초록

A combustor for a gas turbine engine includes a sheet metal combustor wall having a plurality of cooling apertures therein immediately upstream of a corner between two intersecting combustor wall portions.

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We claim: 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 ex

We claim: 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. 2. The combustor as defined in claim 1, wherein the discontinuity provides a sharp corner. 3. The combustor as defined in claim 1, wherein the combustor includes three of said smooth continuous wall portions respectively separated by two of said discontinuities. 4. The combustor as defined in claim 1, wherein the combustor includes four of said smooth continuous wall portions respectively separated by three of said discontinuities. 5. The combustor as defined in claim 1, wherein the at least two smooth continuous wall portions comprise a substantial portion of the long exit duct portion. 6. The combustor as defined in claim 1, wherein the corner is positioned in the combustor wall at a predetermined position corresponding to an expected local region of high temperature within the combustion chamber and thereby adapted to cool said region. 7. The combustor as defined in claim 1, wherein the at least two smooth continuous wall portions comprise surfaces of revolution relative to a combustor axis. 8. The combustor as defined in claim 7, wherein at least one of the at least two smooth continuous wall portions is frustoconical. 9. The combustor as defined in claim 8, wherein all of the at least two smooth continuous wall portions are frustoconical. 10. The combustor as defined in claim 8, wherein at least one of the at least two smooth continuous wall portions is planar and substantially perpendicular to the combustor axis. 11. A gas turbine combustor comprising a sheet metal reverse flow annular combustor wall having at least one corner in an outer wall of a long exit duct portion of the combustor, the long exit duct portion being adapted to substantially reverse the general direction of a flow of combustion gases therethrough, the corner defining an angle between intersecting stream and downstream wall portions of the long exit duct, the upstream wall portion being frustoconical and sloping radially inwards to the corner in a direction towards a central axis of the combustor, the upstream wall portion having a plurality of cooling apertures defined therein immediately upstream of the corner, the apertures each defining a central axis therethrough which is substantially parallel to the downstream wall portion, the cooling apertures adapted to direct a cooling air flow from outside the combustor therethrough and adjacent an inner surface of the downstream wall portion in a direction substantially parallel to the downstream wall portion. 12. The gas turbine combustor as defined in claim 11, wherein the angle is obtuse. 13. The gas turbine combustor as defined in claim 11, wherein the combustor includes three of said wall portions respectively separated by two of said corners. 14. The gas turbine combustor as defined in claim 11, wherein the combustor includes four of said wall portions respectively separated by three of said corners. 15. The gas turbine combustor as defined in claim 11, wherein the portions comprise a substantial portion of the long exit duct portion.