Cooled fuel injector system for a gas turbine engine

1. A gas turbine engine comprising:

a combustor;

a multiple of fuel injectors in communication with said combustor;

a cooling fluid manifold in communication with each of said multiple of fuel injectors, said cooling fluid manifold comprising an intake plenum and an exhaust plenum separated by a barrier, wherein said intake plenum and said exhaust plenum communicates with said multiple of fuel injectors, wherein said cooling fluid manifold is a circular internal split manifold;

an inlet passage in communication with said cooling fluid manifold;

an inlet scoop to direct a portion of an airflow into said inlet passage; and

an exhaust passage in communication with said cooling fluid manifold for discharging the airflow.

2. The gas turbine engine as recited in claim 1 , further comprising a diffuser case module, said multiple of fuel injectors mounted to said diffuser case module.

3. The gas turbine engine as recited in claim 1 , further comprising a heat exchanger operatively associated with said inlet passage for reducing a temperature of fluid flowing in said inlet passage.

4. The gas turbine engine as recited in claim 1 , wherein said airflow is a bypass airflow.

5. The gas turbine engine as recited in claim 4 , wherein said inlet scoop is located through a core nacelle axially upstream of a throat region between said core nacelle and a fan nacelle.

6. The gas turbine engine as recited in claim 1 , further comprising an inlet passage in communication with said cooling fluid manifold and a compressor section of said gas turbine engine.

7. The gas turbine engine as recited in claim 1 , further comprising an inlet passage in communication with said cooling fluid manifold and a 2.5 bleed compartment.

8. The gas turbine engine as recited in claim 1 , further comprising an exhaust from said exhaust passage located through a core nacelle axially downstream of a throat region between said core nacelle and a fan nacelle.