An assembly is provided for a turbine engine with a flowpath. This assembly includes a fuel source and an engine component. The engine component forms a peripheral boundary of the flowpath. The engine component includes a component internal passage. The engine component is configured to receive fuel from the fuel source. The engine component is configured to crack at least some of the fuel within the component internal passage thereby cooling the engine component and providing at least partially cracked fuel. The assembly is configured to direct the at least partially cracked fuel into the flowpath for combustion.

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.

A combustor includes a combustor liner defining a combustion chamber and a fuel and air mixing body connected to the combustor liner to deliver mixed fuel and air into the combustion chamber. The mixing body includes an inner housing member centered on a center axis and an intermediate housing member. A mixing passage is defined between the inner and intermediate housing members. The mixing passage extends along a direction from an upstream end to a downstream end with a circumferential component, a component in an axially downstream direction, and a radially inward component with at least one air inlet into the mixing passage. A fuel supply extends into the mixing passage at a location downstream of the air inlet. The mixing passage extends downstream to supply fuel and air into the combustion chamber. A gas turbine engine is also disclosed.

The present disclosure provides an afterburner structure with fuel injection nozzles. In the condition of a stable inlet flow, the present disclosure forms a sweeping oscillating jet with a certain frequency at the outlet under an alternate feedback action of a feedback channel and the fluid's Coanda effect, so that the spatial uniformity of the fuel injection is improved; Therefore, without increasing the structural complexity of current afterburner of the turbo-engine and the combustion chamber of the subsonic combustion ramjet, the atomization performance and the uniformity of the oil-gas mixture in the afterburner/combustion chamber of the ramjet can be greatly improved, the combustion efficiency and combustion instability of the engine can be improved and meanwhile the length of the afterburner and the combustion chamber of the subsonic combustion ramjet is shortened.

A fluid nozzle includes a first fluid circuit, a second fluid circuit spaced apart from the first fluid circuit and a fuel circuit. The fuel circuit is defined between the first and second fluid circuits and between a first fuel circuit wall and a second fuel circuit wall. A ring-shaped permeable barrier is positioned between the first and second fuel circuit walls configured and adapted to provide a controlled resistance to fuel flow. A fuel distributor includes a first fuel circuit wall and a second fuel circuit wall spaced apart from the first fuel circuit wall. A fuel circuit is defined between the first and second fuel circuit walls. A ring-shaped permeable barrier is positioned between first and second fuel circuit walls. A combustion assembly includes a combustor housing, a combustor dome positioned at an upstream end of the combustor housing, and a fluid nozzle positioned adjacent the combustor dome.

An energy extraction system according to an exemplary embodiment of this disclosure, among other possible things includes an ammonia fuel storage tank assembly that is configured to store a liquid ammonia fuel, a thermal transfer assembly that is configured to transform the liquid ammonia fuel into a vaporized ammonia based fuel, a turbo-expander that is configured to expand the vaporized ammonia based fuel to extract work, and an energy conversion device that is configured to use the vaporized ammonia based fuel from the turbo-expander to generate a work output.

The combustion device includes: a compressor that compresses combustion air; a combustor that combusts the compressed combustion air and fuel ammonia; and an ammonia injector that injects the fuel ammonia into the combustion air during or before compression of the combustion air by the compressor and cools the combustion air.

A combustor with axially staged fuel injection includes an endcover and a fuel injector that extends axially downstream from the endcover. The fuel injector includes a cylindrical shell formed by an outer wall and an inner wall. A first plurality of outlets is circumferentially spaced across the inner wall. A first plurality of premix channels is defined between the outer wall and the inner wall. Each premix channel of the first plurality of premix channels is in fluid communication with a fuel supply, a compressed air supply and a respective outlet of the first plurality of outlets.

A fuel injector for injecting an over-enriched fuel and air mixture to the combustion chamber of an internal combustion engine includes a spray nozzle, a gaseous carrier, a fuel mixing and evaporation chamber and an injector nozzle. During operation, both a liquid fuel and the gaseous carrier are supplied to the fuel mixing and evaporation chamber of the injector through the spray nozzle, where they are mixed and evaporated as a result of elevated temperature, and the mixture reaches the combustion chamber. The gaseous carrier is air or, flue gas, at elevated pressure and temperature and having a composition that prevents the initiation of flame combustion, and the gaseous carrier has an oxygen content low enough to prevent the initiation of combustion, even under conditions of elevated pressure and temperature.

A fuel injection device (70) includes a nozzle body (72) and a stem portion (110) connected to the rear end of the nozzle body at an angle. The stem portion is provided at a free end thereof with an annular wall member (128) defining a recess that receives the rear end of the nozzle body. The stem portion is covered by a heat insulating sleeve (122), and a part of the heat insulating sleeve adjacent to the free end of the stem portion is provided with a cutout (122B) exposing a part of the outer circumferential surface (128A) of the annular wall member. The exposed part of the annular wall member is provided with a heat insulating groove (130) opening at an end surface (128B) of the annular wall member facing the nozzle body.