| 摘要 |
Combustion induced vibrations, which are liable to be caused in a combustion chamber, are reduced by introducing a second burner (13) downstream of the main burner (12), so as to neutralise a standing wave set up in the combustion chamber due to the flame instability of the main burner. In the case of a gas turbine aeroengine (1), the second burner may be an auxiliary reheat combustor (13) having its own control unit (40) to selectively supply fuel to the auxiliary combustor when reheat buzz is likely to arise. <IMAGE> |
