Combustion liner
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.
1 . 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.
2 . The method of claim 1 , further comprising percolating the second dilution air flow between a plurality of discrete jets of the first dilution air flow to prevent a development of a high temperature zone in a proximity of the combustion liner between the plurality of discrete jets.
3 . The method of claim 1 , 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.
4 . The method of claim 1 , wherein the plurality of discrete dilution holes includes a semicircular cross section, an elliptical cross section, a race track cross section, or a triangular cross section with one side of the triangular cross section aligned and parallel with the annular dilution slot.
5 . The method of claim 1 , further comprising flowing the first dilution air flow through the plurality of discrete dilution holes and flowing the second dilution air flow through the annular dilution slot such that the second dilution air flow through the annular dilution slot is downstream of the first dilution air flow through the plurality of discrete dilution holes.
6 . The method of claim 1 , further comprising flowing the first dilution air flow through a first centerline of the plurality of discrete dilution holes and flowing the second dilution air flow through a second centerline of the annular dilution slot such that the first dilution air flow through the first centerline is parallel with the second dilution air flow through the second centerline.
7 . The method of claim 6 , further comprising flowing the first dilution air flow through the first centerline of each of the plurality of discrete dilution holes and flowing the second dilution air flow through the second centerline of the annular dilution slot such that the first dilution air flow through the first centerline is offset from the second dilution air flow through the second centerline and forward of the forward face of the annular dilution slot.
8 . The method of claim 6 , further comprising flowing the first dilution air flow through the first centerline of each of the plurality of discrete dilution holes and flowing the second dilution air flow through the second centerline of the annular dilution slot such that the first dilution air flow through the first centerline is offset aft of the second dilution air flow through the second centerline and aligned with the aft face of the annular dilution slot.
9 . The method of claim 1 , wherein the concatenated geometry includes the plurality of discrete dilution holes positioned forward of the annular dilution slot such that an aft face of the plurality of discrete dilution holes concatenates with the forward face of the annular dilution slot.
10 . The method of claim 1 , further comprising providing hydraulic support to the first dilution air flow with the second dilution air flow.
11 . The method of claim 1 , further comprising enhancing a penetration of the first dilution air flow into the core primary combustion zone of the combustor with the second dilution air flow.
12 . 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.
13 . The method of claim 12 , further comprising percolating the second dilution air flow between a plurality of discrete jets of the first dilution air flow to prevent a development of a high temperature zone in a proximity of the combustion liner between the plurality of discrete jets.
14 . The method of claim 12 , wherein the plurality of discrete dilution holes includes a semicircular cross section, an elliptical cross section, a race track cross section, or a triangular cross section with one side of the triangular cross section aligned and parallel with the annular dilution slot.
15 . The method of claim 12 , further comprising flowing the first dilution air flow through the plurality of discrete dilution holes and flowing the second dilution air flow through the annular dilution slot such that the second dilution air flow through the annular dilution slot is downstream of the first dilution air flow through the plurality of discrete dilution holes.
16 . The method of claim 12 , further comprising flowing the first dilution air flow through a first centerline of the plurality of discrete dilution holes and flowing the second dilution air flow through a second centerline of the annular dilution slot such that the first dilution air flow through the first centerline is parallel with the second dilution air flow through the second centerline.
17 . The method of claim 16 , further comprising flowing the first dilution air flow through the first centerline of each of the plurality of discrete dilution holes and flowing the second dilution air flow through the second centerline of the annular dilution slot such that the first dilution air flow through the first centerline is offset from the second dilution air flow through the second centerline and forward of the forward face of the annular dilution slot.
18 . The method of claim 16 , further comprising flowing the first dilution air flow through the first centerline of each of the plurality of discrete dilution holes and flowing the second dilution air flow through the second centerline of the annular dilution slot such that the first dilution air flow through the first centerline is offset aft of the second dilution air flow through the second centerline and aligned with the aft face of the annular dilution slot.
19 . The method of claim 12 , wherein the concatenated geometry includes the plurality of discrete dilution holes positioned forward of the annular dilution slot such that an aft face of the plurality of discrete dilution holes concatenates with the forward face of the annular dilution slot.
20 . The method of claim 12 , further comprising providing hydraulic support to the first dilution air flow with the second dilution air flow.