DISPOSITIF PNEUMATIQUE DE REACTIVATION RAPIDE D'UN TURBOMOTEUR, ARCHITECTURE D'UN SYSTEME PROPULSIF D'UN HELICOPTERE MULTI-MOTEUR EQUIPE D'UN TEL DISPOSITIF ET HELICOPTERE CORRESPONDANT

The invention relates to a device for the rapid reactivation of a helicopter turbine engine (6), characterised in that it comprises a pneumatic turbine (7) mechanically connected to said turbine engine (6) so as to be able to rotate it and ensure reactivation thereof; a pneumatic storage (9) connect...

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Bibliographic Details
Main Authors MOULON FREDERIC, SERGHINE CAMEL, THIRIET ROMAIN
Format Patent
LanguageFrench
Published 22.07.2016
Subjects
AEROPLANES
AIR INTAKES FOR JET-PROPULSION PLANTS
AIRCRAFT
AVIATION
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
COSMONAUTICS
GAS-TURBINE PLANTS
HEATING
HELICOPTERS
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MECHANICAL ENGINEERING
PERFORMING OPERATIONS
TRANSPORTING
WEAPONS
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Summary:The invention relates to a device for the rapid reactivation of a helicopter turbine engine (6), characterised in that it comprises a pneumatic turbine (7) mechanically connected to said turbine engine (6) so as to be able to rotate it and ensure reactivation thereof; a pneumatic storage (9) connected to said pneumatic turbine (7) by means of a pneumatic circuit (10) for supplying pressurised gas to said pneumatic turbine (7); a controlled fast-opening pneumatic valve (11) arranged on the pneumatic circuit (10) between said storage (9) and said pneumatic turbine (7) and suitable for being on demand placed at least in an open position in which the gas can supply said pneumatic turbine (7), or in a closed position in which said pneumatic turbine (7) is no longer supplied with pressurised gas.
Bibliography:Application Number: FR20140057282