A bearing assembly for a turbine engine includes a first gas bearing configured to receive a load from a rotating shaft of the turbine engine, a transmission disk configured to receive the load from the first gas bearing, and a damping member coupled to a casing of a combustor section of the turbine engine. The transmission disk includes a gas delivery disk, which includes an axial opening configured to facilitate an axial flow through the gas delivery disk and a duct configured to facilitate a radial flow through the gas delivery disk to form the first gas bearing. The damping member is configured to receive the load from the transmission disk.

A nozzle for injecting liquid includes a nozzle body defining a flow channel and a swirl ante-chamber in fluid communication with the flow channel. An injection point orifice is defined in the swirl ante-chamber. The flow channel feeds into the swirl ante-chamber to impart a tangential flow component on fluids entering the swirl ante-chamber to generate swirl on a spray issuing from the injection point orifice. A second flow channel can be included in fluid communication with the swirl ante-chamber. The second flow channel feeds into the swirl ante-chamber in cooperation with or in opposition to the first flow channel. The first flow channel, second flow channel, and swirl ante-chamber are configured and adapted to adjust spray angle of a spray issuing from the injection point orifice by varying flow apportionment among the first and second flow channels.

A nozzle for injecting liquid includes a nozzle body defining a flow channel and a swirl ante-chamber in fluid communication with the flow channel. An injection point orifice is defined in the swirl ante-chamber. The flow channel feeds into the swirl ante-chamber to impart a tangential flow component on fluids entering the swirl ante-chamber to generate swirl on a spray issuing from the injection point orifice. A second flow channel can be included in fluid communication with the swirl ante-chamber. The second flow channel feeds into the swirl ante-chamber in cooperation with or in opposition to the first flow channel. The first flow channel, second flow channel, and swirl ante-chamber are configured and adapted to adjust spray angle of a spray issuing from the injection point orifice by varying flow apportionment among the first and second flow channels.

An assembly includes an injection system and an injector for an aircraft turbomachine combustion chamber. The system includes an aerodynamic bowl including a first end widening toward the downstream end and centred on a central axis of the injection system, this also including a central body along which a film of fuel is intended to flow in the downstream direction. The central body includes a second end widening toward the downstream end, the first and second widening ends between them delimiting an air through duct and the system includes motion inducing a device allowing a relative movement between the first widening end which is stationary and the second widening end, along the central axis of the injection system, by moving the central body relative to the injector.

An assembly includes an injection system and an injector for an aircraft turbomachine combustion chamber. The system includes an aerodynamic bowl including a first end widening toward the downstream end and centred on a central axis of the injection system, this also including a central body along which a film of fuel is intended to flow in the downstream direction. The central body includes a second end widening toward the downstream end, the first and second widening ends between them delimiting an air through duct and the system includes motion inducing a device allowing a relative movement between the first widening end which is stationary and the second widening end, along the central axis of the injection system, by moving the central body relative to the injector.

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 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.

The present disclosure provides methods for controlling volumetric flows of streams into a combustor, and particularly in a combustor utilized in a power production method. A controller can be used to receive a variety of inputs, carry out calculations, and output one or more signals that adjust one or more parameters of one or more of the streams entering the combustor. Such adjustments can be effective to normalize a volumetric flow rate between the combustor and a turbine immediately downstream from the combustor without requiring direct measurement of the volumetric flow rate between the combustor and the turbine immediately downstream from the combustor.

The present disclosure provides methods for controlling volumetric flows of streams into a combustor, and particularly in a combustor utilized in a power production method. A controller can be used to receive a variety of inputs, carry out calculations, and output one or more signals that adjust one or more parameters of one or more of the streams entering the combustor. Such adjustments can be effective to normalize a volumetric flow rate between the combustor and a turbine immediately downstream from the combustor without requiring direct measurement of the volumetric flow rate between the combustor and the turbine immediately downstream from the combustor.