Provided herein is a power generation system and method for transforming thermal energy, such as waste heat, into mechanical energy and/or electrical energy. The system employs features designed to accelerate start times, reduce size, lower cost, and be more environmentally friendly. Tire system may include multiple compressors on separate pinion shafts with multiple expanders, a temperature valve upstream of compressors with a mass management system downstream, an intercooler between compressors, and a cascade exchanger. In one embodiment, the system is configured to drive a synchronous generator, with the separate pinion shafts rotating at two separate, but constant, speeds.

The present application discloses a method of determining one or more fuel characteristics of an aviation fuel suitable for powering a gas turbine engine of an aircraft. The method comprises: determining, during use of the gas turbine engine, one or more exhaust content parameters by performing a sensor measurement on an exhaust of the gas turbine engine; and determining one or more fuel characteristics of the fuel based on the one or more exhaust parameters. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.

The present invention discloses a soundproof cabin of a turbine engine. The soundproof cabin is sleeved on the turbine engine. The soundproof cabin includes a cabin body, an induction noise reduction unit and a ventilation noise reduction unit, wherein the induction noise reduction unit and the ventilation noise reduction unit are disposed on the cabin body, the surrounding of which is filled with soundproof materials, the induction noise reduction unit is used to reduce the induction noise of the turbine engine, the ventilation noise reduction unit is used to reduce the noise of the ventilation system of the turbine engine. Beneficial effects: an induction noise reduction unit is disposed at an air inlet of the turbine engine to reduce the induction noise of the turbine engine; a ventilation noise reduction unit is disposed on the transmission direction of the turbine engine to reduce the ventilation and cooling noise of the turbine engine; the surrounding of the turbine engine is filled with soundproof materials to achieve the overall noise reduction around the turbine engine.

There are provided systems and methods for using fuel-rich partial oxidation to produce an end product from waste gases, such as flare gas. In an embodiment, the system and method use air-breathing piston engines and turbine engines for the fuel-rich partial oxidation of the flare gas to form synthesis gas, and reactors to convert the synthesis gas into the end product. In an embodiment the end product is methanol.

A nozzle for a combustor in which a fuel containing hydrogen is burned is provided. The nozzle includes a first tube disposed in a center of the nozzle and having a first diameter, a plurality of second tubes circumferentially disposed around the first tube to be spaced apart from the first tube and each having a second diameter smaller than that of the first tube, and a plurality of third tubes disposed around the first tube and each having a diameter smaller than the second diameter, wherein the first tube, the plurality of second tubes, and the plurality of third tubes are arranged in parallel with each other.

A method of identifying a fuel contained in a fuel tank of an aircraft and arranged to power a gas turbine engine of the aircraft is performed by processing circuitry of the aircraft and includes: obtaining at least one fuel characteristic of any fuel already present in the fuel tank prior to refuelling; determining at least one fuel characteristic of a fuel added to the fuel tank on refuelling; and calculating at least one fuel characteristic of the resultant fuel in the fuel tank after refuelling. The method may further controlling the propulsion system of the aircraft based on the calculated at least one fuel characteristic of the resultant fuel in the fuel tank after refuelling.

A power generation system includes a combustion system, a liquid supply system, and a vapor supply system. The combustion system is configured to generate power by combusting an alternative fuel. The liquid supply system is configured to channel a liquid alternative fuel to the combustion system. The vapor supply system is configured to channel a vapor alternative fuel to the combustion system. The combustion system is ignited by combusting the liquid alternative fuel from the liquid supply system and is operated by combusting the vapor alternative fuel from the vapor supply system.

A control system for a gas turbine includes a controller. The controller includes a processor configured to receive a plurality of signals comprising a temperature signal, a pressure signal, a speed signal, a mass flow signal, or a combination thereof, from sensors disposed in the gas turbine system. The processor is further configured to apply the plurality of signals as input to a heating value model. The processor is also configured to execute the heating value model to derive a heating value for a fuel combusted by the gas turbine system. The processor is additionally configured to control operations of the gas turbine system based on the heating value for the fuel.

A system for gasifying a carbonaceous feedstock, such as municipal waste, to generate power includes a devolatilization reactor that creates char from the feedstock and a gasifier that creates a product gas from both the char and from volatiles released when devolatilizing the feedstock. The product gas is reacted in a fuel cell to create electrical energy and process heat. The process heat is used to heat the devolatilization reactor and the gasifier. The gasifier comprises a plurality of configurable circuits that can each be tuned to meet the individual needs of the char material being gasified.

A method of operating an aircraft that includes a propulsion system. The propulsion system includes a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine. The method includes: determining at least one fuel characteristic of the fuel arranged to be provided to the gas turbine engine; and controlling the propulsion system based on the at least one fuel characteristic.