Cross engine coordination during gas turbine engine motoring

Patent metadata

Field	Value
Publication number	US-10384791-B2
Application number	US-201715652320-A
Country	US
Kind code	B2
Filing date	Jul 18, 2017
Priority date	Jul 21, 2016
Publication date	Aug 20, 2019
Grant date	Aug 20, 2019

Abstract

A system is provided for cross engine coordination during gas turbine engine motoring. The system includes a first gas turbine engine of a first engine system, a first air turbine starter of the first engine system, a first starter air valve of the first engine system, and a controller. The controller is operable to command the first starter air valve to control delivery of compressed air to the first air turbine starter during motoring of the first gas turbine engine, monitor cross engine data of a second gas turbine engine of a second engine system to detect a present condition or a commanded action that modifies an aspect of the compressed air received at the first starter air valve, and command an adjustment to the first engine system to compensate for the modified aspect of the compressed air based on the cross engine data.

First claim

What is claimed is:

1. A system for cross engine coordination during gas turbine engine motoring, the system comprising:
a first gas turbine engine of a first engine system;
a first air turbine starter of the first engine system;
a first starter air valve of the first engine system; and
a controller operable to command the first starter air valve to control delivery of compressed air to the first air turbine starter during motoring of the first gas turbine engine, monitor cross engine data of a second gas turbine engine of a second engine system to detect a present condition or a commanded action that modifies an aspect of the compressed air received at the first starter air valve, and command an adjustment to the first engine system to compensate for the modified aspect of the compressed air based on the cross engine data.

2. The system as in claim 1 , wherein the compressed air is driven by an auxiliary power unit of the aircraft, a ground cart, or a cross engine bleed.

3. The system as in claim 1 , wherein the controller commands the first starter air valve based on one or more of: an engine speed of a starting spool of the first gas turbine engine, a starter speed of the first air turbine starter, and a starter air pressure.

4. The system as in claim 3 , wherein the adjustment to the first engine system maintains the engine speed of the starting spool of the first gas turbine engine below a resonance speed of the starting spool during motoring.

5. The system as in claim 1 , wherein the present condition comprises one or more of:
a detected fault condition of a second air turbine starter of the second engine system;
a detected fault condition of a second starter air valve of the second engine system;
a transition to start motoring of the second gas turbine engine;
a transition to stop motoring of the second gas turbine engine; and
a control input or modeled value to control motoring of the second gas turbine engine.

6. The system as is claim 1 , wherein the commanded action comprises a commanded change in state of one or more of: a second starter air valve of the second engine system, an engine shutoff valve, and a bleed valve operable to release a portion of the compressed air.

7. The system as in claim 1 , wherein the cross engine data further comprises a scheduled adjustment of one or more control parameters of the second engine system.

8. The system as in claim 1 , wherein the adjustment to the first engine system is based on monitoring a rate of change of one or more parameters received in the cross engine data.

9. 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
a communication bus operable to establish communication of cross engine data between the first controller and the second controller, wherein the first controller is operable to command an adjustment to the first engine system based on the cross engine data from the second controller, and the second controller is operable to command an adjustment to the second engine system based on the cross engine data from the first controller.

10. The system of claim 9 , wherein the first controller commands the first starter air valve based on one or more of: an engine speed of a starting spool of the first gas turbine engine, a starter speed of the first air turbine starter, and a starter air pressure of the first engine system, and wherein the second controller commands the second starter air valve based on one or more of: an engine speed of a starting spool of the second gas turbine engine, a starter speed of the second air turbine starter, and a starter air pressure of the second engine system.

11. The system of claim 10 , wherein the first engine system maintains the engine speed of the starting spool of the first gas turbine engine below a resonance speed during motoring of the first gas turbine engine, and the second engine system maintains the engine speed of the starting spool of the second gas turbine engine below the resonance speed during motoring of the second gas turbine engine.

12. The system of claim 9 , wherein the cross engine data comprises one or more of:
a detected fault condition of the first or second air turbine starter;
a detected fault condition of the first or second starter air valve;
a transition to start motoring of the first or second gas turbine engine;
a transition to stop motoring of the first or second gas turbine engine; and
a control input or modeled value to control motoring of the first or second gas turbine engine.

13. The system of claim 9 , wherein the cross engine data comprises a commanded change in state of one or more of: the first starter air valve, the second starter air valve, an engine shutoff valve, and a bleed valve operable to release a portion of the compressed air.

14. The system of claim 9 , wherein the cross engine data further comprises a scheduled adjustment of one or more control parameters of the first or second engine system.

15. A method for cross engine coordination during gas turbine engine motoring, the method comprising:
commanding, by a controller, a first starter air valve to control delivery of compressed air to a first air turbine starter during motoring of a first gas turbine engine of a first engine system;
monitoring, by the controller, cross engine data of a second gas turbine engine of a second engine system to detect a present condition or a commanded action that modifies an aspect of the compressed air received at the first starter air valve; and
commanding an adjustment to the first engine system to compensate for the modified aspect of the compressed air based on the cross engine data.

16. The method as in claim 15 , further comprising commanding the first starter air valve based on one or more of: an engine speed of a starting spool of the first gas turbine engine, a starter speed of the first air turbine starter, and a starter air pressure, wherein the adjustment to the first engine system maintains the engine speed of the starting spool of the first gas turbine engine below a resonance speed of the starting spool during motoring.

17. The method as in claim 15 , wherein the present condition comprises one or more of:
a detected fault condition of a second air turbine starter of the second engine system;
a detected fault condition of a second starter air valve of the second engine system;
a transition to start motoring of the second gas turbine engine;
a transition to stop motoring of the second gas turbine engine; and
a control input or modeled value to control motoring of the second gas turbine engine.

18. The method as in claim 15 , wherein the commanded action comprises a commanded change in state of one or more of: a second starter air valve of the second engine system, an engine shutoff valve, and a bleed valve operable to release a portion of the compressed air.

19. The method as in claim

Assignees

• United Technologies Corp

Inventors

• Gelwan David
• Clauson Jesse W
• Berry James K

Classifications

• F02C6/00

  Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use · CPC title

• F05D2220/323

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

• F05D2270/304

  Spool rotational speed · CPC title

• F05D2270/13

  to control two or more engines simultaneously · CPC title

• F02C7/277

  the starter being a {separate} turbine · CPC title