A jet engine liquid metal Rankine cycle thermoelectric conversion device

Abstract

The invention proposes a jet engine liquid metal Rankine cycle thermoelectric conversion device, the conversion device cools the jet engine turbine and nozzle wall; liquid metal is stored in the storage tank of the liquid metal Rankine cycle thermoelectric conversion device, The outlet of the storage tank is connected with the inlet of the electromagnetic pump, the outlet of the electromagnetic pump is connected with the inlet of the internal cooling channel of the turbine vane through the casing, the outlet of the internal cooling channel of the turbine vane is connected with the inlet of the cooling channel on the wall of the nozzle, and the outlet of the cooling channel on the wall of the nozzle is connected with the The inlet of the turbine is connected, the outlet of the turbine is connected with the inlet of the working medium of the condenser, and the outlet of the working medium of the condenser is connected with the inlet of the storage tank, forming a flow path of liquid metal; the turbine and the generator rotate coaxially to drive the generator to generate electricity . The invention solves the problems of ablation and the like caused by the high initial temperature of the gas turbine vane of the existing jet engine, solves the dual requirements of the aircraft for electric energy and cooling energy, and improves the performance upper limit of the jet engine.

Description

technical field [0001] The invention relates to a jet engine liquid metal Rankine cycle thermoelectric conversion device, which belongs to the field of jet engine energy comprehensive utilization. Background technique [0002] Jet engine is the main engine type of aircraft at present, and people spend a lot of effort to improve its performance. At present, people often adopt the method of "increasing temperature and improving efficiency", that is, by increasing the gas temperature in front of the turbine, the efficiency of the turbine can be greatly improved and have a higher thrust-to-weight ratio. However, due to the limited heat resistance of the cascade material itself, it is necessary to design a cooling structure for the guide vane of the gas turbine to achieve effective temperature control of the blade, so as to ensure its safe and stable operation for a long time. [0003] At present, the turbine stator blades in air-breathing turbine engines usually adopt film cool...

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Problems solved by technology

[0006] In order to solve the problems of ablation and other problems caused by the high initial temperature of the gas in the turbine vane of the existing jet engine, the present invention cools the nozzle pipe to reduce the problem of the jet engine nozzle pipe being eroded by gas heat. The liquid metal Rankine cycle converts the absorbed heat energy into electrical energy for use by the aircraft, solving the dual needs of the aircraft for electrical energy and cooling energy, and improving the upper limit of the performance of the jet engine

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