Combustion liner
AssigneeGeneral Electric Company
InventorsPradeep Naik, Shai Birmaher, Saket Singh, Krishnendu Chakraborty
Life of this patent
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Abstract
A liner for a combustor in a gas turbine engine and a related method. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution passage having a concatenated geometry extending through the liner body. The dilution passage is configured (i) to integrate a first dilution air flow flowing through the dilution passage from the cold side to the hot side and a second dilution air flow flowing through the dilution passage from the cold side to the hot side into an integrated dilution air flow, and (ii) to inject the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor.
Claims20
A method of diluting a flow through a combustor the combustor having a central engine axis defining a circumferential direction, the method comprising:
- causing a first dilution air flow from a cold side of a combustion liner to a hot side of the combustion liner through a plurality of discrete dilution holes extending through the combustion liner;
- causing a second dilution air flow from the cold side of the combustion liner to the hot side of the combustion liner through an annular dilution slot extending through the combustion liner, the annular dilution slot having a forward face and an aft face;
- integrating the first dilution air flow and the second dilution air flow to provide an integrated dilution air flow, the integrated dilution air flow being formed by a concatenated geometry extending through the combustion liner, the concatenated geometry including the annular dilution slot and the plurality of discrete dilution holes positioned at least partially forward of the annular dilution slot such that the aft face of the annular dilution slot extends only in the circumferential direction;
- injecting the integrated dilution air flow into the combustor to attain a predetermined combustion state of the combustor;
- generating a turbulence in a core primary combustion zone of the combustor with the first dilution air flow;
- and
- filling a region of wakes formed behind the first dilution air flow with the second dilution air flow.
A method of diluting a flow through a combustor the combustor having a central engine axis defining a circumferential direction, the method comprising:
- causing a first dilution air flow from a cold side of a combustion liner to a hot side of the combustion liner by flowing the first dilution air flow through a plurality of discrete dilution holes extending through the combustion liner;
- causing a second dilution air flow from the cold side of the combustion liner to the hot side of the combustion liner by flowing the second dilution air flow through an annular dilution slot extending through the combustion liner, the annular dilution slot having a forward face and an aft face, plurality of discrete dilution holes and the annular dilution slot forming a concatenated geometry, the concatenated geometry including the annular dilution slot and the plurality of discrete dilution holes positioned at least partially forward of the annular dilution slot such that the aft face of the annular dilution slot extends only in the circumferential direction, and wherein the first dilution air flow is ten percent to ninety percent of a total flow from the cold side of the combustion liner to the hot side of the combustion liner;
- integrating the first dilution air flow and the second dilution air flow to provide an integrated dilution air flow;
- injecting the integrated dilution air flow into the combustor to attain a predetermined combustion state of the combustor;
- generating a turbulence in a core primary combustion zone of the combustor with the first dilution air flow;
- and
- filling a region of wakes formed behind the first dilution air flow with the second dilution air flow.
Dependencies are inferred from the claim text.