Turbine guider blade cooling device with low-melting-point metal as flowing working medium

Abstract

The invention discloses a turbine guider blade cooling device with low-melting-point metal as a flowing working medium, and relates to guider blade cooling. A plurality of cooling channels and cavities are arranged in a guider blade. The turbine guider blade cooling device with the low-melting-point metal as the flowing working medium comprises a flow divider, a collector, a radiator and an electromagnetic pump, wherein the electromagnetic pump and the guider blade form a closed loop, liquid low-melting-point metal or alloy thereof is driven by the electromagnetic pump to serve as the flowing working medium to circularly flow in the closed loop, and rapid heat dissipation is achieved through the radiator. According to the turbine guider blade cooling device with the low-melting-point metal as the flowing working medium, air cooling is not adopted, cooling air originally led out from a gas compressor is saved, and the propelling power of an aircraft is increased; the cooling effect is far better than that of a gas cooling mode in a traditional process, the heat transfer efficiency is high, and the temperature drop of the guider blade is larger, so that the service life of the guider blade is prolonged; air film holes do not need to be formed in the outer surface of the guider blade, and the strength of the blade is improved; the whole process is cyclically closed, the low-melting-point metal or the alloy thereof is recycled, and the environment is not affected.

Description

technical field [0001] The application relates to a cooling device for a turbine guide vane of an aviation gas turbine engine, in particular to a cooling device for cooling a turbine guide vane using a low-melting point metal or an alloy thereof as a working medium. Background technique [0002] In order to improve the thrust-to-weight ratio and thermal efficiency of aviation gas turbine engines, it is necessary to achieve the design goals by increasing the total pressure ratio and turbine inlet temperature. Especially the increase of turbine inlet temperature directly affects the efficiency of the engine. At present, the inlet temperature of the turbine has reached as high as 1800-2050K. At such a high temperature, higher requirements are put forward for the heat resistance of various parts of the turbine. On the one hand, it is necessary to develop new heat-resistant materials; on the other hand, it is necessary to take protective measures for hot-end components through a...

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Problems solved by technology

However, the cooling air quoted is drawn from the compressor. In order to meet the cooling demand, the opportunity to do work is lost, which greatly reduces the thermal efficiency and work ability of the engine; During the thermal protection process, the components absorb heat from the main gas flow, which intensifies the heat loss in the main gas flow. After mixing with the main gas flow, it is easy to cause the unstable flow of the air flow and increase the aerodynamic loss of the main gas flow.

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