A hybrid propulsion system includes a gas turbine engine having a low speed spool, a high speed spool, and a combustor. The low speed spool includes a low pressure compressor and a low pressure turbine, and the high speed spool includes a high pressure compressor and a high pressure turbine. The hybrid propulsion system also includes a motor configured to augment rotational power of the high speed spool, a flow modulation device configured to control a combustor bypass air flow around the combustor to the turbine section, and a controller. The controller is operable to determine a mode of operation, apply supplemental power to the high speed spool using the motor, modulate the combustor bypass air flow using the flow modulation device, and adjust a fuel-air ratio at the combustor based on modulation of the combustor bypass air flow and the supplemental power applied to the high speed spool.


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    Title :

    MODULATED COMBUSTOR BYPASS FOR HYBRID IDLE


    Contributors:

    Publication date :

    2021-01-21


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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