An electric motor assisted airblast injector design for gas turbines is disclosed. The electric motor assisted airblast injector assembly consists of an airblast injector, a high speed electric motor and a compressor. The electric motor assisted airblast injector is designed to improve engine light-off and starting reliability without using a fuel staging system to incorporate pressure injectors. A high speed motor is activated during starting to drive a compressor for locally producing pressurized air without sacrificing combustor performance. The pressurized air exiting the air swirler with high velocity penetrates perpendicularly into the fuel spray cone obtained by orifices in the fuel swirler. The amount of pressurized air through the compressor is controlled by motor speed to match fuel starting schedule and produce fuel/air mixture within flammability limits. After engine starting, the high speed motor may cut off as sufficient air pressure differential is available across the combustor.

A method of manufacturing a fuel component for a gas turbine engine combustor includes additive manufacturing a sacrificial core and manufacturing a fuel component body at least partially around the sacrificial core. The sacrificial core is at least partially removed to at least partially define an internal geometry of the fuel component. An additively manufactured sacrificial core for a fuel component of a gas turbine engine combustor includes a first structure and a second structure. The first structure at least partially defines a first passage of the fuel component. The second structure at least partially defines a second passage of the fuel component. The second structure at least partially surrounds the first structure.

An electric motor assisted airblast injector design for gas turbines is disclosed. The electric motor assisted airblast injector assembly consists of an airblast injector, a high speed electric motor and a compressor. The electric motor assisted airblast injector is designed to improve engine light-off and starting reliability without using a fuel staging system to incorporate pressure injectors. A high speed motor is activated during starting to drive a compressor for locally producing pressurized air without sacrificing combustor performance. The pressurized air exiting the air swirler with high velocity penetrates perpendicularly into the fuel spray cone obtained by orifices in the fuel swirler. The amount of pressurized air through the compressor is controlled by motor speed to match fuel starting schedule and produce fuel/air mixture within flammability limits. After engine starting, the high speed motor may cut off as sufficient air pressure differential is available across the combustor.

An internal combustion engine that uses stratification of gasses for compressing air is disclosed. The engine uses a combustion chamber that delivers products of combustion into an elongated compression chamber to drive the products of combustion against resident air within the elongated compression chamber, and push the resident air into a compressed air chamber. After driving the resident air into the compressed air chamber, the products of combustion are used with work-producing devices. Air is then driven into the compression chamber by an air pump or low-pressure compressor to once again fill the compression chamber with fresh air. The air in the compressed air chamber is then delivered to the combustion chamber and used for combustion. Fuel is delivered to the combustion chamber by a fuel injector, and ignited by the heat of the compressed air and/or a glow plug, spark plug, or similar ignition device.

A fuel mixture distributor for a turbine engine assembly includes a mixing chamber that is disposed about a central axis from a back wall to an outlet of a combustion chamber, and a fuel inlet that extends into the mixing chamber along the central axis. The fuel inlet includes a plurality of fuel openings that are angled relative to the central axis and a first air inlet that encircles the mixing chamber and is spaced apart from the fuel inlet. The first air inlet includes a plurality of first air openings that introduce a first air flow into the mixing chamber. A second air inlet introduces a secondary air flow that is axially forward of the fuel inlet and the first air inlet and proximate to the outlet of the mixing chamber.

The gas turbine system comprises a combustor adapted to combust a fuel and an oxidant and generate pressurized hot combustion gas and a turbine fluidly coupled to the combustor and rotated by expansion of the pressurized hot combustion gas from the combustor. A heat exchanger is fluidly coupled to the turbine and adapted to cool expanded combustion gas exhausted from the turbine. A main oxidant supply line is adapted to supply oxidant to the combustor through the heat exchanger. The oxidant streaming through the heat exchanger is in heat exchange relationship with combustion gas exhausted from the turbine. A fuel supply line supplies fuel to the combustor. A secondary oxidant supply line is adapted to supply oxidant in the fuel supply line upstream of a fuel control valve. Also disclosed is a method of operating the system.