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

Patent metadata

Field	Value
Publication number	US-2016376017-A1
Application number	US-201615182663-A
Country	US
Kind code	A1
Filing date	Jun 15, 2016
Priority date	Jun 23, 2015
Publication date	Dec 29, 2016
Grant date	—

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 of the second engine group. In addition, each engine operates with margins relative to operating limits. The second setpoint W 2 * for power is determined so that each secondary engine operates with a lowest second margin that is equal to the lowest first margin of the first engine group.

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 two engine groups 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 having a plurality of main operating limits and operating with first margins respectively relative to each of the main operating limits, each secondary engine having a plurality of secondary operating limits and operating with second margins respectively relative to each of the secondary operating limits, the method comprising the following steps:
determining a first setpoint NR* for the frequency of rotation NR of the main rotor; regulating the operation of each main engine on the first setpoint NR* for the frequency of rotation NR; determining a second setpoint W 2 * for power to be delivered by the second engine group, so that each secondary engine operates with the lowest second margin that is equal to the lowest first margin of the first engine group; and regulating the 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; 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 groups and the second engine group anticipate a power need of the aircraft and act jointly to deliver the flight anticipation power Ws*.

3 . A method of regulating a power plant according to claim 1 , wherein, the main gearbox having a plurality of tertiary operating limits having a limit power that it can transmit to the outlet shaft, each main engine being capable of delivering a maximum power, when the most critical operating limit of the power plant is a tertiary limit of the main gearbox, the second setpoint W 2 * is determined so that it is equal to the limit power of the main gearbox minus the sum of the maximum powers of each main engine.

4 . A method of regulating a power plant according to claim 3 , wherein the maximum power for each main engine is determined depending on the stage of flight of the aircraft.

5 . A method of regulating a power plant according to claim 4 , wherein a selection algorithm is used for determining the stage of flight of the aircraft using the values for a horizontal speed Vh and a vertical speed Vz 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 its maximum power.

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 two engine groups 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 the 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 the operation of each secondary engine on a second setpoint W 2 * for power from the second engine group, each main engine having a plurality of main operating limits and operating with first margins relative to each of the main operating limits, each secondary engine having a plurality of secondary operating limits and operating with second margins relative to the secondary operating limits, the power plant including calculation means configured to determine the second setpoint W 2 * so that each secondary engine operates with the lowest second margin that is equal to the lowest first margin of the first engine group.

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 the 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 ( 10 ) and the second engine group ( 20 ) anticipate a power need of the aircraft ( 30 ) and deliver jointly the flight anticipation power Ws*.

12 . A power plant according to claim 10 , wherein the main gearbox having a plurality of tertiary operating limits having a limit power, each main engine being capable of delivering a maximum power, when the most critical operating limit of the power plant is a limit of the main gearbox, the calculation means determine the second setpoint W 2 * to be equal to the limit power of the main gearbox minus the sum of the maximum powers of each main engine.

13 . A power plant according to claim 12 , wherein the maximum power for each main engine is defined depending on the stage of flight 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 power plant according to claim 10 , wherein in the event of a failure of at least one main engine, the second regulation device is configured to regulate the operation of each secondary engine on the first setpoint NR* for the frequency of rotation NR of the main rotor.

16 . 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 including the power plant that is a power plant according to claim 10 .

Assignees

• Airbus Helicopters

Inventors

• Rossotto Regis

Classifications

• B64D35/08

  characterised by the transmission being driven by a plurality of power plants (for hybrid-electric power plants B64D35/022) · CPC title

• B64D31/09

  in response to power plant failure · CPC title

• B64C27/12 Primary

  Rotor drives · CPC title

• F05D2270/13

  to control two or more engines simultaneously · CPC title

• F05D2220/329

  in helicopters · CPC title