USE OF A GAS TURBINE HEATED FLUID FOR REDUCTANT VAPORIZATION

A system includes a gas turbine engine 12 that may combust a fuel to generate power and an exhaust gas, an exhaust gas path 42 in fluid communication with the gas turbine engine and that may receive the exhaust gas from the gas turbine engine, and a reductant skid 65 fluidly coupled to the exhaust g...

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Bibliographic Details
Main Authors FRESE, Christopher Conrad, KIPPEL, Bradly Aaron
Format Patent
LanguageEnglish
French
German
Published 11.10.2017
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Summary:A system includes a gas turbine engine 12 that may combust a fuel to generate power and an exhaust gas, an exhaust gas path 42 in fluid communication with the gas turbine engine and that may receive the exhaust gas from the gas turbine engine, and a reductant skid 65 fluidly coupled to the exhaust gas path. The reductant skid includes an injection system 74 that may supply a reductant to the exhaust gas path. The system also includes a flow path separate from the exhaust gas path and fluidly coupling the gas turbine engine and the reductant skid. The first flow path may supply a first heated fluid to the reductant skid to aid in vaporization of the reductant.
Bibliography:Application Number: EP20170164272