Abstract: The present invention relates to a gas-turbine combustion chamber having a combustion chamber wall, to which combustion chamber tiles are fastened by means of bolts, where in the bolt fastening area in the combustion chamber wall at least one impingement cooling hole is provided, the center axis of which is inclined to the center axis of the bolt and intersects a transition area between the bolt and the combustion chamber tile.

Abstract: The present invention relates to a gas-turbine combustion chamber having a combustion chamber wall, to which combustion chamber tiles are fastened by means of bolts, where in the bolt fastening area in the combustion chamber wall at least one impingement cooling hole is provided, the center axis of which is inclined to the center axis of the bolt and intersects a transition area between the bolt and the combustion chamber tile.

Abstract: The present invention relates to a pressure-measuring device for measuring dynamic pressures in the high-temperature range, with a pressure line connected to a volume subjected to pressure and with a pressure sensor which is arranged at a distance from the inlet area of the pressure line to the volume, wherein the pressure line is provided with at least one pinhole diaphragm and connected to an additional damping volume, as well as to the use of the pressure-measuring device in a combustion chamber of a gas turbine.

Abstract: A combustion chamber head for a gas turbine, with the gas turbine having a substantially annular outer combustion chamber wall, at least one substantially annular inner combustion chamber wall, and several burners 106 distributed around a circumference of the gas turbine. Several segment-like head segments are arranged over the circumference in equal number to the number of burners and extend in the radial direction between the inner combustion chamber wall and the outer combustion chamber wall and in the circumferential direction between radial planes formed by the burner axes.

Abstract: The present invention relates to a pressure-measuring device for measuring dynamic pressures in the high-temperature range, with a pressure line connected to a volume subjected to pressure and with a pressure sensor which is arranged at a distance from the inlet area of the pressure line to the volume, wherein the pressure line is provided with at least one pinhole diaphragm and connected to an additional damping volume, as well as to the use of the pressure-measuring device in a combustion chamber of a gas turbine.

Abstract: A gas turbine combustion chamber has a starter film for cooling the combustion chamber wall, and a combustion chamber head, into which cooling air can be introduced and which is confined to the combustion chamber by a heat shield (5). A base plate (2) is arranged at a certain distance from the heat shield (5) and the base plate (2) is provided with several openings (6) in its rim area for passing the cooling air. Center axes (17) of the openings (6) are inclined at a shallow angle (?) relative to the combustion chamber wall (4).

Abstract: A combustion chamber head of a gas turbine has a confinement enclosing a dampening volume (207) and including a combustion chamber-opposite confinement (206) and a combustion chamber-side confinement (210). The combustion chamber-side confinement (210) is provided as perforated wall (210). In the edge area of the combustion chamber-side confinement (210), cooling air can be routed onto the combustion chamber-side confinement (210) via recesses (203) in the confinement (206). This cooling air, which flows along the combustion chamber-side confinement (210), crosses the cooling air flow through the perforated wall (210) in the combustion chamber (101) without mixing with the latter, as both are separated by walls.

Abstract: A combustion chamber head of a gas turbine has a substantially annular combustion chamber outer wall 18 as well as a substantially annular combustion chamber inner wall 42 and several burners 6 distributed around the circumference. The combustion chamber head 5 has an inflow-side wall 13 which together with a wall 14 facing the combustion chamber 7 forms a combustion chamber head volume 15. The inflow-side wall 13 is provided with at least one inflow opening 32, the wall 14 facing the combustion chamber 7 is provided with at least one outflow opening 17 for connecting the combustion chamber head volume 15 to the combustion chamber 7, and at least one cooling air duct 29 is provided in the wall 14 facing the combustion chamber 7. A method for cooling and damping of the combustion chamber head is also disclosed.

Abstract: A gas turbine combustion chamber includes an essentially cylindrical flame tube 2, which is made of a ceramic material and circumferentially divided into several circumferential elements 10, 11, 12.

Abstract: A combustion chamber head for a gas turbine, with the gas turbine having a substantially annular outer combustion chamber wall, at least one substantially annular inner combustion chamber wall, and several burners 106 distributed around a circumference of the gas turbine. Several segment-like head segments are arranged over the circumference in equal number to the number of burners and extend in the radial direction between the inner combustion chamber wall and the outer combustion chamber wall and in the circumferential direction between radial planes formed by the burner axes.

Abstract: A combustion chamber for a gas turbine has a metallic supporting structure 6 and several circumferentially distributed ceramic bodies 2 attached to the supporting structure 6. The ceramic bodies 2 each have a straight hollow tubular profile and are arranged as individual segments At least one hollow metallic body 1 having air-passage holes 5 for the passage of cooling air is provided in each ceramic body 2.

Abstract: A gas turbine combustion chamber has a starter film for cooling the combustion chamber wall, and a combustion chamber head, into which cooling air can be introduced and which is confined to the combustion chamber by a heat shield (5). A base plate (2) is arranged at a certain distance from the heat shield (5) and the base plate (2) is provided with several openings (6) in its rim area for passing the cooling air. Center axes (17) of the openings (6) are inclined at a shallow angle (?) relative to the combustion chamber wall (4).

Abstract: A combustion chamber head of a gas turbine has a confinement enclosing a dampening volume (207) and including a combustion chamber-opposite confinement (206) and a combustion chamber-side confinement (210). The combustion chamber-side confinement (210) is provided as perforated wall (210). In the edge area of the combustion chamber-side confinement (210), cooling air can be routed onto the combustion chamber-side confinement (210) via recesses (203) in the confinement (206). This cooling air, which flows along the combustion chamber-side confinement (210), crosses the cooling air flow through the perforated wall (210) in the combustion chamber (101) without mixing with the latter, as both are separated by walls.

Abstract: A gas turbine combustion chamber includes an essentially cylindrical flame tube 2, which is made of a ceramic material and circumferentially divided into several circumferential elements 10, 11, 12.

Abstract: A combustion chamber for a gas turbine has a metallic supporting structure 6 and several circumferentially distributed ceramic bodies 2 attached to the supporting structure 6. The ceramic bodies 2 each have a straight hollow tubular profile and are arranged as individual segments At least one hollow metallic body 1 having air-passage holes 5 for the passage of cooling air is provided in each ceramic body 2.