Abstract: A method and apparatus for the operation of a gas turbine unit with an evaporative intake air cooling system in the intake air pathway, wherein the return water flow of the evaporative intake air cooling system is used for the cooling of components of the gas turbine unit and/or of a generator coupled to the gas turbine unit and/or of another element coupled to the gas turbine unit, and a gas turbine unit adapted to be operated using this method.

Abstract: A method and apparatus for the operation of a gas turbine unit with an evaporative intake air cooling system in the intake air pathway, wherein the return water flow of the evaporative intake air cooling system is used for the cooling of components of the gas turbine unit and/or of a generator coupled to the gas turbine unit and/or of another element coupled to the gas turbine unit, and a gas turbine unit adapted to be operated using this method.

Abstract: In a heat shield (10), in particular for the stator of gas turbines, which heat shield (10) is composed of a plurality of individual segments (10a, b; 20a, b), whose end surfaces (15a, b) respectively abut one another so as to form a gap (12), and which have cooling holes (13a, b) for cooling purposes in the region of the end surfaces (15a, b), through which cooling holes (13a, b) a cooling fluid is blown out into the gap (12), cooling is ensured, even when the gap is closed, by a chamber (11), which is widened relative to the gap (12) and into which the cooling holes (13a, b) open, being arranged in the region of the gap (12).

Abstract: A heat shield for a gas turbine, which heat shield encloses in particular the rotating blades of a stage of the gag turbine in an annular manner, consists of a plurality of heat-shield segments (13), which are arranged one behind the other in the circumferential direction, are curved in a circular-segment shape and are cooled from outside, and the longitudinal sides of which are designed as correspondingly curved rails running in the circumferential direction and possibly provided with recesses and having in each case a first arm (18) projecting in the axial direction, and which, for fastening to the casing of the gas turbine, are mounted with the first arms (18) in each case in an annular intermediate space (20) of constant width.

Abstract: A coolable casing of a gas turbine or the like, with a plurality of arcuate casing segments (10) which are arranged so as to be contiguous with one another in a circumferential direction, to form an essentially closed casing ring surrounding a rotor (110), in particular of a high-pressure turbine, at least one annular casing cooling chamber (15) which is formed in the radial direction between the casing segments (10) and arcuate guide segments (30) provided with a multiplicity of passage orifices (34), at least one air guide chamber (25) which is formed in the radial direction between the guide segments (30) and at least one carrier segment (20), and at least one air supply duct (26) which is made on the carrier segment (20) and opens into the air guide chamber (25), the guide segments (30) being mounted loosely with radial play. This ensures stress-free reception, even in the case of intensive operations having high temperature gradients.

Abstract: A heat shield for a gas turbine, which heat shield encloses in an annular manner the moving blades, rotating in the hot-gas duct of the gas turbine, of a stage of the gas turbine and consists of a plurality of heat-shield segments which are arranged one behind the other in the circumferential direction, are curved in the shape of a segment of a circle and are cooled from outside, and the longitudinal sides which are designed as correspondingly curved rails running in the circumferential direction and having in each case a pair of arms of which project in the axial direction, run in parallel and are at a distance from one another, the heat-shield segments, while forming a cavity to which cooling air can be admitted, are fastened to the inside of an annular carrier, which concentrically surrounds the heat shield in such a way that in each case a radial gap is formed between the longitudinal sides of heat-shield segments and the adjacent elements which define the hot-gas duct on the outside.

Abstract: In a heat shield (10), in particular for the stator of gas turbines, which heat shield (10) is composed of a plurality of individual segments (10a, b; 20a, b), whose end surfaces (15a, b) respectively abut one another so as to form a gap (12), and which have cooling holes (13a, b) for cooling purposes in the region of the end surfaces (15a, b), through which cooling holes (13a, b) a cooling fluid is blown out into the gap (12), cooling is ensured, even when the gap is closed, by a chamber (11), which is widened relative to the gap (12) and into which the cooling holes (13a, b) open, being arranged in the region of the gap (12).