Combustor case arrangement

1 . A combustor assembly for a gas turbine engine, the combustor assembly comprising:

a combustor liner disposed about an axis and defining a combustion chamber, the combustor liner comprising:

an outer wall comprising a plurality of mounting bosses; and

a plurality of first holes open to the combustion chamber;

an outer case disposed about the combustor liner and defining an air flow duct therebetween, the outer case comprising:

a plurality of inlet scoops extending radially inward of the outer case, the plurality of inlet scoops radially aligned with the plurality of first holes and configured to guide an air flow into the plurality of first holes;

wherein the plurality inlet scoops extend axially from an open first end to a closed second end, the second end opposite the first end, and comprise converging walls;

wherein each of the plurality of inlet scoops is attached to the outer case by a strut;

wherein each of the plurality of inlet scoops comprises a radially outer wall connecting two side walls, wherein the radially outer wall is spaced radially from the outer case wherein the plurality of inlet scoops is spaced radially from the outer wall of the combustor liner; and

wherein a subset of the plurality of inlet scoops comprises a splash plate, the splash plate spaced radially inward from the radially outer wall and connecting the two side walls, wherein a height measured between the splash plate and the radially outer wall decreases from the open first end toward the closed second end; and

a plurality of pins fixed to the outer case and slidingly received in openings in the plurality of mounting bosses.

2 . The combustor assembly of claim 1 , wherein the outer case further comprises a plurality of fuel injectors, wherein each of the plurality of fuel injectors extends through the strut of the subset of the plurality of inlet scoops and comprises a nozzle opening oriented to face the splash plate.

3 . The combustor assembly of claim 2 , wherein the outer case further comprises an integral fuel manifold fluidly connected to the plurality of fuel injectors.

4 . The combustor assembly of claim 1 , wherein the two side walls angle inward from the radially outer wall toward the outer wall of the combustor liner.

5 . The combustor assembly of claim 1 , wherein the combustor liner further comprises a plurality of flow guides extending radially outward from the combustor liner, wherein the plurality of flow guides partially surrounds the plurality of first holes and wherein a portion of each of the plurality of inlet scoops is configured to be received in a respective flow guide.

6 . The combustor assembly of claim 5 , wherein the combustor liner further comprises a plurality of chutes projecting from the plurality of first holes into the combustion chamber.

7 . The combustor assembly of 1 , wherein the combustor liner further comprises a plurality of second holes, wherein the plurality of first holes is arranged circumferentially in a first row and the plurality of second holes is arranged circumferentially in a second row aft of the plurality of first holes with respect to a direction of the air flow through the combustor assembly.

8 . The combustor assembly of claim 1 , wherein the outer case further comprises a bypass duct disposed radially outward of the air flow duct.

9 . A combustor assembly for a gas turbine engine, the combustor assembly comprising:

a combustor liner disposed about an axis and defining a combustion chamber, the combustor liner comprising:

an outer wall comprising a plurality of mounting bosses;

a plurality of holes open to the combustion chamber; and

a plurality of flow guides extending radially outward from the outer wall partially around the plurality of holes;

an outer case disposed about the combustor liner and defining an air flow duct therebetween, the outer case comprising a plurality of inlet scoops connected to and extending radially inward of the outer case and radially aligned with the plurality of holes, the plurality of inlet scoops extending axially from an open first end to a closed second end, the second end opposite the first end, and comprising walls that converge in extension from the first end to the second end; and

a plurality of pins fixed to the outer case and slidingly received in openings in the plurality of mounting bosses.

10 . The combustor assembly of claim 9 , wherein each of the plurality of inlet scoops is attached to the outer case by a strut.

11 . The combustor assembly of claim 10 , wherein each of the plurality of inlet scoops comprises a radially outer wall and two side walls and wherein a subset of the plurality of inlet scoops comprises a splash plate, the splash plate spaced radially inward from the radially outer wall and connecting the two side walls.

12 . The combustor assembly of claim 11 , wherein the outer case further comprises a fuel manifold integrally formed therewith and a plurality of fuel injectors, the plurality of fuel injectors extending through the strut and radially outer wall of the subset of the plurality of inlet scoops.

13 . The combustor assembly of claim 9 , wherein the plurality of flow guides are sized to receive a portion of the plurality of inlet scoops such that the plurality of flow guides and the portions of the plurality of inlet scoops overlap radially.

14 . The combustor assembly of claim 9 , wherein the combustor liner further comprises a plurality of chutes projecting from the plurality of holes into the combustion chamber.