Turbine engine control system
AssigneeROLLS-ROYCE plc
InventorsNicholas C. Corbett, Norman P. Lines
Life of this patent
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Abstract
Fuel flow is scheduled to a plurality of combustion stages by putting a plurality of engine fuel flow governors in parallel with each other and letting the governor which outputs the lowest fuel demand signal be the one which schedules the total fuel flow to the engine. Fuel flows to the plurality of combustion stages are then individually schedulled to achieve the lowest fuel flows consistent with predefined temperature limits for the corresponding stages of combustion.
Claims10
A method of scheduling fuel flow to a plurality of combustion stages in a combustion turbine engine, comprising the steps of putting a plurality of engine fuel flow governors in parallel with each other, letting the governor which outputs the lowest fuel demand signal be the one which schedules the total fuel flow to the engine, defining predetermined temperature limits for the combustion process in each stage of combustion, and individually scheduling fuel flows to the plurality of combustion stages to achieve the lowest fuel flows consistent with the predetermined temperature limits for the corresponding stages of combustion, wherein a primary combustion stage is operated sequentially in a diffusion flame first combustion mode and in a lean burn second combustion mode and a secondary combustion stage and any further combustion stages are operated in a lean burn combustion mode.
A control system for scheduling fuel flow to a plurality of combustion stages in a combustion turbine engine, comprising;
- a plurality of engine fuel flow governors arranged to output fuel demand signals in parallel with each other,
- lowest wins means for receiving the fuel demand signals and outputting the lowest fuel demand signal for scheduling the total fuel flow to the engine, and
- a plurality of control logic stages corresponding to the plurality of combustion stages, the logic stages including means defining predetermined temperature limits for corresponding stages;
- the control logic stages being adapted to individually schedule fuel demand signals to corresponding combustion stages to achieve the lowest fuel flows consistent with the predetermined temperature limits for the corresponding stages of combustion;
- wherein a primary combustion stage is adapted to operate sequentially in a diffusion flame first combustion mode and in a lean burn second combustion mode and a secondary combustion stage and any further combustion stages are adapted to operate in a lean burn combustion mode.
A control system for controlling fuel flow to at least primary and secondary combustion stages arranged in flow series in a combustion turbine engine, the primary combustion stage being adapted to operate in a diffusion flame first combustion mode and a lean burn second combustion mode and the secondary and any further combustion stages being adapted to operate in a lean burn combustion mode, wherein the control system comprises:
- first combustion mode control logic means for outputting a first combustion mode fuel demand signal (F.sub.dc) to the primary combustion stage during operation in its first combustion mode,
- second combustion mode control logic means for outputting respective second combustion mode fuel demand signals (F.sub.dp, F.sub.ds, F.sub.dt) to the primary combustion stage and at least one further combustion stage during operation of the primary combustion stage in its second combustion mode, and
- further control logic means for scheduling the first and second combustion mode fuel demand signals (F.sub.dc, F.sub.dp) to the primary combustion stage to achieve therein changeover between and simultaneous operation of the first and second combustion modes.
Dependencies are inferred from the claim text.