Method for cooling turbine disc and moving blade of combustion gas turbine

Abstract

The invention relates to a method for cooling a turbine disc and a moving blade of a combustion gas turbine. High-temperature high-pressure air pumped out by an air compressor is divided into two air flows by a sealing structure after being cooled by an intercooler, wherein the two air flows are a cooling air flow and a sealing air flow; the cooling air flow is used for cooling a one-stage turbine moving blade and a one-stage turbine disc respectively, the other sealing air flow enters a channel between the one-stage turbine moving blade and a one-stage static blade to prevent gas from flowing backwards. According to the method, the one-stage turbine disc and the moving blade can be effectively cooled and the sealing effect of the front end of the one-stage turbine disc is achieved; besides, a radial channel in the one-stage turbine disc can achieve a rotary pump effect and a heat-exchange function of the cooling air, so that the cooling method can cool the one-stage turbine disc while performing pressurization and temperature rise on the cooling gas, the cooling air flow rate needed by the one-stage turbine disc and the one-stage turbine moving blade can be ensured, and the thermal stress of the one-stage turbine moving blade is reduced.

Description

technical field [0001] The invention relates to the field of gas turbines, in particular to a method for cooling a turbine disk and moving blades of a gas turbine. Background technique [0002] With the continuous innovation and development of modern gas turbine technology, in order to improve the overall thermal efficiency of the gas turbine, the temperature before the turbine continues to rise. As a high-speed rotating part, the turbine rotor blades work in an extremely high temperature environment. Due to the limitation of materials, only relying on the existing high-temperature resistant materials can no longer meet the actual needs. The turbine rotor blades must be cooled in a certain form. [0003] The air used to cool the turbine rotor blades generally comes from compressor extraction. As the cooling requirements become higher and higher, the demand for air extraction is also increasing, which will lead to a decrease in the thermal efficiency of the gas turbine. Ther...

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Problems solved by technology

[0004] However, since the air used to cool the swirling blades needs to pass through the intercooler, a large pressure loss will inevitably occur. However, the cooling of the turbine moving blades requires a high pressure of the cooling air to ensure the cooling air flow

At the same time, because the cooled air may generate too low temperature, it will cause excessive thermal stress when the turbine rotor blades are cooled.

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