Abstract: An aerofoil for a gas turbine, wherein the aerofoil extends from a platform and includes a concave and a convex side that meet at a trailing edge and a leading edge. The aerofoil has a tip and one or more voids. Each of the one or more voids is completely encapsulated within the aerofoil such that each of the one or more voids is not fluidly connected with an outside of the aerofoil. Moreover, a total volume of the one or more voids is between 5 percent and 30 percent of a volume of the aerofoil.

Abstract: A rotor component for a rotor assembly of a fluid energy machine, particularly of a gas turbine, a steam turbine, a compressor or the like, wherein the rotor component is at least partly made of a material susceptible to corrosion and/or oxidation and can be arranged concentrically to a rotation axis of the rotor assembly. The rotor component includes a circular surface for checking concentricity of the rotor component with respect to the rotation axis. The rotor component includes at least one additional circular surface for checking concentricity of the rotor component with respect to the rotation axis, wherein the additional circular surface is coated with a corrosion and/or oxidation protection coating.

Abstract: A rotor component for a rotor assembly of a fluid energy machine, particularly of a gas turbine, a steam turbine, a compressor or the like, wherein the rotor component is at least partly made of a material susceptible to corrosion and/or oxidation and can be arranged concentrically to a rotation axis of the rotor assembly. The rotor component includes a circular surface for checking concentricity of the rotor component with respect to the rotation axis. The rotor component includes at least one additional circular surface for checking concentricity of the rotor component with respect to the rotation axis, wherein the additional circular surface is coated with a corrosion and/or oxidation protection coating.

Abstract: A system is provided for balancing a movable turbine part of a turbine or of a compressor. The system includes a balancing weight element with a first hole and a second hole and a fixing element. The first hole and the second hole are formed in such a manner that the fixing element is detachably insertable in either the first hole or the second hole. The first hole is formed in such a manner that the inserted fixing element in the first hole detachably couples the balancing weight element to the movable turbine part in a spatially fixed position. The second hole is formed in such a manner that the fixing element is receivable in the second hole.

Abstract: A system is provided for balancing a movable turbine part of a turbine or of a compressor. The system includes a balancing weight element with a first hole and a second hole and a fixing element. The first hole and the second hole are formed in such a manner that the fixing element is detachably insertable in either the first hole or the second hole. The first hole is formed in such a manner that the inserted fixing element in the first hole detachably couples the balancing weight element to the movable turbine part in a spatially fixed position. The second hole is formed in such a manner that the fixing element is receivable in the second hole.

Abstract: A combustion chamber is provided, including an inner casing with a sliding surface and an outer casing with a sliding wall portion. The sliding surface and the sliding wall portion are slidably attached to each other. A cooling hole is located in the sliding wall portion. The cooling hole is at least partially located in the sliding wall portion such that it opens due to a sliding movement of the sliding surface relative to the sliding wall portion when the inner casing thermally expands and/or closes due to a sliding movement of the sliding surface relative to the sliding wall portion when the inner casing thermally contracts. Moreover, a gas turbine including an inventive combustion chamber is disclosed.

Abstract: A combustion chamber is provided, including an inner casing with a sliding surface and an outer casing with a sliding wall portion. The sliding surface and the sliding wall portion are slidably attached to each other. A cooling hole is located in the sliding wall portion. The cooling hole is at least partially located in the sliding wall portion such that it opens due to a sliding movement of the sliding surface relative to the sliding wall portion when the inner casing thermally expands and/or closes due to a sliding movement of the sliding surface relative to the sliding wall portion when the inner casing thermally contracts. Moreover, a gas turbine including an inventive combustion chamber is disclosed.