초록 ▼

Embodiments of the present invention provide resonators (260, 460) that have lateral walls (268, 270) disposed at non-square angles relative to the liner's longitudinal (and flow-based) axis (219) such that a film cooling of substantial portions of an intervening strip (244, 444) is provided from ap

Embodiments of the present invention provide resonators (260, 460) that have lateral walls (268, 270) disposed at non-square angles relative to the liner's longitudinal (and flow-based) axis (219) such that a film cooling of substantial portions of an intervening strip (244, 444) is provided from apertures (226A, 226B, 426) in a resonator box (262, 462) adjacent and upstream from the intervening strip (244, 444). This film cooling also cools weld seams (280) along the lateral walls (268, 270) of the resonator boxes (262, 462). In various embodiments the lateral wall angles are such that film cooling may be provided to include the most of the downstream portions of the intervening strips (244, 444). These downstream portions are closer to the combustion heat source and therefore expected to be in greater need of cooling.

대표청구항 ▼

1. A combustor for a gas turbine engine comprising: a combustor liner defining an interior combustion chamber having a flow-based longitudinal axis, the combustor liner comprising a plurality of circumferentially arranged arrays of apertures there through, each said array defined by a non-rectangula

1. A combustor for a gas turbine engine comprising: a combustor liner defining an interior combustion chamber having a flow-based longitudinal axis, the combustor liner comprising a plurality of circumferentially arranged arrays of apertures there through, each said array defined by a non-rectangular four-sided shape having an upstream edge, a downstream edge, and two lateral edges, each lateral edge, based on projection of the array onto a plane, intersecting with the upstream and downstream edges at an angle other than a right angle;a plurality of resonator boxes affixed to the liner, each said resonator box covering a respective array and having lateral walls conforming with the respective angles of the lateral edges, and each said resonator box comprising an upstream wall, a downstream wall, and lateral walls affixed to the liner;a downstream-TBC disposed along the inside surface of the combustor liner from a location downstream of the plurality of resonator boxes to a TBC first edge disposed upstream of the downstream wall, wherein no apertures through the liner pass through a portion of the downstream-TBC that is upstream of the downstream wall, andwherein impingement apertures through a top plate of the resonator box are provided over the portion of the downstream-TBC that is upstream of the downstream wall,wherein intervening strips of liner remain between adjacent resonator boxes; andwherein fluid flowing from the apertures within and adjacent the lateral wall upstream of a respective intervening strip is disposed to provide a film cooling to the intervening strip. 2. The combustor of claim 1, wherein the two lateral edges are disposed substantially parallel to one another. 3. The combustor of claim 1, wherein the two lateral edges are defined by lines that converge beyond the upstream edge or the downstream edge. 4. The combustor of claim 3, additionally wherein each said array forms, based on the projection of the array onto the plane, a trapezoid-like shape. 5. The combustor of claim 1, wherein the apertures of each array are arranged in rows perpendicular to the flow-based longitudinal axis, and wherein the apertures of a first row are offset sideways in relation to apertures of an adjacent row, to provide a staggered pattern effective for cooling the liner. 6. The combustor of claim 1, the combustor additionally comprising an upstream-TBC along the liner interior surface from a location upstream of the plurality of resonator boxes and ending at a second edge disposed downstream of the upstream wall, wherein no apertures through the liner pass through a portion of the upstream-TBC that is downstream of the upstream wall, and wherein impingement apertures through a top plate of the resonator box are provided over the portion of the upstream-TBC that is downstream of the upstream wall. 7. The combustor of claim 1, wherein the first TBC edge is tapered in thickness along the flow-based longitudinal axis. 8. The combustor of claim 6, wherein the second TBC edge is tapered in thickness along the flow-based longitudinal axis. 9. The combustor of claim 1, wherein each said angle of intersecting of the array lateral edges is between about 15 and about 75 degrees. 10. The combustor of claim 1, wherein the lateral walls additionally comprise a plurality of lateral apertures effective to purge a zone between adjacent resonators. 11. A gas turbine engine comprising the combustor of claim 1. 12. The combustor of claim 1, wherein each said lateral wall is disposed at an angle between about 15 and about 75 degrees relative to the longitudinal flow-based axis. 13. The combustor of claim 1, wherein each said lateral wall is disposed at an angle between about 30 and about 60 degrees relative to the longitudinal flow-based axis. 14. A gas turbine engine comprising the combustor of claim 12. 15. A combustor for a gas turbine engine comprising: a plurality of portions of a liner of the combustor, each portion comprising a pattern of apertures there through, to provide a staggered pattern effective for cooling the liner;a plurality of resonators arranged circumferentially about the liner of the combustor, each resonator comprising a resonator box covering a respective portion of the liner and comprising an upstream wall, a downstream wall, two lateral walls each affixed to the liner by welding thereby forming weld seams, and a top plate attached to or integral with the walls, the top plate comprising a plurality of apertures, wherein the two lateral walls are disposed so as to lie not parallel to a longitudinal flow-based axis and wherein a plurality of lateral effusion apertures are provided on the lateral walls; anda thermal barrier coating (TBC) disposed along an inside surface of the liner from a liner downstream end to a tapered edge disposed upstream of a weld seam attaching the downstream wall to the liner, wherein no apertures through the liner pass through a portion of the TBC upstream of the weld seam attaching the downstream wall to the liner, and a plurality of top plate apertures are provided radially outward from the TBC edge and between the weld seam attaching the downstream wall to the liner and the TBC edge. 16. The combustor of claim 15, additionally comprising a second TBC disposed along the inside surface of the liner from a liner upstream end to a tapered edge downstream of a weld seam attaching the upstream wall to the liner, wherein no apertures through the liner pass through the second TBC edge and a plurality of top plate apertures are provided radially outward from the second TBC edge. 17. The combustor of claim 15, wherein each said lateral wall is disposed at an angle between about 15 and about 75 degrees relative to the longitudinal flow-based axis. 18. A combustor for a gas turbine engine comprising: a combustor liner defining an interior combustion chamber having a flow-based longitudinal axis, the combustor liner comprising a plurality of circumferentially arranged arrays of apertures there through, each said array defined by a non-rectangular four-sided shape having an upstream edge, a downstream edge, and two lateral edges, each lateral edge, based on projection of the array onto a plane, intersecting with the upstream and downstream edges at an angle other than a right angle; a plurality of resonator boxes affixed to the liner, each said resonator box covering a respective array and having lateral walls conforming with the respective angles of the lateral edges, and each said resonator box comprising an upstream wall, a downstream wall, and lateral walls affixed to the liner;an upstream thermal barrier coating TBC disposed along an inside surface of the combustor liner from a location upstream of the plurality of resonator boxes to a TBC edge disposed downstream of an upstream wall of each said resonator box,wherein no apertures through the liner pass through a portion of the upstream-TBC that is downstream of the upstream wall, and wherein a plurality of apertures through a top plate of the resonator box are provided over the portion of the upstream-TBC that is downstream of the upstream wall;wherein intervening strips of liner remain between adjacent resonator boxes; andwherein fluid flowing from apertures in the liner within and adjacent the lateral wall upstream of a respective intervening strip is disposed to provide a film cooling to the intervening strip. 19. The combustor of claim 18, wherein the two lateral edges are disposed substantially parallel to one another. 20. A gas turbine engine comprising the combustor of claim 18.