A combustion system includes a head end comprising a liquid fuel cartridge. The liquid fuel cartridge has liquid fuel injection ports and is configured to produce combustion products via a diffusion flame. A liner is configured to deliver the combustion products from the head end to an aft frame, and an injector having an outlet is located along the liner between the head end and the aft frame. The injector outlet delivers a stream of oxidant inwardly into the liner, such that a mixedness and a velocity of the combustion products are increased prior to the combustion products reaching the aft frame. A method of producing combustion products having characteristics of a premixed flame in a liquid fuel combustion system is also provided herein.

Provided are turbine engines and methods of operating thereof by heating and evaporating liquid fuels in a controlled manner prior to burning. Specifically, a fuel is heated and evaporated while avoiding coking. Coking is caused by pyrolysis when the fuel contacts a metal surface within a certain temperature range, which is referred herein to a coking temperature range. In the described methods, the fuel is transferred from one component, maintained below the coking temperature range, to another component, maintained above this range. The fuel is airborne and does not contact any metal surfaces during this transfer, and coking does not occur. In some examples, the fuel is also mixed with hot air during this transfer. The heated fuel, e.g., as an air-fuel mixture, is then supplied into a combustor, where more air is added to reach flammability conditions.

Provided are turbine engines and methods of operating thereof by heating and evaporating liquid fuels in a controlled manner prior to burning. Specifically, a fuel is heated and evaporated while avoiding coking. Coking is caused by pyrolysis when the fuel contacts a metal surface within a certain temperature range, which is referred herein to a coking temperature range. In the described methods, the fuel is transferred from one component, maintained below the coking temperature range, to another component, maintained above this range. The fuel is airborne and does not contact any metal surfaces during this transfer, and coking does not occur. In some examples, the fuel is also mixed with hot air during this transfer. The heated fuel, e.g., as an air-fuel mixture, is then supplied into a combustor, where more air is added to reach flammability conditions.

A system for producing high purity carbon monoxide and hydrogen as well as activated carbon includes a pyrolysis reactor, a gasifier, a combustion turbine, a boiler, a steam turbine, a combined cycle unit and an electrolysis unit. Liquid fuel from the pyrolysis reactor is provided to the combustion turbine. Liquid and gaseous fuels are provided to the boiler. Compressed oxygen from the electrolysis unit is provided to the combustion turbine. Electric power from the combustion turbine and steam turbine are provided to the electrolysis unit. The gasifier includes a preheat region, a gasification region, and a cooling region. CO.sub.2 and O.sub.2 are injected into the gasifier at multiple injection levels to create an isothermal gasification region to produce CO. The CO.sub.2 and O.sub.2 are preheated in a heat exchanger using the CO exiting from the gasifier prior to injection.

A process is provided for separating syngas fuel into a CO-rich stream for feeding to oxyfuel combustor means of CO2 turbine means and a H2-rich stream for feeding to air-fuel gas turbine means for generating power provides opportunity to realize operating and equipment advantages.

A process is provided for separating syngas fuel into a CO-rich stream for feeding to oxyfuel combustor means of CO2 turbine means and a H2-rich stream for feeding to air-fuel gas turbine means for generating power provides opportunity to realize operating and equipment advantages.

Described is a propulsion system (1) for hypersonic aircraft, having an air inlet (10) of a fluid (110), a containment duct (20) and an exhaust nozzle (30). The propulsion system (1) comprises a bypass duct (40) for a flow (100) of fluid (110), an air-breathing engine (22) and a rocket (23) configured for processing respective flows (22a, 23a) of fluid (110). The bypass duct (40), the air-breathing engine (22) and the rocket (23) are operatively associated with each other in such a way as to generate a thermodynamic-fluid interaction in a same portion of space (33) between the respective flows (40a, 22a, 23a) processed in an operating configuration of the propulsion system (1) and wherein the portion of space (33) is inside the containment duct (20).

Described is a propulsion system (1) for hypersonic aircraft, having an air inlet (10) of a fluid (110), a containment duct (20) and an exhaust nozzle (30). The propulsion system (1) comprises a bypass duct (40) for a flow (100) of fluid (110), an air-breathing engine (22) and a rocket (23) configured for processing respective flows (22a, 23a) of fluid (110). The bypass duct (40), the air-breathing engine (22) and the rocket (23) are operatively associated with each other in such a way as to generate a thermodynamic-fluid interaction in a same portion of space (33) between the respective flows (40a, 22a, 23a) processed in an operating configuration of the propulsion system (1) and wherein the portion of space (33) is inside the containment duct (20).

Modifying existing commercial jet engine technology to leverage the temperature and pressure available in the combustion of kerosene A-1 jet fuel (or other fuels) to include the Haber process (or other industrial processes requiring high temperatures and high pressures) presents possibilities for the creation of ammonia and other down-stream compounds suitable for atmospheric seeding of reflective or absorptive compounds. Compounds such as ammonia and urea (or other compoundsas time goes on) provide alternatives to high-altitude (20 km) seeding of sulfur dioxide (which is destructive to atmosphere, vegetation, and ozone alike). Additionally, the changes required to existing engine technology analogous to adding a catalytic converter to the exhaust system of a car, provide, through the leveraging of the strong chemical bond of atmospheric nitrogen (N2), additional overall energy output to the engine system (through heat) and the production of a potentially combustible liquid or gas (ammonia and down-stream ammonia compounds or other compounds) which could be used as a downstream fuel source by the engine itself.

A method for operating a rotating detonation engine, having a radially outer wall extending along an axis; a radially inner wall extending along the axis, wherein the radially inner wall is positioned within the radially outer wall to define an annular detonation chamber having an inlet and an outlet, wherein the method includes flowing liquid phase fuel along at least one wall of the radially inner wall and the radially outer wall in a direction from the outlet toward the inlet to cool the at least one wall and heat the liquid fuel to provide a heated liquid fuel; flowing the heated liquid fuel to a mixer at the inlet to reduce pressure of the heated liquid fuel, flash vaporize the heated liquid fuel and mix flash vaporized fuel with oxidant to produce a vaporized fuel-oxidant mixture; and detonating the mixture in the annular detonation chamber.