A power plant with a multi-stage intercooled compressor, a combustion chamber, a turbine which is arranged downstream of the combustion chamber, a compressor air line which connects the compressor to the combustion chamber, and a first heat exchanger which is connected into the compressor air line and into an exhaust gas line branching off from the turbine. A first compressor air expander is arranged in the compressor air line between the first heat exchanger and the combustion chamber, and the power plant includes a device for regasifying liquid natural gas, having a natural gas line, wherein a heat exchanger device is connected into the natural gas line between two compressor stages of the compressor.

The high pressure compressor wheel of a two stage turbocharger assembly is cooled by charge air bled from the charge air flowpath downstream of the aftercooler. A wastegate may be arranged across the high pressure stage and operated by an actuator which in turn is operable by the static or dynamic pressure of the charge air in the cooling flowpath. The cooling airflow may be blocked to open the wastegate and released or resumed to close the wastegate so that cooling air is supplied only while the high pressure compressor wheel is under load.

A propulsion system includes an electric fan propulsion motor with a plurality of propulsion motor windings. The propulsion system also includes a means for controlling a flow rate of a working fluid through a cryogenic working fluid flow control assembly to the propulsion motor windings. The propulsion system further includes a controller operable to control supplying a pre-cooling flow of the working fluid from a cryogenic liquid reservoir through the cryogenic working fluid flow control assembly to the propulsion motor windings.

A compressed air energy storage system may have an accumulator and a thermal storage subsystem having a cold storage chamber for containing a supply of granular heat transfer, a hot storage chamber and at least a first mixing chamber in the gas flow path and having an interior in which the compressed gas contacts the granular heat transfer particles at a mixing pressure that is greater than the cold storage pressure and the hot storage pressure and a conveying system operable to selectably move the granular heat transfer particles from the cold storage chamber, through the first mixing chamber and into the hot storage chamber, and vice versa.

A system for an aircraft includes an engine bleed source of a gas turbine engine. The system also includes a means for chilling an engine bleed air flow from the engine bleed source to produce a chilled working fluid. The system further includes a means for providing the chilled working fluid for an aircraft use.

A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor having a downstream end. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor, and the boost compressor passes the air back to a location to be cooled. The boost compressor is driven by a shaft in the engine through an epicyclic gear system. A speed control changes the relative speed between an input and an output to the epicyclic gear system.

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.

An engine driven environmental control system (ECS) air circuit includes a gas turbine engine having a compressor section. The compressor section includes a plurality of compressor bleeds. A selection valve selectively connects each of said bleeds to an input of an intercooler. A second valve is configured to selectively connect an output of said intercooler to at least one auxiliary compressor. The output of each of the at least one auxiliary compressors is connected to an ECS air input.

A power plant with a multi-stage intercooled compressor, a combustion chamber, a turbine which is arranged downstream of the combustion chamber, a compressor air line which connects the compressor to the combustion chamber, and a first heat exchanger which is connected into the compressor air line and into an exhaust gas line branching off from the turbine. A first compressor air expander is arranged in the compressor air line between the first heat exchanger and the combustion chamber, and the power plant includes a device for regasifying liquid natural gas, having a natural gas line, wherein a heat exchanger device is connected into the natural gas line between two compressor stages of the compressor.

A process for retrofitting an industrial gas turbine engine of a power plant where an old industrial engine with a high spool has a new low spool with a low pressure turbine that drives a low pressure compressor using exhaust gas from the high pressure turbine, and where the new low pressure compressor delivers compressed air through a new compressed air line to the high pressure compressor through a new inlet added to the high pressure compressor. The old electric generator is replaced with a new generator having around twice the electrical power production. One or more stages of vanes and blades are removed from the high pressure compressor to optimally match a pressure ratio split. Closed loop cooling of one or more new stages of vanes and blades in the high pressure turbine is added and the spent cooling air is discharged into the combustor.