Abstract: Disclosed is a gas turbine for a thermal power plant, especially a gas turbine, comprising a rotatable rotor and a duct which can be penetrated by a gas and in which turbine blades for driving the rotor are disposed. The inventive gas turbine is characterized by a blocking device which at least partially prevents the gas from penetrating the duct in a closed position.

Abstract: A gas turbine, comprising a turbine and a compressor provided with a compressor housing, and to a method for the operation thereof. The compressor is tapped in order to cool the turbine by means of at least one tap line for removing compressed or partially compressed air. The tap line comprises a locking device, particularly a valve, in order to regulate the outflow of tapped air and thus the cooling of the housing.

Abstract: Disclosed is a gas turbine for a thermal power plant, especially a gas turbine, comprising a rotatable rotor and a duct which can be penetrated by a gas and in which turbine blades for driving the rotor are disposed. The inventive gas turbine is characterized by a blocking device which at least partially prevents the gas from penetrating the duct in a closed position.

Abstract: The invention relates to a compressor, which is axially flowed through, for a gas turbine having an axially displaceable rotor. An annular flow channel, which narrows in an axial direction, is formed between a rotationally fixed outer delimiting surface and an inner delimiting surface on the rotor. A stationary ring comprised of guide profiles and at least one ring comprised of moving profiles attached to the rotor are placed inside said annular flow channel. The end of each moving or guide blade is located opposite an axial section of one of both delimiting surfaces while forming a radial gap. The aim of the invention is to provide a non-positive-displacement machine having an axially displaceable rotor whose velocity losses are at least not increased during an axial displacement of the rotor.

Abstract: The invention relates to a compressor, which is axially flowed through, for a gas turbine having an axially displaceable rotor. An annular flow channel, which narrows in an axial direction, is formed between a rotationally fixed outer delimiting surface and an inner delimiting surface on the rotor. A stationary ring comprised of guide profiles and at least one ring comprised of moving profiles attached to the rotor are placed inside said annular flow channel. The end of each moving or guide blade is located opposite an axial section of one of both delimiting surfaces while forming a radial gap. The aim of the invention is to provide a non-positive-displacement machine having an axially displaceable rotor whose velocity losses are at least not increased during an axial displacement of the rotor.

Abstract: The invention relates to a gas turbine, comprising a turbine and a compressor provided with a compressor housing, and to a method for the operation thereof The compressor is tapped in order to cool the turbine by means of at least one tap line for removing compressed or partially compressed air. The tap line comprises a locking device, particularly a valve, in order to regulate the outflow of tapped air and thus the cooling of the housing.

Abstract: A combustion chamber (4) for a gas turbine (1), the combustion chamber wall (24) of which is furnished on the inside with a lining formed of a number of heat shield elements (26), is to be designed for a particularly high level of operating safety. To this end, one or a number of temperature sensors (28) is/are located according to the invention between combustion chamber wall (24) and heat shield elements (26).

Abstract: A combustion chamber (4) for a gas turbine (1), the combustion chamber wall (24) of which is furnished on the inside with a lining formed of a number of heat shield elements (26), is to be designed for a particularly high level of operating safety. To this end, one or a number of temperature sensors (28) is/are located according to the invention between combustion chamber wall (24) and heat shield elements (26).