CPC F23R 3/002 (2013.01) [F23R 3/06 (2013.01); B33Y 80/00 (2014.12); F23R 2900/03044 (2013.01)] | 18 Claims |
1. A liner for a combustor in a gas turbine engine, the liner comprising:
a liner body having a cold side and a hot side, the liner body comprising:
a first portion;
a second portion axially offset from the first portion; and
a third portion joining the first portion and the second portion, the third portion having a first axially facing side surface and a second axially facing side surface;
a dilution opening extending through the liner body; and
a passage positioned adjacent the dilution opening and extending through the third portion of the liner body from the cold side to the hot side, the passage having an inlet at a forward side of the dilution opening and extending through the first axially facing side surface of the third portion and an outlet extending through the second axially facing side surface of the third portion,
wherein a dilution flow flows through the dilution opening from the cold side to the hot side, and
wherein a secondary flow flows through the passage from the inlet to the outlet such that the secondary flow exits into the hot side aft of the dilution flow to suppress wakes formed aft of the dilution flow on the hot side of the liner.
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