Flashback Suppression System for a Gas Turbine Combustor
AssigneePower Systems Mfg., LLC
InventorPeter Stuttaford
Life of this patent
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Abstract
A gas turbine combustor having improved flashback margin is disclosed. Multiple embodiments of the present invention are disclosed including combustors having a single premix chamber as well as multiple premix chambers. Flashback margin is increased for the combustor by incorporating a means for introducing an inert gas, such as nitrogen, into the premix chamber(s) at the region proximate the boundary layer to purge the boundary layer of combustible mixture, thereby ensuring that no combustion reaction occurs in the boundary layer.
Claims12
A gas turbine combustor having increased flashback margin, said combustor comprising:
- A premix chamber having a first generally annular wall;
- A combustion chamber having a second generally annular wall, said combustion chamber in fluid communication with said premix chamber;
- At least one fuel nozzle for injecting a fuel into said premix chamber to form a mixture with compressed air in said premix chamber;
- and,
- A means for introducing an inert gas into said premix chamber proximate said first generally annular wall.
A gas turbine combustor having increased flashback margin, said combustor comprising:
- A premix chamber having a first generally annular wall and a combustion chamber having a second generally annular wall, said combustion chamber in fluid communication with said premix chamber;
- At least one fuel nozzle for injecting a fuel into said premix chamber to form a mixture with compressed air in said premix chamber;
- A boundary layer located in said premix chamber and said combustion chamber generally along said first and second generally annular walls, said boundary layer containing said fuel and compressed air at a lower velocity than said mixture;
- and,
- A means for injecting an inert gas into said boundary layer to purge said boundary layer thereby ensuring that no combustion reaction occurs in said boundary layer.
A gas turbine combustor having increased flashback margin, said combustor comprising:
- At least one premix chamber having a first generally annular wall and a combustion chamber having a second generally annular wall, said combustion chamber in fluid communication with said at least one premix chamber;
- At least one fuel nozzle for injecting a fuel into said at least one premix chamber to form a mixture with compressed air in said at least one premix chamber;
- A boundary layer located in said at least one premix chamber and said combustion chamber generally along said first and second generally annular walls, said boundary layer containing said fuel and compressed air at a lower velocity than said mixture;
- and,
- A means for injecting an inert gas into said boundary layer to purge said boundary layer thereby ensuring that no combustion reaction occurs in said boundary layer.
Dependencies are inferred from the claim text.