A powerplant is provided for an aircraft. This powerplant includes an engine and an energy recovery system. The engine includes an engine combustor, an engine turbine, a flowpath and a fluid delivery system. The flowpath extends out of the engine combustor and through the engine turbine. The fluid delivery system is configured to provide fluid hydrogen and fluid oxygen for combustion within the engine combustor to produce combustion products within the flowpath. The energy recovery system includes an energy recovery system condenser, an energy recovery system pump, an energy recovery system evaporator and an energy recovery system turbine. The energy recovery system pump is configured to pump liquid water from the energy recovery system condenser to the energy recovery system evaporator. The energy recovery system evaporator is configured to transfer heat from the combustion products into the liquid water to evaporate at least some of the liquid water into water vapor to drive the energy recovery system turbine.

Disclosed are a hybrid power generation facility and a control method thereof. The hybrid power generation facility includes a gas turbine including a compressor configured to compress air introduced from an outside, a combustor configured to mix the compressed air with fuel and to combust the air and fuel mixture, and a turbine configured to produce power with first combustion gas discharged from the combustor, a GT (gas turbine) generator configured to generate electric power using a driving force generated by the gas turbine, a boiler including a combustion chamber and configured to mix the first combustion gas supplied from the turbine of the gas turbine with air and fuel supplied from the outside, a steam turbine through which steam generated in the combustion chamber passes, a ST (steam turbine) generator configured to generate electric power using a driving force generated by the steam turbine, and an energy storage system configured to be charged based on a decrease rate of power demand of a grid and a maximum decrease rate of power supply from the GT generator and the ST generator.

Disclosed is a hybrid power generation facility. The hybrid power generation facility includes a gas turbine including a compressor configured to compress air introduced from an outside, a combustor configured to mix the compressed air with fuel and to combust the air and fuel mixture, and a turbine configured to produce power with first combustion gas discharged from the combustor, a boiler configured to burn a mixture of the first combustion gas and air, a first water heat exchanger configured to pass second combustion gas discharged from the boiler and to heat water through heat exchange to between the water and the second combustion gas, a water supply device configured to supply water to the first water heat exchanger, a steam turbine through which steam generated in the boiler passes, and a fuel heat exchanger configured to pass fuel supplied to the combustor and to pass a portion of water that is returned to the water supply device from the first water heat exchanger and has a higher temperature than the water supplied to the first water heat exchanger.

A combined cycle heat engine (10). The engine (10) comprises a first gas turbine engine (11) comprising a first air compressor system (14), a first combustion system (16) and a first turbine system (18) and a second gas turbine engine (32) comprising a second air compression system (36), a second turbine system (40), and a heat exchanger (38) configured to transfer heat from an exhaust (24) of the first turbine system (18) to compressed air from the second air compressor (36). The second gas turbine engine (32) comprises a second combustion system (20) downstream of the heat exchanger (38) and upstream of the second turbine system (40).

A hybrid electric propulsion system including: a gas turbine engine comprising a low speed spool, a high speed spool, and a combustor; a lubrication circuit comprising a bearing compartment, a supply pump, and a scavenger pump; an electric motor configured to augment rotational power of the low speed spool or the high speed spool; and a controller operable to: control the electric motor based upon a pressure differential between an interior of the bearing compartment and an exterior of the bearing compartment and to drive rotation of the low speed spool and/or the high speed spool via the electric motor responsive to a thrust command while fuel flow to the combustor is inhibited.

A turbojet engine capable of operation in an Air Turbo Rocket (ATR) mode includes a compressor, a rotatable turbine wheel comprising turbine blades, a non-rotating guide vane ring comprising guide vanes, a turbine shaft configured to power said compressor, a combustor, a gas generator, and a main combustor. The main combustor is configured to combust hot, fuel rich gas from the gas generator in air compressed by the compressor. Hot, fuel rich gas from the gas generator is directed towards the turbine blades by a directing means.

A combined cycle heat engine (10). The engine (10) comprises a first gas turbine engine (11) comprising a first air compressor (14), a first combustion system (16, 20) and a first turbine system (18, 22), and a second gas turbine engine (32) comprising a second air compressor (36) and a second turbine system (40). The engine further comprises a heat exchanger (38) configured to transfer heat from an exhaust of the first turbine system (18, 22) to compressed air from the second air compressor (36). The first combustion system comprises a first combustor (16) provided downstream of the first air compressor (14) and upstream of the first turbine system (18, 22), and a second combustor (20) downstream of a first turbine section (18) of the first turbine system and upstream of a second turbine section (22) of the first turbine system.

In one embodiment, a plant control apparatus includes a first stop controller configured to, when stopping a plant, stop a steam turbine to start to drop rotating speed of a second shaft of the steam turbine from rated speed, and start to drop rotating speed of a first shaft of a gas turbine from the rated speed while continuing combustion of a combustor after the stop of the steam turbine. The apparatus further includes a second stop controller configured to shut off fuel of the combustor to stop the gas turbine when the rotating speed of the first shaft drops to first speed. The second stop controller stops the gas turbine such that the rotating speed of the first shaft catches up with the rotating speed of the second shaft at second speed that is equal to or lower than the first speed and a clutch is engaged.

A power plant can comprise a gas turbine productive of an exhaust gas, a steam turbine, a heat recovery steam generator that extracts heat from gas turbine exhaust gas and supplies fluid to the steam turbine, a thermal storage unit storing a thermal storage working medium that is configured to discharge thermal energy into the fluid supplied from the heat recovery steam generator to supplement power generation by the steam turbine, a first heat exchanger disposed within the heat recovery steam generator to transfer thermal energy from the exhaust gas to the thermal storage working medium, and a second heat exchanger in flow communication with the heat recovery steam generator and the thermal storage unit, the second heat exchanger facilitating a direct heat transfer of thermal energy from the thermal storage working medium in the thermal storage unit to the fluid supplied from the heat recovery steam generator.

Wind funnel and gas combustion turbine systems are disclosed. Air travels through a wind funnel where it is compressed, and then flows into a compression section of a gas turbine that is fueled by a hydrocarbon fuel source such as natural gas. Compressed air from the wind funnel enters the compressor section of the gas turbine at relatively high density and force, and then flows to the combustion section of the gas turbine where oxygen from the wind-compressed air is used to combust the hydrocarbon fuel supplied to the gas turbine. In other embodiments, systems are provided for supplying compressed air to the combustion chamber of linear combustion devices, such as engines and generators.