Combustor liner v-band with directed air flow
AssigneePratt & Whitney Canada Corp.
InventorsJacob Weber, Safouane Tebib, Mohammad Mortada Ahmed, Jeffrey Verhiel
Life of this patent
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Abstract
A combustion liner v-band includes a louver segment having an arcuate member, an array of scoops, and outlet openings. The arcuate member includes an interior wall and side walls extending partially circumferentially about a centerline axis of the combustor to bound a channel that is open at a radial outer boundary of the arcuate member. The scoops extend from the interior wall. The outlet openings extend through the interior wall and the scoops to place the channel in fluid communication with a region exterior to the louver segment. Each outlet opening extends along a discharge axis that has a nonzero axial angle component and a nonzero circumferential angle component.
Claims17
A louver segment for a gas turbine combustor having a circumferentially extending liner wall, the louver segment comprising:
- an arcuate member extending partially circumferentially about a centerline axis, the arcuate member comprising:
- an interior wall and side walls extending circumferentially about the centerline axis to bound a channel that is open at a radial outer boundary of the arcuate member, wherein the side walls converge towards the interior wall;
- a plurality of scoops extending from the interior wall;
- and
- a plurality of first outlet openings extending through the interior wall and the plurality of scoops to place the channel in fluid communication with a region exterior to the louver segment, each first outlet opening comprises:
- a discharge axis extending through a geometric center of a cross-sectional area of the respective first outlet opening and extending normal to the cross-sectional area of the respective first outlet opening, each discharge axis having a nonzero axial angle component and a nonzero circumferential angle component,
- wherein the axial angle component is an acute angle between the discharge axis and a tangent to a circumferential direction relative to the centerline axis projected into a plane normal to a radial direction relative to the centerline axis, and
- wherein the circumferential angle component is an acute angle between the discharge axis and a tangent to the circumferential direction relative to the centerline axis projected into a plane normal to the centerline axis, and
- wherein the axial component angle is greater than zero degrees and less than or equal to sixty degrees.
A gas turbine combustor assembly comprising:
- a combustor having a liner wall and
- a louver segment extending circumferentially around an interior surface of the liner wall, the louver segment comprising:
- an arcuate member extending partially circumferentially about a centerline axis, the arcuate member comprising:
- an interior wall and side walls extending circumferentially about the centerline axis to bound a channel that is open at a radial outer boundary of the arcuate member, wherein the side walls converge towards the interior wall;
- a plurality of scoops extending from the interior wall;
- and
- a plurality of first outlet openings extending through the interior wall and the plurality of scoops to place the channel in fluid communication with a region exterior to the louver segment, each first outlet opening comprises:
- a discharge axis extending through a geometric center of a cross-sectional area of the respective first outlet opening and extending normal to the cross-sectional area of the respective first outlet opening, each discharge axis having a nonzero axial angle component and a nonzero circumferential angle component,
- wherein the axial angle component is an acute angle between the discharge axis and a tangent to a circumferential direction relative to the centerline axis projected into a plane normal to a radial direction relative to the centerline axis, and
- wherein the circumferential angle component is an acute angle between the discharge axis and a tangent to the circumferential direction relative to the centerline axis projected into a plane normal to the centerline axis, and
- wherein the axial component angle is greater than zero degrees and less than or equal to sixty degrees.
Dependencies are inferred from the claim text.