Gas inlet control system of gas turbine

Abstract

The invention relates to a gas inlet control system of a gas turbine. The gas inlet control system is characterized in that a central control unit adjusts an adjusting valve arranged on a nozzle and a guide vane opening and closing angle arranged on a gas compressor connected with a combustion chamber according to real-time carbon deposition thickness detection data so as to determine the initial guide vane opening and closing angle and the opening and closing degree of the adjusting valve, and meanwhile, a detection interval is set, the carbon deposition thickness is detected again after the interval is detected, the guide vane opening and closing angle and the adjusting valve parameters are corrected, and the whole detection process is periodic, so that the guide vane opening and closing angle and the opening and closing degree of the adjusting valve in the gas turbine are continuously and accurately controlled, and the optimal combustion effect is obtained.

Description

technical field [0001] The field of the invention is the field of control, specifically a gas turbine air intake control system. Background technique [0002] In the main process of air and gas in the gas turbine, only the gas turbine cycle composed of three major components: the compressor (Compressor), the combustor (Combustor) and the gas turbine (Turbine), is generally called a simple cycle, and the compressor sucks in air from the external atmosphere , and is compressed step by step by the axial flow compressor to increase the pressure, and the air temperature is also increased accordingly; the compressed air is sent to the combustion chamber and mixed with the injected fuel to generate high-temperature and high-pressure gas; and then enters the turbine Expansion works, pushing the turbine to drive the compressor and the external load rotor to rotate together at high speed, realizing the partial conversion of the chemical energy of the gas or liquid fuel into mechanical...

AI Technical Summary

Problems solved by technology

[0003] 1. The existing gas turbine aerodynamic method lacks a control method for adjusting the guide vanes of the compressor and fuel input in combination with the combustion conditions in the combustion chamber;

[0004] 2. The combustion efficiency of traditional gas turbines is not good, and the combustion chamber often has carbon deposits. There is no way to adjust the guide vanes of the compressor according to the carbon deposits.

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