Method for assisting a turboshaft engine in standby of a multiple-engine helicopter, and architecture of a propulsion system of a helicopter comprising at least one turboshaft engine that can be in standby

Patent metadata

Field	Value
Publication number	US-10337409-B2
Application number	US-201515124669-A
Country	US
Kind code	B2
Filing date	Mar 20, 2015
Priority date	Mar 27, 2014
Publication date	Jul 2, 2019
Grant date	Jul 2, 2019

Abstract

The invention relates to an architecture of a propulsion system of a multiple-engine helicopter comprising turboshaft engines ( 5, 6 ), characterised in that it comprises: at least one hybrid turboshaft engine ( 5 ) that is capable of operating in at least one standby mode during a stable flight of the helicopter, the other turboshaft engines ( 6 ) operating alone during this stable flight; an air turbine ( 30 ) that is mechanically connected to the gas generator ( 17 ) of the hybrid turboshaft engine ( 5 ) and is suitable for rotating said gas generator ( 17 ); means for withdrawing pressurised air from the gas generator ( 27 ) of a running turboshaft engine ( 6 ); and a duct ( 31 ) for routing this withdrawn air to said air turbine ( 30 ).

First claim

The invention claimed is:

1. Architecture of a propulsion system of a multiple-engine helicopter comprising turboshaft engines, each turboshaft engine comprising a gas generator and a free turbine that is rotated by gases from said gas generator,
wherein said propulsion system comprises:
at least one turboshaft engine from among said turboshaft engines, referred to as a hybrid turboshaft engine, that is capable of operating in at least one standby mode during a stable flight of the multiple-engine helicopter, the turboshaft engines, referred to as running turboshaft engines, operating alone during this stable flight,
an air turbine that is mechanically connected to said gas generator of said hybrid turboshaft engine,
means for withdrawing pressurized air from the gas generator of a running turboshaft engine,
a duct for routing withdrawn pressurized air to said air turbine such that the air turbine can transform energy from said pressurized air into mechanical energy that drives said gas generator of said hybrid turboshaft engine.

2. Architecture according to claim 1 , wherein said means for withdrawing pressurized air from the gas generator of a running turboshaft engine comprise a withdrawal port that is arranged on a compressor of this running turboshaft engine.

3. Architecture according to claim 1 , wherein said means for withdrawing pressurized air comprise a discharge jet that makes it possible to meter a flow of air withdrawn from said running turboshaft engine.

4. Architecture according to claim 1 , wherein said air turbine is connected to said gas generator by means of an accessory gearbox ( 32 ).

5. Architecture according to claim 1 , further comprising adjustment means for adjusting the mechanical power delivered by said air turbine to said gas generator of said hybrid turboshaft engine.

6. Architecture according to claim 5 , wherein said adjustment means comprise control means for controlling flow and/or pressure of air provided to said air turbine.

7. Architecture according to claim 1 , further comprising a controlled mechanical disconnection device that is arranged between the air turbine and said gas generator of said hybrid turboshaft engine and that is capable of disconnecting said air turbine from said gas generator if there is no supply of air to the air turbine.

8. Architecture according to claim 1 , wherein said air turbine comprises an air outlet which opens into an engine compartment of said hybrid turboshaft engine so as to limit a drop in temperature in said engine compartment and to facilitate restarting said hybrid turboshaft engine.

9. Helicopter comprising a propulsion system, wherein said propulsion system has an architecture according to claim 1 .

10. Method for mechanically assisting a turboshaft engine that operates in a standby mode during a stable flight of a helicopter comprising running turboshaft engines, each said running turboshaft engine comprising a gas generator and a free turbine, wherein said method comprises:
a step of withdrawing pressurized air from the gas generator of one of said running turboshaft engines,
a step of routing withdrawn air to an air turbine that is mechanically connected to said gas generator of said turboshaft engine in standby mode,
a step of transforming, by means of said air turbine, energy from air provided by said step of routing withdrawn air into mechanical energy for driving said gas generator of said turboshaft engine in standby mode.

11. Method according to claim 10 , wherein said step of withdrawing pressurized air includes withdrawing air from a compressor of said gas generator of one of said running turboshaft engines.

12. Method according to claim 10 , further comprising a step of adjusting mechanical power provided by said air turbine to said turboshaft engine in standby mode.

13. Method according to claim 12 , wherein said step of adjusting power comprises a step of controlling flow and/or pressure of air delivered to said air turbine.

Assignees

• Safran Helicopter Engines

Inventors

• Bedrine Olivier
• Descubes Olivier Pierre

Classifications

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title

• F05D2220/329

  in helicopters · CPC title

• F02C6/02 Primary

  Plural gas-turbine plants having a common power output · CPC title

• B64C27/04

  Helicopters · CPC title

• F02C7/277 Primary

  the starter being a {separate} turbine · CPC title