Turbine exhaust gas temperature calculation and difference degree protection method

Abstract

The invention discloses a turbine exhaust gas temperature calculation and difference degree protection method. The method comprises the steps of obtaining real-time thermocouple data collected by thermocouples arranged at different positions of a turbine exhaust gas channel of a gas turbine in advance; performing cold junction compensation on the real-time thermocouple data; carrying out quality judgment, and removing the thermocouples with the quality of defective pixels; carrying out high-low sorting; performing fault judgment on the thermocouple data after high-low sorting, and outputting final thermocouple data; removing the highest value and the lowest value of all thermocouple temperatures of the final thermocouple data, then carrying out average value calculation, and obtaining the turbine exhaust gas temperature; and according to the final thermocouple data and the pre-acquired exhaust gas temperature difference allowed by the operation condition of the gas turbine, determining a trigger instruction of an over-high exhaust gas temperature difference alarm or difference protection. The method has the advantages that the exhaust gas temperature of the gas turbine is accurately calculated, whether the exhaust gas temperature field of the gas turbine is uniform or not can be judged, and effective protection measures are taken when thermocouple faults are measured or the temperature field distribution is non-uniform.

Description

technical field [0001] The invention relates to a calculation and differential protection method of exhaust gas temperature of a turbine, and belongs to the technical field of gas turbine control. Background technique [0002] Gas turbine turbine temperature monitoring plays a vital role in gas turbine operation. Since the gas turbine operates at high temperature, components such as the combustion tube or the transition section are very likely to have failures such as rupture due to high temperature. Due to the high temperature of the gas turbine, it is difficult to directly detect these high-temperature components. Only the indirect detection method of measuring the exhaust gas temperature of the turbine and the exhaust temperature of the compressor can be used to judge whether the high-temperature components are working normally. When a few fuel nozzles are blocked and the combustion temperature of each combustion chamber is not uniform, or when the combustion chamber is ...

AI Technical Summary

Problems solved by technology

Since the gas turbine operates at high temperature, the components such as the combustion tube or the transition section are very likely to have failures such as rupture due to high temperature

Due to the high temperature of the gas turbine, it is difficult to directly detect these high-temperature components. Only the indirect detection method of measuring the exhaust gas temperature of the turbine and the exhaust temperature of the compressor can be used to judge whether the high-temperature components are working normally.

When a few fuel nozzles are blocked and the combustion temperature of each combustion chamber is not uniform, or when the combustion chamber is broken, the combustion is abnormal, or when the transition section is broken and the turbine inlet temperature is not uniform, the inlet flow field and exhaust of the turbine will be caused. The temperature distribution of the smoke is seriously uneven. Therefore, a method is urgently needed to judge the uniformity of the temperature field of the exhaust gas in order to judge whether the combustion is normal.

[0003] Since domestic gas turbine control systems have been provided by foreign gas turbine manufacturers such as GE, Siemens, and Mitsubishi, each manufacturer has mature algorithm modules for gas turbine exhaust gas temperature calculation and exhaust gas temperature difference protection. The core technology is strictly locked, and our country has not yet completely broken through

In order to realize the localization of the gas turbine control system, the gas turbine exhaust gas temperature calculation and the exhaust gas temperature difference protection control strategy are one of the major difficulties and must be overcome. At present, the localization of the gas turbine control system is still blank, and the gas turbine exhaust temperature Calculation and exhaust temperature difference protection control strategy has not been overcome

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