Integrated thrust reverser actuation system

1. A turbofan engine comprising:

a turbine engine;

a nacelle surrounding at least a portion of the turbine engine and defining an annular bypass duct between the nacelle and the turbine engine defining a forward-to-aft bypass air flow path;

a thrust reverser having at least one movable control surface, movable to and from a reversing position, where at least a portion of a bypass air flow is at least partially reversed, wherein the at least one movable control surface is a slidable portion of an inner cowling of the nacelle capable of an axial motion with respect to a forward portion of the nacelle, and in the reversing position limits an annular bypass area between the at least one movable control surface and the turbine engine;

a thrust reverser actuation system having at least one actuator operably coupled to the at least one movable control surface to move the at least one movable control surface into and out of the reversing position; and

a guide comprising a rail having a guiding portion including three planar surfaces lying in three distinct, non-parallel, intersecting planes, wherein the three distinct, non-parallel, intersecting planes are distinct from one another and are perpendicular to a common cross section plane and wherein each plane of the three distinct, non-parallel, intersecting planes intersects the other two planes, and a bogie having three bearing surfaces coupled to the rail at the three planar surfaces for relative translational movement between the rail and the bogie;

wherein one of the rail and the bogie is mounted to the turbine engine and other of the rail and the bogie is mounted to the at least one movable control surface such that an operation of the at least one actuator moves the at least one movable control surface by translation movement between the rail and the bogie; and

wherein the three bearing surfaces each comprise a rotatable bearing surface, each rotatable bearing surface in contact with and arranged to provide opposing bearing forces to a corresponding one of the three planar surfaces to prevent separation of the rail and the bogie during translational movement between the rail and the bogie.

2. The turbofan engine of claim 1 , wherein the nacelle comprises a cowling portion defining the at least one movable control surface.

3. The turbofan engine of claim 2 , wherein the rail is provided on the cowling portion and the bogie is provided on an engine mount.

4. The turbofan engine of claim 3 , wherein the bogie is fixedly mounted to the engine mount.

5. The turbofan engine of claim 4 , further comprising an engine pylon forming the engine mount.

6. The turbofan engine of claim 1 , further comprising an engine pylon and one of the rail and the bogie is mounted to the engine pylon and other of the rail and the bogie is mounted to the at least one movable control surface.

7. The turbofan engine of claim 6 , wherein the bogie is fixedly mounted to the engine pylon.

8. The turbofan engine of claim 1 , wherein in the reversing position, the at least one movable control surface exposes a thrust reverser cascade, between the at least one movable control surface and the forward portion of the nacelle, to at least the portion of the bypass air flow.

9. A thrust reverser comprising:

at least one movable, control surface that includes a slidable portion of an inner cowling of a nacelle, movable to and from a reversing position with respect to a forward portion of the nacelle, wherein the nacelle surrounds at least a portion of a turbine engine and defines an annular bypass duct between the nacelle and the turbine engine defining a forward-to-aft bypass air flow path;

a thrust reverser actuation system having at least one actuator operably coupled to the at least one movable control surface to move the at least one movable control surface into and out of the reversing position; and

a guide that includes a rail having a guiding portion including three planar surfaces lying in three distinct, non-parallel, intersecting planes, wherein the three distinct, non-parallel, intersecting planes are distinct from one another and are perpendicular to a common cross section plane and wherein each plane of the three distinct, non-parallel, intersecting planes intersects the other two planes, and a bogie having three rotatable bearing surfaces coupled to the rail at the three planar surfaces for relative translational movement between the rail and the bogie;

wherein one of the rail and the bogie is mounted to the turbine engine and the other of the rail and the bogie is mounted to the at least one movable control surface such that operation of the at least one actuator moves the at least one movable control surface by translation movement between the rail and the bogie, and in the reversing position, the at least one movable control surface limits an annular bypass area of the annular bypass duct formed between the at least one movable control surface and the turbine engine; and

wherein the three bearing surfaces each comprise a rotatable bearing surface, each rotatable bearing surface in contact with and arranged to provide opposing bearing forces to a corresponding one of the three planar surfaces to prevent separation of the rail and the bogie during translational movement between the rail and the bogie.

10. The thrust reverser of claim 9 , wherein in the reversing position, at least a portion of a bypass air flow is at least partially reversed.

11. The thrust reverser of claim 10 , wherein in the reversing position, the at least one movable control surface exposes a thrust reverser cascade, between the at least one movable control surface and the forward portion of the nacelle, to at least the portion of the bypass airflow.