Combustor with improved cooling holes arrangement

Details Combustor with improved cooling holes arrangement Combustor with improved cooling holes arrangement

F - Mech Eng,Light,Heat,Weapons

23

R

F23R 3/04 (2006.01) F01D 25/12 (2006.01)

Patent

CA 2664056

A gas turbine engine combustor liner with at least one of the inner and outer liners that is effusion cooled and has a row of groups of circumferentially spaced apart dilution holes defined therethrough. Each group is located within a respective zone of the combustor liner defined by an overlap of adjacent conical sections corresponding to the sprays of adjacent fuel nozzles.

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