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A gas turbine engine combustor liner with at least one of the inner and outer liners that is effusion cooled and has a row of groups of circumferentially spaced apart dilution holes defined therethrough. Each group is located within a respective zone of the combustor liner defined by an overlap of a

A gas turbine engine combustor liner with at least one of the inner and outer liners that is effusion cooled and has a row of groups of circumferentially spaced apart dilution holes defined therethrough. Each group is located within a respective zone of the combustor liner defined by an overlap of adjacent conical sections corresponding to the sprays of adjacent fuel nozzles.

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1. A gas turbine engine combustor liner comprising a dome having a series of circumferentially spaced apart fuel nozzle receiving holes defined therethrough, the liner having an inner liner and an outer liner defining a combustion chamber therebetween, the combustion chamber having a plurality of ov

1. A gas turbine engine combustor liner comprising a dome having a series of circumferentially spaced apart fuel nozzle receiving holes defined therethrough, the liner having an inner liner and an outer liner defining a combustion chamber therebetween, the combustion chamber having a plurality of overlap zones corresponding to an overlap of adjacent fuel cones centered on a respective receiving hole and corresponding to a fuel/air spray cone produced by a fuel nozzle received in the receiving holes, at least one of the inner and outer liners being effusion cooled and having a row of spaced apart dilution holes defined therethrough, the dilution holes being grouped in pairs of adjacent holes, the spacing between adjacent pairs being greater than a spacing between the adjacent holes of a pair, each pair being entirely located within a respective overlap zones. 2. The combustor liner as defined in claim 1, wherein the at least one of the inner and outer liners include both the inner liner and the outer liner, and the dilution holes of the pairs of the inner liner are at least substantially aligned with the dilution holes of the pairs of the outer liner. 3. The combustor liner as defined in claim 1, wherein the at least one of the inner and outer liners includes effusion holes provided in first and second annular bands, the first annular band being located upstream of the second annular band, the first annular band having a greater density of the effusion holes than the second annular band. 4. The combustor liner as defined in claim 3, wherein the hole density of the second band is at least 2 times that of the first band. 5. The combustor liner as defined in claim 3, wherein the at least one of the inner and outer liners include both the inner liner and the outer liner. 6. The combustor liner as defined in claim 1, wherein the row is a first row, the at least one of the inner and outer liners further including a second row of non equidistantly circumferentially spaced apart dilution holes defined therethrough, the second row being located downstream of the first row, the dilution holes of the second row being defined in pairs with the dilution holes of each pair being located on a respective side of and equidistant from an axis of a respective one of the nozzle receiving holes. 7. The combustor liner as defined in claim 6, wherein the at least one of the inner and outer liners includes the inner liner, the inner liner including effusion holes provided in first and second annular bands, the second annular band being located upstream of the first annular band, the second annular band having a greater density of the effusion holes than the first annular band, and the second row is located at least substantially between the first and second annular bands. 8. The combustor liner as defined in claim 1, wherein the at least one of the inner and outer liners includes the outer liner and the row is a first row, the outer liner further including a second row of dilution holes defined therethrough, the second row being defined downstream of the first row, the dilution holes of the second row including one nozzle sector hole aligned with an axis of each one of the fuel nozzle receiving holes, and a plurality of intermediate dilution holes between each pair of adjacent nozzle sector holes, the intermediate dilution holes having a diameter smaller than that of the nozzle sector holes. 9. The combustor liner as defined in claim 1, wherein a distance between adjacent dilution holes of adjacent pairs is at least 3.25 times that between adjacent dilution holes of a same pair. 10. The combustor liner as defined in claim 9, wherein the distance between adjacent dilution holes of adjacent pairs is approximately 7.5 times that between adjacent dilution holes of the same pair. 11. A gas turbine engine combustor comprising a dome end having receiving holes defined therethrough, an inner liner wall and an outer liner wall extending from the dome end and defining a combustion chamber therebetween, a fuel nozzle received in each of the receiving holes for producing a conical spray within the combustion chamber, at least one of the outer liner wall and the inner liner wall being effusion cooled and including a circumferential row of dilution holes defined therethrough, the dilution holes of the row being disposed in groups with the row being free of dilution holes between adjacent ones of the groups, each group being entirely located between adjacent ones of the receiving holes within an overlap zone of the conical sprays of the fuel nozzles. 12. The combustor as defined in claim 11, wherein the groups of dilution holes are pairs of circumferentially spaced apart dilution holes. 13. The combustor as defined in claim 11, wherein the at least one of the inner and outer liners include both the inner liner and the outer liner, and the dilution holes of the groups of the inner liner are at least substantially aligned with the dilution holes of the groups of the outer liner. 14. The combustor as defined in claim 11, wherein the at least one of the inner and outer liners includes effusion holes located within first and second annular regions defined around the combustor, the first region being located upstream of the second region, the first region having a greater density of the effusion holes than the second region. 15. The combustor as defined in claim 14, wherein the hole density of the second region is at least 2 times that of the first region. 16. The combustor as defined in claim 14, wherein the at least one of the inner and outer liners includes both the inner liner and the outer liner. 17. The combustor as defined in claim 11, wherein the row is a first row, the at least one of the inner and outer liners further including a second row of non equidistantly circumferentially spaced apart dilution holes defined therethrough, the second row being located downstream of the first row, the dilution holes of the second row being defined in pairs with the dilution holes of each pair being located on a respective side of and equidistant from an axis of a respective one of the receiving holes. 18. The combustor as defined in claim 17, wherein the at least one of the inner and outer liners includes the inner liner, the inner liner including effusion holes provided in first and second regions defined around the combustor, the first region being located upstream of the second region, the first region having a greater density of the effusion holes than the second region, and the second row is located at least substantially between the first and second regions. 19. The combustor as defined in claim 11, wherein the at least one of the inner and outer liners includes the outer liner and the row is a first row, the outer liner further including a second row of dilution holes defined therethrough, the second row being defined downstream of the first row, the dilution holes of the second row including one nozzle sector hole aligned with an axis of each one of the receiving holes, and a plurality of intermediate dilution holes between each pair of adjacent nozzle sector holes, the intermediate dilution holes having a diameter smaller than that of the nozzle sector holes. 20. The combustor liner as defined in claim 11, wherein a distance between adjacent dilution holes of adjacent groups is at least 3.25 times that between adjacent dilution holes of a same group. 21. The combustor liner as defined in claim 20, wherein the distance between adjacent dilution holes of adjacent groups is approximately 7.5 times that between adjacent dilution holes of the same group.