Abstract: A temperature measuring device is provided. The temperature measuring device measures the temperature in a combustion system, in particular for that of a combustion system of a gas turbine. The temperature measuring device is equipped with a heat absorbing element disposed in or on the combustion system, a measurement end disposed remotely from the combustion system having, disposed thereon, a temperature sensor measuring the temperature of the measurement end, a heat conducting element which connects the heat absorbing element to the measurement end in a thermally conductive manner, and a cooling device acting on the heat conducting element in a quantifiable manner for heat removal. A gas turbine having a temperature measuring device and method for directly determining the temperature in a combustion chamber are also provided.

Abstract: A gas turbine power plant and a method for operating a gas turbine power plant are provided. The power plant includes a gas turbine installation which may supply a mains supply network with electric power and includes a compressor and an associated first gas turbine. Differing from previous gas turbine installations, the compressor of the gas turbine installation and the first gas turbine of the gas turbine installation are decoupled from each other. A second turbine is provided which drives compressor. As a result, the compressor of the gas turbine installation is operated independently of the first gas turbine. Influences on the mains supply network side, such as generating deficiencies in the main supply network, which act upon the first gas turbine as a result of speed reduction, are also not able to have an impact upon the compressor which is decoupled from the first gas turbine.

Abstract: An axial turbine for a gas turbine including a rotor blade cascade is provided. The rotor blade cascade is formed from rotor blades each including, a front edge, a blade tip, and an annular space wall that surrounds the rotor blade cascade and includes an annular space inner side, enabling the annular space wall to be arranged directly adjacent to the blade tip forming a radial gap between the covering of the blade tip and the annual space inner side. When the turbine is in operation, the area of the blade tip with the highest pressure load is disposed in the region of the front edges, and the rotor blades in the region of their front edges include a radial projection and the annular space wall includes on the annular space inner side, a peripheral radial recess that interacts with the radial projections such that a minimum is established in the direction of the main through-flow of the turbine.

Abstract: A temperature measuring device is provided. The temperature measuring device measures the temperature in a combustion system, in particular for that of a combustion system of a gas turbine. The temperature measuring device is equipped with a heat absorbing element disposed in or on the combustion system, a measurement end disposed remotely from the combustion system having, disposed thereon, a temperature sensor measuring the temperature of the measurement end, a heat conducting element which connects the heat absorbing element to the measurement end in a thermally conductive manner, and a cooling device acting on the heat conducting element in a quantifiable manner for heat removal. A gas turbine having a temperature measuring device and method for directly determining the temperature in a combustion chamber are also provided.

Abstract: The invention relates to a burner (100) having a combustion air duct (104), in which a swirl generator (109), which is formed from a number of swirl generator elements (108), is arranged in such a way that the swirl generator (109) can increase the mean velocity at which combustion air (112) flows through the swirl generator (109) to a Mach number of at least 0.4. This results in flow-acoustic decoupling of the combustion area from the combustion-air feed area.

Abstract: The invention relates to a burner (100) having a combustion air duct (104), in which a swirl generator (109), which is formed from a number of swirl generator elements (108), is arranged in such a way that the swirl generator (109) can increase the mean velocity at which combustion air (112) flows through the swirl generator (109) to a Mach number of at least 0.4. This results in flow-acoustic decoupling of the combustion area from the combustion-air feed area.