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1. IN201617033857 - ARCHITECTURE OF A MULTI ENGINE HELICOPTER PROPULSION SYSTEM AND CORRESPONDING HELICOPTER

Office
India
Application Number 201617033857
Application Date 04.10.2016
Publication Number 201617033857
Publication Date 10.02.2017
Publication Kind A
IPC
F02C 7/262
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
7Features, component parts, details or accessories, not provided for in, or of interest apart from, groups F02C1/-F02C6/158; Air intakes for jet-propulsion plants
26Starting; Ignition
262Restarting after flame-out
B64C 27/04
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
27Rotorcraft; Rotors peculiar thereto
04Helicopters
B64D 35/08
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
35Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
08characterised by the transmission being driven by a plurality of power plants
Applicants SAFRAN HELICOPTER ENGINES
Inventors MERCIER CALVAIRAC Fabien
HUMBERT Sophie
BEDDOK St├ęphane
Priority Data 1452651 27.03.2014 FR
Title
(EN) ARCHITECTURE OF A MULTI ENGINE HELICOPTER PROPULSION SYSTEM AND CORRESPONDING HELICOPTER
Abstract
(EN)
The invention relates to an architecture of a multi engine helicopter propulsion system comprising turbine engines (1 2) connected to a power transmission gearbox (3) and a low voltage on board DC network (7) intended to power helicopter equipment during flight characterized in that the architecture comprises: a hybrid turbine engine (1) able to operate in at least one standby state during steady stabilized flight of the helicopter; an electrotechnical pack (20) for the rapid restart of said hybrid turbine engine in order to cause it to exit said standby state and attain a state in which it supplies mechanical power said restart pack (20) being connected to said onboard network (7); and at least two sources (4 16 18) for electrically powering said on board network (7).