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 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 tesla-type turbine for converting the enthalpy of a gas volume flow into mechanical energy, a method for operating the Tesla-type turbine, and an apparatus for converting thermal energy into mechanical energy, a method for converting thermal energy into mechanical energy, and a method for converting thermal energy into electrical energy. The Tesla-type turbine has at least one disc which is positioned on an axis of rotation and is set into rotation by a gas volume flow flowing substantially tangentially, so that mechanical energy can be collected at a shaft coupled to the disc. A disc body that forms the disc has at least one cavity in which, for the purpose of cooling the disc body, a cooling medium, in particular a cooling liquid, is received or can be received.

Systems and methods for cooling electrical components disposed in a jet engine. An example system includes an evaporation chamber configured to contain the electrical components in contact with a coolant liquid. The coolant vapor formed during the heat transfer from the electrical components to the coolant liquid flows to a condenser assembly having a fuel-cooled condenser and an air-cooled condenser. The air-cooled condenser cools the coolant vapor to condensation using either fan stream air or engine bleed air from the intermediate pressure compressor or the high pressure compressor. An air cycle machine cools the engine bleed air. A controller may be used to select a coolant source for condensing the coolant vapor based on operating conditions of the aircraft. Spent air from the air-cooled condenser may be recycled back to the engine for engine cooling, added thrust, oil sump buffering, oil or fuel cooling, or blade tip clearance control.

A gas turbine engine system includes a gas turbine engine and a fuel turbine system. The gas turbine engine includes an air inlet, compressor, combustor, turbine, and heat exchange system. The heat exchange system is configured to transfer thermal energy from an inlet air flow or exhaust air flow to a fuel to produce a gaseous fuel that is used to drive a fuel turbine and fuel pump and used for combustion in the gas turbine engine. The fuel turbine is in fluid communication with the heat exchange system and the combustor and configured to extract energy from expansion of the gaseous fuel. The fuel pump is configured to be driven by the fuel turbine and is in fluid communication with the heat exchanger system.

A gas turbine engine includes an engine core having a compressor section, a combustor fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor section. At least one compressor bleed connects a compressor flowpath with a first cooled cooling air path. The first cooled cooling air path includes a supplementary coolant injector connected to a supplementary coolant supply. The cooled cooling air path including a portion exterior to the engine core.

A cooling system for a turbine engine is provided. The turbine engine includes a compressor, a compressor discharge chamber (CDC), a combustor assembly, and a turbine coupled in a serial flow relationship such that a first portion of air from the CDC is channeled to the combustor assembly. The turbine is coupled to the compressor via a rotor. The cooling system includes an air duct configured to channel a second portion of air from the CDC to a mid-rotor region of the rotor, and a fluid supply system coupled to the air duct at a coupling. The fluid supply system is configured to channel a flow of fluid to the coupling. The coupling is configured to cool the second portion of CDC air via absorption of heat by the fluid from the second portion of CDC air.

A cooling system for a gas turbine engine comprising a closed circuit containing a change-phase fluid, the closed circuit having at least one cooling exchanger configured to be exposed to a flow of cooling air for the change-phase fluid to release heat to the cooling air. A plurality of heat exchangers in are heat exchange relation with the change-phase fluid in the closed circuit, the plurality including at least a first heat exchanger configured to receive a first coolant from a first engine system for the change-phase fluid to absorb heat from the first coolant, and a second heat exchanger configured to receive a second coolant from a second engine system for the change-phase fluid to absorb heat from the second coolant. The system is configured so that the fluid at least partially vaporizes when absorbing heat from at least one of the first coolant and the second coolant and at least partially condenses when releasing heat to the cooling air. A method for cooling engine systems of a gas turbine engine is also provided.

A combined cycle power plant that includes a gas turbine and HRSG engaged with a steam turbine via a water steam cycle having higher and lower pressure levels. The CCPP further includes a fuel line and fuel preheater. A higher pressure feedwater line delivers higher pressure feedwater to a higher pressure feedwater branch that extends through the fuel preheater, the high pressure feedwater branch including upstream and downstream segments defined to each side of the fuel preheater. A lower pressure feedwater line delivers lower pressure feedwater to a lower pressure feedwater branch. The downstream segment of the higher pressure feedwater branch is combined with the lower pressure feedwater branch at a junction point and a combined feedwater line extends therefrom. A first heat exchanger exchanges heat between the combined feedwater line and fuel line. A second heat exchanger exchanges heat between the higher pressure feedwater branch and fuel line.

A cooling system in a hybrid electric propulsion gas turbine engine is provided for cooling electrical components therein. The cooling system includes an electrical component disposed in proximity to an aircraft power generation component in the hybrid electric propulsion gas turbine engine such that the electrical component is thermally heated by the aircraft power generation component. A loop heat pipe structure is in thermal communication with the electrical component to transfer heat away from the electrical component. Wherein the loop heat pipe includes an evaporator portion, a condenser portion, a first pipe to supply a biphasic working fluid in a liquid state to the evaporator portion, and a second pipe to return the biphasic working fluid in a gaseous state to the condenser portion.