Monolithic combustor for attritiable engine applications
A monolithic combustor apparatus comprises an outer casing comprising a forward flange, a fuel manifold disposed on the outer casing and defining an annular chamber extending perimetrically around the outer casing, a combustor liner disposed within the outer casing, the combustor liner defining an annular combustion chamber, a first annular plenum disposed between the outer casing and the combustor liner, an inner liner disposed radially from the combustor liner, a first inner flange extending forward from the combustor liner, and a second inner flange extending radially inward from the first inner flange.
1. A monolithic apparatus, comprising:
an outer casing comprising a forward flange;
a fuel manifold disposed on the outer casing and defining an annular chamber extending perimetrically around the outer casing;
a combustor liner disposed within the outer casing, the combustor liner defining an annular combustion chamber;
a first annular plenum disposed between the outer casing and the combustor liner, wherein the fuel manifold is disposed radially outward from the first annular plenum;
an inner liner disposed radially from the combustor liner;
a first inner flange extending forward from the combustor liner;
a second inner flange extending radially inward from the first inner flange; and
an aft wall of the outer casing at least partially defining a flow path for a flow of air around the combustor liner, wherein the aft wall extends from the inner liner at an angle with respect to a centerline axis of the monolithic apparatus.
2. The monolithic apparatus of claim 1 , further comprising an injector port extending into the annular combustion chamber from the combustor liner.
3. The monolithic apparatus of claim 2 , wherein the injector port defines a diamond-shaped aperture.
4. The monolithic apparatus of claim 2 , further comprising a gusset extending from a forward edge of the injector port.
5. The monolithic apparatus of claim 1 , wherein the angle is between thirty and eighty degrees.
6. The monolithic apparatus of claim 1 , wherein an aft, radially inner corner of the combustor liner comprises a chamfer.
7. The monolithic apparatus of claim 1 , further comprising a diffuser disposed at an inlet of the first annular plenum.
8. The monolithic apparatus of claim 1 , further comprising a turbine nozzle disposed at an exit of the annular combustion chamber.
9. The monolithic apparatus of claim 1 , further comprising a second annular plenum disposed between the inner liner and the annular combustion chamber.
10. A turbine engine arrangement, comprising:
a forward housing;
a rotor shaft rotatably mounted to the forward housing;
a compressor wheel operatively coupled to the rotor shaft;
a turbine wheel operatively coupled to the rotor shaft; and
a monolithic combustor, comprising:
an outer casing comprising a forward flange, wherein the forward housing is coupled to the monolithic combustor at the forward flange;
a fuel manifold disposed on the outer casing and defining an annular chamber extending perimetrically around the outer casing;
a combustor liner disposed within the outer casing, the combustor liner defining an annular combustion chamber;
a first annular plenum disposed between the outer casing and the combustor liner, wherein the fuel manifold is disposed radially outward from the first annular plenum;
an inner liner disposed radially from the combustor liner;
a first inner flange extending forward from the combustor liner; and
a second inner flange extending radially inward from the first inner flange; and
an aft wall of the outer casing at least partially defining a flow path for a flow of air around the combustor liner, wherein the aft wall extends from the inner liner at an angle with respect to a centerline axis of the monolithic combustor.
11. The turbine engine arrangement of claim 10 , further comprising an injector port extending into the annular combustion chamber from the combustor liner.
12. The turbine engine arrangement of claim 10 , further comprising a diffuser disposed at an inlet of the first annular plenum, wherein the diffuser receives a flow of air from the compressor wheel.
13. The turbine engine arrangement of claim 10 , further comprising a turbine nozzle disposed at an exit of the annular combustion chamber, wherein the turbine nozzle directs a flow of combustion gas towards the turbine wheel.
14. The turbine engine arrangement of claim 12 , wherein a geometry of the first inner flange is complementary to that of the compressor wheel.
15. The turbine engine arrangement of claim 13 , wherein a geometry of the second inner flange is complementary to that of the turbine wheel.
16. The turbine engine arrangement of claim 10 , further comprising a second annular plenum disposed between the inner liner and the annular combustion chamber.
17. The turbine engine arrangement of claim 10 , wherein the turbine wheel extends at least partially into the inner liner.
18. The turbine engine arrangement of claim 10 , wherein the monolithic combustor is configured to direct a flow of air in a first longitudinal direction through the first annular plenum, in a second longitudinal direction through the annular combustion chamber, and in the first longitudinal direction through the inner liner.
19. The monolithic apparatus of claim 2 , further comprising a fuel injector aligned with the injector port and configured to direct a fuel from the fuel manifold to the injector port.
20. The turbine engine arrangement of claim 11 , further comprising a fuel injector aligned with the injector port and configured to direct a fuel from the fuel manifold to the injector port.