BURNER UNIT FOR A GAS TURBINE AND GAS TURBINE

摘要

Multiple burner stages (30) are set up on a gas turbine combustor (4) and differ from each other regarding the acoustic impedance of their fuel feed line, the acoustic impedance of their air passage and/or flame delay time or injection delay time. These stages are arranged one behind the other in respect of a gas turbine's lengthwise direction and each have throttle devices (40). An independent claim is also included for a gas turbine with a number of burner units for the present invention.