Patent ID: 7269958
Filing Date: 2007-09-18
Classification: F23R

Abstract:
1. A combustor for a gas turbine engine comprising: an inner reverse-flow annular combustor liner; and an outer reverse-flow annular sheet metal combustor liner, the outer liner including a long exit duct portion adapted to redirect combustion gases in the combustor towards a combustor exit, the long exit duct portion of the outer liner including at least two discontinuities between smooth continuous wall portions on either side of the discontinuities, the wall portions intersecting each other at the discontinuities to define an obtuse inner angle therebetween, the smooth continuous wall portions including an upstream wall and a downstream wall relative to each of the discontinuities, the downstream wall of a first one of the discontinuities being coplanar with the upstream wall of a second one of the discontinuities upstream from the first one, the coplanar downstream and upstream walls extending rectilinearly and uninterrupted between the first and second discontinuities, the upstream wall having a plurality of apertures defined therein immediately upstream of each of the discontinuities, the apertures each extending through the upstream wall at an angle such that the apertures are substantially parallel to the downstream wall, the apertures thereby delivering pressurized air surrounding the outer liner through the outer liner and along the downstream wall in a direction substantially parallel to the downstream wall.