SUPPLEMENTARY LASER FIRING FOR COMBUSTION STABILITY

摘要

The present invention relates to a combustion system for a gas turbine. The combustion system comprises a combustion chamber (100) having an end section (101) and a pre-combustion section (102) extending from the end section (101) along a centre axis (103) of the combustion chamber (100), a swirler device (110), an optional pilot burner device (120) and a light emitting arrangement (130). The swirler device (110) is mounted to the pre-combustion section (102) such that a main fuel (111) is injectable by or through the swirler device (110) into an inner volume (104) of the pre-combustion section (102). The main flame (108) using the main fuel (111) is producible inside the inner volume (104). The optional pilot burner device (120) is mounted to the end section (101) of the combustion chamber (100) such that a pilot fuel (121) is injectable by or through the pilot burner device (120) into the inner volume (104) of the pre-combustion section (102), wherein a pilot flame (122) using the pilot fuel (121) is producible inside the inner volume (104) for stabilizing the main flame (108). The light emitting arrangement (130) emits an electromagnetic radiation (131) into the inner volume (104), wherein the light emitting arrangement (130) is arranged to the combustion chamber (100) such that an energy input to the pilot flame (122) and/or the main flame (108) is generatable by the electromagnetic radiation (131) for stabilizing the pilot flame (122) and/or the main flame (108), particularly to reduce the fuel required by the pilot flame and hence the emissions. The light emitting arrangement could also be used to replace the function of the pilot flame and be used to stabilise the main flame instead of using a pilot flame.