To provide a combustor capable of improving a heat transfer, hardly increasing a pressure drop.
This combustor for gas turbine engine comprises a plurality of liner segments 12 and a support shell. The support shell comprises an inner surface, an outer surface, a plurality of mounting holes, and a plurality of impingement cooling holes extendedly passed through the support shell. Each of the liner segments 12 comprises a panel 24 and a plurality of mounting studs 32. The panel 24 comprises a front surface, a rear surface 36, and a plurality of cooling holes 38 extendedly passed through these surfaces. The rear surface 36 of the panel 24 comprises a surface profile for preventing the drop of a pressure passing in the combustor from substantially increasing and increasing the heat transfer of the liner segments 12.
SISKIND KENNETH S
GRAVES CHARLES B
