A fuel burner includes a tube extending from a first end to a second end and having an outer surface and an inner surface defining a central passage. The central passage is supplied at the first end with a mixture of air and combustible fuel pre-mixed upstream of the tube. The second end is closed by an end wall in a fluid-tight manner. The tube includes fluid directing structure for directing the pre-mixed mixture radially outward from the central passage to an exterior of the tube such that the pre-mixed mixture rotates radially about the central axis along the exterior of the tube.

A supersonic combustor containing an injector module, a combustor core and an outer shell. The injector module houses both fuel and oxidizer nozzles. The combustor core contains grooves within which the combustion process takes place. The outer shell holds both the injector module and the combustor core and allows for other cooling, mounting and structural mechanisms required for operation.

A deflector for a gas turbine engine combustor. The combustor includes a liner defining a combustion zone and a mixer assembly configured to supply the combustion zone with a predetermined mixture of fuel and air. The deflector includes a deflector body configured to couple to the liner. The deflector body includes a first surface configured to reflect thermal radiation to a predetermined focal area, and an aperture extending through the deflector body and configured to receive the mixer assembly therethrough.

The invention relates to an air/fuel injection system for a turbomachine, comprising: —an injector comprising a duct and an injection nose, arranged inside said duct, which extends from upstream to downstream along a longitudinal axis; —a mixer device comprising a bowl comprising an annular inlet, forming the inlet of the mixer device, from which there extends a conical portion flared in the downstream direction, said mixer device being arranged downstream of the injection nose; the injection system being characterized in that the injector comprises an air-injection annulus extending from the duct and from which there extends a connection ring comprising a divergent portion, said ring being arranged externally around the annular inlet of the mixer device.

The proposed solution relates to a nozzle assembly for a combustion chamber of an engine, having at least one nozzle, which includes a nozzle head that extends along a nozzle longitudinal axis and has at least one nozzle exit opening for injecting fuel into a combustion space of the combustion chamber, and at least one air-guiding duct, by way of which a swirl-affected air flow can be created in the direction of the combustion space along an outer lateral surface of the nozzle head.

At least one guide element which protrudes on the outer lateral surface of the nozzle head is in a flow path for the air flow of the at least one air-guiding duct and is configured to guide at least a part of the air flow radially inwards in relation to the nozzle longitudinal axis into a central injection region downstream of the nozzle exit opening.

A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can have a combustor with a combustor liner at least partially defining a combustion chamber, as well as a fuel-air mixer including at least one set of mixing tubes.

A method of operating a combustor of a turbomachine on a total fuel input that contains a concentration of hydrogen that is greater than about 80% is provided. The method includes injecting a first mixture of air and a first fuel containing a first amount of hydrogen into the primary combustion zone of the combustor to generate a first flow of combustion gases having a first temperature. The method further includes injecting, with one or more premix injectors disposed downstream of the fuel nozzles, a second mixture of air and a second fuel containing a second amount of hydrogen into the secondary combustion zone of the combustor to generate a second flow of combustion gases having a second temperature. The method further includes separately injecting a third fuel into secondary combustion zone to generate a third flow of combustion gases having a third temperature.

A ferrule in a fuel-air mixer assembly. The ferrule includes a body having (i) a plurality of channels having sidewalls, the plurality of channels leading to a corresponding plurality of exit openings, the plurality of channels configured to guide a first airflow therein and (ii) a plurality of cascade holes formed within the sidewalls of the plurality of channels and defining a plurality of passageways therein that are transverse to the plurality of channels. The ferrule also includes a plurality of airflow modifiers provided within the plurality of channels. The plurality airflow modifiers are configured to reduce a velocity of the first airflow when the first airflow exits through the plurality of exit openings and to generate low velocity vortex pairs to reduce interaction of the first airflow with a second airflow provided through primary vanes located downstream of the plurality of exit openings of the plurality of channels.

A burner assembly includes a plurality of bumers for mixing fuel and air. Each of the plurality of burners includes: at least one fuel nozzle for injecting the fuel; and a mixing passage into which the fuel injected from the at least one fuel nozzle and the air are introduced. Each fuel nozzle includes a protruding portion protruding upstream of an inlet of the mixing passage in a flow direction of the air. Each fuel nozzle includes a fuel injection hole formed on a side surface of the protruding portion. At least a portion of a first air passage for flowing the air is formed inside the protruding portion. The first air passage includes: an inlet formed on a surface of the protruding portion on an upstream side of the fuel injection hole in the flow direction of the air; and an outlet formed on a side surface of the protruding portion or a passage wall of the mixing passage. At least a portion of the outlet is formed downstream of the fuel injection hole in the flow direction of the air.

A cartridge tip includes a main body having an outer annular wall and an inner core each extending between a respective upstream end and a respective downstream end. The inner core is radially spaced apart from the outer annular wall such that an annular air passage is defined at least partially between the outer annular wall and the inner core. A pilot fuel circuit extends between a pilot inlet defined in the upstream end of the inner core and a pilot outlet defined in a downstream end of the inner core. The pilot fuel circuit extends at least partially along an axial centerline of the cartridge tip. A main fuel circuit extends between a main inlet in the upstream end of the inner core and a plurality of main outlets circumferentially spaced apart from one another and disposed upstream from the from the pilot outlet.