofan engines, each turbofan engine having fan blades, a gas turbine coupled with the fan blades and a by-pass duct bypassing the gas turbine. The cabin fluidly communicates with the by-pass duct downstream of the fan blades so that, during operation, cabin outflow air is discharged into the by-pass duct downstream of the fan blades. By re-utilizing excess cabin air, engine thrust and efficiency is improved, and fuel consumption is reduced.

A method of operating an aircraft engine of an aircraft, the aircraft engine having a common-rail fuel injection system for injecting fuel into a combustion chamber of the aircraft engine, including: pressurizing fuel for circulation through the common-rail injection system; circulating a portion of the pressurized fuel through a motive flow inlet of an ejector pump; and entraining a flow through the ejector pump with the portion of the pressurized fuel circulating through the motive flow inlet.

The invention provides a vehicle engine system, comprising: a hydraulic pump for providing an oil supply during braking; an accumulator configured to: receive the oil supply during braking; store the oil supply under pressure; and release the oil supply under pressure during acceleration; and a turbo charger for receiving the oil supply released under pressure during acceleration.

A compressed air energy storage (CAES) power generation apparatus includes a motor driven by renewable energy, a compressor driven by the motor, a pressure accumulating tank storing compressed air compressed by the compressor, an expander driven by the compressed air from the pressure accumulating tank, and a generator connected to the expander. The apparatus includes a first heat exchanger that performs heat exchange between the compressed air from the compressor to the pressure accumulating tank and a heat medium, cools the compressed air, and heats the heat medium, a heat accumulating tank that stores the heat medium heated by the first heat exchanger, a second heat exchanger that performs heat exchange between the compressed air from the pressure accumulating tank to the expander, heats the compressed air, and cools the heat medium, and third heat exchangers that perform heat exchange between the exhaust heat outside a system and a fluid in the system. The power generation efficiency of the apparatus is improved using the exhaust heat outside the system while the exhaust heat outside the system is cooled using the cold heat generated in the system of the apparatus.

The manufacturing method for a turbocharger includes: connecting a shaft-side member to an actuator while the shaft-side member is inserted into a bush; combining the shaft-side member with a valve body-side member; and fixing the shaft-side member to the valve body-side member in a state where a wastegate valve is driven by the actuator so as to close the wastegate valve, and a contact surface of the valve body is pressed against a bearing surface.

Various systems and methods are provided for a turbocharger system. In one example, a system for use with a power generator having a rotary machine including a combustor comprises: a heat exchanger positioned to receive exhaust gases from the combustor; and a turbocharger system, comprising: a low pressure compressor fluidly coupled to the heat exchanger and adapted to supply gases to the heat exchanger; a low pressure turbine and a high pressure turbine each fluidly coupled to the heat exchanger and adapted to receive gases from the heat exchanger; a high pressure compressor fluidly coupled to the rotary machine and the low pressure compressor, adapted to receive gases from the low pressure compressor and supply compressed air to the rotary machine; and a water injector adapted to inject water into a flow path between the low pressure compressor and the heat exchanger.