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AssigneeSociete National d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."
InventorsDenis Roger Henri Ansart, Jean-Claude Marcel Boudot, Thierry Andre Jacques Chevalier, Denis Jean Maurice Sandelis
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A wall is disclosed for a gas turbine engine combustion chamber having a generally annular configuration around a central axis wherein the wall has an inner surface bounding at least a portion of the combustion chamber and a plurality of rows of cooling openings, each cooling opening having an elongated, generally rectangular configuration with a length l and a width e such that l is greater than e, the cooling openings in each row being equidistantly spaced apart a distance d in which d is not greater than the length l. The cooling openings of a given row are circumferentially displaced from cooling openings of an adjacent row and, since the distance d is not greater than the length l of the cooling openings, the opening areas overlap in adjacent rows to provide an even distribution of the cooling film within the combustion chamber.
A wall for a gas turbine engine combustion chamber having a generally annular configuration around a central axis, the wall having an inner surface bounding at least a portion of the combustion chamber and comprising a plurality of rows of cooling openings, each cooling opening having an elongated generally rectangular configuration with a length l and a width e wherein l>e, the cooling openings in each row being equidistantly spaced apart a distance d in which d is not greater than l wherein the length l is at least ten times the width e.
A wall for a gas turbine engine combustion chamber having a generally annular configuration around a central axis, the wall having an inner surface bounding at least a portion of the combustion chamber and comprising a plurality of rows of cooling openings, each cooling opening having an elongated generally rectangular configuration with a length l and a width e wherein l>e, the cooling openings in each row being equidistantly spaced apart a distance d in which d is not greater than l wherein each cooling opening has opposite ends, each having a generally semi-circular configuration.
Dependencies are inferred from the claim text.