Detection of fan case liner damage during turbine engine operation
An aircraft includes a turbine engine, a vibration sensor, and a processor. The vibration sensor is attached to the turbine engine and is configured to output a vibration sensor signal. The processor is programmed to determine whether the vibration sensor signal indicates that fan case liner damage has occurred due to icing conditions. The processor is further programmed to indicate that a fan case inspection should be conducted in response to the vibration sensor signal indicating that fan case liner damage has occurred.
1. An aircraft, comprising:
a turbine engine having a fan case with a fan case liner;
a vibration sensor attached to the turbine engine and configured to output a vibration sensor signal that indicates broadband acceleration of the turbine engine; and
a processor programmed to:
determine whether the broadband acceleration of the turbine engine indicates that damage to the fan case liner has occurred due to icing conditions; and
indicate that inspection of the fan case should be conducted in response to the broadband acceleration of the turbine engine indicating that damage to the fan case liner has occurred.
2. The aircraft of claim 1 , wherein the processor is further programmed to:
extract a broadband vibration value from the vibration sensor signal; and
determine that the vibration sensor signal indicates that damage to the fan case liner has occurred in response to the broadband vibration value exceeding a broadband vibration threshold that indicates damage to the fan case liner due to ice shedding in the turbine engine may have occurred.
3. The aircraft of claim 1 , wherein the processor is further programmed to:
retrieve a rotor rotation frequency of the turbine engine;
form a harmonic indicator based on at least one harmonic frequency of the rotor rotation frequency; and
determine that the vibration sensor signal indicates that damage to the fan case liner has occurred in response to the harmonic indicator exceeding a harmonic threshold that indicates damage to the fan case liner may have occurred due to an unbalanced rotor in the turbine engine.
4. The aircraft of claim 3 , wherein the processor is further programmed to form the harmonic indicator using at least two higher order harmonic frequencies.
5. The aircraft of claim 4 , wherein the processor is further programmed to form the harmonic indicator as an aggregate magnitude of the at least two higher order harmonic frequencies.
6. The aircraft of claim 1 , wherein the processor is further configured to indicate that no damage has occurred to the turbine engine when the vibration sensor signal indicates that a broadband vibration value and harmonic frequencies of the turbine engine do not exceed damage indicator thresholds.
7. The aircraft of claim 1 , wherein the processor is an engine controller on the aircraft.
8. The aircraft of claim 1 , wherein the processor is a component of an external device that is configured to communicate with the vibration sensor to receive the vibration sensor signal during operation of the turbine engine.
9. The aircraft of claim 8 , wherein the processor is further programmed to receive an input indicating a model of the aircraft and to determine whether the vibration sensor signal indicates that fan case liner damage has occurred based on the model of the aircraft.
10. A device for damage monitoring of a turbine engine having a fan case with a fan case liner, the device comprising:
an input port configured to receive a vibration sensor signal from a vibration sensor attached to the turbine engine, the vibration sensor signal indicating broadband acceleration of the turbine engine; and
a processor programmed to:
determine whether the broadband acceleration of the turbine engine indicates that damage to the fan case liner has occurred in the turbine engine due to icing conditions; and
indicate that inspection of the fan case should be conducted in response to the broadband acceleration of the turbine engine indicating that damage to the fan case liner has occurred.
11. The device of claim 10 , wherein the processor is further programmed to:
extract a broadband vibration value from the vibration sensor signal; and
determine that the vibration sensor signal indicates that damage to the fan case liner has occurred in response to the broadband vibration value exceeding a broadband vibration threshold that indicates damage to the fan case liner due to ice shedding in the turbine engine may have occurred.
12. The device of claim 10 , wherein the processor is further programmed to:
retrieve a rotor rotation frequency of the turbine engine;
form a harmonic indicator based on at least one harmonic frequency of the rotor rotation frequency; and
determine that the vibration sensor signal indicates that damage to the fan case liner has occurred in response to the harmonic indicator exceeding a harmonic threshold that indicates damage to the fan case liner may have occurred due to an unbalanced rotor in the turbine engine.
13. The device of claim 12 , wherein the processor is further programmed to form the harmonic indicator using at least two higher order harmonic frequencies.
14. The device of claim 13 , wherein the processor is further programmed to form the harmonic indicator as an aggregate magnitude of the at least two higher order harmonic frequencies.
15. The device of claim 10 , wherein the processor is further configured indicate that no damage has occurred to the turbine engine when the vibration sensor signal indicates that a broadband vibration value and harmonic frequencies of the turbine engine do not exceed damage indicator thresholds.
16. The device of claim 10 , wherein the device is external to the turbine engine and an aircraft on which the turbine engine is installed and is configured to communicate with the vibration sensor to receive the vibration sensor signal during operation of the turbine engine.
17. The device of claim 16 , wherein the processor is further programmed to receive an input indicating a model of the aircraft and to determine whether the vibration sensor signal indicates that fan case liner damage has occurred based on the model of the aircraft.
18. A device for damage monitoring of a turbine engine having a fan case with a fan case liner, the device comprising:
at least one non-transitory computer readable storage device having executable instructions stored thereon; and
at least one processor associated with the at least one non-transitory computer readable storage device, wherein the executable instructions are configurable to cause the at least one processor to perform a method comprising the steps of:
receiving a vibration sensor signal provided by an accelerometer attached to the turbine engine, the vibration sensor signal indicating broadband acceleration of the turbine engine during operation;
retrieving a rotor rotation frequency of the turbine engine;
forming a harmonic indicator based on at least one harmonic frequency of the rotor rotation frequency;
extracting, from the vibration sensor signal, a vibration amplitude at the at least one harmonic frequency; and
generating a potential engine damage alert based on characteristics of the harmonic indicator and the vibration amplitude.