A fuel injector includes: a pilot fuel injection portion including a pilot fuel supply block and a pilot shroud; a main fuel injection portion arranged so as to surround the pilot fuel injection portion from an outer side in a radial direction; and an intermediate air passage arranged between the pilot fuel injection portion and the main fuel injection portion. The pilot shroud includes: a throat located at a downstream side of the pilot fuel supply block; and a flame holding portion surrounding flame located at the downstream side of the throat. An air injection slit is formed at the flame holding portion, the air injection slit being configured to inject compressed air of the intermediate air passage in a direction along an inner peripheral surface of the flame holding portion such that the compressed air covers the inner peripheral surface over an entire periphery.

An assembly is provided for an engine. This engine assembly includes an engine structure and a fuel injector. The engine structure includes an injector receptacle. The injector receptacle extends longitudinally through the engine structure along a centerline. The fuel injector is received by the injector receptacle. The fuel injector includes a fuel nozzle and a splash plate. The fuel nozzle is configured to direct fuel out of the fuel injector to impinge against the splash plate.

A gas turbine combined-cycle power plant can comprise a gas turbine engine, a heat recovery steam generator, a steam turbine, a fuel regasification system and a Rankine Cycle system. The gas turbine engine can comprise a compressor for generating compressed air, a combustor that can receive a fuel and the compressed air to produce combustion gas, and a turbine for receiving the combustion gas and generating exhaust gas. The heat recovery steam generator is configured to generate steam from water utilizing the exhaust gas. The steam turbine is configured to produce power from steam from the heat recovery steam generator. The fuel regasification system is configured to convert the fuel from a liquid to a gas before entering the combustor. The Organic Rankine Cycle system is configured to cool compressed air extracted from the compressor to cool the gas turbine engine, and heat liquid fuel entering the fuel regasification system.

A fuel system for a vehicle having an engine is provided. The fuel system including: a fuel tank for holding a hydrogen fuel in a liquid phase; a fuel delivery assembly extending from the fuel tank to the engine for providing the hydrogen fuel from the fuel tank to the engine; a vaporizer in communication with the fuel delivery assembly for heating the hydrogen fuel in the liquid phase to a gaseous phase, to a supercritical phase, or both; and a high pressure pump in fluid communication with the fuel delivery assembly at a location downstream of the vaporizer for inducing a flow of the hydrogen fuel through the fuel delivery assembly to the engine.

A fuel system for a power generator using hydrogen fuel and a method of recovering a safety marker added to the hydrogen fuel. The hydrogen fuel may be stored in a tank and delivered, in at least one of a gaseous phase and a supercritical phase, to a power generator. The hydrogen fuel is delivered with a fuel delivery assembly and contains at least one safety marker when the fuel is in the fuel delivery assembly. The at least one safety marker is separated from the hydrogen fuel, using, for example, a separator. The at least one safety marker separated from the hydrogen fuel is stored in a safety marker storage tank. The safety marker may be a visual safety marker, such as a noble gas, or an odorant.

A powerplant is provided that includes a pre-burner, a combustor, a power turbine, a mechanical load and a propellant system. The combustor is fluidly coupled with and downstream of the pre-burner. The power turbine is fluidly coupled with and downstream of the combustor. The mechanical load is rotatably driven by the power turbine. The propellant system is configured to direct fluid oxygen and fluid hydrogen to the pre-burner to provide an oxygen rich fuel mixture for combustion within the pre-burner. The propellant system is also configured to direct the fluid hydrogen to the combustor for combustion within the combustor with oxygen within combustion products received from the pre-burner.

Aircraft engines include a turbine engine comprising a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the burner section passes through the turbine section, a condensing assembly arranged downstream of the turbine section of the turbine engine along the core flow path, and an exhaust compressor arranged downstream of the condensing assembly along the core flow path. The condensing assembly is configured to reduce a mass flow of the exhaust compressor by condensing water vapor from the core flow and removing liquid water from the core flow.

A fuel supply system for a combustion section of a turbine engine. The turbine engine including a heat source. The fuel supply system comprising a first fuel supply having a liquid fuel, a second fuel supply having a first gaseous fuel, and a heat exchanger fluidly coupled to the first fuel supply and the heat source. The heat exchanger producing a heat sufficient to change the liquid fuel to a second gaseous fuel that is the same type of fuel as the first gaseous fuel.

A fuel delivery system for a gas turbine engine comprises a cryogenic fuel tank, a first fuel line for connection to the cryogenic fuel tank, a fuel pump connected to receive fuel via the first fuel line, a plurality of fuel lines connecting the fuel pump to a combustor of the gas turbine engine, a controller configured to operate the fuel delivery system, a purge gas tank connected to the first fuel line and configured to store a purge gas for purging the plurality of fuel lines and a fuel gas tank connected to the first fuel line and configured to store a fuel gas for flushing purge gas from the plurality of fuel lines.

A combustor nozzle capable of injecting fuel uniformly, and a combustor and gas turbine including the same are provided. The combustor nozzle includes a main cylinder having a fuel passage through which fuel flows, a nozzle shroud surrounding the main cylinder, and a fuel injection module disposed between the main cylinder and the nozzle shroud to inject fuel, wherein the fuel injection module includes a plurality of first struts protruding from the main cylinder and having strut injection holes to inject fuel, a first support tube coupled to outer ends of the first struts, and a plurality of second struts protruding from the first support tube and having strut injection holes to inject fuel, and each of the first and second struts includes a swirl guide inclined with respect to a longitudinal direction of the main cylinder.