Claims
- 1. A method for assembling a combustor for a gas turbine engine, the combustor including a liner including at least one trapped vortex, said method comprising the steps of:assembling a spray bar assembly to include a heat shield having an upstream side, a downstream side, and a pair of sidewalls extending therebetween, wherein the upstream and downstream sides are aerodynamically-shaped; and securing the spray bar assembly to the combustor such that the spray bar assembly is configured to supply fuel to the at least one trapped vortex.
- 2. A method in accordance with claim 1 wherein said step of assembling a spray bar assembly further comprises the steps of:inserting a spray bar that includes at least two fuel circuits and a plurality of injector fuel tips into the cavity defined within the heat shield; and attaching at least two caps to the spray bar.
- 3. A method in accordance with claim 2 wherein the two fuel circuits include a pilot fuel circuit and a main fuel circuit, said step of inserting a spray bar further comprising the step of attaching pilot tip heat shields to the pilot fuel circuit injector fuel tips.
- 4. A method in accordance with claim 2 further comprising the step of attaching a plurality of injector tubes around the heat shield.
- 5. A method in accordance with claim 2 wherein said step of securing the spray bar assembly further comprises the step of securing the spray bar assembly to ferrules extending from the combustor.
- 6. A method in accordance with claim 2 wherein said step of securing the spray bar assembly further comprises the step of securing the spray bar assembly caps to ferrules that permit the combustor to thermally expand relative to the spray bar assembly.
- 7. A combustor for a gas turbine comprising a fuel spray bar assembly configured to supply fuel to said combustor, said fuel spray bar assembly comprising a spray bar and a heat shield, said spray bar comprising a plurality of injectors, said heat shield comprising an upstream side, a downstream side, and a pair of sidewalls extending therebetween, said upstream side and said downstream side aerodynamically-shaped, said combustor further comprising a combustor liner comprising at least one trapped vortex cavity; said at least one trapped vortex cavity downstream from said fuel spray bar assembly.
- 8. A combustor in accordance with claim 7 wherein said fuel spray bar assembly heat shield upstream side, said downstream side, and said sidewalls connected to define a cavity sized to receive said spray bar, said spray bar further comprising a plurality of fuel circuits, at least one of said plurality of fuel circuits configured to supply fuel to said at least one trapped vortex cavity.
- 9. A combustor in accordance with claim 7 wherein said fuel spray bar assembly heat shield further comprises a cavity and a ring step, said cavity sized to receive said spray bar and defined by said heat shield sidewalls and said upstream and downstream sides, said ring step between said spray bar and said heat shield.
- 10. A combustor in accordance with claim 9 wherein said ring step configured to prevent fuel leakage into said spray bar cavity.
- 11. A combustor in accordance with claim 7 further comprising a plurality of ferrules configured to secure said fuel spray bar assembly to said combustor.
- 12. A combustor in accordance with claim 11 wherein said fuel spray bar assembly further comprises a plurality of injector tubes radially outward from said heat shield, said ferrules configured to permit said combustor to thermally expand relative to said fuel spray bar assembly.
Parent Case Info
This application is divisional of U.S. application Ser. No. 09/604,985, filed Jun. 28, 2000, now U.S. Pat. No. 6,540,162 which is hereby incorporated by reference
US Referenced Citations (6)