| 摘要 |
PROBLEM TO BE SOLVED: To realize an integrated gas turbine engine monitoring and control system for detecting a broad range of possible combustor failures or more satisfactorily precursors to faults during combustion by sharing common sensors and, if necessary, a common controller.SOLUTION: A time-of-flight for acoustic signals traveling along a line-of-sound path is processed to determine an individual combustor path temperature along each line-of-sound path. |
