Reverse scissor thrust reverser for a turbine engine

1. A turbine engine system, comprising:

a nacelle including a first portion and a second portion that are arranged along an axis, wherein the second portion of the nacelle moves axially relative to the first portion of the nacelle; and

a thrust reverser including a blocker door and a linkage that links the blocker door to the first portion of the nacelle, wherein the blocker door is located within and pivotally connected to the second portion of the nacelle;

wherein the linkage comprises a strut, a first end of the strut is directly pivotally connected to the first portion of the nacelle, and a second end of the strut is directly pivotally connected to the blocker door; and

wherein a straight-line distance between the first end and the second end is constant as the linkage moves the blocker door.

2. The system of claim 1 , wherein the first portion of the nacelle comprises a forward portion of the nacelle, and the second portion of the nacelle comprises an aft portion of the nacelle.

3. The system of claim 1 , wherein the linkage deploys the blocker door as the second portion of the nacelle moves axially between a stowed position and a deployed position.

4. The system of claim 1 , wherein

the linkage is seated in a slot of the blocker door where the second portion of the nacelle is in a stowed position; and

the linkage extends out from the slot where the second portion of the nacelle is in a deployed position.

5. The system of claim 1 , wherein

the blocker door is seated in a pocket of the second portion of the nacelle where the second portion of the nacelle is in a stowed position; and

the blocker door extends radially inward from the second portion of the nacelle where the second portion of the nacelle is in a deployed position.

6. The system of claim 5 , wherein the blocker door is seated in the pocket where the second portion of the nacelle is in a semi-deployed position.

7. The system of claim 1 , wherein

the blocker door extends between a forward end and an aft end; and

the blocker door is pivotally connected to the second portion of the nacelle at the forward end, and pivotally connected to the linkage at the aft end.

8. The system of claim 1 , wherein

the thrust reverser further includes a cascade of turning vanes;

the second portion of the nacelle covers the cascade in a stowed position and at least partially uncovers the cascade in a deployed position; and

the blocker door directs air through the cascade where the second portion of the nacelle is in the deployed position.

9. The system of claim 1 , wherein the nacelle extends circumferentially at least partially around the axis, and the second portion of the nacelle comprises a sleeve.

10. The system of claim 1 , wherein the blocker door is one of a plurality of blocker doors that are arranged circumferentially around the axis and that are pivotally connected to the second portion of the nacelle.

11. The system of claim 1 , wherein the linkage is one of a plurality of linkages that are arranged circumferentially around the axis and that link the blocker door to the first portion of the nacelle.

12. The system of claim 1 , wherein the blocker door is pivotally connected to the second portion of the nacelle with one or more hinges.

13. A turbine engine system, comprising:

a nacelle extending circumferentially at least partially around an axis, and including a sleeve; and

a thrust reverser including a blocker door and a strut that extends between a first end and a second end, the first end is pivotally connected to and static relative to the blocker door and the second end is pivotally connected to and static relative to a stationary first portion of the nacelle;

wherein the blocker door is pivotally connected to the sleeve, and the strut deploys the blocker door as the sleeve moves axially away from the first portion of the nacelle;

wherein a straight line distance between the first end and the second end is fixed throughout movement of the strut during blocker door deployment.

14. The system of claim 13 , wherein

the blocker door is seated in a pocket of the sleeve where the sleeve is in a stowed position; and

the blocker door extends radially inward from the sleeve where the sleeve is in a deployed position.

15. A turbine engine system, comprising:

a nacelle including a first portion and a second portion that are arranged along an axis, wherein the second portion of the nacelle is configured to move axially relative to the first portion of the nacelle; and

a thrust reverser including a blocker door and a strut, wherein the blocker door is located within and pivotally connected to and static relative to the second portion of the nacelle, wherein the strut extends axially from the first portion of the nacelle to the blocker door, wherein a first end of the strut is pivotally connected to and static relative to the first portion of the nacelle, and

wherein a second end of the strut is pivotally connected to the blocker door;

wherein the strut is configured such that the first end is static relative to the second end.