An aircraft power plant for a fuel cell including a turbo assembly, a compressor assembly, a turbo assembly, a compressor assembly controller, a first stage turbo assembly and compressor assembly operation configured to generate a first stage compressed fluid generated from ambient air and excess oxygen exhausted from a fuel cell of an aircraft power plant. A second stage turbo assembly and compressor assembly operation configured to receive the first stage compressed fluid, and a controller bleed valve coupled with the first stage turbo assembly and compressor assembly and the second stage turbo assembly and compressor assembly. An oxygen supply system, the oxygen supply system fluidically coupled with the first stage turbo assembly and compressor assembly wherein a first compressed oxygen is generated by the first stage turbo assembly is combined with a second compressed oxygen generated by the second stage turbo assembly to generate a combined oxygen controlled by the controller bleed valve. A third stage turbo assembly and compressor assembly operation configured to receive the combined oxygen, and a hydrogen supply system configured to provide hydrogen fluidically coupled with the third stage turbo assembly and compressor assembly.

A turbofan engine includes a fan, a core turbine engine having one or more turbines and an exhaust section, and a hydrogen-exhaust gas heat exchanger in flow communication with the exhaust section and hydrogen flowing along a hydrogen supply line. The hydrogen-exhaust gas heat exchanger defines a load capacity factor determined by raising a product to a one-quarter power, the product being determined by multiplying a heat transfer surface area density associated with the hydrogen-exhaust gas heat exchanger by a process conductance parameter that relates characteristics of hydrogen, ambient air, and exhaust gas at takeoff, as well as a fan diameter of the fan and a number of turbine stages of the turbofan engine. The load capacity factor is between 4.37 and 28.65 for the fan diameter being between 0.5 and 3.5 meters and the heat transfer surface area density being between 500 m.sup.2/m.sup.3 and 10,000 m.sup.2/m.sup.3.

A waste heat recovery system for recovering waste heat of in internal combustion engine includes a turbine expander. The turbine expander includes a turbine blade, a shaft coupled to and rotatable by the turbine blade, and a nozzle assembly. The nozzle assembly includes a nozzle block disposed about the shaft and adjacent the turbine blade, a first nozzle component coupled to the nozzle block, and a second nozzle component coupled to the nozzle block. The first nozzle component defines a first nozzle having a first geometrical configuration. The second nozzle component defines a second nozzle having a second geometrical configuration that is different from the first geometrical configuration. The waste heat recovery system also includes a flow control device in fluid communication with the turbine expander. The waste heat recovery system further includes a controller in communication with the flow control device.

A combination stove and space heater is provided, comprising a stove portion and a removable heater portion disposed over the stove portion. The stove portion includes an enclosure having a removable drawer configured to receive one or more burnable fuels, a grating suspended by the enclosure over the removable drawer and configured to be heated by burning the one or more fuels. The removable heater portion includes a radiator having a plurality of vertical plates, each having a length along a lateral axis and a height along a vertical axis, an axial fan disposed at one side of the radiator and with an axis of flow substantially parallel to the lateral axis, and a cover disposed surrounding the radiator and the axial fan, the cover having openings on opposing ends along the lateral axis.

A propulsion system for an aircraft includes a hydrogen fuel system suppling hydrogen fuel to the combustor through a fuel flow path. A condenser extracts water from a high energy gas flow. The condenser includes a plurality of rotating passages that are disposed within a collector. The passages are configured to rotate about a condenser axis to generate a transverse pressure gradient to direct water out of the high energy gas flow toward the collector.

A turbine section and an exhaust section for a gas turbine engine includes a low pressure (LP) turbine having first stage LP turbine blades that rotate in a first direction at a first speed, and final stage LP turbine blades downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed. The second speed is lower than the first speed.

An energy generation plant in which the exhaust gas from a gas turbine is guided into a thermal energy store, wherein the thermal energy store can be used for various purposes. The energy generation plant has at least one gas turbine having an exhaust gas apparatus, at least one generator, at least one thermal energy store, wherein the generator can be driven by the gas turbine, wherein the hot exhaust gas from the gas turbine is passed directly to a thermal energy store via the exhaust gas apparatus, wherein the thermal energy from the thermal energy store can be used to generate power.

An aircraft power plant comprising novel air management features for high-power fuel cell applications, the features combine supercharging and turbocharging elements with air and hydrogen gas pathways, utilize novel airflow concepts and provide for much stronger integration of various fuel cell drive components.

The invention relates to an aircraft propulsion system, comprising a main transmission unit (12) and at least two turbojet engines connected to the main transmission unit (12), respectively a first turbojet engine (14a) and a second turbojet engine (14b), each turbojet engine comprising a free turbine (24a, 24b), characterized in that the first turbojet engine (14a) comprises a heat exchanger (30) configured to recover some of the thermal energy from the exhaust gas at the outlet of the free turbine, and in that the propulsion system comprises at least one computer (28a, 28b) configured to control the two turbojet engines and to limit the acceleration and the deceleration of the first turbojet engine (14a) when neither of the turbojet engines is broken down, in order to limit the reactor power transients at the heat exchanger (30).

A method and system of wastewater evaporation uses a turbine-based wastewater evaporation system to convert wastewater to steam. The wastewater evaporation system includes a wastewater heating track disposed in the interior of the exhaust collector of the turbine in the flow path of turbine exhaust. The wastewater fluidly communicated therethrough is heated by the turbine exhaust and fluidly communicated to a plurality of atomization nozzles. The plurality of atomization nozzles direct atomized wastewater into the interior of the exhaust port of the turbine that is converted to steam in the presence of turbine exhaust within the exhaust port. The system may be disposed on a mobile trailer or skid to facilitate disposing the system on a job site and may be remotely controllable by a remote operator.