STABILIZING A GAS TURBINE ENGINE VIA INCREMENTAL TUNING
First Claim
1. A computerized method, implemented by a processing unit, for automatically tuning a combustor of a gas turbine engine, the method comprising:
- monitoring one or more operating conditions of the gas turbine engine;
determining whether the one or more operating conditions have overcome a threshold value; and
when the threshold value is overcome, adjusting a fuel flow split by a predefined increment, wherein the fuel flow split governs a portion of a total fuel flow that is directed to each fuel nozzle of the combustor'"'"'s fuel circuit.
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Accused Products
Abstract
An auto-tune controller and tuning process implemented thereby for measuring and tuning the combustion dynamics and emissions of a GT engine, relative to predetermined upper limits, are provided. Initially, the tuning process includes monitoring the combustion dynamics of a plurality of combustors and emissions for a plurality of conditions. Upon determination that one or more of the conditions exceeds a predetermined upper limit, a fuel flow split to a fuel circuit on all of the combustors on the engine is adjusted by a predetermined amount. The control system continues to monitor the combustion dynamics and to recursively adjust the fuel flow split by the predetermined amount until the combustion dynamics and/or emissions are operating within a prescribed range of the GT engine.
64 Citations
20 Claims
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1. A computerized method, implemented by a processing unit, for automatically tuning a combustor of a gas turbine engine, the method comprising:
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monitoring one or more operating conditions of the gas turbine engine; determining whether the one or more operating conditions have overcome a threshold value; and when the threshold value is overcome, adjusting a fuel flow split by a predefined increment, wherein the fuel flow split governs a portion of a total fuel flow that is directed to each fuel nozzle of the combustor'"'"'s fuel circuit. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14)
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15. A system for automatically stabilizing combustor dynamics or emissions of a gas turbine by employing a tuning process, the system comprising:
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the gas turbine engine including one or more combustors that are each provided with a fuel flow split for governing a portion of a total fuel flow that is directed to each fuel nozzle of the combustor'"'"'s fuel circuit; and an auto-tune controller for carrying out the tuning process comprising; (a) measuring one or more parameters from the gas turbine engine, wherein the one or more parameters represent at least one of pressure data or gas composition; (b) deriving amplitudes for the one or more measured parameters, respectively; (c) determining whether the amplitudes overcome predefined limits mapped to the one or more measured parameters; and (d) when the predefined limit is overcome, accessing a schedule to select an appropriate fuel flow split to alter. - View Dependent Claims (16, 17, 18, 19)
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20. One or more computer readable media that, when invoked by computer-executable instructions, perform a method for auto-tuning a gas turbine engine, the method comprising:
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monitoring one or more operating conditions of the gas turbine engine; determining whether the one or more operating conditions have overcome a threshold value; and when the threshold value is overcome, adjusting a fuel flow split by a predefined increment, wherein the fuel flow split governs a portion of a total fuel flow that is directed to each fuel nozzle of the combustor'"'"'s fuel circuit.
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Specification