Film cooling hole arrangement for acoustic resonators in gas turbine engines
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United States of America Patent
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Jul 23, 2019
Grant Date -
Aug 10, 2017
app pub date -
Aug 26, 2014
filing date -
Aug 26, 2014
priority date (Note) -
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Abstract
The present disclosure provides a gas turbine combustor liner (34) comprising an outer surface (38) and an inner surface (36), a plurality of film cooling holes (44) through a thickness of the gas turbine combustor liner (34), and a plurality of resonator boxes (32) affixed to the outer surface (38) of the gas turbine combustor liner (34). The film cooling holes (44) extend circumferentially around the gas turbine combustor liner (34) and comprise a first set of holes (56) having a first axial row spacing X and a second set of holes (58) having a second axial row spacing X′. The second set of holes (58) is formed in the gas turbine combustor liner (34) in a downstream direction relative to the first set of holes (56). The second axial row spacing X′ is greater than the first axial row spacing X.
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