Abstract: A burner supply tube, and a burner arrangement having such a burner supply tube, which includes a tube wall extending having a tube diameter and at least one integrated fuel channel extending from a fuel input at an upstream tube end to a fuel output at a downstream tube end. To enable an integrated design, the fuel channel is along the majority of the tube length helical with a gradient of at least 0.5 times and at most 5 times the tube diameter.

Abstract: A fuel nozzle for use in a combustion arrangement of a gas turbine includes a main body extending from a cold side to an opposite hot side and at least five air passages arranged next to each other extending from the cold side towards the hot side. A fuel distribution chamber is arranged within the main body next to the cold side, wherein the air passages cross the fuel distribution chamber separated by passage walls. To inject fuel into the air passages, fuel holes are arranged within the passage walls.

Abstract: A turbomachine component having a solid body with an elongated clearance, a channel located within the clearance of that body, where the channel is free of struts between the channel and a section of the body which is surrounding the channel to provide a continuous thermal insulation gap between the channel and the section of the body. The channel and the body are built in an additive manufacturing generation process synchronously layer by layer, from a metallic powder, wherein successive layers are selectively fused to build the body and the channel. The channel is arranged inside the body as a loose component, loose inside of the clearance and distant to the body. Spacer elements are provided, wherein each of the spacer elements is physically attached to only one of its ends either to the channel or to the body and put the channel in position and distant to the body.

Abstract: A turbomachine component having a solid body with an elongated clearance, a channel located within the clearance of that body, where the channel is free of struts between the channel and a section of the body which is surrounding the channel to provide a continuous thermal insulation gap between the channel and the section of the body. The channel and the body are built in an additive manufacturing generation process synchronously layer by layer, from a metallic powder, wherein successive layers are selectively fused to build the body and the channel. The channel is arranged inside the body as a loose component, loose inside of the clearance and distant to the body. Spacer elements are provided, wherein each of the spacer elements is physically attached to only one of its ends either to the channel or to the body and put the channel in position and distant to the body.

Abstract: An assembly includes a gas turbine and a heat exchanger for heating up a gas turbine process fluid by thermal energy. The gas turbine has a compressor, a combustor and a turbine downstream of the combustor, wherein the thermal energy is from the solar receiver. To improve efficiency and reduce power generation fluctuations, the assembly includes a first line to conduct the gas turbine process fluid downstream a compression by the compressor to the heat exchanger, and a second line to conduct the gas turbine process fluid from the heat exchanger to the combustor to generate hot combustion gas from the warmed up gas turbine process fluid burning fuel in the combustor.

Abstract: A method for operating a gas turbine engine unit with a compressor section operable by a O2-rich first working fluid and a turbine section operable by a O2-lean second working fluid, and a unit for an oxygen extraction process, the method including: discharging all O2-rich first working fluid of the compressor section from a compressor of the compressor section to the unit for the oxygen extraction process so that all O2-rich first working fluid of the compressor section is used for the oxygen extraction process, extracting O2 from the O2-rich first working fluid by an oxygen extraction process, cooling at least one wall of the at least one combustion chamber of the combustion section by the O2-rich first working fluid while bypassing the at least one combustion chamber and heating the O2-rich first working fluid while by-passing the at least one combustion chamber.

Abstract: An assembly includes a gas turbine and a heat exchanger for heating up a gas turbine process fluid by thermal energy. The gas turbine has a compressor, a combustor and a turbine downstream of the combustor, wherein the thermal energy is from the solar receiver. To improve efficiency and reduce power generation fluctuations, the assembly includes a first line to conduct the gas turbine process fluid downstream a compression by the compressor to the heat exchanger, and a second line to conduct the gas turbine process fluid from the heat exchanger to the combustor to generate hot combustion gas from the warmed up gas turbine process fluid burning fuel in the combustor.