Liquid metal Rankine cycle thermoelectric conversion device for jet engine

Abstract

The invention provides a liquid metal Rankine cycle thermoelectric conversion device for a jet engine. The liquid metal Rankine cycle thermoelectric conversion device is capable of cooling turbines Iand the wall surface of a spray pipe of the jet engine; liquid metal is stored in a storage box of the liquid metal Rankine cycle thermoelectric conversion device, the outlet of the storage box communicates with the inlet of an electromagnetic pump, the outlet of the electromagnetic pump communicates with the inlets of internal cooling channels of the turbines I through a machine case, the outletsof the internal cooling channels of the turbines I communicate with the inlet of a cooling channel of the wall surface of the spray pipe, the outlet of the cooling channel of the wall surface of thespray pipe communicates with the inlet of a turbine II, the outlet of the turbine II communicates with the working medium inlet of a condenser, and the working medium outlet of the condenser communicates with the inlet of the storage box, so that a liquid metal flow path is formed; and the turbine II and a power generator rotate coaxially, so that the power generator is driven to generate electricity. Through the liquid metal Rankine cycle thermoelectric conversion device, the problem that in the prior art, a static blade of a turbine of a jet engine is subjected to ablation caused by the toohigh initial temperature of gas can be solved; the dual requirements of an aircraft for electric energy and cold energy can be met; and the upper limit of the performance of the jet engine can be improved.

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

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