System and method for detecting a flame in a fuel nozzle of a gas turbine

A system (200) may detect a flame about a fuel nozzle (112) of a gas turbine (100). The gas turbine (100) may have a compressor (104) and a combustor (106). The system (200) may include a first pressure sensor (204), a second pressure sensor (206), and a transducer (208). The first pressure sensor (...

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Bibliographische Detailangaben
Hauptverfasser:	LIPINSKI JOHN, KRAEMER GILBERT OTTO, MARSHALL JASON RANDOLPH, KRULL ANTHONY, STOREY JAMES M, WILLIAMSON DAVID LEE, MESTRONI JULIO ENRIQUE
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	BLASTING COMBUSTION APPARATUS COMBUSTION PROCESSES DETECTING MASSES OR OBJECTS GEOPHYSICS GRAVITATIONAL MEASUREMENTS HEATING LIGHTING MEASURING MECHANICAL ENGINEERING PHYSICS REGULATING OR CONTROLLING COMBUSTION TESTING TESTING STATIC OR DYNAMIC BALANCE OF MACHINES ORSTRUCTURES TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR WEAPONS
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Beschreibung
Zusammenfassung:	A system (200) may detect a flame about a fuel nozzle (112) of a gas turbine (100). The gas turbine (100) may have a compressor (104) and a combustor (106). The system (200) may include a first pressure sensor (204), a second pressure sensor (206), and a transducer (208). The first pressure sensor (204) may detect a first pressure upstream of the fuel nozzle. The second pressure sensor (206) may detect a second pressure downstream of the fuel nozzle (112). The transducer (208) may be operable to detect a pressure difference between the first pressure sensor (204) and the second pressure sensor (206).