Method and apparatus for gas turbine engine ignition systems

1. A method for testing an igniter coupled within a gas turbine engine, wherein the gas turbine engine includes a combustor, a pressure transducer coupled to the combustor, and a spark detector, said method comprising:

operating the gas turbine engine;

monitoring the operating pressure within the gas turbine engine;

operating the igniter when the monitored pressure is within a first predefined pressure range;

generating a first indication if the igniter failed to generate a spark within the first predefined pressure range; and

transmitting the first indication for viewing by an operator.

2. A method in accordance with claim 1 further comprising replacing the igniter based on the first indication.

3. A method in accordance with claim 1 further comprising:

operating the igniter when the monitored pressure is within a second predefined pressure range that is different than the first predefined pressure range; and

generating a second indication that is different than the first indication if the igniter failed to generate a spark within the second predefined pressure range.

4. A method in accordance with claim 3 further comprising scheduling an igniter maintenance event based on the second indication.

5. A method in accordance with claim 3 further comprising:

detecting the igniter spark utilizing the spark detector; and

correlating the combustor pressure to the moment of occurrence of the detected igniter spark to determine whether the igniter produced a spark within at least one of the first and second predefined pressure ranges.

6. A method in accordance with claim 3 wherein the second predefined pressure range is greater than the first predefined pressure range.

7. A method in accordance with claim 3 further comprising:

operating the igniter when the monitored pressure is within a third predefined pressure range that is less than the first predefined pressure range; and

generating a third indication that is different than the first and second indications, wherein the third indication is utilized to verify that at least one of the pressure transducer, the spark detector, and the igniter are operational.

8. A method in accordance with claim 7 further comprising transmitting at least one of the first indication, the second indication, and the third indication to a remote location.

9. A control system coupled to a gas turbine engine, wherein the gas turbine engine includes a combustor, at least one igniter, a pressure transducer coupled to the combustor, and a spark detector, said control system comprising a processor programmed to:

operate the gas turbine engine;

monitor the operating pressure within the gas turbine engine;

operate the igniter when the monitored pressure is within a first predefined pressure range;

generate a first indication if the igniter failed to generate a spark within the first predefined pressure; and

transmit the first indication for viewing by an operator.

10. A control system in accordance with claim 9 wherein said processor is further programmed to prompt an operator to replace the igniter based on the first indication.

11. A control system in accordance with claim 9 wherein said processor is further programmed to:

operate the igniter when the monitored pressure is within a second predefined pressure range that is greater than the first predefined pressure range; and

generate a second indication that is different than the first indication if the igniter failed to generate a spark within the second predefined pressure range.

12. A method in accordance with claim 11 wherein said processor is further programmed to prompt an operator to schedule an igniter maintenance event based on the second indication.

13. A control system in accordance with claim 11 wherein said processor is further programmed to:

detect the igniter spark utilizing the spark detector; and

correlate the combustor pressure to the moment of occurrence of the detected igniter spark to determine whether the igniter produced a spark within at least one of the first and second predefined pressure ranges.

14. A control system in accordance with claim 11 wherein said processor is further programmed to:

operate the igniter when the monitored pressure is within a third predefined pressure range that is less than the first predefined pressure range; and

generate a third indication that is different than the first and second indications, wherein the third indication is utilized to verify that at least one of the pressure transducer, the spark detector, and the igniter are operational.

15. A control system in accordance with claim 11 wherein said processor is further programmed to transmit at least one of the first indication, the second indication, and the third indication to a remote location.

16. A gas turbine engine assembly comprising:

a gas turbine engine including a combustor, at least one igniter, a pressure transducer coupled to combustor, and a spark detector; and

a control system coupled to said gas turbine engine, said control system comprising a processor programmed to:

operate the gas turbine engine;

monitor the operating pressure within the gas turbine engine;

operate the igniter when the monitored pressure is within a first predefined pressure range;

generate a first indication if the igniter failed to generate a spark within the first predefined pressure range;

operate the igniter when the monitored pressure is within a second predefined pressure range that is greater than the first predefined pressure range;

generate a second indication that is different than the first indication if the igniter failed to generate a spark within the second predefined pressure range; and

transmit at least one of the first indication and the second indication for viewing by an operator.

17. A gas turbine engine assembly in accordance with claim 16 , wherein said processor is further programmed to:

prompt an operator to replace the igniter based on the first indication; and

prompt an operator to schedule an igniter maintenance event based on the second indication.

18. A gas turbine engine assembly in accordance with claim 16 , wherein said processor is further programmed to:

detect the igniter spark utilizing the spark detector; and

correlate the combustor pressure to the moment of occurrence of the detected igniter spark to determine whether the igniter produced a spark within at least one of the first and second predefined pressure ranges.

19. A gas turbine engine assembly in accordance with claim 16 , wherein said processor is further programmed to:

operate the igniter when the monitored pressure is within a third predefined pressure range that is less than the first predefined pressure range; and

generate a third indication that is different than the first and second indications, wherein the third indication is utilized to verify that at least one of the pressure transducer, the spark detector, and the igniter are operational.

20. A gas turbine engine assembly in accordance with claim 19 , wherein said processor is further programmed to transmit at least one of the first indication, the second indication, and the third indication to a remote location.