Method for determining faulty combustion chamber of gas turbine

Abstract

The invention discloses a method for determining a faulty combustion chamber of a gas turbine. According to the method for determining the fault combustion chamber of the gas turbine, the relationshipbetween the adopted combustion chamber and exhaust temperature dispersity at a turbine exhaust monitoring point is obtained by the influence area of the high-temperature fluid mass at the monitoringpoint, and is a range value instead of a certain specific numerical value; and therefore not only can the position of the fault combustion chamber or the fault position of a turbine through-flow component be accurately inferred through an exhaust temperature dispersion degree at the monitoring point, but also the severity of the fault of the fault combustion chamber or the turbine through-flow component can be judged. Gas turbine operation and maintenance personnel can timely stop a unit to check and process the fault combustion chamber / turbine according to the determined fault combustion chamber / turbine and the fault damage severity information, so that the combustion condition of the gas turbine unit is restored to a better operation state; and the state maintenance of the combustion chamber / turbine is realized.

Description

technical field [0001] The invention relates to the field of data analysis, in particular to a method for determining a faulty combustion chamber of a gas turbine. Background technique [0002] The combustor is one of the three core system components of the gas turbine (compressor, combustor and turbine), and its working process has the characteristics of high temperature, high pressure, high speed, high excess air coefficient, and high combustion heat intensity. Combustion chamber flame tube, transition section and other components work in the high temperature area for a long time, and the working environment is harsh. After a period of operation, the above components will inevitably have various failures such as rupture and damage. [0003] Once the combustor components fail, it may pose a threat to the safety of downstream turbine nozzles and turbine blade components. During the actual operation of the gas turbine, because it is difficult to directly monitor the temperat...

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Problems solved by technology

[0005] However, in the past, when gas turbines had abnormal exhaust dispersion, the abnormal points of exhaust thermocouples in the operating data were usually used, and then the faulty combustion chamber location formula / fitting formula of the corresponding relationship between the thermocouple and the combustion chamber of this type of gas turbine was used, The method of judging the location of the faulty combustion chamber, but this method has the problem of being unable to determine the location of all faulty combustion chambers, the predicted location of the faulty combustion chamber is not comprehensive, and it cannot judge the severity of the damage of the faulty combustion chamber. After the machine is forced to deal with the faulty combustion chamber, the processing time is long and inefficient, and it cannot be predicted in advance in the early stage of the faulty combustion chamber

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