Micro-grooved heat transfer combustor wall

Claim 2

A combustor for use in a gas turbine engine comprising: an annular inner liner; an annular outer liner, said inner liner and said outer liner being operable to be disposed in a hot gas flow of said engine flowing through said combustor, wherein at least one of said inner and outer liners comprises a heat transfer wall; a longitudinal cross-sectional shape having a longitudinally extending centerline disposed midway between said inner and outer liners; means for reducing NOx emissions of said combustor and for inhibiting heat transfer from the hot gas flow to said wall, said means for reducing and inhibiting comprising: a portion of said wall which is devoid of film cooling apertures, said portion having a hot surface operable for exposure to the hot gas flow; and a plurality of longitudinally extending grooves etched in said portion along said hot surface in a first direction substantially parallel to said centerline; wherein said grooves are sized so as to inhibit heat transfer from the hot gas flow to said hot surface of said wall while reducing NOx emissions of said combustor relative to an otherwise similar combustor having a liner wall portion which includes film cooling apertures for directing cooling air into the otherwise similar combustor, wherein said grooves form a plurality of longitudinally extending riblets, each of said riblets being disposed between an adjacent pair of said grooves; wherein said grooves have a depth and a width on the order of magnitude of a predetermined thickness of a laminar sublayer of a turbulent boundary layer along said combustor liner, said depth being defined as the distance between an innermost portion of said groove and an outermost portion of an adjacent one of said riblets as measured in a second direction which is substantially perpendicular to a plane passing through said outermost portion of an adjacent pair of said riblets, said width being defined as the greatest distance between opposing sidewalls of said groove as measured in a third direction which is substantially perpendicular to said second direction and which is substantially parallel to said plane.

Claim 3

A combustor as claimed in claim 1 wherein each of said riblets has a lateral cross-sectional shape from a group of shapes, said group of shapes consisting of square, rectangular, and triangular shapes.

Claim 4

A combustor for use in a gas turbine engine comprising: an annular inner liner; an annular outer liner, said inner liner and said outer liner being operable to be disposed in a hot gas flow of said engine flowing through said combustor, wherein at least one of said inner and outer liners comprises a heat transfer wall; a longitudinal cross-sectional shape having a longitudinally extending centerline disposed midway between said inner and outer liners; means for reducing NOx emissions of said combustor and for inhibiting heat transfer from the hot gas flow to said wall, said means for reducing and inhibiting comprising: a portion of said wall which is devoid of film cooling apertures, said portion having a hot surface operable for exposure to the hot gas flow; and a plurality of longitudinally extending grooves etched in said portion along said hot surface in a first direction substantially parallel to said centerline; wherein said grooves are sized so as to inhibit heat transfer from the hot gas flow to said hot surface of said wall while reducing NOx emissions of said combustor relative to an otherwise similar combustor having a liner wall portion which includes film cooling apertures for directing cooling air into the otherwise similar combustor; wherein said grooves form a plurality of longitudinally extending riblets, each of said riblets being disposed between an adjacent pair of said grooves; wherein said grooves have a depth and a width in a range of between about 0.001 inches and 0.005 inches, said depth being defined as the distance between and innermost portion of said groove and an outermost portion of an adjacent one of said riblets as measured in a second direction which is substantially perpendicular to a plane passing through said outermost portion of an adjacent pair of said riblets, said width being defined as the greatest distance between opposing sidewalls of said grooves as measured in a third direction which is substantially perpendicular to said second direction and which is substantially parallel to said plane.

Claim 5

A combustor for use in a gas turbine engine comprising: an annular inner liner; an annular outer liner, said inner liner and said outer liner being operable to be disposed in a hot gas flow of said engine flowing through said combustor, wherein at least one of said inner and outer liners comprises a heat transfer wall; a longitudinal cross-sectional shape having a longitudinally extending centerline disposed midway between said inner and outer liners; means for reducing NOx emissions of said combustor and for inhibiting heat transfer from the hot gas flow to said wall, said means for reducing and inhibiting comprising: a portion of said wall which is devoid of film cooling apertures, said portion having a hot surface operable for exposure to the hot gas flow; and a plurality of longitudinally extending grooves etched in said portion along said hot surface in a first direction substantially parallel to said centerline; wherein said grooves are sized so as to inhibit heat transfer from the hot gas flow to said hot surface of said wall while reducing NOx emissions of said combustor relative to an otherwise similar combustor having a liner wall portion which includes film cooling apertures for directing cooling air into the otherwise similar combustor; wherein said grooves form a plurality of longitudinally extending riblets, each of said riblets being disposed between an adjacent pair of said grooves; wherein said grooves have a depth and a width in a range of between about 0.001 inches and 0.005 inches, said depth being defined as the distance between and innermost portion of said groove and an outermost portion of an adjacent one of said riblets as measured in a second direction which is substantially perpendicular to a plane passing through said outermost portion of an adjacent pair of said riblets, said width being defined as the greatest distance between opposing sidewalls of said grooves as measured in a third direction which is substantially perpendicular to said second direction and which is substantially parallel to said plane.

Claim 6

A combustor as claimed in claim 3 wherein each of said riblets has a lateral cross-sectional shape from a group of shapes, said group of shapes consisting of square, rectangular, and triangular shapes.

Claim 7

A combustor for use in a gas turbine engine comprising: an annular inner liner; an annular outer liner, said inner liner and said outer liner being operable to be disposed in a hot gas flow of said engine flowing through said combustor, wherein at least one of said inner and outer liners comprises a heat transfer wall; a longitudinal cross-sectional shape having a longitudinally extending centerline disposed midway between said inner and outer liners; means for reducing NOx emissions of said combustor and for inhibiting heat transfer from the hot gas flow to said wall, said means for reducing and inhibiting comprising: a portion of said wall which is devoid of film cooling apertures, said portion having a hot surface operable for exposure to the hot gas flow; and a plurality of longitudinally extending grooves etched in said portion along said hot surface in a first direction substantially parallel to said centerline; wherein said groove are sized so as to inhibit heat transfer from the hot gas flow to said hot surface of said wall while reducing NOx emissions of said combustor relative to an otherwise similar combustor having a liner wall portion which includes film cooling apertures for directing cooling air into the otherwise similar combustor, wherein said grooves form a plurality of longitudinally extending riblets, each of said riblets being disposed between an adjacent pair of said grooves; wherein said grooves have a depth and a width of about 0.001 inches, said depth being defined as the distance between an innermost portion of said grooves and an outermost portion of an adjacent one of said riblets as measured in a second direction which is substantially perpendicular to a plane passing through said outermost portion of an adjacent pair of said riblets, said width being defined as the greatest distance between opposing sidewalls of said groove as measured in a third direction which is substantially perpendicular to said second direction and which is substantially parallel to said plane.

Claim 8

A combustor for use in a gas turbine engine comprising: an annular inner liner; an annular outer liner, said inner liner and said outer liner being operable to be disposed in a hot gas flow of said engine flowing through said combustor, wherein at least one of said inner and outer liners comprises a heat transfer wall; a longitudinal cross-sectional shape having a longitudinally extending centerline disposed midway between said inner and outer liners; means for reducing NOx emissions of said combustor and for inhibiting heat transfer from the hot gas flow to said wall, said means for reducing and inhibiting comprising: a portion of said wall which is devoid of film cooling apertures, said portion having a hot surface operable for exposure to the hot gas flow; and a plurality of longitudinally extending grooves etched in said portion along said hot surface in a first direction substantially parallel to said centerline; wherein said groove are sized so as to inhibit heat transfer from the hot gas flow to said hot surface of said wall while reducing NOx emissions of said combustor relative to an otherwise similar combustor having a liner wall portion which includes film cooling apertures for directing cooling air into the otherwise similar combustor, wherein said grooves form a plurality of longitudinally extending riblets, each of said riblets being disposed between an adjacent pair of said grooves; wherein said grooves have a depth and a width of about 0.001 inches, said depth being defined as the distance between an innermost portion of said grooves and an outermost portion of an adjacent one of said riblets as measured in a second direction which is substantially perpendicular to a plane passing through said outermost portion of an adjacent pair of said riblets, said width being defined as the greatest distance between opposing sidewalls of said groove as measured in a third direction which is substantially perpendicular to said second direction and which is substantially parallel to said plane.

Claim 9

A combustor as claimed in claim 5 wherein each of said riblets has a lateral cross-sectional shape from a group of shapes, said group of shapes consisting of square, rectangular, and triangular shapes.

Claim 10

A combustor for use in a gas turbine engine comprising: an annular inner liner; an annular outer liner, said inner liner and said outer liner being operable to be disposed in a hot gas flow of said engine flowing through said combustor, wherein at least one of said inner and outer liners comprises a heat transfer wall; a longitudinal cross-sectional shape having a longitudinally extending centerline disposed midway between said inner and outer liners; means for reducing NOx emissions of said combustor and for inhibiting heat transfer from the hot gas flow to said wall, said means for reducing and inhibiting comprising: a portion of said wall which is devoid of film cooling apertures, said portion having a hot surface operable for exposure to the hot gas flow; and a plurality of longitudinally extending grooves etches in said portion along said hot surface in a first direction substantially parallel to said centerline; wherein said grooves are sized so as to inhibit heat transfer from the hot gas flow to said hot surface of said wall while reducing NOx emissions of said combustor relative to an otherwise similar combustor having a liner wall portion which includes film cooling apertures for directing cooling air into the otherwise similar combustor, wherein said grooves form a plurality of longitudinally extending riblets, each of said riblets being disposed between an adjacent pair of said grooves; wherein said grooves have a depth and a width in a range of between about 0.001 inches and 0.005 inches, said depth being defined as the distance between an innermost portion of said groove and an outermost portion of an adjacent one of said riblets as measured in a second direction which is substantially perpendicular to a plane passing through said outermost portion of an adjacent pair of said riblets, said width being defined as the greatest distance between opposing sidewalls of said groove as measured in a third direction which is substantially perpendicular to said second direction and which is substantially parallel to said plane, and wherein said grooves are spaced apart along said hot surface in said third direction by said width.

Claim 11

A combustor for use in a gas turbine engine comprising: an annular inner liner; an annular outer liner, said inner liner and said outer liner being operable to be disposed in a hot gas flow of said engine flowing through said combustor, wherein at least one of said inner and outer liners comprises a heat transfer wall; a longitudinal cross-sectional shape having a longitudinally extending centerline disposed midway between said inner and outer liners; means for reducing NOx emissions of said combustor and for inhibiting heat transfer from the hot gas flow to said wall, said means for reducing and inhibiting comprising: a portion of said wall which is devoid of film cooling apertures, said portion having a hot surface operable for exposure to the hot gas flow; and a plurality of longitudinally extending grooves etches in said portion along said hot surface in a first direction substantially parallel to said centerline; wherein said grooves are sized so as to inhibit heat transfer from the hot gas flow to said hot surface of said wall while reducing NOx emissions of said combustor relative to an otherwise similar combustor having a liner wall portion which includes film cooling apertures for directing cooling air into the otherwise similar combustor, wherein said grooves form a plurality of longitudinally extending riblets, each of said riblets being disposed between an adjacent pair of said grooves; wherein said grooves have a depth and a width in a range of between about 0.001 inches and 0.005 inches, said depth being defined as the distance between an innermost portion of said groove and an outermost portion of an adjacent one of said riblets as measured in a second direction which is substantially perpendicular to a plane passing through said outermost portion of an adjacent pair of said riblets, said width being defined as the greatest distance between opposing sidewalls of said groove as measured in a third direction which is substantially perpendicular to said second direction and which is substantially parallel to said plane, and wherein said grooves are spaced apart along said hot surface in said third direction by said width.

Claim 12

A combustor as claimed in claim 7 wherein each of said riblets has a lateral cross-sectional shape from a group of shapes, said group of shapes consisting of square, rectangular, and triangular shapes.