Gas turbine adaptive secondary fuel filling profile
AssigneePratt & Whitney Canada Corp.
InventorsLouis Duranleau-Hendrickx, Gabriel Meunier
Life of this patent
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Abstract
An apparatus comprises a combustion chamber of a gas turbine engine, a primary manifold for injecting fuel into the combustion chamber via a first plurality of nozzles and a secondary manifold for injection fuel into the combustion chamber via a second plurality of nozzles. A fuel control system provides fuel flow to the primary manifold and to the secondary manifold. The fuel control system determines at least one control parameter responsive to a first point at which the fuel flow level causes the secondary manifold to start draining and a second point at which an acceleration request is made and selects one of a plurality of secondary manifold filling profiles responsive to the determined at least one control parameter.
Claims20
An apparatus comprising:
- a combustion chamber of a gas turbine engine;
- a primary manifold for injecting fuel into the combustion chamber via a first plurality of nozzles;
- a secondary manifold for injection fuel into the combustion chamber via a second plurality of nozzles;
- a fuel control system for providing fuel flow to the primary manifold and to the secondary manifold;
- wherein the fuel control system:
- determines at least one control parameter responsive to a first point at which a fuel flow level causes the secondary manifold to start draining and a second point at which an acceleration request is made;
- and
- selects one of a plurality of secondary manifold filling profiles responsive to the at least one control parameter.
A method for controlling filling of a secondary manifold of a gas turbine engine comprising:
- providing fuel flow to a primary manifold and to the secondary manifold of the gas turbine engine using a fuel control system;
- determining at least one control parameter responsive to a first point at which a fuel flow level causes the secondary manifold to start draining and a second point at which an acceleration request of the gas turbine engine is made;
- and
- selecting one of a plurality of secondary manifold filling profiles responsive to the at least one control parameter.
An apparatus comprising:
- a combustion chamber of a gas turbine engine;
- a primary manifold for injecting fuel into the combustion chamber via a first plurality of nozzles;
- a secondary manifold for injection fuel into the combustion chamber via a second plurality of nozzles;
- a fuel control system for providing fuel flow to the primary manifold and to the secondary manifold, wherein the fuel control system further comprises:
- a timer associated with the fuel control system;
- a plurality of secondary manifold filling profiles each associated with a predetermined time value;
- wherein the fuel control system:
- initiates the timer when a fuel flow level causes the secondary manifold to start draining;
- stops the timer when an acceleration request is made;
- determines a time value between when the fuel flow level causes the secondary manifold to start draining and when the acceleration request is made responsive to a time measured by the timer;
- and
- selects one of a plurality of secondary manifold filling profiles responsive to the time value.
Dependencies are inferred from the claim text.