Method for managing the propulsive power of an aircraft

Patent metadata

Field	Value
Publication number	US-11840338-B2
Application number	US-201917263119-A
Country	US
Kind code	B2
Filing date	Jul 18, 2019
Priority date	Aug 1, 2018
Publication date	Dec 12, 2023
Grant date	Dec 12, 2023

Abstract

A method for managing the propulsive power of an aircraft, the aircraft extending longitudinally along an axis X from the rear forwards and comprising at least two lateral propulsion systems each comprising a fan, each lateral propulsion system having a fan rotation speed N2 and at least one rear propulsion system configured to ingest a boundary layer of said aircraft, the rear propulsion system comprising a fan having a fan rotation speed N3, the management system comprising, during a cruising phase P4, a step of adjusting the rotation speed N3 of the rear propulsion system according to the following formula N3=a*N2 in which a is a constant.

First claim

The invention claimed is:

1. A method for managing the propulsive power of an aircraft, the aircraft extending longitudinally along an axis X from the rear forwards and comprising at least two thermal lateral propulsion systems each comprising a fan, each lateral propulsion system having a fan rotation speed N2 and at least one rear propulsion system configured to ingest a boundary layer of said aircraft, the rear propulsion system comprising a fan having a fan rotation speed N3, management method wherein, during a cruise phase P4, a step of adjusting the rotation speed N3 of the rear propulsion system according to the following formula:
N 3 =a*N 2

in which a is a constant.

2. The management method according to claim 1 , wherein, the fan of a lateral propulsion system having a diameter d2, the fan of a rear propulsion system having a diameter d3, the method comprises, during a cruise phase P4, a step of adjusting the rotation speed N3 of the rear propulsion system according to the following formula:
d 3 *N 3 =b*d 2 *N 2

in which b is a constant comprised between 0.85 and 1.15.

3. The management method according to claim 1 , comprising, during a climb phase P1 of the aircraft, a step of adjusting the rotation speed N 3 of the rear propulsion system to a first reference rotation speed N S1 in such a way as to supply a first predetermined constant propulsive power VP 1 .

4. The management method according to claim 3 , comprising, during an idle phase P3, a step of adjusting the rotation speed N 3 of the rear propulsion system as a function of the rotation speed N 2 of the lateral propulsion systems wherein:
if the rotation speed N 2 of the lateral propulsion systems multiplied by the constant a is less than the first reference rotation speed N S1 , the rotation speed N 3 of the rear propulsion system is adjusted according to the following formula:
N 3 =a*N 2

if the rotation speed N 2 of the lateral propulsion systems multiplied by the constant a is greater than the first reference rotation speed N S1 , the rotation speed N 3 of the rear propulsion system is equal to the first reference rotation speed N S1 .

5. The management method according to claim 3 , comprising during a take-off phase P2, a step of adjusting the rotation speed N 3 of the rear propulsion system to a second reference rotation speed N S2 in such a way as to supply a second predetermined propulsive power VP 2 strictly greater than the first predetermined propulsive power VP 1 .

6. The management method according to claim 5 , wherein the second predetermined propulsive power VP 2 is defined according to the following formula:
V p2 =V p1 +F 1
in which F1 is a positive adaptation function which depends notably on the altitude and the speed of the aircraft.

7. The management method according to claim 3 , wherein the rear propulsion system comprising at least one fan driven by an electric motor, the first propulsive power is predetermined as a function of the continuous maximum power of the electric motor of the rear propulsion system.

8. The management method according to claim 3 , comprising:
in the event of breakdown of one of the lateral propulsion systems, a step of adjusting the rotation speed N 3 of the rear propulsion system in such a way as to be equal to a third reference rotation speed N S3 in order to supply half of the first predetermined propulsive power V P1 .

9. The management method according to claim 1 , wherein each lateral propulsion system comprising at least one bleed valve, the method comprising:
in the event of breakdown of the rear propulsion system, a step of opening the bleed valves of the lateral propulsion systems.

10. The management method according to claim 1 , wherein outside of the cruise phase, the rotation speed N 3 of the rear propulsion system is defined according to the following formula N 3 ≤a*N 2 .

11. A computer program comprising instructions for the execution of the steps of the management method according to claim 1 when said program is executed by the computer.

Assignees

• Safran

Inventors

• Zarati Khaled
• Giannakakis Panagiotis

Classifications

• B64D31/06

  actuated automatically · CPC title

• B64D27/32

  within, or attached to, fuselages · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• B64D27/12 Primary

  within, or attached to, wings · CPC title