| CPC F23R 3/34 (2013.01) [F23R 3/06 (2013.01); F23R 3/14 (2013.01); F23R 3/36 (2013.01); F02C 7/22 (2013.01); F23R 3/28 (2013.01); F23R 3/346 (2013.01)] | 20 Claims |
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1. A turbine engine comprising:
a compressor section, a combustion section, and a turbine section in serial flow arrangement, with the combustion section including a combustor defining a longitudinal axis, the combustor comprising:
a combustor liner partially defining a combustion chamber; and
a set of dilution holes provided in the combustor liner, with the set of dilution holes arranged into pairs of adjacent dilution holes, with each pair of adjacent dilution holes being spaced to define a distance defined in one or both of an axial direction and a circumferential direction, relative to the longitudinal axis;
wherein, relative to the longitudinal axis, a first pair of adjacent dilution holes are positioned forward of a second pair of adjacent dilution holes, the first pair of adjacent dilution holes are spaced to define a first distance, and the second pair of adjacent dilution holes are spaced to define a second distance lesser than the first distance; and
wherein at least one dilution hole of the set of dilution holes is arranged at a non-orthogonal angle relative to the longitudinal axis.
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