Hybrid propulsion system for a multi-engine aircraft

Patent metadata

Field	Value
Publication number	US-10737795-B2
Application number	US-201515519878-A
Country	US
Kind code	B2
Filing date	Oct 15, 2015
Priority date	Oct 20, 2014
Publication date	Aug 11, 2020
Grant date	Aug 11, 2020

Abstract

The hybrid propulsion system for a multi-engine aircraft includes a plurality of free-turbine engines, each having a gas generator, among which at least a first engine, or hybrid engine, is suitable for operating in at least one standby mode during stabilized flight of the aircraft, while other engines of the plurality of engines operate alone during such stabilized flight. The hybrid engine is associated with first and second identical electric powertrains, each including a respective electrical machine capable of operating as a starter and as a generator, itself connected to a respective electronic power module, itself selectively connected to a specific electrical power supply network, such as an onboard network, and to a respective at least one electrical energy storage member. Each of the electric powertrains is adapted to deliver maximum power not less than half the total power needed for rapid reactivation of the hybrid engine.

First claim

The invention claimed is:

1. A hybrid propulsion system for a multi-engine aircraft, the system comprising:
a plurality of free-turbine engines each having a gas generator, the plurality of free-turbine engines including a first hybrid engine operable in a standby mode during a stabilized flight of the multi-engine aircraft, while other engines of said plurality of free-turbine engines operate alone during the stabilized flight, the hybrid engine being electrically connected to a first electric powertrain and a second electric powertrain identical to and distinct from the first electric powertrain,
the first electric powertrain comprising
a first electrical machine operable as a starter and as a generator,
a first electronic power module connected to the first electrical machine,
a specific electrical power supply network, and
a first electrical energy storage member,

the second electric powertrain comprising
a second electrical machine operable as a starter and as a generator,
a second electronic power module connected to the second electrical machine, and
a second electrical energy storage member,

wherein the first electric power module is configured to
selectively connect to the specific electrical power supply network to provide a standby power, a half standby power, a normal reactivation power, and a half normal reactivation power, to the first electrical machine, and
selectively connect to the first electrical energy storage to provide a half rapid reactivation power and the normal reactivation power, to the first electrical machine, wherein the second electric power module is configured to
selectively connect to the specific electrical power supply network to provide the standby power, the half standby power, the normal reactivation power, and the half normal reactivation power, to the second electrical machine, and
selectively connect to the second electrical energy storage to provide the half rapid reactivation power and the normal reactivation power, to the second electrical machine, and

wherein the normal reactivation power is less than the rapid reactivation power, and the standby power is less than the normal reactivation power.

2. The hybrid propulsion system according to claim 1 , wherein said normal reactivation power or is 20% of the rapid reactivation power.

3. The hybrid propulsion system according to claim 1 , wherein said standby power is 3% to 5% of the rapid reactivation power.

4. The hybrid propulsion system according to claim 1 , wherein each of the first and second electronic power modules is further configured to receive power respectively from the first and the second electrical energy storage members in order to power respectively in isolated manner and in alternation with the other of the first and the second electronic power modules, each of the first and the second electrical machines with the normal reactivation power.

5. The hybrid propulsion system according to claim 4 , wherein each of the first and the second electronic power modules is further configured to receive power from the specific electrical power supply network or respectively from the first and the second electrical energy storage member in order to power respectively in isolated manner and in alternation with the other of the first and the second electronic power modules, or in simultaneous manner, the first and second electrical machines with a variable power being less than or equal to the half rapid reactivation power.

6. The hybrid propulsion system according to claim 1 , wherein each of the first and the second electronic power modules is further configured to receive power respectively from the first and the second electrical energy storage member for powering respectively and simultaneously with the other of the first and the second electronic power modules, each of the first and the second electrical machines with the half rapid reactivation power.

7. The hybrid propulsion system according to claim 1 , wherein each of the first and the second electronic power modules is further configured to receive power from the specific electrical power supply network in order to power respectively and simultaneously with the other of the first and the second electronic power modules the first and second electrical machines either with the half normal reactivation power, or with the half standby power.

8. The hybrid propulsion system according to claim 1 , wherein each of the first and the second electronic power modules is further configured to receive power respectively from the first and the second electrical energy storage member in order to power respectively and simultaneously with the other of the first and the second electronic power modules the first and second electrical machines, either with the half normal reactivation power or with the half standby power.

9. The hybrid propulsion system according to claim 1 , wherein each of the first and the second electronic power modules is further configured to receive power from the specific electrical power supply network in order to power respectively in isolated manner and in alternation with the other of the first and the second electronic power modules, the first and the second electrical machines either with the normal reactivation power or with the standby power.

10. The hybrid propulsion system according to claim 1 , wherein the first and second electrical energy storage members comprise two storage members that are physically dissociated.

11. The hybrid propulsion system according to claim 1 , wherein the first and second electrical energy storage members comprise two storage members that are distinct but physically grouped together.

12. A multi-engine aircraft comprising the hybrid propulsion system according to claim 1 .

Assignees

• Safran Helicopter Engines

Inventors

• Moulon Frederic
• Mercier-Calvairac Fabien
• Le Maux David

Classifications

• B64D27/35

  Arrangements for on-board electric energy production, distribution, recovery or storage · CPC title

• B64D27/33 Primary

  Hybrid electric aircraft · CPC title

• B64C27/12 Primary

  Rotor drives · CPC title

• F01D15/10

  Adaptations for driving, or combinations with, electric generators · CPC title

• B64D33/00 Primary

  Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for · CPC title