| 摘要 |
A method of detecting a partial flame failure in a gas turbine (10) having a gas duct (34) for guiding propulsion gas (18) and several combustors (24), each of which combustors (24) leads into the gas duct (34) and comprises a burner (36) is provided. The method comprises the steps of: measuring a first temperature over time at each of at least two probing points (32a; 32b) located downstream from the combustors (24) in the gas duct (34), measuring a second temperature over time in each of at least two of the burners (36), and detecting a partial flame failure from the first temperature measurements and said second temperature measurements. |
