Thrust reverser assembly and method of operating

1. A thrust reverser assembly for a turbine engine including a core engine, a nacelle surrounding at least a portion of the core engine to at least partially define a bypass duct between the nacelle and the core engine, including:

a translating cowl moveable between a first position and a second position;

a fixed cascade element located within the translating cowl when the translating cowl is in the first position;

a blocker door having a leading edge and a trailing edge that is operably coupled to the translating cowl and where the blocker door is movable between a stowed position wherein the blocker door forms a portion of the bypass duct and a deployed position, where the blocker door extends into a bypass duct conduit to deflect an airflow through the cascade element;

a biasing element operably coupled to the blocker door and configured to push the blocker door from the stowed position into an initial position wherein the blocker door is partially within the bypass duct conduit and the leading edge forms a gap with a portion of the thrust reverser assembly through which the airflow enters the gap;

a spring-damper assembly operably coupled to the blocker door and wherein the spring-damper assembly is configured to moderate a speed of the blocker door as the blocker door moves to the deployed position; and

a second spring-damper assembly operably coupled to the translating cowl and wherein the spring-damper assembly is configured to bias the translating cowl to the first position.

2. The thrust reverser assembly of claim 1 , further comprising a latch assembly operable between a latch position, where the blocker door is held in the stowed position, and a release position, where the blocker door may be pivoted to the deployed position.

3. The thrust reverser assembly of claim 2 , wherein the latch assembly includes

a latch keep carried by one of the blocker door and a portion of the thrust reverser assembly and having a strike seat in which a strike may be removably received, and

a latch carried by the other of the blocker door and the portion of the thrust reverser assembly and having a catch configured to engage the strike.

4. The thrust reverser assembly of claim 2 , further comprising a Full Authority Digital Engine/Electronics Control configured to control a movement of the latch assembly to the release position.

5. The thrust reverser assembly of claim 1 wherein the spring-damper assembly further includes a biasing element that is configured to move the blocker door to the stowed position when the airflow through the bypass duct is stopped.

6. The thrust reverser assembly of claim 5 wherein the biasing element is further configured to move the blocker door towards the stowed position when the airflow through the bypass duct reduces with a slowing speed of an aircraft.

7. The thrust reverser assembly of claim 1 , wherein the blocker door is configured to create a scooping effect that moves the blocker door to the deployed position and moves the translating cowl to the second position.

8. A method of operating an aircraft engine, comprising: the aircraft engine comprising: a thrust reverser assembly for the aircraft engine including a core engine, a nacelle surrounding at least a portion of the core engine to at least partially define a bypass duct between the nacelle and the core engine, including: a translating cowl moveable between a first position and a second position; a fixed cascade element located within the translating cowl when the translating cowl is in the first position; a blocker door having a leading edge and a trailing edge that is operably coupled to the translating cowl and where the blocker door is movable between a stowed position wherein the blocker door forms a portion of the bypass duct and a deployed position, where the blocker door extends into a bypass duct conduit to deflect an airflow through the cascade element; a biasing element operably coupled to the blocker door and configured to push the blocker door from the stowed position into an initial position wherein the blocker door is partially within the bypass duct conduit and the leading edge forms a gap with a portion of the thrust reverser assembly through which the airflow enters the gap; a spring-damper assembly operably coupled to the blocker door and wherein the spring-damper assembly is configured to moderate a speed of the blocker door as the blocker door moves to the deployed position; and a second spring-damper assembly operably coupled to the translating cowl and wherein the spring-damper assembly is configured to bias the translating cowl to the first position, the method comprising generating a fore-to-aft airflow through the bypass duct of the aircraft engine; and deploying the blocker door from the stowed position to the initial position where the blocker door is partially within the bypass duct such that the leading edge of the blocker door forms the gap with the portion of the thrust reverser assembly, and moving the blocker door to the deployed position when the airflow passes through the gap to interact with the blocker door such that the blocker door is moved to the deployed position.

9. The method of claim 8 wherein the deploying the blocker door to the initial position comprises unlatching the leading edge of the blocker door.

10. The method of claim 8 wherein the deploying the blacker door to the initial position comprises biasing the leading edge of the blocker door to the initial position.

11. The method of claim 8 , further comprising applying hydraulic pressure to provide a damping force to suppress the speed of the blocker door moving to the deployed position.

12. The method of claim 8 , wherein the translating cowl is simultaneously moved with the blocker door from the first position to the second position based on the airflow.

13. The method of claim 12 , further comprising redirecting, via the blocker door in the deployed position, the airflow to exit through the cascade element that is located within the translating cowl when the translating cowl is in the first position.