Starter Control Valve Prediction System to Predict and Trend Starter Control Valve Failures in Gas Turbine Engines Using a Starter Control Valve Health Prognostic, Computer Readable Medium and Related Methods

• US 20130133306A1
• Filed: 01/24/2013
• Published: 05/30/2013
• Est. Priority Date: 08/14/2009
• Status: Active Grant

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Qiu, Hai, Yan, Weizhong, Iyer, Naresh Sundaram
• Granted Patent: US 8,838,359 B2
• Time in Patent Office: Days
• US Class Current: 60/39.091
• CPC Class Codes: F01D 19/00 Starting of machines or engines; Regulating, controlling, or safety means in connection therewith warming-up before starting F01D25/10; turning or inching gear F01D25/34
• CPC Class Codes: F02C 7/26 Starting; Ignition
• CPC Class Codes: F02C 7/262 Restarting after flame-out
• CPC Class Codes: F05D 2270/708 with comparison tables

Abstract

Starter control valve failure prediction machines, systems, computer readable media, program products, and computer implemented methods to predict and trend starter control valve failures in gas turbine engines using a starter control valve health prognostic and to make predictions of starter control valve failures, are provided. A computer implemented method according to an embodiment of the present invention can include the steps of generating a continuous starter control valve deterioration trend function responsive to a plurality of health indices derived from gas turbine engine startup data downloaded from gas turbine engine sensors for a plurality of startups and analyzing the continuous starter control valve deterioration trend function to identify potential starter control valve failure points where the points on the starter control valve deterioration trend function correlate to a starter control valve health prognostic responsive to historic gas turbine engine startup data downloaded from gas turbine engine sensors.

Claims

1. A computer implemented method to predict starter control valve failures in gas turbine engines using a starter control valve health prognostic, the method comprising the steps of:

extracting one or more health index features from operational gas turbine engine startup data received for one or more gas turbine engine startups of one or more gas turbine engines of a certain gas turbine engine model;

calculating a starter control valve health index for each of the one or more gas turbine engine startups responsive to the one or more health index features extracted from the operational gas turbine engine startup data to thereby define one or more health indices;

comparing each of the one or more health indices to a starter control valve health prognostic for the certain gas turbine engine model; and

determining, responsive to the step of comparing, a potential predictive starter control valve failure point, the potential predictive starter control valve failure point being located where one of the one or more health indices correlates to the starter control valve health prognostic for the certain gas turbine engine model.

2. A computer implemented method as defined in claim 1, wherein the one or more health index features comprise time to reach post-light-off RPM during a normal, fault-free startup phase of the one or more gas turbine engines.

3. A computer implemented method as defined in claim 1, wherein the one or more health index features comprise time to reach total gas turbine engine RPM rise time during a normal, fault-free startup phase of the one or more gas turbine engines.

4. A computer implemented method as defined in claim 1, wherein the health index features are extracted for each gas turbine engine of a certain aircraft having a plurality of gas turbine engines of the certain gas turbine engine model, and wherein the starter control valve health index comprises a value of a function of entropy of one or more of the following:

time to reach post-light-off RPM and total engine RPM rise time, of each of the plurality of gas turbine engines during a normal, fault-free startup.

5. A computer implemented method as defined in claim 1, wherein the health index features are extracted for each gas turbine engine of a certain aircraft having a plurality of gas turbine engines of the certain gas turbine engine model, wherein the starter control valve health index comprises a single starter control valve health prognostic for all of the plurality of gas turbine engines, and wherein the method further comprises step of:

analyzing the starter control value health prognostic over time to predict a failure point of a starter control valve of one or more of the plurality of gas turbine engines of the certain aircraft in advance of an actual point of failure.

6. A computer implemented method as defined in claim 5, further comprising the step of:

analyzing one or more of the following;

current operational rise time data and an entropy value calculated responsive to the current operational rise time data, to determine when proactive maintenance action is required.

7. A computer implemented method as defined in claim 1,

wherein the at least one gas turbine engine startup is a plurality of gas turbine engine startups;

and

wherein the computer implemented method further comprises the steps of;

constructing a continuous starter control valve deterioration trend function responsive to a plurality of starter control valve health indices calculated for each of the plurality of gas turbine engine startups responsive to the one or more health index features extracted from the operational gas turbine engine startup data; and

determining, using the continuous starter control valve deterioration trend function, a point on the continuous starter control valve deterioration trend function that correlates to the starter control valve health prognostic for the certain gas turbine engine model to thereby identify the potential predictive starter control valve failure point.

8. A computer implemented method as defined in claim 7,

wherein the continuous starter control valve deterioration trend function is a function of two variables, a first variable representing one or more of the one or more extracted health index features and a second variable representing the gas turbine engine startup number associated with the one or more of the one or more extracted health index features;

and

wherein a mathematical limit of the continuous starter control valve deterioration trend function approaches zero as the gas turbine engine startup number associated with the one or more of the one or more extracted health index features increases.

9. A computer implemented method as defined in claim 1,

wherein the one or more gas turbine engines of the certain gas turbine engine model are associated with an aircraft;

and

wherein the computer implemented method further comprises the steps of;

analyzing the operational gas turbine engine startup data,

determining, responsive to analyzing the operational gas turbine engine startup data, the existence of one or more mechanical problems associated with one or more of the following;

an auxiliary power unit, a compressor, an air turbine, an ignition system, a fuel system, or a lube pressure system of the aircraft, at the potential predictive starter control valve failure point,

determining, responsive to analyzing the operational gas turbine engine startup data, the existence of pilot initiated purging of a fuel injection system of each of the one or more gas turbine engines at the potential predictive starter control valve failure point, and

reducing false positive indications of a starter control valve failure responsive to determining the existence of one or more mechanical problems and determining the existence of pilot initiated purging of the fuel injection system of each of the one or more gas turbine engines at the potential predictive starter control valve failure point.

10. A computer implemented method as defined in claim 1,

wherein the starter control valve health prognostic for the certain gas turbine engine model is constructed responsive to one or more health index features extracted from a starter control valve pre-failure signature determined responsive to historic gas turbine engine startup data received for the plurality of gas turbine engine startups for one or more gas turbine engines of the certain gas turbine engine model, the gas turbine engine startup data including an indication that at least one of the plurality of gas turbine engine startups failed due to a starter control valve failure;

wherein the one or more gas turbine engines is at least three gas turbine engines;

wherein the operational gas turbine engine startup data includes RPM sensor readings for each of the plurality of gas turbine engine startups of each of the at least three gas turbine engines; and

wherein the computer implemented method further comprises the steps of;

determining the lowest and highest RPM sensor readings of each of the at least three gas turbine engines produced during the plurality of gas turbine engine startups,

determining two median RPM sensor readings,

calculating an average difference between the two median RPM sensor readings and the lowest RPM sensor reading when the lowest RPM sensor reading does not equal the highest RPM sensor reading to thereby define a first difference;

calculating an average difference between the two median RPM sensor readings and the highest RPM sensor reading when the lowest RPM sensor reading does not equal the highest RPM sensor reading to thereby define a second difference, and

identifying one of the at least three gas turbine engines that is associated with the potential predictive starter control valve failure point, the identified one of the at least three gas turbine engines being the gas turbine engine associated with the highest RPM sensor reading when the first difference is greater than the second difference and the identified one of the at least three gas turbine engines being the gas turbine engine associated with the lowest RPM sensor reading when the first difference is less than the second difference.

11. Non-transitory computer readable medium having processor readable program code embodied on the computer readable medium, the processor readable program code for programming one or more processors to perform operations for to predict starter control valve failures in gas turbine engines using a starter control valve health prognostic, the processor readable program code comprising a set of instructions that when executed by the one or more processors, cause the one or more processors to perform the operations of:

receiving operational gas turbine engine startup data collected for one or more gas turbine engine startups of one or more gas turbine engines of a certain gas turbine engine model;

extracting one or more health index features from received operational gas turbine engine startup data;

calculating a starter control valve health index for each of the one or more gas turbine engine startups responsive to the one or more health index features extracted from the operational gas turbine engine startup data to thereby define one or more health indices;

comparing each of the one or more health indices to a starter control valve health prognostic for the certain gas turbine engine model; and

determining, responsive to the operation of comparing, a potential predictive starter control valve failure point, the potential predictive starter control valve failure point being located where one of the one or more health indices correlates to the starter control valve health prognostic for the certain gas turbine engine model.

12. Non-transitory computer readable medium as defined in claim 11, wherein the one or more health index features comprise one or more of the following:

time to reach post-light-off RPM during a normal, fault-free startup phase of the one or more gas turbine engines; and

time to reach total gas turbine engine RPM rise time during a normal, fault-free startup phase of the one or more gas turbine engines.

13. Non-transitory computer readable medium as defined in claim 11, wherein the health index features are extracted for each gas turbine engine of a certain aircraft having a plurality of gas turbine engines of the certain gas turbine engine model, and wherein the starter control valve health index comprises a value of a function of entropy of one or more of the following:

time to reach post-light-off RPM and total engine RPM rise time, of each of the plurality of gas turbine engines during a normal, fault-free startup.

14. Non-transitory computer readable medium as defined in claim 11, wherein the health index features are extracted for each gas turbine engine of a certain aircraft having a plurality of gas turbine engines of the certain gas turbine engine model, wherein the starter control valve health index comprises a single starter control valve health prognostic for all of the plurality of gas turbine engines, and wherein the operations further comprise:

analyzing the starter control value health prognostic over time to predict a failure point of a starter control valve of one or more of the plurality of gas turbine engines of the certain aircraft in advance of an actual point of failure.

15. Non-transitory computer readable medium as defined in claim 14, further comprising the operation of:

analyzing one or more of the following;

current operational rise time data and an entropy value calculated responsive to the current operational rise time data, to determine when proactive maintenance action is required.

16. Non-transitory computer readable medium as defined in claim 11,

wherein the at least one gas turbine engine startup is a plurality of gas turbine engine startups;

and

wherein the operations further comprise;

constructing a continuous starter control valve deterioration trend function responsive to a plurality of starter control valve health indices calculated for each of the plurality of gas turbine engine startups responsive to the one or more health index features extracted from the operational gas turbine engine startup data; and

determining, using the continuous starter control valve deterioration trend function, a point on the continuous starter control valve deterioration trend function that correlates to the starter control valve health prognostic for the certain gas turbine engine model to thereby identify the potential predictive starter control valve failure point.

17. Non-transitory computer readable medium as defined in claim 16,

wherein the continuous starter control valve deterioration trend function is a function of two variables, a first variable representing one or more of the one or more extracted health index features and a second variable representing the gas turbine engine startup number associated with the one or more of the one or more extracted health index features;

and

wherein a mathematical limit of the continuous starter control valve deterioration trend function approaches zero as the gas turbine engine startup number associated with the one or more of the one or more extracted health index features increases.

18. Non-transitory computer readable medium as defined in claim 11,

wherein the one or more gas turbine engines of the certain gas turbine engine model are associated with an aircraft;

and

wherein the operations further comprise;

analyzing the operational gas turbine engine startup data,

determining, responsive to analyzing the operational gas turbine engine startup data, the existence of one or more mechanical problems associated with one or more of the following;

an auxiliary power unit, a compressor, an air turbine, an ignition system, a fuel system, or a lube pressure system of the aircraft, at the potential predictive starter control valve failure point,

determining, responsive to analyzing the operational gas turbine engine startup data, the existence of pilot initiated purging of a fuel injection system of each of the one or more gas turbine engines at the potential predictive starter control valve failure point, and

reducing false positive indications of a starter control valve failure responsive to determining the existence of one or more mechanical problems and determining the existence of pilot initiated purging of the fuel injection system of each of the one or more gas turbine engines at the potential predictive starter control valve failure point.

19. Non-transitory computer readable medium as defined in claim 11,

wherein the starter control valve health prognostic for the certain gas turbine engine model is constructed responsive to one or more health index features extracted from a starter control valve pre-failure signature determined responsive to historic gas turbine engine startup data received for the plurality of gas turbine engine startups for one or more gas turbine engines of the certain gas turbine engine model, the gas turbine engine startup data including an indication that at least one of the plurality of gas turbine engine startups failed due to a starter control valve failure;

wherein the one or more gas turbine engines is at least three gas turbine engines;

wherein the operational gas turbine engine startup data includes RPM sensor readings for each of the plurality of gas turbine engine startups of each of the at least three gas turbine engines; and

wherein the operations further comprise;

determining the lowest and highest RPM sensor readings of each of the at least three gas turbine engines produced during the plurality of gas turbine engine startups,

determining two median RPM sensor readings,

calculating an average difference between the two median RPM sensor readings and the lowest RPM sensor reading when the lowest RPM sensor reading does not equal the highest RPM sensor reading to thereby define a first difference;

calculating an average difference between the two median RPM sensor readings and the highest RPM sensor reading when the lowest RPM sensor reading does not equal the highest RPM sensor reading to thereby define a second difference, and

identifying one of the at least three gas turbine engines that is associated with the potential predictive starter control valve failure point, the identified one of the at least three gas turbine engines being the gas turbine engine associated with the highest RPM sensor reading when the first difference is greater than the second difference and the identified one of the at least three gas turbine engines being the gas turbine engine associated with the lowest RPM sensor reading when the first difference is less than the second difference.

20. A starter control valve failure prediction system to predict and trend starter control valve failures in gas turbine engines using a starter control valve health prognostic, the starter control valve failure prediction system comprising a computer having one or more processors, memory in communication with the processor, and computer readable program code defining a starter control valve failure protection program comprising a set of instructions, that when executed by the one or more processors, cause the one or more processors to perform the operations of:

receiving operational gas turbine engine startup data collected for one or more gas turbine engine startups of one or more gas turbine engines of a certain gas turbine engine model;

extracting one or more health index features from received operational gas turbine engine startup data;

calculating a starter control valve health index for each of the one or more gas turbine engine startups responsive to the one or more health index features extracted from the operational gas turbine engine startup data to thereby define one or more health indices;

comparing each of the one or more health indices to a starter control valve health prognostic for the certain gas turbine engine model; and

determining, responsive to the operation of comparing, a potential predictive starter control valve failure point, the potential predictive starter control valve failure point being located where one of the one or more health indices correlates to the starter control valve health prognostic for the certain gas turbine engine model.