Method of regulating a three-engined power plant for a rotary wing aircraft

Patent metadata

Field	Value
Publication number	US-10106268-B2
Application number	US-201615175269-A
Country	US
Kind code	B2
Filing date	Jun 7, 2016
Priority date	Jun 23, 2015
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

A power plant comprising two engine groups and a main power transmission gearbox. Each engine group drives the main gearbox mechanically in order to rotate a main rotor of an aircraft at a frequency of rotation NR. A first engine group comprising two main engines is regulated on a first setpoint NR* for the frequency of rotation NR, while a second engine group comprising a secondary engine is regulated on a second setpoint W 2 * for power. The second setpoint W 2 * for power is determined so that each secondary engine operates only when a flight power W vol necessary for the flight of the aircraft is greater than the sum of the main maximum powers W Max1 from each main engine.

First claim

What is claimed is:

1. A method of regulating a power plant of a rotary wing aircraft, the power plant comprising a first engine group, a second engine group, and a main power transmission gearbox, the first engine group and the second engine group mechanically driving the main gearbox in order to rotate a main outlet shaft of the main gearbox, the main outlet shaft being constrained to rotate with a main rotor of the aircraft having a frequency of rotation NR, the first engine group having at least two main engines, the second engine group having at least one secondary engine, each main engine being capable of delivering a main maximum power W Max1 , each secondary engine being capable of delivering a secondary maximum power W Max2 , the method comprising the following steps:
determining a first setpoint NR* for the frequency of rotation NR of the main rotor;
regulating operation of each main engine on the first setpoint NR* for the frequency of rotation NR;
determining a flight power W vol needed for the flight of the aircraft, the flight power W vol being delivered by the power plant;
determining a second setpoint W 2 * for power to be delivered by the second engine group so that each secondary engine operates only when the flight power W vol is greater than the sum of the main maximum powers W Max1 of each main engine; and
regulating operation of each secondary engine on the second setpoint W 2 for power.

2. A method of regulating a power plant according to claim 1 , comprising the following steps:
determining a flight anticipation power Ws* needed for the flight of the aircraft and to be delivered jointly by the first engine group and the second engine group; and
determining a third setpoint W 1 * for power to be delivered by the first engine group, such that:
Ws*=W 1 *+W 2 *

using the third setpoint W 1 * for power so that the first engine group and the second engine group anticipate a power need of the aircraft and deliver jointly the flight anticipation power Ws*.

3. A method of regulating a power plant according to claim 1 , wherein the second setpoint W 2 * is equal to:
the value zero when a first sum of the main maximum powers W Max1 from each main engine is greater than or equal to the flight power W vol ;
the difference between the flight power W vol and the first sum of the main maximum powers W Max1 when the difference is positive and less than a second sum of the main secondary maximum power W Max2 from each secondary engine; and
the second sum of the secondary maximum powers W Max2 when the difference is greater than the second sum of the secondary maximum powers W Max2 .

4. A method of regulating a power plant according to claim 1 , wherein the flight power W vol needed for the flight of the aircraft is determined depending on the stage of flight of the aircraft.

5. A method of regulating a power plant according to claim 1 , wherein the flight power W vol necessary for the flight of the aircraft is determined from performance plots of the aircraft.

6. A method of regulating a power plant according to claim 1 , wherein in the event of a failure of at least one main engine, the operation of each secondary engine is regulated on the first setpoint NR* for the frequency of rotation NR of the main rotor.

7. A method of regulating a power plant according to claim 1 , wherein in the event of a failure of at least one main engine, the operation of each secondary engine is regulated on the second setpoint W 2 * for power.

8. A method of regulating a power plant according to claim 1 , wherein in the event of a failure of at least one main engine, the operation of each secondary engine is regulated so that it delivers the secondary maximum power W Max2 .

9. A method of regulating a power plant according to claim 1 , wherein the first engine group comprises two identical main engines, and the second engine group comprises one secondary engine.

10. A power plant for an aircraft, the power plant comprising a first engine group, a second engine group, and a main power transmission gearbox, the first engine group and the second engine group mechanically driving the main gearbox in order to rotate at least one main outlet shaft of the main gearbox, the main outlet shaft being constrained to rotate with a main rotor of the aircraft having a frequency of rotation NR, the first engine group having at least two main engines, and a first regulator device, the first regulator device being configured to regulate operation of each main engine on a first setpoint NR* for the frequency of rotation NR of the main rotor, the second engine group comprising at least one secondary engine and a second regulator device, the second regulator device being configured to regulate operation of each secondary engine on a second setpoint W 2 * for power from the second engine group, the power plant being required to deliver a flight power W vol necessary for the flight of the aircraft, each main engine being capable of delivering a main maximum power W Max1 , each secondary engine being capable of delivering a secondary maximum power W Max2 , wherein the power plant includes calculation means configured to determine the second setpoint W 2 * so that each secondary engine operates only when the flight power W vol is greater than the sum of the main maximum powers W Max1 from each main engine.

11. A power plant according to claim 10 , wherein the calculation means comprise anticipation means configured to determine a flight anticipation power Ws* necessary for the flight of the aircraft and that needs to be delivered jointly by the first engine group and second engine group, a third setpoint W 1 * to be delivered by the first engine group and defined such that:
Ws*=W 1 *+W 2 *

being used so that the first engine group and the second engine group anticipate a power need of the aircraft and deliver jointly the flight anticipation power Ws*.

12. A power plant according to claim 10 , wherein the second setpoint W 2 * is equal to:
the value zero when a first sum of the main maximum powers W Max1 from each main engine is greater than or equal to the flight power W vol ;
the difference between the flight power W vol and the first sum of the main maximum powers W Max1 from each main engine when the difference is positive and less than a second sum of the main secondary maximum power W Max2 ; and
the second sum of the secondary maximum powers W Max2 when the difference is greater than the second sum of the secondary maximum powers W Max2 .

13. A power plant according to claim 10 , wherein the flight power W vol necessary for the flight of the aircraft is defined depending on the stage of flight of the aircraft on the basis of performance plots of the aircraft.

14. A power plant according to claim 10 , wherein the first engine group comprises two identical main engines and the second engine group comprises one secondary engine.

15. A rotary wing aircraft having at least a main rotor, a power plant, and an avionics installation, the power plant driving the main rotor in rotation, and the aircraft being wherein the power plant is a power plant according to claim 10 .

Assignees

• Airbus Helicopters

Inventors

• Rossotto Regis

Classifications

• F02C9/42

  specially adapted for the control of two or more plants simultaneously · CPC title

• B64C27/06

  with single rotor · CPC title

• F02C6/206

  the vehicles being airscrew driven · CPC title

• B64C27/12 Primary

  Rotor drives · CPC title

• F05D2220/329

  in helicopters · CPC title