Can to can modal decoupling using can-level fuel splits
A fuel flow, fuel flow rate technology, applied in the control of thermal conditions of the combustion chamber, turbine/propulsion fuel delivery system, fuel control of the turbine/propulsion unit, etc., can solve problems such as limited maneuverability space
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[0087] figure 1 Diagrammatically shows a side view of a gas turbine system 100 in which an exemplary multi-circuit manifold may be implemented. In the exemplary embodiment, gas turbine 100 includes a compressor 110 configured to compress ambient air. One or more combustor cans 120 are in flow communication with compressor 110 through diffuser 150 . Combustor can 120 is configured to receive compressed air 115 from compressor 110 and combust fuel flow from fuel nozzles 160 to generate combustor exit airflow 165 that travels through combustor 140 to turbine 130 . Portions of the combustor 140 are included in a transition piece 145 that is coupled to the combustor can 120 . Turbine 130 is configured to expand the combustor out of airflow 165 to drive an external load. Combustor can 120 includes an outer shroud 170, and an end cap 175 configured to couple with a fuel hose (not shown) from a combustion manifold (not shown). Currently, a single fuel manifold provides a single f...
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