AIRCRAFT TURBOJET ENGINE NACELLE, PROPULSION UNIT AND AIRCRAFT INCLUDING SUCH A NACELLE

• US 20190316545A1
• Filed: 05/24/2019
• Published: 10/17/2019
• Est. Priority Date: 11/30/2016
• Status: Active Grant

• Current Assignee: Safran Nacelles
• Original Assignee: Safran Nacelles
• Inventors: HEAU, Alexis, VALLEROY, Laurent Georges, LANSONNEUR, Goulwen
• Granted Patent: US 11,624,339 B2
• Time in Patent Office: Days
• CPC Class Codes: B64D 29/06 Attaching of nacelles, fairings or cowlings
• CPC Class Codes: F02K 1/72 the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An aircraft turbojet engine nacelle includes a rear section without a lower bifurcation, the rear section including a thrust reverser system, and the thrust reverser system including a movable cowl. The nacelle includes a guide system including a movable portion and a fixed portion, the movable portion being secured in translation to the movable cowl and cooperating with the fixed portion and the fixed portion being fixed relative to the nacelle. The guide system is disposed proximate to a position called the “6 O'"'"'clock” position. In one form, the length of the fixed portion of the guide system is larger than or equal to 50% of the length of the movable portion.

Claims

1. An aircraft turbojet engine nacelle comprising:

a rear section without a lower bifurcation, the rear section including a thrust reverser system having a movable cowl; and

a guide system including a movable portion and a fixed portion, the movable portion being secured in translation to the movable cowl and cooperating with the fixed portion, the fixed portion being fixed relative to the nacelle, the guide system being disposed proximate to a 6 O'"'"'clock position,

wherein a length of the fixed portion of the guide system is larger than or equal to 50% of a length of the movable portion.

2. The nacelle according to claim 1, wherein the length of the fixed portion of the guide system is larger than or equal to 80% of the length of the movable portion.

3. The nacelle according to claim 1, wherein the fixed portion forms a rail cooperating with the movable portion, the movable portion forming a guideway and including a cavity adapted to receive the fixed portion.

4. The nacelle according to claim 1, wherein the fixed portion is secured to a peripheral frame fastened to a fan casing of a turbojet engine, or directly fastened to the fan casing.

5. The nacelle according to claim 4, wherein the fixed portion includes at least two fastening points.

6. The nacelle according to claim 1, wherein the thrust reverser system includes thrust reverser cascades.

7. The nacelle according to claim 6, wherein the thrust reverser cascades are sliding-type, and a front end of the movable portion is secured to a front peripheral frame secured to the thrust reverser cascades.

8. The nacelle according to claim 6, wherein the movable portion is disposed between two thrust reverser cascades.

9. The nacelle according to claim 8, wherein the movable portion is disposed at a location occupied by a solid cascade.

10. The nacelle according to claim 7, wherein the movable portion is secured to the front peripheral frame.

11. The nacelle according to claim 1, wherein a rear end of the movable portion is secured to a peripheral frame of the movable cowl.

12. The nacelle according to claim 1, wherein the movable portion is extended by a beam secured to the movable cowl.

13. An aircraft propulsion unit including a bypass turbojet engine, the propulsion unit comprising a nacelle according to claim 1.

14. The propulsion unit according to claim 13, wherein the fixed portion of the guide system is fastened to a fan casing.

15. An aircraft including at least one propulsion unit according to claim 13, the propulsion unit being supported by a mast, the aircraft including guide rails for guiding the movable cowl of the nacelle, the guide rails being fastened on the mast or on a structure secured to at least one of the mast and the turbojet engine.