Thrust reverser
View Patent ↗The thrust reverser is used with an aircraft gas turbine engine and includes upper and lower doors pivotable between a stowed position and a deployed position. When deployed, the doors redirect a portion of the efflux to generate a nose-down pitching moment on an aircraft to improve handling during thrust reversing on a runway.
1. A thrust reverser for a nacelle of an aircraft's gas turbine engine, the thrust reverser comprising an upper reverser door and a lower reverser door defining a portion of an aft section of the nacelle, the doors having a respective trailing edge adjacent to a propulsive jet outlet of the nacelle, the doors being pivotable together between respective stowed and a deployed positions, the trailing edge of the upper door being positioned behind the trailing edge of the lower door in the deployed position, the trailing edges of the doors in the deployed position delimiting a rear opening that is generally oriented aft and downwardly relative to the engine, the rear opening communicating in use with a portion of thrust generated by the engine to create a nose-down pitching moment on the aircraft.
2. The thrust reverser as defined in claim 1 , wherein the trailing edges of the doors have a substantially semi-circular shape, the rear opening defined by the trailing edges being substantially crescent-shaped.
3. The thrust reverser as defined in claim 1 , wherein the thrust reverser has a centerline that is collinear with a centerline of the engine.
4. A thrust reverser for a gas turbine engine of an aircraft, the thrust reverser comprising an upper door and a lower door having trailing edges and pivotable between a stowed position and a deployed position, the doors configured and disposed in the deployed position to define a rear opening at said trailing edges to redirect a first portion of an engine thrust forwardly to create a braking force and a second portion of the engine thrust downwardly to create a nose-down pitching moment on the aircraft.
5. The thrust reverser as defined in claim 4 , wherein the trailing edges of the doors have a substantially semi-circular shape, the rear opening defined by the trailing edges being substantially crescent-shaped.
6. The thrust reverser as defined in claim 4 , wherein the thrust reverser has a centerline that is collinear with a centerline of the engine.
7. The thrust reverser as defined in claim 4 , wherein the first portion of the efflux is larger than the second portion of the efflux.
8. The thrust reverser as defined in claim 4 , wherein the efflux comprises core and by-pass flows of the engine.
9. The thrust reverser as defined in claim 4 , wherein the lower door has a trailing edge that goes within the upper door when the thrust reverser is active.
10. The thrust reverser as defined in claim 4 , wherein the nose-down pitching moment M has a magnitude tailored to suit the aircraft.
11. The thrust reverser as defined in claim 10 , wherein the nose-down pitching moment is adjusted by modifying an opening angle of the upper door in the deployed position.
12. The thrust reverser as defined in claim 11 , wherein the nose-down pitching moment is decreased upon decreasing the opening angle of the upper door in the deployed position.
13. The thrust reverser as defined in claim 11 , wherein the nose-down pitching moment is increased upon increasing the opening angle of the upper door in the deployed position.
14. The thrust reverser as defined in claim 4 , wherein the thrust reverser is a retrofit component, the engine having a thrust vector produced by the engine that is substantially similar when the doors are stowed to that of the engine before the thrust reverser was added.
15. The thrust reverser as defined in claim 4 , wherein, when the doors are deployed, the second portion of the engine thrust is significantly smaller than the first portion of the engine thrust.
16. The thrust reverser as defined in claim 4 , wherein the engine is tail-mounted on the aircraft.
17. A method of thrust reversing an aircraft on a runway, the aircraft having at least one gas turbine engine producing an efflux through a jet outlet at a thrust reverser including upper and lower reverser doors, the method comprising the steps of: (a) generating a braking force by deploying said upper and lower doors to redirect a first portion of the efflux; and (b) generating a nose-down pitching moment on the aircraft by deploying said upper door behind said lower door to create a rear opening therebetween oriented downward to redirect a second portion of the efflux at a rear of the engine.
18. The method as defined in claim 17 , wherein steps (a) and (b) are performed at a same time.
19. The method as defined in claim 17 , wherein the first portion of the efflux is redirected toward a front of the aircraft.
20. The method as defined in claim 17 , wherein the second portion of the efflux is redirected toward the rear bottom of the aircraft.
21. The method as defined in claim 17 , wherein the nose-down pitching moment is proportional to the efflux produced by the gas turbine engine.
22. The method as defined in claim 17 , wherein the aircraft has at least two engines.
23. The method as defined in claim 22 , wherein the engines are tail-mounted.