Inlet configuration enabling rapid in-flight engine restart

Patent metadata

Field	Value
Publication number	US-11898500-B2
Application number	US-202017130358-A
Country	US
Kind code	B2
Filing date	Dec 22, 2020
Priority date	Dec 22, 2020
Publication date	Feb 13, 2024
Grant date	Feb 13, 2024

Abstract

Embodiments are directed to systems and methods for controlling an aircraft engine inlet comprises determining a required engine RPM for an engine in-flight restart based upon current aircraft parameters, detecting a command to initiate the engine in-flight restart, and managing a position of an engine inlet barrier to control a volume of air entering an engine intake, wherein the ram air causes an engine turbine to achieve the required engine RPM. The required engine RPM may be an N1 gas generator RPM. The engine inlet barrier may be a hinged door positioned within the engine inlet or a series of inlet variable guide vanes that are configured to rotate between a closed position and an opened position. The position of the engine inlet barrier may be controlled by a flight control computer or an engine control computer.

First claim

What is claimed is:

1. A method for controlling an aircraft engine inlet, comprising:
maintaining an engine inlet barrier in a closed position while an engine is shut down during flight;
determining a required engine RPM for an engine in-flight restart based upon current aircraft parameters;
detecting a command to initiate the engine in-flight restart;
managing a position of the engine inlet barrier to control a volume of ram air entering an engine intake;
monitoring parameters of the ram air in the engine intake; and
adjusting the position of the engine inlet barrier, in response to the parameters of the air in the engine intake, such that the ram air causes the engine to achieve the required engine RPM.

2. The method of claim 1 , wherein the required engine RPM is gas generator speed.

3. The method of claim 1 , wherein the engine inlet barrier is a hinged door positioned within the engine inlet.

4. The method of claim 1 , wherein the engine inlet barrier is a series of engine inlet variable guide vanes that are configured to rotate between a closed position and an opened position.

5. The method of claim 1 , wherein the position of the engine inlet barrier is controlled by a flight control computer or an engine control computer.

6. The method of claim 1 , further comprising:
monitoring current aircraft parameters, wherein the aircraft parameters comprise one or more of: an airspeed, an altitude, and an outside air temperature; and
wherein the required engine RPM for the engine in-flight restart is updated at regular intervals or when the current aircraft parameters change by a threshold amount.

7. The method of claim 1 , further comprising:
detecting a command to shut down the engine while in flight; and
managing the position of the engine inlet barrier to block ram air from entering the engine intake.

8. The method of claim 7 , further comprising:
monitoring engine parameters during a shutdown sequence; and
closing the engine inlet barrier when the engine is below a minimum engine RPM.

9. The method of claim 1 , further comprising monitoring a current engine RPM, and wherein adjusting the position of the engine inlet barrier further comprises adjusting the position of the engine inlet barrier, in response to the parameters of the air in the engine intake and the current engine RPM, to maximize the rate at which the engine achieves the required engine RPM.

10. The method of claim 1 , wherein managing the position of the engine inlet barrier comprises:
adjusting the position of the engine inlet barrier according to a predetermined schedule.

11. The method of claim 1 , wherein the required engine RPM is determined from aircraft performance chart data.

12. The method of claim 1 , wherein managing the position of the engine inlet barrier comprises:
providing a command to one or more actuators to adjust the engine inlet barrier to conform to a calculated engine inlet area.

13. An aircraft, comprising:
an engine inlet configured to provide air to an engine during flight;
an engine inlet barrier configured to manage a volume of air provided to the engine;
a flight control system configured to:
maintain the engine inlet barrier in a closed position while the engine is shut down during flight
determine a required engine RPM for an engine in-flight restart based upon current aircraft parameters;
manage a configuration of the engine inlet barrier to control the volume of air entering the engine inlet during the engine in-flight restart, the volume of air selected to cause the engine to achieve the required engine RPM;
monitor parameters of the air in the engine intake during the engine in-flight restart; and
adjust the configuration of the engine inlet barrier during the engine in-flight restart, in response to the parameters of the air in the engine intake during the engine in-flight restart, to achieve the volume of air selected to cause the engine to achieve the required engine RPM.

14. The aircraft of claim 13 , wherein the flight control system is further configured to:
determine the required engine RPM after detecting a command to initiate the engine in-flight restart.

15. The aircraft of claim 13 , wherein the engine inlet barrier is a hinged door positioned within the engine inlet.

16. The aircraft of claim 13 , wherein the engine inlet barrier is a series of engine inlet variable guide vanes that are configured to rotate between a closed position and an opened position.

17. The aircraft of claim 13 , wherein the flight control system is further configured to:
detect a command to shut down the engine while in flight; and
manage the position of the engine inlet barrier to block air from entering the engine intake.

18. A flight control computer for an aircraft, comprising:
one or more processors;
one or more non-transitory computer-readable storage media having stored thereon computer-executable instructions that, when executed by the one or more processors, causes the processors to:
maintain an engine inlet barrier in a closed position while an engine is shut down during flight;
determine a required engine RPM for an engine in-flight restart based upon current aircraft parameters;
select a volume of air entering an engine intake during the engine in-flight restart to cause the engine to achieve the required engine RPM; and
manage a configuration of the engine inlet barrier to control the volume of air entering the engine intake during the engine in-flight restart;
monitor parameters of the air in the engine intake during the engine in-flight restart; and
adjust the position of the engine inlet barrier during the engine in-flight restart, in response to the parameters of the air in the engine intake during the engine in-flight restart, to achieve the volume of air selected to cause the engine to achieve the required engine RPM.

19. The flight control computer of claim 18 , wherein the computer-executable instructions further cause the processors to:
monitor a current engine RPM during the engine in-flight restart; and
adjust the position of the engine inlet barrier, in response to the parameters of the air in the engine intake during the engine in-flight restart and the current engine RPM during the engine in-flight restart, to maximize the rate at which the engine achieves the required engine RPM.

20. The flight control computer of claim 18 , wherein the computer-executable instructions further cause the processors to:
adjust the position of the engine inlet barrier according to a predetermined schedule.

Assignees

• Bell Textron Inc
• Textron Innovations Inc

Inventors

• Parsons Thomas Dewey

Classifications

• F02C9/20 Primary

  by throttling; by adjusting vanes · CPC title

• F02C7/057

  Control or regulation (conjointly with fuel supply control F02C9/50, with nozzle area control F02K1/16) · CPC title

• F02C7/26 Primary

  Starting; Ignition · CPC title

• F02C7/262

  Restarting after flame-out · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title