Segmented effusion cooled gas turbine engine combustor

1. A gas turbine engine combustor, comprising:

an inner liner and having an inner surface, an outer surface, an upstream end, a downstream end, the inner liner extending in an axial direction between the upstream and downstream ends;

an outer liner having an inner surface, an outer surface, an upstream end, and a downstream end, the outer liner extending in the axial direction between the upstream and downstream ends and spaced apart from, and at least partially surrounding, the inner liner;

a dome assembly coupled between the upstream ends of the inner and outer annular liners to define a combustion chamber between the inner liner outer surface and the outer liner inner surface; and

two or more sets of effusion cooling holes extending through the outer liner between the outer liner outer and inner surfaces, each set of effusion cooling holes including one or more initial rows of effusion cooling holes, one or more final rows of effusion cooling holes disposed downstream of the one or more initial rows, and a plurality of interposed rows of effusion cooling holes disposed between the initial and final rows, wherein:

each effusion cooling hole in the one or more initial rows is disposed at a tangential angle of between about 70° and about 90° relative to the axial direction,

each effusion cooling hole in the one or more final rows is disposed at a tangential angle of between about 0° and about 20° relative to the axial direction, and

each effusion cooling hole in each of the interposed rows disposed at a tangential angle, relative to the axial direction, that is less than the tangential angle of the effusion cooling holes in the one or more initial rows and greater than the tangential angle of the effusion cooling holes in the one or more final rows.

2. The combustor of claim 1 , further comprising:

one or more rows of dilution openings extending through the outer liner and disposed between each set of effusion cooling holes.

3. The combustor of claim 2 , wherein the one or more rows of dilution openings includes:

a row of primary dilution openings; and

a row of secondary dilution openings disposed adjacent the primary dilution openings.

4. The combustor of claim 1 , wherein each effusion cooling hole in each set of effusion cooling holes has a diameter between about 0.010-inches and 0.030-inches.

5. The combustor of claim 1 , wherein each effusion cooling hole in each set of effusion cooling holes extends through the outer liner at an acute angle relative to the outer liner outer surface.

6. The combustor of claim 1 , further comprising:

two or more sets of effusion cooling holes extending through the inner liner, each set of effusion cooling holes including one or more initial rows of effusion cooling holes, one or more final rows of effusion cooling holes disposed downstream of the one or more initial rows, and a plurality of interposed rows of effusion cooling holes disposed between the initial and final rows, wherein:

each effusion cooling hole in the one or more initial rows is disposed at a tangential angle of between about 70° and about 90° relative to the axial direction,

each effusion cooling hole in the one or more final rows is disposed at a tangential angle of between about 0° and about 20° relative to the axial direction, and

each effusion cooling hole in each of the interposed rows disposed at a tangential angle, relative to the axial direction, that is less than the tangential angle of the effusion cooling holes in the one or more initial rows and greater than the tangential angle of the effusion cooling holes in the one or more final rows.

7. The combustor of claim 6 , further comprising:

one or more rows of dilution openings extending through the inner liner and disposed between each set of effusion cooling holes in the inner liner; and

one or more rows of dilution openings extending through the outer liner and disposed between each set of effusion cooling holes in the outer liner.

8. The combustor of claim 7 , wherein the one or more rows of dilution openings includes:

a row of primary dilution openings; and

a row of secondary dilution openings disposed adjacent the primary dilution openings.

9. The combustor of claim 6 , wherein each effusion cooling hole in each set of effusion cooling holes has a diameter between about 0.010-inches and 0.030-inches.

10. The combustor of claim 6 , wherein:

each effusion cooling hole in each set of effusion cooling holes in the outer liner extends through the outer liner at an acute angle relative to the outer liner outer surface; and

each effusion cooling hole in each set of effusion cooling holes in the inner liner extends through the inner liner at an acute angle relative to the inner liner outer surface.

11. A gas turbine engine combustor, comprising:

an inner liner and having an inner surface, an outer surface, an upstream end, a downstream end, the inner liner extending in an axial direction between the upstream and downstream ends;

an outer liner extending in the axial direction and having an inner surface, an outer surface, an upstream end, and a downstream end, the outer liner spaced apart from, and at least partially surrounding, the inner liner;

a dome assembly coupled between the upstream ends of the inner and outer annular liners to define a combustion chamber therebetween;

two or more sets of effusion cooling holes extending through the inner liner between the inner liner outer and inner surfaces; and

two or more sets of effusion cooling holes extending through the outer liner between the outer liner outer and inner surfaces,

wherein each set of effusion cooling holes in both the inner and outer liners includes one or more initial rows of effusion cooling holes, one or more final rows of effusion cooling holes disposed downstream of the one or more initial rows, and a plurality of interposed rows of effusion cooling holes disposed between the initial and final rows, and

wherein:

each effusion cooling hole in the one or more initial rows is disposed at a tangential angle of between about 70° and about 90° relative to the axial direction,

each effusion cooling hole in the one or more final rows is disposed at a tangential angle of between about 0° and about 20° relative to the axial direction, and

each effusion cooling hole in each of the interposed rows disposed at a tangential angle, relative to the axial direction, that is less than the tangential angle of the effusion cooling holes in the one or more initial rows and greater than the tangential angle of the effusion cooling holes in the one or more final rows.

12. The combustor of claim 11 , further comprising:

one or more rows of dilution openings extending through the inner liner and disposed between each set of effusion cooling holes disposed therein; and

one or more rows of dilution openings extending through the outer liner and disposed between each set of effusion cooling holes disposed therein.

13. The combustor of claim 12 , wherein the one or more rows of dilution openings includes:

a row of primary dilution openings; and

a row of secondary dilution openings disposed adjacent the primary dilution openings.

14. The combustor of claim 11 , wherein each effusion cooling hole in each set of effusion cooling holes has a diameter between about 0.010-inches and 0.030-inches.

15. The combustor of claim 11 , wherein:

each effusion cooling hole in each set of effusion cooling holes in the outer liner extends through the outer liner at an acute angle relative to the outer liner outer surface; and

each effusion cooling hole in each set of effusion cooling holes in the inner liner extends through the inner liner at an acute angle relative to the inner liner outer surface.

16. A gas turbine engine, comprising:

a compressor, a combustor, and a turbine disposed in flow series with one another, the combustor including:

an inner liner and having an inner surface, an outer surface, an upstream end, and a downstream end, the inner liner extending in an axial direction between the upstream and downstream ends;

an outer liner extending in the axial direction and having an inner surface, an outer surface, an upstream end, and a downstream end, the outer liner spaced apart from, and at least partially surrounding, the inner liner;

a dome assembly coupled between the upstream ends of the inner and outer annular liners to define a combustion chamber therebetween; and

two or more sets of effusion cooling holes extending through the outer liner between the outer liner outer and inner surfaces, each set of effusion cooling holes including one or more initial rows of effusion cooling holes, one or more final rows of effusion cooling holes disposed downstream of the one or more initial rows, and a plurality of interposed rows of effusion cooling holes disposed between the initial and final rows, wherein:

each effusion cooling hole in the one or more initial rows is disposed at a tangential angle of between about 70° and about 90° relative to the axial direction,

each effusion cooling hole in the one or more final rows is disposed at a tangential angle of between about 0° and about 20° relative to the axial direction, and

each effusion cooling hole in each of the interposed rows disposed at a tangential angle, relative to the axial direction, that is less than the tangential angle of the effusion cooling holes in the one or more initial rows and greater than the tangential angle of the effusion cooling holes in the one or more final rows.

17. The engine of claim 16 , further comprising:

two or more sets of effusion cooling holes extending through the inner liner, each set of effusion cooling holes including one or more initial rows of effusion cooling holes, one or more final rows of effusion cooling holes disposed downstream of the one or more initial rows, and a plurality of interposed rows of effusion cooling holes disposed between the initial and final rows, wherein:

each effusion cooling hole in the one or more initial rows is disposed at a tangential angle of between about 70° and about 90° relative to the axial direction,

each effusion cooling hole in the one or more final rows is disposed at a tangential angle of between about 0° and about 20° relative to the axial direction, and

each effusion cooling hole in each of the interposed rows disposed at a tangential angle, relative to the axial direction, that is less than the tangential angle of the effusion cooling holes in the one or more initial rows and greater than the tangential angle of the effusion cooling holes in the one or more final rows.

18. The combustor of claim 17 , further comprising:

one or more rows of dilution openings extending through the inner liner and disposed between each set of effusion cooling holes in the inner liner; and

one or more rows of dilution openings extending through the outer liner and disposed between each set of effusion cooling holes in the outer liner.

19. The combustor of claim 18 , wherein the one or more rows of dilution openings includes:

a row of primary dilution openings; and

a row of secondary dilution openings disposed downstream of the primary dilution openings.

20. The combustor of claim 16 , wherein:

each effusion cooling hole in each set of effusion cooling holes in the outer liner is disposed at an inward angle of between about 10° and about 30° relative to the outer liner inner surface; and

each effusion cooling hole in each set of effusion cooling holes in the inner liner is disposed at an inward angle of between about 10° and about 30° relative to the inner liner inner surface.