초록 ▼

A method for reducing the emissions from combustion gases produced during a combustion process includes injecting a hydrocarbon-based reducing agent into the combustion gases to form a combustion gas mixture. The combustion gas mixture including oxides of nitrogen, NOx, is directed through a selecti

A method for reducing the emissions from combustion gases produced during a combustion process includes injecting a hydrocarbon-based reducing agent into the combustion gases to form a combustion gas mixture. The combustion gas mixture including oxides of nitrogen, NOx, is directed through a selective catalyst reduction (SCR) system including a catalyst bed to remove NOx from the combustion gas mixture and to produce an exhaust gas. In one embodiment, the exhaust gases are released from the SCR to the atmosphere.

대표청구항 ▼

1. A combustion chamber exhaust system comprising: a combustion gas exhaust duct coupled in flow communication with a combustion chamber;a first transport line coupled in flow communication with said combustion exhaust duct that contains a supply of combustion gases including oxides of nitrogen (NOx

1. A combustion chamber exhaust system comprising: a combustion gas exhaust duct coupled in flow communication with a combustion chamber;a first transport line coupled in flow communication with said combustion exhaust duct that contains a supply of combustion gases including oxides of nitrogen (NOx) produced during a combustion process, said first transport line configured to extract a portion of the combustion gases from said combustion gas exhaust duct for use as an exhaust gas;a heat exchanger coupled to said first transport line downstream of said combustion gas exhaust duct, said heat exchanger facilitates decreasing a temperature of the extracted exhaust gases;at least one recirculation fan coupled downstream from said heat exchanger, said at least one recirculation fan configured to extract a portion of the extracted exhaust gas from said heat exchanger for use as a carrier gas, the carrier gas having a lower temperature and a higher pressure than a temperature and a pressure of the extracted exhaust gas;a vaporizer chamber coupled downstream from said at least one recirculation fan, said vaporizer chamber configured to: receive the carrier gas from said at least one recirculation fan and a supply of liquid hydrocarbon-based reducing agent;vaporize the liquid hydrocarbon-based reducing agent; andform a mixture of the vaporized liquid hydrocarbon-based reducing agent with the carrier gas;a flame arrestor positioned within said vaporizer chamber, said flame arrestor including a plurality of packing beads configured to prevent combustion of the mixture and to efficiently mix the vaporized liquid hydrocarbon-based reducing agent and the carrier gas; anda second transport line coupled in flow communication with said vaporizer chamber, said second transport line configured to channel the mixture to an agent injection grid (AIG) positioned upstream from a selective catalyst reduction (SCR) system, wherein said heat exchanger is configured to indirectly cool the extracted exhaust gases to facilitate preventing combustion of the mixture downstream from said AIG, said SCR comprising a catalytic bed configured to facilitate reducing NOx within the combustion gases. 2. A combustion chamber exhaust system in accordance with claim 1 wherein said AIG further comprises at least one injector configured to inject the mixture upstream from said SCR system. 3. A combustion chamber exhaust system in accordance with claim 1 wherein said AIG further comprises at least one lance extending inwardly from an inner wall of said combustion gas exhaust duct, said at least one lance configured to distribute the mixture across said catalyst bed. 4. A combustion chamber exhaust system in accordance with claim 1 wherein said AIG further comprises an array of lances, each of said lances extends inwardly from an inner wall surface of said combustion gas exhaust duct. 5. A combustion chamber exhaust system in accordance with claim 4 wherein each said lance is coupled to a header positioned on an outer wall surface of said combustion gas exhaust duct. 6. A combustion chamber exhaust system in accordance with claim 4 wherein each said lance further comprises a pipe defining at least one nozzle oriented at an angle relative to the combustion gas flow. 7. A combustion chamber exhaust system in accordance with claim 6 wherein said at least one nozzle is oriented substantially perpendicular to the combustion gas flow. 8. A combustion chamber exhaust system in accordance with claim 1 further comprising a perforated plate coupled within said combustion gas exhaust duct upstream of said AIG. 9. A turbine comprising: a combustion chamber sized to contain a supply of combustion gases, including oxides of nitrogen (NOx) produced during operation of said turbine;a combustion gas exhaust duct coupled in flow communication with said combustion chamber;a heat exchanger coupled downstream from said combustion gas exhaust duct, said heat exchanger configured to receive a portion of combustion gases extracted from said combustion gas exhaust duct for use as an exhaust gas, said heat exchanger facilitates decreasing a temperature of the extracted exhaust gases;at least one recirculation fan coupled downstream from said heat exchanger, said at least one recirculation fan configured to extract a portion of the extracted exhaust gas from said heat exchanger for use as a carrier gas, the carrier gas having a lower temperature and a higher pressure than a temperature and a pressure of the extracted exhaust gas;a vaporizer chamber coupled in flow communication with said at least one recirculation fan, said vaporizer chamber configured to receive the carrier gas from said at least one recirculation fan and a supply of liquid hydrocarbon-based reducing agent, said vaporizer chamber further configured to vaporize the liquid hydrocarbon-based reducing agent and mix the carrier gases with the vaporized liquid hydrocarbon-based reducing agent to form a mixture of the liquid hydrocarbon-based reducing agent and the carrier gas;a flame arrestor positioned within said vaporizer chamber, said flame arrestor including a plurality of packing beads configured to prevent combustion of the mixture and to efficiently mix the vaporized liquid hydrocarbon-based reducing agent and the carrier gas; anda selective catalyst reduction (SCR) system coupled in flow communication with and downstream from said vaporizer chamber, said vaporizer chamber further configured to discharge the mixture of the reducing agent and the carrier gas to an agent injection grid (AIG) coupled upstream from said SCR system, wherein said heat exchanger is configured to indirectly cool the extracted combustion gases to facilitate preventing combustion of the mixture downstream from said AIG, said SCR system comprises a catalytic bed configured to facilitate reducing NOx within the combustion gases. 10. The turbine in accordance with claim 9 wherein said AIG further comprises at least one injector configured to inject the mixture upstream from said SCR system. 11. The turbine in accordance with claim 9 wherein said AIG further comprises extending at least one lance inwardly from an inner wall of a duct in flow communication with said combustion gas exhaust duct. 12. The turbine in accordance with claim 11 wherein said at least one lance is configured to distribute the mixture across said catalytic bed. 13. The turbine in accordance with claim 12 wherein said AIG further comprises an array of lances, each of said lances extend inwardly from an inner wall surface of a said combustion gas exhaust duct. 14. The turbine in accordance with claim 13 wherein each said lance is coupled to a header positioned on an outer wall surface of said gas exhaust duct. 15. The turbine in accordance with claim 14 wherein each said lance further comprises a pipe defining at least one nozzle oriented at an angle relative to the combustion gas flow. 16. The turbine in accordance with claim 15 wherein said at least one nozzle is oriented substantially perpendicular to the combustion gas flow. 17. The turbine in accordance with claim 9 further comprising a perforated plate coupled within said combustion gas exhaust duct upstream of said AIG.