A gas turbine engine (10) includes a first spool (16) of a primary flow path (216) and a second spool (12) of a secondary flow path (220). The second spool (12) is nonconcentric with the first spool (16). The second spool (12) includes a boost compressor (...

The invention concerns a damper arrangement (112) for reducing combustion-chamber pulsation arising inside a gas turbine (100), wherein the gas turbine (100) essentially comprises at least one compressor (103), a primary combustor (101) which is connected ...

The method involves sensing air flow rates individually in each of air bleed lines (11a,12a,13a) from engines (11,12,13) with respective flow rate sensors (S1-S3). The air flow rates are compared to air bleed lines to derive flow matching signals (30b,31b,...