초록 ▼

In a gas turbine having a combustion chamber ( 6 ) and a first row of guide vanes ( 3 ) arranged on the outflow side of the combustion chamber ( 6 ), a plurality of temperature sensors ( 8 ) for measuring temperature value, and a plurality of means ( 7;71,72,73,74,75,76 ) for introducing fuel into t

In a gas turbine having a combustion chamber ( 6 ) and a first row of guide vanes ( 3 ) arranged on the outflow side of the combustion chamber ( 6 ), a plurality of temperature sensors ( 8 ) for measuring temperature value, and a plurality of means ( 7;71,72,73,74,75,76 ) for introducing fuel into the combustion chamber ( 6 ), which means can be controlled on the basis of the temperature values, the temperature sensors ( 8 ) are spectrometers, are designed to measure a combustion-gas temperature and are arranged so as to measure a gas temperature which prevails immediately in front of the first row of guide vanes ( 3 ).

대표청구항 ▼

1. A gas turbine, comprising:a combustion chamber;a first row of guide vanes arranged on the outflow side of the combustion chamber;a plurality of temperature sensors are distributed uniformly over a circumference of the gas turbine, the temperature sensors for measuring temperature values, each of

1. A gas turbine, comprising:a combustion chamber;a first row of guide vanes arranged on the outflow side of the combustion chamber;a plurality of temperature sensors are distributed uniformly over a circumference of the gas turbine, the temperature sensors for measuring temperature values, each of said temperature sensors having an associated controller and means for introducing fuel into the combustion chamber, which means can be controlled on the basis of the temperature values, wherein the temperature sensors are spectrometers, are designed to measure a combustion-gas temperature and are arranged so as to measure a gas temperature which prevails immediately in front of the first row of guide vanes, wherein the means for introducing fuel are controlled on the basis of temperature values from the temperature sensors, in order to compensate for azimuthal fluctuations in combustion. 2. The gas turbine as claimed in claim 1, wherein the temperature sensors are designed to measure a gas temperature of steam, carbon dioxide, nitrogen, oxygen or some other combustion-gas component. 3. The gas turbine as claimed in claim 2, wherein the temperature sensors have bandpass filters, which transmit radiation corresponding to the combustion-gas component under consideration. 4. The gas turbine as claimed in claim 1, wherein the temperature sensors measure a combustion-gas temperature at a distance of 0.1 to 5 cm in front of the first row of guide vanes. 5. A method for suppressing azimuthal fluctuation modes in a gas turbine, in which a plurality of temperature sensors are used to measure temperature values, and means for introducing fuel into a combustion chamber are controlled on the basis of these temperature values for suppressing said fluctuation modes, wherein the temperature sensors are spectrometers which are designed to measure a combustion-gas temperature and are used to measure combustion-gas temperatures which prevail immediately in front of a first row of guide vanes, and wherein temperature values from a plurality of temperature sensors are used to determine an associated gas-temperature profile in the azimuthal direction in front of the first row of guide vanes. 6. A method for suppressing azimuthal fluctuation modes in a gas turbine, in which a plurality of temperature sensors are used to measure temperature values, and means for introducing fuel into a combustion chamber are controlled on the basis of these temperature values for suppressing said fluctuation modes, wherein the temperature sensors are spectrometers which are designed to measure a combustion-gas temperature and are used to measure combustion-gas temperatures which prevail immediately in front of a first row of guide vanes, wherein a desired quantity of fuel is reduced according to a deviation of a temperature value of a temperature sensor from an associated reference value for all the means for introducing fuel. 7. A method for suppressing azimuthal fluctuation modes in a gas turbine, in which a plurality of temperature sensors are used to measure temperature values, and means for introducing fuel into a combustion chamber are controlled on the basis of these temperature values, wherein the temperature sensors are spectrometers which are designed to measure a combustion-gas temperature and are used to measure combustion-gas temperatures which prevail immediately in front of a first row of guide vanes, wherein the means for introducing fuel are controlled on the basis of temperature values from a plurality of temperature sensors, in order to compensate for azimuthal fluctuations in combustion.