Multi-engine coordination during gas turbine engine motoring

Patent metadata

Field	Value
Publication number	US-11674411-B2
Application number	US-202117359894-A
Country	US
Kind code	B2
Filing date	Jun 28, 2021
Priority date	Jul 21, 2016
Publication date	Jun 13, 2023
Grant date	Jun 13, 2023

Abstract

A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode.

First claim

The invention claimed is:

1. A system for multi-engine coordination of gas turbine engine motoring in an aircraft, the system comprising:
a controller configured to:
determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines, wherein the at least one temperature is used to determine current conditions of the gas turbine engines and select a multi-engine dry motoring envelope to identify a multi-engine dry motoring capability that indicates whether a dry motoring threshold speed can be reached by the gas turbine engines at the same time; and
initiate dry motoring based on the motoring mode.

2. The system as in claim 1 , wherein the at least one temperature is a measured core engine temperature or an oil temperature.

3. The system as in claim 1 , wherein dry motoring is inhibited when the aircraft is not on the ground.

4. The system as in claim 1 , wherein the motoring mode is further determined based on a plurality of performance parameters that are based on one or more of: an ambient condition, engine drag, parasitic factors, and performance limitations of a compressed air source that drives at least one air turbine starter of the gas turbine engines.

5. The system as in claim 4 , wherein the performance parameters are determined based on one or more of: an ambient air temperature, an ambient pressure, and an oil temperature.

6. The system as is claim 4 , wherein the single engine dry motoring mode and the multi-engine dry motoring mode are driven by the compressed air source, and the compressed air source is an auxiliary power unit of the aircraft, a ground cart, or a cross engine bleed.

7. The system as in claim 1 , wherein the controller is further operable to monitor a speed of each of the gas turbine engines when dry motoring is active and switch from the multi-engine dry motoring mode to the single engine dry motoring mode based on one or more of the gas turbine engines failing to reach or maintain the dry motoring threshold speed for a predetermined time limit.

8. The system as in claim 7 , wherein the dry motoring threshold speed is dynamically adjusted to match a dry motoring profile.

9. A method for multi-engine coordination of gas turbine engine motoring in an aircraft, the method comprising:
determining at least one temperature of a plurality of gas turbine engines;
determining a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on the at least one temperature of the gas turbine engines, wherein the at least one temperature is used to determine current conditions of the gas turbine engines and select a multi-engine dry motoring envelope to identify a multi-engine dry motoring capability that indicates whether a dry motoring threshold speed can be reached by the gas turbine engines at the same time; and
initiating dry motoring based on the motoring mode.

10. The method as in claim 9 , wherein the at least one temperature is a measured core engine temperature or an oil temperature.

11. The method as in claim 9 , further comprising:
inhibiting dry motoring when the aircraft is not on the ground.

12. The method as in claim 9 , further comprising:
determining a plurality of performance parameters based on one or more of: an ambient condition, engine drag, parasitic factors, and performance limitations of a compressed air source that drives at least one air turbine starter of the gas turbine engines; and
determining the motoring mode based on one or more of the performance parameters.

13. The method as in claim 12 , wherein the performance parameters are determined based on one or more of: an ambient air temperature, an ambient pressure, and an oil temperature.

14. The method as in claim 12 , wherein the single engine dry motoring mode and the multi-engine dry motoring mode are driven by the compressed air source, and the compressed air source is an auxiliary power unit of the aircraft, a ground cart, or a cross engine bleed.

15. The method as in claim 9 , further comprising:
monitoring a speed of each of the gas turbine engines when dry motoring is active; and
switching from the multi-engine dry motoring mode to the single engine dry motoring mode based on one or more of the gas turbine engines failing to reach or maintain the dry motoring threshold speed for a predetermined time limit.

16. The method as in claim 15 , further comprising:
dynamically adjusted the dry motoring threshold speed to match a dry motoring profile.

17. A system of an aircraft, the system comprising:
a means for determining a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiating dry motoring based on the motoring mode, wherein the at least one temperature is used to determine current conditions of the gas turbine engines and select a multi-engine dry motoring envelope to identify a multi-engine dry motoring capability that indicates whether a dry motoring threshold speed can be reached by the gas turbine engines at the same time.

18. The system as in claim 17 , wherein dry motoring is inhibited when the aircraft is not on the ground, and the motoring mode is further determined based on a plurality of performance parameters that are based on one or more of: an ambient condition, engine drag, parasitic factors, and performance limitations of a compressed air source that drives at least one air turbine starter of the gas turbine engines.

19. The system as in claim 17 , further comprising:
a means for monitoring a speed of each of the gas turbine engines when dry motoring is active and switching from the multi-engine dry motoring mode to the single engine dry motoring mode based on one or more of the gas turbine engines failing to reach or maintain the dry motoring threshold speed for a predetermined time limit.

20. The system as in claim 19 , wherein the dry motoring threshold speed is dynamically adjusted to match a dry motoring profile.

Assignees

• Raytheon Tech Corp

Inventors

• Chowdhury Subhradeep
• Bostwick David M
• Gelwan David
• Schwarz Frederick M

Classifications

• F05D2260/85

  Starting · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• B64D2041/002

  Mounting arrangements for auxiliary power units (APU's) · CPC title

• F05D2220/50

  for auxiliary power units (APU's) · CPC title