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.

A gas turbine engine system includes a gas turbine engine and a turbo-generator. The gas turbine engine includes a heat exchange system configured to transfer thermal energy from an air flow (i.e., inlet air flow or exhaust gas flow) to a fuel to produce a gaseous fuel. The turbo-generator includes a fuel turbine fluidly coupled to the heat exchange system and a combustor of the gas turbine engine, a fuel pump configured to be driven by the fuel turbine and fluidly coupled to the heat exchange system, and a motor/generator configured to be driven by the fuel turbine. The fuel turbine is configured to extract energy from expansion of the gaseous fuel to produce a gaseous fuel for combustion in the combustor. The motor/generator includes a cooling jacket, which is fluidly coupled to the fuel pump.

A gas turbine engine system includes a gas turbine engine and a fuel turbine system. The gas turbine engine includes a heat exchange system configured to transfer thermal energy from a first compressed air flow and an exhaust gas flow to a fuel to produce a gaseous fuel. The fuel turbine system includes a fuel turbine fluidly coupled to the heat exchange system and a combustor of the gas turbine engine, and a fuel pump fluidly coupled to the heat exchange system and configured to be driven by the fuel turbine. The fuel turbine is configured to extract energy from expansion of the gaseous fuel to produce the gaseous fuel at a lower pressure for delivery to the combustor.

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.

A cooling device includes a cooler disposed inside a shell main body formed in a cylindrical shape, and having a first surface facing an inlet nozzle and an outlet nozzle, and a partition member fixed to the first surface, and partitioning a portion between the cooler and an inner peripheral surface of the shell main body into a first space communicating with the inlet nozzle and a second space communicating with the outlet nozzle. The partition member includes a main partition plate disposed between the inlet nozzle and the outlet nozzle in an axial direction, a first guide portion extending from an end portion of the main partition plate toward a first end surface of the shell main body, and a second guide portion extending from an end portion of the main partition plate toward a second end surface of the shell main body.

Intercooling systems and methods for an aircraft engine are provided. An intercooling system includes: a first inlet configured to receive a first air flow of ambient air into the aircraft engine; a second inlet separate from the first inlet and configured to receive a second air flow of ambient air into the aircraft engine separately from the first air flow of ambient air; and a heat exchanger configured to facilitate heat transfer between at least a portion of the first air flow compressed by a compressor section of the aircraft engine and the second air flow.

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.

The invention relates to a system and to a method for compressed-gas energy storage and recovery comprising at least a first and at least a second heat exchanger, a cold liquid storage means and a hot liquid storage means.

The first heat exchangers comprise at least one heat exchanger without direct contact, and at least one second heat exchanger is a direct-contact heat exchanger.

A gas turbine engine includes a main compressor section and a turbine section. The turbine section has a first turbine blade and vane and a downstream turbine component. A tap is configured to tap air from the compressor section at a location upstream of a most downstream location. The tap is connected to a heat exchanger. The heat exchanger is connected to a cooling compressor. The cooling compressor is connected to the downstream turbine component. A second tap is configured to tap air from a location in the main compressor section. The second tap is connected through a check valve to a line leading to the downstream turbine component. A control operates the cooling compressor such that when the cooling compressor is operating, air downstream of the cooling compressor is at a pressure higher than the pressure of the second tap, and the control is operational to selectively drive the cooling compressor at high power operation of an associated gas turbine engine, and to stop operation of the cooling compressor at lower power operations, such that air is delivered through the cooling compressor to the downstream turbine component at the high power operations, and air is delivered from the second tap at least some time when the cooling compressor is not operational. A method is also disclosed.

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.