IP Library › Granted Patent US 11,161,603

Granted Patent B2

US 11,161,603 · App. 15/517,924 · Granted Nov 2, 2021

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

Inventors: Philippe Vallart (Gan, FR); Jean-Michel Bazet (Gelos, FR); Loïc Le Duigou (Montrouge, FR)

Assignees: SAFRAN HELICOPTER ENGINES; SAFRAN ELECTRICAL & POWER

B64C27/14 B64D27/24 F01D13/00 F01D13/003 F01D19/00 F02C7/36 B64D2027/026 F02C7/268 F05D2220/329 F05D2220/76 F05D2270/13 Y02T50/60

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Quick Facts

Patent No.: US 11,161,603
App. No.: 15/517,924
Granted: Nov 2, 2021
Kind: B2

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Abstract

The invention relates to an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines connected to a power transmission gearbox, characterised in that it comprises: at least one hybrid turboshaft engine ( 20 ) capable of operating in at least one standby mode during a stable cruise flight of the helicopter; at least two systems ( 30; 40 ) for controlling each hybrid turboshaft engine ( 20 ), each system ( 30; 40 ) comprising an electric machine ( 31; 41 ) connected to the hybrid turboshaft engine ( 20 ) and suitable for rotating the gas generator thereof, and at least one source ( 33; 43 ) of electrical power for said electric machine ( 31; 41 ), each reactivation system ( 30; 40 ) being configured such that it can drive said turboshaft engine ( 20 ) in at least one operating mode among a plurality of predetermined modes.

Claims (45)

1. A method for reactivating a hybrid turboshaft engine, said hybrid turboshaft engine being comprised in an architecture of a propulsion system of a multi-engine helicopter, said architecture having turboshaft engines connected to a power transmission gearbox, said hybrid turboshaft engine being capable of operating in at least one standby mode during a stable cruise flight of the helicopter and a second turboshaft engine operating during the stable cruise flight,

said architecture further comprising at least a first reactivation system and a second reactivation system configured to control the hybrid turboshaft engine, each reactivation system comprising an electric machine connected to the hybrid turboshaft engine for rotating said hybrid turboshaft engine, and at least one source of electrical power for said electric machine,

said method comprising:

driving the hybrid turboshaft engine in a rapid reactivation mode, wherein said hybrid turboshaft engine is rotated at a speed of 105% of a nominal speed of a gas generator of said hybrid turboshaft engine in a period of less than 10 seconds;

driving the hybrid turboshaft engine in a normal reactivation mode, wherein said hybrid turboshaft engine is rotated to a speed in the range of between 80% and 105% of the nominal speed of the gas generator of said hybrid turboshaft engine in a period in the range of between 10 seconds and 60 seconds;

driving the hybrid turboshaft engine in an assisted super-idle standby mode, in which the hybrid turboshaft engine is rotating to a speed in the range of between 20% and 60% of the nominal speed of the gas generator of said hybrid turboshaft engine;

driving the hybrid turboshaft engine in a turning standby mode, in which the gas generator of said hybrid turboshaft engine is rotating to a speed in the range of between 5% and 20% of the nominal speed of the gas generator of said hybrid turboshaft engine,

said first reactivation system being configured to drive said hybrid turboshaft engine in the rapid reactivation mode, the normal reactivation mode, and at least one of the assisted super-idle standby mode or the turning standby mode; and

said second reactivation system being configured to drive said hybrid turboshaft engine in said normal reactivation mode.

2. A method for reactivating a hybrid turboshaft engine, said hybrid turboshaft engine being comprised in an architecture of a propulsion system of a multi-engine helicopter, said architecture having turboshaft engines connected to a power transmission gearbox, said hybrid turboshaft engine being capable of operating in at least one standby mode during a stable cruise flight of the helicopter and a second turboshaft engine operating during the stable cruise flight,

said method comprising:

driving the hybrid turboshaft engine in a rapid reactivation mode, wherein said hybrid turboshaft engine is rotated up to a speed greater in the range of between 80% and 105% of a nominal speed of a gas generator of said hybrid turboshaft engine in a period of less than 10 seconds;

driving the hybrid turboshaft engine in a normal reactivation mode, wherein said hybrid turboshaft engine is rotated at the speed of 105% of the nominal speed of the gas generator of said hybrid turboshaft engine in a period in the range of between 10 seconds and 60 seconds;

driving the hybrid turboshaft engine in an assisted super-idle standby mode, in which the hybrid turboshaft engine is rotating up to a speed in the range of between 20% and 60% of the nominal speed of the gas generator of said hybrid turboshaft engine;

driving the hybrid turboshaft engine in a turning standby mode, in which the gas generator of said hybrid turboshaft engine is rotating up to a speed in the range of between 5% and 20% of the nominal speed of the gas generator of said hybrid turboshaft engine,

said second reactivation system being configured to drive said hybrid turboshaft engine in said normal reactivation mode.

3. A method for reactivating a hybrid turboshaft engine, said hybrid turboshaft engine being comprised in an architecture of a propulsion system of a multi-engine helicopter, said architecture having turboshaft engines connected to a power transmission gearbox, said hybrid turboshaft engine being capable of operating in at least one standby mode during a stable cruise flight of the helicopter and a second turboshaft engine operating during the stable cruise flight,

said method comprising:

driving the hybrid turboshaft engine in a normal reactivation mode, wherein said hybrid turboshaft engine is rotated up to a speed in the range of between 80% and 105% of the nominal speed of the gas generator of said hybrid turboshaft engine in a period in the range of between 10 seconds and 60 seconds;

driving the hybrid turboshaft engine in an assisted super-idle standby mode, in which the hybrid turboshaft engine is rotating at the speed of 60% of the nominal speed of the gas generator of said hybrid turboshaft engine;

said second reactivation system being configured to drive said hybrid turboshaft engine in said normal reactivation mode.

4. A method for reactivating a hybrid turboshaft engine, said hybrid turboshaft engine being comprised in an architecture of a propulsion system of a multi-engine helicopter, said architecture having turboshaft engines connected to a power transmission gearbox, said hybrid turboshaft engine being capable of operating in at least one standby mode during a stable cruise flight of the helicopter and a second turboshaft engine operating during the stable cruise flight,

said method comprising:

driving the hybrid turboshaft engine in a turning standby mode, in which the gas generator of said hybrid turboshaft engine is rotating at the speed of 20% of the nominal speed of the gas generator of said hybrid turboshaft engine,

said second reactivation system being configured to drive said hybrid turboshaft engine in said normal reactivation mode.

5. A method for reactivating a hybrid turboshaft engine, said hybrid turboshaft engine being comprised in an architecture of a propulsion system of a multi-engine helicopter, said architecture having turboshaft engines connected to a power transmission gearbox, said hybrid turboshaft engine being capable of operating in at least one standby mode during a stable cruise flight of the helicopter and a second turboshaft engine operating during the stable cruise flight,

said method comprising:

driving the hybrid turboshaft engine in a rapid reactivation mode, wherein said hybrid turboshaft engine is rotated at the speed of 105% of a nominal speed of a gas generator of said hybrid turboshaft engine in a period of less than 10 seconds;

said second reactivation system being configured to drive said hybrid turboshaft engine in said normal reactivation mode.

Assignments (1)

ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Aug 15, 2019

From: VALLART, PHILIPPE; BAZET, JEAN-MICHEL; LE DUIGOU, LOÏC

To: TURBOMECA; LABINAL POWER SYSTEMS

Reel/Frame 050062/0843 →

Priority Claims (1)

FR 1459777 · Oct 13, 2014 · national

Continuity (1)

Related Publication 20170305541A1 · Oct 26, 2017

Cited By (16)

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