Surge margin control

Patent metadata

Field	Value
Publication number	US-9341076-B2
Application number	US-201213493433-A
Country	US
Kind code	B2
Filing date	Jun 11, 2012
Priority date	Jun 16, 2011
Publication date	May 17, 2016
Grant date	May 17, 2016

Abstract

A gas turbine engine control system comprising a variable stator vane schedule for normal operation of the gas turbine engine. The system is configured to generate an arm signal indicating potential shaft break. Then the system is configured to alter the variable stator vane schedule to slew each variable stator vane to decrease the available surge margin in response to the arm signal. Or the system is configured to limit a response rate of a variable stator vane actuator in response to the arm signal. Or the system is configured to alter the variable stator vane schedule and limit the response rate of the actuator.

First claim

The invention claimed is:

1. A gas turbine engine control system comprising:
a nominal variable stator vane schedule for normal operation of the gas turbine engine, and an altered variable stator vane schedule for decreasing the available surge margin of the gas turbine engine, the system is configured to:
generate an arm signal indicating potential shaft break; and
switch from the nominal variable stator vane schedule to the altered variable stator vane schedule to slew each variable stator vane to decrease the available surge margin in response to the arm signal.

2. The gas turbine engine control system as claimed in claim 1 , further configured to limit a response rate of a variable stator vane actuator in response to the arm signal.

3. The gas turbine engine control system as claimed in claim 1 , wherein the variable stator vanes are each slewed by 5°.

4. The gas turbine engine control system as claimed in claim 1 , wherein the variable stator vanes are each slewed by an angle dependent on engine power.

5. The gas turbine engine control system as claimed in claim 1 , wherein the variable stator vanes are each slewed by an angle dependent on an environmental operating condition experienced by the gas turbine engine.

6. The gas turbine engine control system as claimed in claim 1 , further configured to:
generate a shaft failure signal in response to a shaft failure indicator; and
command gas turbine engine shut down in response to the shaft failure signal.

7. The gas turbine engine control system as claimed in claim 6 , wherein the command to shut down the gas turbine engine comprises a command to close a fuel shut-off valve.

8. The gas turbine engine control system as claimed in claim 6 , wherein the command to shut down the gas turbine engine comprises a command to slew closed a fuel metering valve.

9. The gas turbine engine control system as claimed in claim 6 , wherein the arm signal comprises one of the group comprising an air system temperature, a rate of increase of an air system temperature and a bleed valve actuation failure.

10. A gas turbine engine comprising a gas turbine engine control system as claimed in claim 1 .

11. A gas turbine engine control system that is configured to:
generate an arm signal indicating potential shaft break; and
limit a response rate of a variable stator vane actuator by shifting from a normal deceleration schedule to a variable stator vane actuator response rate schedule in response to the arm signal.

12. The gas turbine engine control system as claimed in claim 11 , further configured to alter a variable stator vane schedule to slew each variable stator vane to decrease the available surge margin in response to the arm signal.

13. The gas turbine engine control system as claimed in claim 12 , wherein the variable stator vanes are each slewed by 5°.

14. The gas turbine engine control system as claimed in claim 12 , wherein the variable stator vanes are each slewed by an angle dependent on engine power.

15. The gas turbine engine control system as claimed in claim 12 , wherein the variable stator vanes are each slewed by an angle dependent on an environmental operating condition experienced by the gas turbine engine.

16. The gas turbine engine control system as claimed in claim 11 , further configured to:
generate a shaft failure signal in response to a shaft failure indicator; and
command gas turbine engine shut down in response to the shaft failure signal.

17. The gas turbine engine control system as claimed in claim 16 , wherein the command to shut down the gas turbine engine comprises a command to close a fuel shut-off valve.

18. The gas turbine engine control system as claimed in claim 16 , wherein the command to shut down the gas turbine engine comprises a command to slew closed a fuel metering valve.

19. The gas turbine engine control system as claimed in claim 16 , wherein the arm signal includes one of the group comprising an air system temperature, a rate of increase of an air system temperature and a bleed valve actuation failure.

20. A gas turbine engine comprising a gas turbine engine control system as claimed in claim 11 .

Assignees

• Rowe Arthur L
• Redfern Christopher
• Rolls Royce Plc

Inventors

• Rowe Arthur L
• Redfern Christopher

Classifications

• F05D2270/09

  to cope with emergencies · CPC title

• F01D21/06 Primary

  Shutting-down · CPC title

• F05D2270/101

  Compressor surge or stall · CPC title

• F01D17/162

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F05D2270/095

  by temporary overriding set control limits · CPC title