Systems and methods for reducing the pressure of a first pressurized fluid, thereby reducing the temperature of the pressurized fluid, and utilization of the reduced-pressure and temperature fluid to cool a second fluid. Such an approach can enable a reduction in the size and weight of a hydraulic system, utilize waste energy in a system, and/or minimize electrical power requirements of a system, among other benefits.

A propulsion system for an aircraft includes a hydrogen fuel system, a water recovery system and a water pressure and quantity monitoring system. The water recovery system uses a condenser to extract water from an exhaust gas flow. The water pressure and quantity monitoring system measures water pressures and quantities at various locations in the water recovery system to assess the health and efficiency of the water recovery/supply system and the propulsion system.

A heat exchanger array includes a first row of heat exchangers, a second row of heat exchangers, and side curtains. The first row heat exchangers are spaced apart to define first gaps. The second row heat exchangers are spaced apart to define second gaps and are positioned downstream of and staggered from the first row heat exchangers such that the second row heat exchangers are aligned with the first gaps and the first row heat exchangers are aligned with the second gaps. Each side curtain is in close proximity to a first row heat exchanger and a second row heat exchanger. The side curtains define a neck region upstream of and aligned with each first row heat exchanger and each second row heat exchanger. Each neck region has a neck area that is less than a frontal area of the heat exchanger with which it is aligned.

A turbine inlet cooling method and system is disclosed that takes advantage of chilled fuel gas from one or more turbo-expanders, while taking advantage of the power generated from this process for refrigerant compression. In particular, mechanical work from the pressure drop of fuel gas through the turbo expanders will allow power generators to provide electricity to turn a refrigeration compressor's electric motor. In addition, the temperature drop of the fuel gas can operate as a first stage of cooling for a refrigeration medium returning from a turbine inlet cooler housing, among other advantages.

An intercooled cooling system for a gas turbine engine is provided. The intercooled cooling system includes cooling stages in fluid communication with an air stream utilized for cooling. A first cooling stage is fluidly coupled to a bleed port of the gas turbine engine to receive and cool bleed air with the air stream to produce a cool bleed air. The intercooled cooling system includes a pump fluidly coupled to the first cooling stage to receive and increase a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. The intercooled cooling system includes an air cycle machine in fluid communication to outputs of the cooling stages to selectively receive the cool bleed air or the intercooled cooling air.

The combustion device includes: a compressor that compresses combustion air; a combustor that combusts the compressed combustion air and fuel ammonia; and an ammonia injector that injects the fuel ammonia into the combustion air during or before compression of the combustion air by the compressor and cools the combustion air.

The present disclosure relates to the field of energy storage, and provides a rapid-response energy storage system and a using method thereof. The system comprises an air storage chamber, a compressor unit, an expander unit, a compressor unit lubrication station, an expander unit lubrication station, a compressor unit oil cooler, an expander unit oil cooler, a compressor unit oil pump and an expander unit oil pump; an outlet of the compressor unit communicates with an inlet of the air storage chamber through a heating pipe inside the expander unit lubrication station, and an outlet of the air storage chamber communicates with a heating pipe inside the compressor unit lubrication station sequentially through a regulating valve and the expander unit; the compressor unit lubrication station, the compressor unit oil pump, an oil way inside the compressor unit and the high-temperature side of the compressor unit oil cooler are sequentially connected end to end to form a first oil circulation loop; and the expander unit lubrication station, the expander unit oil pump, an oil way inside the expander unit and the high-temperature side of the expander unit oil cooler are sequentially connected end to end to form a second oil circulation loop. According to the present disclosure, rapid responses can be achieved and the lubricating oil can be heated without the consumption of external thermal energy.

A gas turbine engine includes a main compressor section with a downstream most location. A turbine section has a high pressure turbine. A tap line is connected to tap air from a location upstream of the downstream most location in the main compressor section. The tapped air is connected to a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and is connected to deliver air into the high pressure turbine. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions.

A variable orifice flow device controls the flow of a fluid between a volute casing and a compressor motor casing in a compressor. The variable orifice flow device may be a shuttling valve, with positions controlled by, for example, valves controlling the flow of the fluid into a space opposite a side within the shuttling valve assembly. The variable orifice flow device may have one or more orifices through which a fluid can enter the compressor motor casing, and the surface area of the orifices may be controlled by the position of the shuttling valve.

In a compressed air energy storage and power generation device, a compressed air energy storage and power generation method defines, as a reference storage value, a storage value indicating that a storage amount of air in an accumulator tank is in a predetermined intermediate state. At the reference storage value, at least one of a motor and a generator rotates at a rated rotation speed. When a storage value indicating a current storage amount in the accumulator tank is larger than the reference storage value, at least one of the motor and the generator is controlled to rotate at equal to or less than the rated rotation speed. When the storage value indicating the current storage amount in the accumulator tank is smaller than the reference storage value, at least one of the motor and the generator is controlled to rotate at equal to or more than the rated rotation speed and equal to or less than a maximum permissible rotation speed.