Method for operating a lean premix burner of an aircraft gas turbine and device for carrying out the method
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
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N/A
Issued Date -
N/A
app pub date -
Aug 23, 2013
filing date -
Aug 28, 2012
priority date (Note) -
Abandoned
status (Latency Note)
Importance
Abstract
The present invention relates to a method for operating a lean premix burner of an aircraft gas turbine, where fuel and primary supporting air are supplied by means of a supporting burner (pilot burner) arranged centrically to the burner axis, where secondary air surrounding the supporting burner is supplied, and where fuel and air are supplied by means of a main burner, characterized in that the primary supporting air is supplied in an amount of 5 vol % to 10 vol % of the total air quantity, that the secondary supporting air is supplied in an amount of 5 vol % to 20 vol % and that 35 vol % to 75 vol % of the total air quantity are supplied via the main burner in the partial load range and in the full load range.
First Claim
Other Claims data not available