Patent ID: 6964170
Filing Date: 2005-11-15
Classification: F23M,F23R,Y02T

Abstract:
1. A gas turbine engine combustor defining a combustion zone therein and being adapted for receiving compressed air from a compressor, said combustor comprising: inner and outer walls spaced-apart by a predetermined spacing distance and defining a cavity therebetween; said outer wall having a first area defining at least an impingement aperture therein, said impingement aperture permitting fluid flow communication between said compressor and said cavity; said inner wall having a second area corresponding to said first area and defining a plurality of effusion apertures therein, said effusion apertures permitting fluid flow communication between said cavity and said combustion zone, and each said effusion aperture defining a cross-sectional area smaller than that of said impingement aperture; and said effusion apertures being disposed in groups having a predetermined geometric arrangement relative to said impingement aperture and defining a ratio of number of effusion apertures to said impingement aperture of between about 2:1 and about 4:1; whereby said combustor provides damping of audible frequencies less that about 1600 Hz passing therethrough.