A gas turbine turbine rotor cooling adjustment method and cooling gas system

Abstract

The invention discloses a method for cooling a turbine rotor of a gas turbine. The gas turbine comprises a compressor, a combustion chamber and a turbine. An air extraction pipeline (5) is connected between the compressor and the turbine, and the air extraction pipeline (5) is provided with an air extraction pipeline (5). A suction regulating valve (4), a heat exchanger (2) for cooling gas is arranged on the suction pipeline between the compressor and the suction regulating valve (4), and a water supply pipeline entering the heat exchanger (2) is provided with water supply A regulating valve (8), the feedwater regulating valve (8) is controlled by a control system which controls the suction regulating valve (4) and the feeding water regulating valve (8) to meet the temperature required for cooling the gas turbine turbine blades and discs ,flow. The invention can control the temperature and flow rate of the exhaust gas (extraction) of the compressor respectively, and control the temperature of the gas discharged from the heat exchanger within a certain range by controlling the water inlet flow rate, so as to achieve the best cooling gas volume with the least amount. cooling effect, thereby improving the operating power and efficiency of the unit.

Description

technical field [0001] The invention relates to the field of gas turbines, in particular to a cooling adjustment method for a gas turbine turbine rotor and a cooling gas system. Background technique [0002] Turbine vanes, moving vanes and discs in the hot passage of gas turbines are in a high temperature environment. Due to the limitation of materials, cooling gas is required for cooling to enable them to operate reliably and ensure the necessary life. It is usually the case that the compressor discharge (extraction) is directed directly into the turbine for cooling. Under the full load condition of the gas turbine, the temperature of the exhaust gas (extraction) of the compressor is relatively high, which is directly used to cool the turbine hot passage components, and the required flow rate is relatively large. Excessive exhaust gas flow will affect the efficiency of the unit. [0003] In addition, because the disc clearance does not change linearly during the change of ...

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Problems solved by technology

[0004] The present invention aims at the above problems, and in order to solve the shortcomings of the existing turbine rotor cooling system that the energy is not fully utilized and the amount of cooling gas cannot be adjusted, the present invention provides a new cooling adjustment method for the turbine rotor of a gas turbine and a cooling gas system , this method can not only cool the compressor exhaust (air extraction), make full use of the heat released by the compressor exhaust (air extraction), but also adjust the amount of air extraction, and control the cooling gas entering the turbine according to the operating conditions of the gas turbine In addition, it can make full use of the exhaust heat of the compressor to improve the performance of the gas-steam combined cycle

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