Gas turbine engine combustor with improved cooling

Details Gas turbine engine combustor with improved cooling Gas turbine engine combustor with improved cooling

F - Mech Eng,Light,Heat,Weapons

23

R

F23R 3/06 (2006.01) F01D 25/12 (2006.01) F02C 7/12 (2006.01) F23R 3/42 (2006.01) F23R 3/54 (2006.01)

Patent

CA 2546881

A gas turbine engine combustor liner having a plurality of holes defined therein for directing air into the combustion chamber. The plurality of holes provide a greater cooling air flow in fuel nozzle regions than in other areas of the combustor liner.

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