Combustion liner
AssigneeGeneral Electric Company
InventorsPradeep Naik, Shai Birmaher, Saket Singh, Krishnendu Chakraborty
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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 liner for a combustor in a gas turbine engine, the liner comprising:
- a liner body having a cold side and a hot side;
- and
- a dilution passage having a concatenated geometry extending through the liner body, the dilution passage 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.
A method of diluting a flow through a combustor, 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;
- causing a second dilution air 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,
- wherein the integrated dilution air flow is formed by a concatenated geometry through the combustion liner.
Dependencies are inferred from the claim text.