Geared annular airflow actuation system for variable cycle gas turbine engines
An annular airflow control system for a gas turbine engine includes a sync ring rotatable to move the multiple of contra-rotatable variable vanes through a respective multiple of geared interfaces to throttle an airflow through the multiple of contra-rotatable variable vanes.
1. An annular airflow control system for a gas turbine engine comprising:
a multiple of contra-rotatable variable vanes; and
a sync ring engaged with said multiple of contra-rotatable variable vanes through a respective multiple of geared interfaces to throttle an airflow through said multiple of contra-rotatable variable vanes,
wherein said sync ring defines a multiple of first gear rack segments and a multiple of second gear rack segments,
wherein said multiple of first gear rack segments are axially opposed and circumferentially alternate with respect to said multiple of second gear rack segments.
2. The system as recited in claim 1 , wherein said multiple of contra-rotatable variable vanes are located between an outer ring and an inner ring.
3. The system as recited in claim 2 , wherein said sync ring is located radially outboard of said outer ring.
4. The system as recited in claim 3 , further comprising an actuator to rotate said sync ring.
5. The system as recited in claim 2 , wherein each of said multiple of contra-rotatable variable vanes includes a gear mounted to a pivot post.
6. The system as recited in claim 2 , wherein each of said multiple of contra-rotatable variable vanes includes a segment gear mounted to a pivot post.
7. The system as recited in claim 6 , wherein each of said segment gears is in meshed engagement with one of said multiple of first gear rack segments or said multiple of second gear rack segments of said sync ring.
8. The system as recited in claim 7 , wherein each of said segment gears alternatively extend toward either a leading edge or a trailing edge of each of said multiple of contra-rotatable variable vanes.
9. The system as recited in claim 8 , wherein each of said multiple of first gear rack segments of said sync ring are defined around a central longitudinal engine axis.
10. The system as recited in claim 1 , wherein said airflow is located in a third stream airflow path, where said third stream airflow path is located radially outward of a second stream airflow path defined by the gas turbine engine, and wherein said second stream airflow path is located radially outward of a primary airflow path defined by the gas turbine engine.
11. The system as recited in claim 10 , wherein said primary airflow path exhausts through a convergent divergent nozzle.
12. The system as recited in claim 1 , wherein said multiple of first gear rack segments are directed engine forward and said multiple of second gear rack segments are directed engine aft.
13. The system as recited in claim 1 , wherein said gas turbine engine is defined along a central longitudinal engine axis, and wherein said multiple of contra-rotatable variable vanes are located in a common axial plane with respect to said central longitudinal engine axis.
14. A method of operating a gas turbine engine comprising:
throttling an annular airflow path with a sync ring and a multiple of contra-rotatable variable vane pairs,
wherein said sync ring defines a multiple of first gear rack segments and a multiple of second gear rack segments,
wherein, said multiple of first gear rack segments are axially opposed and circumferentially alternate with respect to said multiple of second gear rack segments.
15. The method as recited in claim 14 , further comprising rotating said sync ring to rotate each of the multiple of contra-rotatable variable vanes.
16. The method as recited in claim 15 , further comprising rotating a segment gear that extends from each of the multiple of contra-rotatable variable vanes with one of said multiple of first gear rack segments or said multiple of second gear rack segments.
17. The method as recited in claim 14 , wherein each of the multiple of contra-rotatable variable vane pairs includes a first contra-rotatable variable vane and a second contra-rotatable variable vane that contra-rotate with respect to each other.
18. The method as recited in claim 17 , wherein a leading edge of the first contra-rotatable variable vane contra-rotates toward a leading edge of the second contra-rotatable variable vane to define a closed position.
19. The method as recited in claim 14 , wherein said gas turbine engine is defined along a central longitudinal engine axis, and wherein said multiple of contra-rotatable variable vane pairs are located in a common axial plane with respect to said central longitudinal engine axis.
20. The method as recited in claim 14 , wherein said gas turbine engine is defined along a central longitudinal engine axis, and wherein said throttling of an annular airflow path includes throttling an airflow in said annular airflow path in an axial direction with respect to said central longitudinal axis.