Gas turbine engine failure detection

Patent metadata

Field	Value
Publication number	US-8954228-B2
Application number	US-61806009-A
Country	US
Kind code	B2
Filing date	Nov 13, 2009
Priority date	Dec 30, 2008
Publication date	Feb 10, 2015
Grant date	Feb 10, 2015

Abstract

A gas turbine engine control system is disclosed having a fault detection system capable of detecting a high N1 condition. N1 rotational speed is measured and, in two different locations, subtracted from a target N1 value and a requested N1 value. The resultant error values are scaled by a gain that is scheduled as a function of N2 rotational rate. Each error value is accumulated with separate integrators that have independent maximum and minimum limits. The integrators are reset based upon a number of conditions. A number of additional conditions must also be satisfied for the fault detection system to trigger a fault condition. If the additional conditions are satisfied and the integrators are accumulating values, then a fault condition is set if either or both integrators accumulate a value that reaches a selected limit.

First claim

What is claimed is:

1. A method comprising:
establishing a rotational speed of a gas turbine engine fan;
determining a first error signal based upon the difference between the rotational speed and an operational reference speed;
weighting the first error signal based upon a rotational acceleration of an engine core;
accumulating the first error signal to create a first accumulation value;
determining a second error signal based upon the difference between the rotational speed and a commanded reference speed;
accumulating the second error signal to create a second accumulation value; and
setting a fault indication when either the second accumulation value or the first accumulation value exceeds a threshold.

2. The method of claim 1 , wherein accumulating the first error signal includes integrating the first error signal with an integrator, wherein the rotational speed is N1 and the operational reference speed is a maximum N1.

3. The method of claim 1 , wherein accumulating the second error signal includes integrating the second error signal with an integrator, wherein the rotational speed is N1 and the commanded reference speed is an autopilot commanded N1.

4. The method of claim 1 , which further includes limiting the first accumulation value within a first selected accumulation value limit.

5. The method of claim 1 , which further includes resetting the first accumulation value to an initial condition.

6. The method of claim 5 , which further includes satisfying a reset condition prior to resetting the first accumulation value.

7. The method of claim 6 , wherein the reset condition is selected from a group that comprises whether a throttle command indicates an increase in power command; whether the controller lane is in control; and whether the engine core is decelerating.

8. The method of claim 1 , which further includes prohibiting a fault indication when the gas turbine engine is in a reversionary mode, when a main metering valve is in an open loop backup mode, or when the engine has completed a start sequence for less than a selected time period.

9. A method, comprising:
establishing a rotational speed of a gas turbine engine compressor fan;
establishing a rotational acceleration of a compressor;
forming an error signal based upon the difference between a reference speed and the rotational speed of the gas turbine engine compressor fan and accumulating the error signal to form an accumulated value;
weighting the error signal based upon a rotational acceleration of the compressor;
determining a fault signal based upon the reference speed, the rotational speed of the gas turbine engine compressor fan, and the rotational acceleration of the compressor; and
setting a fault indication when the fault signal exceeds a threshold.

10. The method of claim 9 , wherein weighting the error signal is determined by multiplying the error signal by a gain determined from a gain schedule.

11. The method of claim 9 , which further includes resetting the fault indication.

12. The method of claim 9 , which further includes prohibiting a fault condition.

13. An apparatus, comprising:
a gas turbine engine including a compressor rotor;
a sensor operable to generate a sensed value representative of the speed of the compressor rotor;
a controller for use with the gas turbine engine having:
an operational reference value representative of a first monitored condition;
a first error value representative of the difference between the sensed value and the operational reference value;
a weight based upon a rotational acceleration of an engine core and applied to the first error value;
a commanded reference value representative of a second monitored condition;
a second error value representative of the difference between the sensed value and the commanded reference value; and
a fault detector responsive to the first error value, and operable to accumulate the first error value, and responsive to the second error value and operable to accumulate the second error value, and configured to set a fault indicator when either the first accumulation value or the second accumulation value exceeds a threshold.

14. The apparatus of claim 13 , wherein the controller further includes a means for resetting the fault detector.

15. The apparatus of claim 13 , wherein the controller further includes a protection configured to prevent a false or unintended failure indicator.

16. The apparatus of claim 13 , wherein the operational reference value comprises a maximum reference value, the commanded reference value comprises an autopilot commanded reference value, and the controller is configured to limit the first accumulation value within a first selected accumulation value limit.

17. The apparatus of claim 13 , wherein the controller is configured to reset the first accumulation value to an initial condition, and the controller is configured to determine whether a reset condition is satisfied and to reset the first accumulation value if the controller determines that the reset condition is satisfied.

18. The apparatus of claim 17 , wherein the reset condition is selected from a group that comprises whether a throttle command indicates an increase in power command; whether the controller lane is in control; and whether the engine core is decelerating.

19. The apparatus of claim 13 , wherein the controller is configured to prohibit setting of a fault indicator when the gas turbine engine is in a reversionary mode, when a main metering valve is in an open loop backup mode, or when the engine has completed a start sequence for less than a selected time period.

Assignees

• Falkmann Ronald Alan
• Elliott Michael T
• Lheureau Edward A
• Rolls Royce Corp

Inventors

• Falkmann Ronald Alan
• Elliott Michael T
• Lheureau Edward A

Classifications

• F02C9/00 Primary

  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

• F05D2270/708

  with comparison tables · CPC title

• F05D2270/304

  Spool rotational speed · CPC title