Abstract: A combustion chamber of a gas turbine, wherein downstream of the combustion chamber an expansion turbine with a turbine inlet is arranged. The combustion chamber has an annular design with a component, which has a chamber wall and an end wall arranged next to the turbine inlet and a corner as connection of the chamber wall and the end wall. To increase the cooling performance the component further has an air guidance piece arranged at a distance from the chamber wall with a cooling channel in-between. Further, the corner is fluid tight, wherein the distance of the air guidance piece to the end wall is at least 0.5-times and at most 2-times the lowest width of the cooling channel.

Abstract: A combustion chamber of a gas turbine, wherein downstream of the combustion chamber an expansion turbine with a turbine inlet is arranged. The combustion chamber has an annular design with a component, which has a chamber wall and an end wall arranged next to the turbine inlet and a corner as connection of the chamber wall and the end wall. To increase the cooling performance the component further has an air guidance piece arranged at a distance from the chamber wall with a cooling channel in-between. Further, the corner is fluid tight, wherein the distance of the air guidance piece to the end wall is at least 0.5-times and at most 2-times the lowest width of the cooling channel.

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.