Hybrid aircraft propulsion systems are disclosed comprising an electrically driven ducted fan, a peripheral duct or enclosure, a combustion-produced source of radiant energy, radiant energy receivers or cold mirrors, and thermophotovoltaic or thermoelectric cell energy converters. An electric motor drives a partially or completely duct enclosed fan. Downstream and within the duct enclosure, radiant energy emitters irradiated receiver fins and thermophotovoltaic cells or thermoelectric cells. The receiver fins heat and expand the fan air, and the thermophotovoltaic cells or thermoelectric cells convert the radiant energy into electrical energy which is available to charge batteries and energize the fan motor. Thrust is provided via the acceleration of air by the fan and by the acceleration of air due to heat driven expansion.


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    Title :

    Hybrid radiant energy aircraft engine


    Contributors:

    Publication date :

    2016-03-29


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B60K Anordnung oder Einbau von Antriebseinheiten oder von Kraft- bzw. Drehmomentübertragungen in Fahrzeugen , ARRANGEMENT OR MOUNTING OF PROPULSION UNITS OR OF TRANSMISSIONS IN VEHICLES / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS





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