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Architecture of a multiple-engine helicopter propulsion system, and corresponding helicopter

A technology for a propulsion system and a helicopter, applied in the field of helicopters, can solve the problems of increasing the total weight and loss of a turboshaft engine

Active Publication Date: 2017-02-22
SAFRAN HELICOPTER ENGINES +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] This assembly for restarting a turboshaft engine on standby has the disadvantage of substantially increasing the overall weight of the turboshaft engine
Therefore, especially when each turboshaft engine is equipped with an emergency restart device of this type, the benefit in terms of fuel consumption obtained by putting the turboshaft engine on standby is due to the restart device and the energy required for storing the restart partly lost due to the additional weight of the device

Method used

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  • Architecture of a multiple-engine helicopter propulsion system, and corresponding helicopter

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Embodiment Construction

[0054] figure 1 is a schematic view of the architecture of the propulsion system of a twin-engine helicopter according to an embodiment of the present invention. The architecture comprises two turboshaft engines 1 , 2 connected to a power transmission gearbox 3 . Each turboshaft engine 1 , 2 is controlled by its own monitoring and control device, which is not shown in the figure for reasons of clarity.

[0055] As is known, each turboshaft engine further comprises a gas generator and a free turbine rigidly connected to an output shaft rotated by the gas generator. The output shaft of each free turbine is adapted to induce the motion of a power transmission gearbox 3 (hereinafter referred to by the abbreviation BTP), which itself drives the rotor of the helicopter equipped with a blade.

[0056] According to the invention, the turboshaft engine 1 is a hybrid turboshaft engine capable of operating in at least one standby mode during steady flight of the helicopter.

[0057] ...

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Abstract

The invention relates to an architecture of a multiple-engine helicopter propulsion system comprising turbine engines (1, 2) which are connected to a power transmission gearbox (3), comprising: a hybrid turbine engine (1) able to operate in at least one standby state during steady stabilized flight of the helicopter; a pack (5, 6) with a rapid restarting of said hybrid turbine engine (1) to cause it to exit said standby state and attain a nominal operating state; an auxiliary power unit (11) connected to said electro-technical restart pack (5, 6) via a first (10) AC / DC converter designed, on demand, to supply said restart pack (5, 6) with the power required to cause said hybrid turbine engine (1) to leave said standby state.

Description

technical field [0001] The invention relates to the architecture of the propulsion system of a multi-engine helicopter, in particular a twin-engine or triple-engine helicopter, and to a helicopter comprising a propulsion system with such an architecture. Background technique [0002] As is known, twin- or triple-engine helicopters have a propulsion system comprising two or three turboshaft engines, each turboshaft engine comprising a gas generator and a free turbine, the gas generator rotating the free turbine, the The free turbine is rigidly connected to the output shaft. The output shaft of each free turbine is adapted to induce the movement of a power transmission gearbox (hereinafter referred to by the abbreviation BTP), which itself drives the rotor of the helicopter equipped with blades of variable pitch . [0003] Furthermore, it is known that when a helicopter is in cruising flight conditions (i.e. when it is advancing in normal conditions, in AEO (All Engines Oper...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/14F02C7/262F02C7/275F02C9/42B64D27/40
CPCB64C27/14F02C7/262F02C7/275F02C9/42F05D2220/76F05D2220/50F05D2220/329B64D35/08Y02T50/60B64D27/402F02C3/04F05D2220/323F05D2240/35F05D2260/85B64D27/40B64D27/026F02C7/268
Inventor 法比恩·梅希尔-卡尔瓦伊拉克史蒂芬·贝多克史蒂芬·舍瓦莱尔索菲·亨伯特
Owner SAFRAN HELICOPTER ENGINES
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