A device for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter, includes a pneumatic turbine that is mechanically connected to the turboshaft engine and is supplied with gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate the turboshaft engine and ensure that it is reactivated. The testing device has an apparatus configured to withdraw pressurized air from the turboshaft engine and a duct for conveying the withdrawn air to the pneumatic circuit for supplying the pneumatic turbine with gas. The device further includes a sensor for determining the rotational speed of the pneumatic turbine.


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    Title :

    DISPOSITIF ET PROCEDE DE TEST D'INTEGRITE D'UN SYSTEME DE REACTIVATION RAPIDE D'UN TURBOMOTEUR D'UN HELICOPTERE


    Contributors:

    Publication date :

    2016-10-21


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    French


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64C AEROPLANES , Flugzeuge



    DISPOSITIF ET PROCEDE DE TEST D'INTEGRITE D'UN SYSTEME DE REACTIVATION RAPIDE D'UN TURBOMOTEUR D'UN HELICOPTERE

    THIRIET ROMAIN / BAZET JEAN-MICHEL / SERGHINE CAMEL et al. | European Patent Office | 2022

    Free access


    ARCHITECTURE D'UN SYSTEME PROPULSIF D'UN HELICOPTERE COMPRENANT UN TURBOMOTEUR HYBRIDE ET UN SYSTEME DE REACTIVATION DE CE TURBOMOTEUR HYBRIDE

    VALLART PHILIPPE / BAZET JEAN-MICHEL / LE DUIGOU LOIC | European Patent Office | 2023

    Free access

    ARCHITECTURE D'UN SYSTEME PROPULSIF D'UN HELICOPTERE COMPRENANT UN TURBOMOTEUR HYBRIDE ET UN SYSTEME DE REACTIVATION DE CE TURBOMOTEUR HYBRIDE

    VALLART PHILIPPE / BAZET JEAN-MICHEL / LE DUIGOU LOIC | European Patent Office | 2016

    Free access