Multi-engine coordination during gas turbine engine motoring

Patent metadata

Field	Value
Publication number	US-11047257-B2
Application number	US-201715656444-A
Country	US
Kind code	B2
Filing date	Jul 21, 2017
Priority date	Jul 21, 2016
Publication date	Jun 29, 2021
Grant date	Jun 29, 2021

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

What is claimed is:

1. A system of an aircraft, the system comprising:
a compressed air source operable to supply compressed air;
a first engine system comprising a first gas turbine engine, a first air turbine starter, a first starter air valve, and a first controller operable to command the first starter air valve to control delivery of the compressed air to the first air turbine starter during motoring of the first gas turbine engine;
a second engine system comprising a second gas turbine engine, a second air turbine starter, a second starter air valve, and a second controller operable to command the second starter air valve to control delivery of the compressed air to the second air turbine starter during motoring of the second gas turbine engine; and
at least one engine control interface comprising one or more processors and memory comprising a plurality of instructions that when executed by the one or more processors cause the at least one engine control interface to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on a first temperature of the first gas turbine engine and a second temperature of the second gas turbine engine, identify a present multi-engine dry motoring capability by determining whether a dry motoring threshold speed can be reached by the first gas turbine engine and the second gas turbine engine at a same time based on the first temperature and the second temperature, select between the single engine dry motoring mode and the multi-engine dry motoring mode based on the present multi-engine dry motoring capability, and initiate dry motoring based on the motoring mode.

2. The system of 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, performance limitations of the compressed air source and each air turbine starter driven by the compressed air source, engine drag, and parasitic factors.

3. The system of claim 1 , wherein the compressed air source is an auxiliary power unit of the aircraft, a ground cart, or a cross engine bleed.

4. The system of claim 1 , wherein the at least one engine control interface is further operable to monitor a first speed of the first gas turbine engine and a second speed of the second gas turbine engine and switch from the multi-engine dry motoring mode to the single engine dry motoring mode based on the first gas turbine engine or the second gas turbine engine failing to reach or maintain the dry motoring threshold speed for a predetermined time limit.

5. The system of claim 4 , wherein the dry motoring threshold speed is dynamically adjusted to match a dry motoring profile.

6. The system of claim 1 , wherein the first temperature is a measured core engine temperature or an oil temperature of the first gas turbine engine.

7. The system of claim 1 , wherein the second temperature is a measured core engine temperature or an oil temperature of the second gas turbine engine.

8. The system of claim 1 , wherein dry motoring is inhibited when the aircraft is not on the ground.

9. A method for multi-engine coordination during gas turbine engine motoring, the method comprising:
determining, by at least one engine control interface comprising one or more processors and memory comprising a plurality of instructions, a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on a first temperature of a first gas turbine engine and a second temperature of a second gas turbine engine;
identifying a present multi-engine dry motoring capability by determining whether a dry motoring threshold speed can be reached by the first gas turbine engine and the second gas turbine engine at a same time based on the first temperature and the second temperature;
selecting between the single engine dry motoring mode and the multi-engine dry motoring mode based on the present multi-engine dry motoring capability; and
initiating dry motoring based on the motoring mode, wherein the first gas turbine engine is part of a first engine system comprising a first air turbine starter, a first starter air valve, and a first controller operable to command the first starter air valve to control delivery of compressed air from a compressed air source to the first air turbine starter during motoring of the first gas turbine engine, and the second gas turbine engine is part of a second engine system comprising a second air turbine starter, a second starter air valve, and a second controller operable to command the second starter air valve to control delivery of the compressed air to the second air turbine starter during motoring of the second gas turbine engine.

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

11. The method as in claim 9 , 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, performance limitations of the compressed air source and each air turbine starter driven by the compressed air source, engine drag, and parasitic factors.

12. The method as in claim 9 , wherein the compressed air source is an auxiliary power unit of the aircraft, a ground cart, or a cross engine bleed.

13. The method as in claim 9 , further comprising:
monitoring a speed of each of the first and second 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 first and second gas turbine engines failing to reach or maintain the dry motoring threshold speed for a predetermined time limit.

14. The method as in claim 13 , wherein the dry motoring threshold speed is dynamically adjusted to match a dry motoring profile.

15. A system of an aircraft, the system comprising:
a first engine system comprising a first gas turbine engine and a first means to control dry motoring of the first gas turbine engine;
a second engine system comprising a second gas turbine engine and a second means to control dry motoring of the second gas turbine engine; and
at least one engine control interface comprising one or more processors and memory comprising a plurality of instructions that when executed by the one or more processors cause the at least one engine control interface to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on a first temperature of the first gas turbine engine and a second temperature of the second gas turbine engine, identify a present multi-engine dry motoring capability by determining whether a dry motoring threshold speed can be reached by the first gas turbine engine and the second gas turbine engine at a same time based on the first temperature and the second temperature, select between the single engine dry motoring mode and the multi-engine dry motoring mode based on the present multi-engine dry motoring capability, and initiate dry motoring based on the motoring mode.

16. The system of claim 15 , wherein the first temperature is a measured core engine temperature or an oil temperature of the first gas turbine engine.

17. The system of claim 15 , wherein the second temperature is a measured core engine temperature or an oil temperature of the second gas turbine engine.

18. The system of claim 15 , wherein dry motoring is inhibited when the aircraft is not on the ground.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

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

Classifications

• B64F1/34

  for starting propulsion plant · CPC title

• F01D19/02 Primary

  dependent on temperature of component parts, e.g. of turbine-casing · CPC title

• F05D2260/85

  Starting · CPC title

• F02C9/00

  Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants (controlling air intakes F02C7/057; controlling turbines F01D; controlling compressors F04D27/00; controlling in general G05) · CPC title

• F02C3/04

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