Architecture for a propulsion system of a helicopter including a hybrid turboshaft engine and a system for reactivating said hybrid turboshaft engine

A turboshaft engine, reactivation technology, applied in the direction of engine starting, combined engine, engine components, etc., can solve the problems of turboshaft engine weight and fuel consumption disadvantages

Active Publication Date: 2017-05-31
SAFRAN HELICOPTER ENGINES +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] These oversized turboshaft engines are disadvantageous in terms of weight and fuel consumption

Method used

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  • Architecture for a propulsion system of a helicopter including a hybrid turboshaft engine and a system for reactivating said hybrid turboshaft engine
  • Architecture for a propulsion system of a helicopter including a hybrid turboshaft engine and a system for reactivating said hybrid turboshaft engine
  • Architecture for a propulsion system of a helicopter including a hybrid turboshaft engine and a system for reactivating said hybrid turboshaft engine

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Embodiment Construction

[0059] The embodiments described below are some examples for carrying out the invention. Although the detailed description refers to one or more embodiments, this does not necessarily mean that every reference refers to the same embodiment or that a feature applies to only a single embodiment. Individual features of different embodiments may also be combined to provide other embodiments. Also, in the drawings, for purposes of illustration and clarity, dimensions and proportions are not necessarily exact.

[0060] figure 1 is a schematic illustration of the architecture of a known helicopter propulsion system comprising a turboshaft engine 10 and a system for controlling said turboshaft engine. The control system comprises an electric machine 11 adapted to rotate the turboshaft engine 10 as required in order to ensure the starting of the turboshaft engine 10 . The motor 11 is powered directly from the helicopter's low-voltage on-board network 12, which is usually a network p...

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Abstract

The invention relates to an architecture for a propulsion system of a multi-engine helicopter including turboshaft engines connected to a power gearbox. Said architecture is characterized in that it includes: - at least one hybrid turboshaft engine (20) capable of operating in at least one standby mode during a stabilized coasting flight of the helicopter; - at least two chains (30, 40) for controlling each hybrid turboshaft engine (20), each chain (30, 40) including an electrical machine (31, 41) connected to the hybrid turboshaft engine (20) and being suitable for rotating a gas producer thereof; and - at least one source (33, 43) for supplying electrical power to said electrical machine (31, 41). Each reactivation chain (30, 40) is configured so as to be able to drive said turboshaft engine (20) in at least one operation mode from among a plurality of predetermined modes.

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, two- or three-engine helicopters have a propulsion system comprising two or three turboshaft engines, each turboshaft engine comprising a gas generator and a free turbine rotated by the gas generator and rigidly connected to the output shaft. The output shaft of each free turbine is adapted to cause the movement of its own power transmission gearbox driving the rotor of the helicopter. [0003] It is well known that a turboshaft engine produces less than Low power level for maximum continuous output of a turboshaft engine. These low power levels result in a Specific Consumption (hereinafter referred to as SC), defined as the ratio of the hourly fuel consumption of the turboshaft e...

Claims

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Application Information

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Patent Type & AuthorityApplications(China)
IPC IPC(8): F01D13/00F01D19/00F02C7/36
CPCF01D13/00F01D13/003F01D19/00F02C7/36F05D2270/13F05D2220/329F05D2220/76F02C7/268Y02T50/60B64C27/12B64D27/10B64D27/026B64C27/14B64D27/24
Inventor菲利普·瓦拉尔特让·米歇尔·巴泽卢瓦克·勒达够
OwnerSAFRAN HELICOPTER ENGINES