Contoured dilution passages for gas turbine engine combustor
A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than the first inner periphery. Another wall assembly for use in a combustor of a gas turbine engine includes an annular grommet mounted between the support shell and the liner panel. The annular grommet defines a contoured inner wall.
1. A wall assembly for use in a combustor of a gas turbine engine, the wall assembly comprising:
a support shell;
a liner panel; and
a converging annular grommet mounted between and connecting the support shell and the liner panel, wherein the converging annular grommet defines a converging contoured inner wall that is at least one of convex or funnel shaped, the converging contoured inner wall extending from a first grommet end of the converging annular grommet to a second grommet end of the converging annular grommet opposite the first grommet end, the second grommet end mounted against a cold side of the liner panel opposite a hot side of the liner panel;
wherein the converging contoured inner wall continuously converges from the first grommet end to the second grommet end, where the first grommet end has a first inner periphery and the second grommet end has a second inner periphery, the second inner periphery defining a second cross-sectional area which is smaller than that of a first cross-sectional area defined by the first inner periphery;
wherein the converging contoured inner wall defines a contoured converging dilution passage extending through the liner panel and the support shell about an axis (D);
wherein a first point (W) on the first inner periphery, a second point (X) on the second inner periphery and a third point (Y) define a triangle;
wherein a first line defined between the second point (X) and the third point (Y) is parallel to the axis (D) of the contoured converging dilution passage;
wherein the triangle is defined by the first line, a second line and third line, wherein the second line is defined between the first point and the third point, and the third line is defined between the first point and the second point; and
wherein the converging contoured inner wall forms a convergent nozzle.
2. The wall assembly of claim 1 , wherein the converging contoured inner wall is non-linear.
3. The wall assembly of claim 1 , wherein the converging contoured inner wall converges toward the axis (D) from the first inner periphery toward the second inner periphery.
4. The wall assembly of claim 3 , further comprising a flow guide along the converging contoured inner wall.
5. The wall assembly of claim 4 , wherein the converging contoured inner wall is defined between the first inner periphery and the second inner periphery.
6. The wall assembly of claim 1 , wherein the support shell comprises a first hole and the liner panel comprises a second hole, the first hole and the second hole being coaxial with the contoured converging dilution passage extending through the liner panel and the support shell about the axis (D).
7. The wall assembly of claim 6 , wherein the second hole comprises a second hole cross-sectional area that is the same as the second cross-sectional area defined by the second inner periphery.
8. The wall assembly of claim 6 , wherein the converging annular grommet is disposed, in part, within the first hole of the support shell.
9. A wall assembly for use in a combustor of a gas turbine engine, the wall assembly comprising:
a support shell;
a liner panel; and
a converging annular grommet mounted between and connecting the support shell and the liner panel, wherein the converging annular grommet defines a converging contoured inner wall that is at least one of convex or funnel shaped, the converging contoured inner wall extending from a first grommet end of the converging annular grommet to a second grommet end of the converging annular grommet opposite the first grommet end, the second grommet end mounted against a cold side of the liner panel opposite a hot side of the liner panel;
wherein the converging contoured inner wall continuously converges from the first grommet end to the second grommet end, where the first grommet end has a first inner periphery and the second grommet end has a second inner periphery, the second inner periphery defining a second cross-sectional area which is smaller than that of a first cross-sectional area defined by the first inner periphery;
wherein the converging contoured inner wall defines a contoured converging dilution passage extending through the liner panel and the support shell about an axis (D);
wherein a first point (W) on the first inner periphery, a second point (X) on the second inner periphery and a third point (Y) define a triangle;
wherein a first line defined between the second point (X) and the third point (Y) is parallel to the axis (D) of the contoured converging dilution passage;
wherein the triangle defines an angle of twenty five (25) degrees between a second line and a third line, wherein the second line is defined between the first point and the third point, and the third line is defined between the first point and the second point; and
wherein the converging contoured inner wall forms a convergent nozzle.
10. The wall assembly of claim 9 , wherein the converging contoured inner wall is non-linear.
11. The wall assembly of claim 9 , wherein the converging contoured inner wall converges toward the axis (D) from the first inner periphery toward the second inner periphery.
12. The wall assembly of claim 11 , further comprising a flow guide along the converging contoured inner wall.
13. The wall assembly of claim 12 , wherein the converging contoured inner wall is defined between the first inner periphery and the second inner periphery.
14. A wall assembly for use in a combustor of a gas turbine engine, the wall assembly comprising:
a support shell;
a liner panel;
a converging annular grommet mounted between the support shell and the liner panel, wherein the converging annular grommet defines a converging contoured inner wall that is at least one of convex or funnel shaped, the converging contoured inner wall extending from a first grommet end of the converging annular grommet to a second grommet end of the converging annular grommet opposite the first grommet end, the second grommet end in contact with the liner panel;
wherein the converging contoured inner wall converges from a first inner periphery at the first grommet end and to second inner periphery at the second grommet end where the second inner periphery defines a second cross-sectional area which is smaller than that of a first cross-sectional area defined by the first inner periphery, wherein
the first inner periphery and the second inner periphery define a contoured converging dilution passage extending through the liner panel and the support shell about an axis (D);
a first point (W) on the first inner periphery, a second point (X) on the second inner periphery and a third point (Y) define a triangle;
a first line defined between the second point (X) and the third point (Y) is parallel to the axis (D) of the contoured converging dilution passage;
the triangle is defined by the first line, a second line and third line, wherein the second line is defined between the first point and the third point, and the third line is defined between the first point and the second point; and
the converging contoured inner wall forms a convergent nozzle; and
a flow guide extending along the converging contoured inner wall and protruding towards the axis (D) and having a triangular shape.