Method and apparatus for gas turbine engine ignition systems
AssigneeGeneral Electric Company
InventorRobert Ponziani
Life of this patent
Estimating the term…
Abstract
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. The method includes 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, and generating a first indication if the igniter failed to generate a spark within the first predefined pressure range.
Claims20
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;
- and
- generating a first indication if the igniter failed to generate a spark within the first predefined pressure range.
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;
- and
- generate a first indication if the igniter failed to generate a spark within the first predefined pressure range.
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;
- 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.
Dependencies are inferred from the claim text.