Abstract: A gas turbine combustor is provided. The gas turbine combustor has a pilot nozzle having a pilot fuel injection port at a downstream end, in terms of the direction flow of a fuel, and lies on the axial centreline of the gas turbine combustor. It also has a main combustion zone, downstream of the pilot nozzle, and a pilot cone projecting from the vicinity of the pilot fuel injection port and having a diverged end adjacent to the main combustion zone, wherein a half angle of the pilot cone is increasing in the downstream direction.

Abstract: A gas-turbine burner having a plurality of main swirl generators, each having an inlet flow opening formed by the main swirl generator edge, is provided. In order to achieve a uniform flow of combustion air through the main swirl generator, the gas-turbine burner has an inlet-flow guide means with a flow guide surface which runs from one of the inlet-flow openings to an adjacent inlet-flow opening, to which the main swirl generator edges which form the inlet-flow openings are connected, and the flow guide surface widens from there radially upwards. The main swirl generators are central-symmetrically arranged around a pilot burner and the flow guide surface runs radially outside the main swirl generators.

Abstract: A swirl generator, a method for preventing flashback in a burner with a swirl generator and a burner are provided. The swirl generator includes a central fuel distributor element, an outer wall enclosing the central fuel distributor element and bounding an axial flow channel for combustion air, swirl vanes extending in a radial direction to the outer wall and giving the flowing combustion air a tangential flow component, and a separating wall enclosing the central fuel distributor element and being positioned radially within the outer wall. The separating wall divides the flow channel into a radially inner channel segment and a radially outer channel segment. The radially inner channel segment allows the combustion air to pass without giving it a tangential flow component or while giving it a tangential flow component counter to the orientation of the tangential flow component in the radially outer channel segment.

Abstract: A method is for operating a burner of a gas turbine. A fossil fuel is gasified and the gasified fossil fuel is fed as synthesis gas into the burner for combustion. The burner is connected to the gas turbine. The synthesis gas is divided into a first partial current and a second partial current and the partial currents are each fed into the burner for combustion. A power plant, particularly a gas and steam turbine system, includes a gasification device for a fossil fuel.

Abstract: A miniaturized spring element is intended to be particularly suitable for use as a beam probe or cantilever for detecting atomic or molecular forces, in particular in an atomic force microscope, and, to this end, is intended to make it possible to detect its deflection in a particularly reliable manner and with high resolution. For this purpose, the spring element contains a basic body which is formed from a matrix containing embedded nanoparticles or defects. The spring element is produced using the principle of local deposition with focused energetic particles or electromagnetic waves or by pyrolytically induced deposition.

Abstract: A combustion chamber according to the invention, in particular for a gas turbine, includes at least one combustion chamber wall through which cooling fluid flows and at least one resonator device. The combustion chamber according to the invention is distinguished in that the resonator device is integrated into the combustion chamber wall in such a way that it has the cooling fluid flow passing there through.

Abstract: The invention relates to a combustion chamber of a gas turbine, inside of which a supplied fuel is reacted with supplied combustion air in order to produce a working medium. The inside of the combustion chamber wall is provided with a lining formed from a number of heat shield elements. The or each heat shield element, together with the combustion chamber wall, forms an interior space that can be subjected to the action of a coolant. The aim of the invention is to provide a combustion chamber with a comparatively simple design that has a high system efficiency. To this end, the invention provides that a flow element is placed in the respective interior space while serving to effect a locally specific control of the flow of coolant.

Abstract: A combustion chamber according to the invention, in particular for a gas turbine, includes at least one combustion chamber wall through which cooling fluid flows and at least one resonator device. The combustion chamber according to the invention is distinguished in that the resonator device is integrated into the combustion chamber wall in such a way that it has the cooling fluid flow passing there through.

Abstract: The invention relates to a method for operating a burner (7) of a gas turbine (2), whereby a fossil fuel (B) is gasified and the gasified fossil fuel (B) is fed as synthesis gas (SG) into the burner (7) for combustion, said burner being connected to the gas turbine (2). The synthesis gas (SG) is divided into a first partial current (SG1) and a second partial current (SG2) and the partial currents (SG1, SG2) are each fed into the burner (7) for combustion. The invention also relates to a power plant (3), particularly a gas and steam turbine system (1), comprising a gasification device (132) for a fossil fuel (B).

Abstract: A printing press web tensioning system comprising a motion driven belt drive for the paper reel, dancer roll means, pneumatic means for changing the tension required for deflection of the dancer roll and control means for automatically varying operating values of subcomponents of the tensioning system to carry out webbing, slack removal, start up and normal running operation.