AIRCRAFT TURBOJET ENGINE NACELLE

Abstract

The present disclosure relates to an aircraft turbojet engine nacelle, the nacelle including a rear section without a lower bifurcation, the rear section including a thrust reversal system, the thrust reversal system including a mobile cowl. The nacelle includes a guide system that translates as one with the mobile cowl, the guide system collaborating with at least one slide that is fixed in relation to the nacelle, the guide system and the slide being arranged near the position referred to as the 6 o'clock position.

Claims

1. An aircraft turbojet engine nacelle comprising: a rear section without a lower bifurcation, wherein the rear section includes a thrust reverser system, the thrust reverser system including a movable cowl; and a guide system translatably secured to the movable cowl, wherein the guide system cooperates with at least one crosshead fixed relative to the nacelle, and wherein the guide system and the crosshead are disposed at a “6 o'clock” position.

2. The nacelle according to claim 1, wherein the crosshead cooperates with the guide system by at least one bearing member, wherein the crosshead is shaped such that a spacing, along a translation direction of the guide system, between farthest bearing points of the crosshead is less than one fifth of a guiding length provided by the guide system.

3. The nacelle according to claim 2, wherein the bearing member is a pad.

4. The nacelle according to claim 1, wherein the crosshead is secured to a peripheral frame that is fastened to at least one of a fan casing of a turbojet engine and a fan casing.

5. The nacelle according to claim 1, wherein the guide system includes a guide rail.

6. The nacelle according to claim 5, wherein the guide rail includes two slides.

7. The nacelle according to claim 6, wherein the crosshead includes at least two guide pads, each of the guide pads cooperating with one of the two slides of the guide rail.

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

9. The nacelle according to claim 8, wherein the thrust reverser cascades are sliding.

10. The nacelle according to claim 9, wherein a front end of the guide system is secured to a front peripheral frame, the front peripheral frame being secured to the thrust reverser cascades.

11. The nacelle according to claim 8, wherein the guide system is disposed between two thrust reverser cascades.

12. The nacelle according to claim 11, wherein the guide system is disposed at a location normally occupied by a solid cascade.

13. The nacelle according to claim 10, wherein the guide system is secured to a front peripheral frame.

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

15. The nacelle according to claim 1, wherein the guide system is extended by a beam secured to the movable cowl.

16. An aircraft propulsion unit, including a bypass turbojet engine, the

1. on unit including a nacelle according to claim 1.

15. An aircraft including at least one propulsion unit in accordance with claim 14, the propulsion unit being supported by a pylon, the pylon including guide rails of the movable cowl of the nacelle.

Description

DRAWINGS

[0037] In order that the disclosure may be well understood, there will now be described various forms thereof, given by way of example, reference being made to the accompanying drawings, in which:

[0038] FIG. 1a is a perspective view of a nacelle in “direct jet” configuration in accordance with the teachings of the present disclosure;

[0039] FIG. 1b is a perspective view of a nacelle in a “reverse jet” configuration in accordance with the teachings of the present disclosure;

[0040] FIG. 2a is a perspective view of a rear section of a nacelle having a thrust reverser system in a retracted position in accordance with the teachings of the present disclosure;

[0041] FIG. 2b is a perspective view of a rear section of a nacelle having a thrust reverser system in a deployed position in accordance with the teachings of the present disclosure;

[0042] FIG. 3a is an enlarged perspective view of the rear section of the nacelle of FIG. 2a in accordance with the teachings of the present disclosure;

[0043] FIG. 3b is an enlarged perspective view of the rear section of the nacelle of FIG. 2b in accordance with the teachings of the present disclosure;

[0044] FIG. 3c is a, enlarged perspective view corresponding to FIG. 3a, without a crosshead and a peripheral frame to which the crosshead is secured in accordance with the teachings of the present disclosure;

[0045] FIG. 4a is a perspective view of a guide system and a crosshead in a position corresponding to a thrust reverser system in a retracted position in accordance with the teachings of the present disclosure;

[0046] FIG. 4b is a perspective view of a guide system and a crosshead in a position corresponding to a thrust reverser system in a deployed position in accordance with the teachings of the present disclosure;

[0047] FIGS. 5a and 5b are partial perspective views of a nacelle rear section having an enlarged guide rail in accordance with the teachings of the present disclosure; and

[0048] FIG. 6 is a partial side view of a nacelle rear section showing a guide system and a crosshead in accordance with the teachings of the present disclosure.

[0049] The drawings described herein are for illustration purposes only and are not intended to limit the scope of the present disclosure in any way.

DETAILED DESCRIPTION

[0050] The following description is merely exemplary in nature and is not intended to limit the present disclosure, application, or uses. It should be understood that throughout the drawings, corresponding reference numerals indicate like or corresponding parts and features.

[0051] FIGS. 1a and 1b show a view of a nacelle 1 in accordance with the present disclosure. Said nacelle includes an air inlet 2, a mid-section 3, as well as a rear section 4. In FIG. 1a, the nacelle 1 is represented alone, while in FIG. 1b, the nacelle 1 may be seen mounted on a pylon 5 (also known under the name of “engine mast”). Moreover, FIG. 1a shows the nacelle in the “direct jet” configuration, that is to say with the thrust reverser system in the retracted position, while FIG. 1b shows the nacelle in the “reverse jet” configuration, that is to say with the thrust reverser system in the deployed position. Thus, it is visible in FIG. 1b that a movable cowl 20 of the rear section 4 is in the backward position, exposing a thrust reverser cascade assembly 22. In the example, the movement of the movable cowl 20 is supported and guided by rails 50 disposed on either side of the pylon 5.

[0052] In the example, the structure of the nacelle is of the “O-duct” type and therefore includes no bifurcation in the lower part of the cold flow path. It should be noted that the present disclosure is also applicable to a nacelle with a C-duct structure.

[0053] FIGS. 2a and 2b represent one part of the rear section of the nacelle of FIGS. 1a and 1b, showing the members of the thrust reverser system respectively in the retracted position and in the deployed position.

[0054] The thrust reverser system comprises a movable cowl 20, in one piece, which forms the outer surface of the rear section of the nacelle. The movable cowl 20 is slidably mounted, in the example via rails 50, secured to the pylon 5 supporting the propulsion unit (namely, the assembly formed by a turbojet engine and the associated nacelle). The thrust reverser system further comprises thrust reverser cascades 22, in the example sliding cascades, and blocking flaps 24 movable in rotation. The thrust reverser system includes actuators (not shown), in particular electromechanical actuators, allowing sliding the movable cowl between the retracted position (FIG. 2a) and the deployed position (FIG. 2b) thereof, and conversely.

[0055] When the thrust reverser system is retracted (FIG. 2a): [0056] the movable cowl 20 is in the retracted position, corresponding to a forward position in which it provides the aerodynamic continuity with the mid-section of the nacelle; [0057] the blocking flaps 24 are in the retracted position, a position in which they are aligned with the inner surface of the movable cowl 20; [0058] the thrust reverser cascades 22 are in the retracted (or forward) position, a position in which they are disposed around the fan casing of the turbojet engine.

[0059] When the thrust reverser system is deployed (FIG. 2b): [0060] the movable cowl is in the deployed position, corresponding to a backward position, in which it uncovers the thrust reverser cascades 22 which are in the backward position thereof; [0061] the blocking flaps 24 are in the deployed position, a position in which they obstruct at least partially the cold flow path; [0062] the thrust reverser cascades 22 are in the deployed (or backward) position, a position in which they are disposed backwards of the fan casing of the turbojet engine, and in which they redirect the cold flow outwardly of the nacelle.

[0063] It should be noted that since the thrust reverser cascades 22 are in the example sliding cascades, said sliding cascades being linked in translation to the movable cowl 20, and the relative position of the thrust reverser cascades 22 relative to the movable cowl 20 may not vary during the deployment or the retraction of the thrust reverser system.

[0064] The thrust reverser cascades 22 are secured to a front peripheral frame 26. Several housings 28 are provided for the actuators of the thrust reverser system. These housings 28, four housings in the example of FIGS. 2a and 2b, are disposed between some of the thrust reverser cascades 22.

[0065] In the “six o'clock” position (or in the vicinity of this position), at the location normally occupied by a cascade called solid cascade, such a solid cascade being provided to limit a redirection of the cold flow downwards, a guide system 30 is disposed. Thus, the guide system 30 is advantageously disposed between two thrust reverser cascades 22, backwards of the front peripheral frame 26 of the cascades 22.

[0066] According to the present disclosure, the guide system 30 is fixed relative to the movable cowl 20 (and therefore, in the example, relative to the thrust reverser cascades 22), being in the example secured to the front peripheral frame 26. The guide system 30 cooperates with a crosshead 32, movable relative to the movable cowl 20 and to the thrust reverser cascades, and therefore relative to the guide system 30. The crosshead 32 is however fixed relative to the non-movable members of the nacelle and of the propulsion unit. In the example, the crosshead 32 is secured to a peripheral frame 34, which is in the example a part secured to the fan casing, known under the name of intermediate casing shroud. Alternatively, the crosshead 32 may be fastened directly to the fan casing. Thus, as visible in FIGS. 2a and 2b, the relative position of the crosshead 32 and of the guide system 30 is related to the position of the movable cowl 20 and therefore of the thrust reverser cascades 22. This relative position has two extremes, corresponding to the retracted and deployed positions of the thrust reverser system. These two extreme positions are more visible in FIGS. 3a (retracted thrust reverser) and 3b (deployed thrust reverser).

[0067] FIGS. 4a and 4b are isolated views of the guide system 30 and of the crosshead 32. The guide system 30 includes a body 300 which has a front part 302, provided to be fastened to the front peripheral frame 26, for example by splicing, and a rear part 304, provided to be fastened to the movable cowl 20, for example by riveting and/or splicing. In the example, the guide system 30 is secured to a peripheral frame 202 (visible in FIG. 3c) of the movable cowl 20. The guide system 30 includes a protruding portion, a guide rail 306. In the example, the guide rail 306 includes two lateral slides 308, 310. In the example of FIGS. 4a and 4b, the guide system 30 constitutes a one-piece part. However, it might be desired to make this member in two or more parts, for example the body 300 and the guide rail 306, for example in order to allow fastening the rail 306 to the body 300 in an adjustable manner (for example in height). Furthermore, these two members might be made of different materials, for example a composite material for the body 300 and a metal material for the rail 306.

[0068] The crosshead 32 includes guide pads 320 (visible in FIG. 5b) cooperating with each of the lateral slides 308, 310. In the example, the crosshead 32 includes four guide pads, disposed on either side of the rail 306, facing each other in pairs. The guide pads are constituted or coated with a material facilitating the sliding, such as for example Teflon. The guide pads 320 may be mounted in rotation on the crosshead 32, or form sliding pads.

[0069] FIG. 5a shows an enlarged guide rail 306, thereby increasing the rigidity of the guide system.

[0070] FIG. 6 shows the guide system and the crosshead 32 seen from the side. In the example, the guiding length R provided by the rail 306 is of 500 mm, while the longitudinal spacing L between the bearing points of the guide pads is of 80 mm. In order to provide a satisfactory lateral strain absorbing while reducing the risk of hyperstatism, it is advantageous to carry out a short guiding. To this end, the ratio between the longitudinal spacing L between the bearing points of the pads and the guide length R is lower than 0.2.

[0071] In a variant not represented, the guide rail might have, at its rear part, an extension extending in the form of a beam secured to the movable cowl 20. Thus, via this extension, the guide system will be fixedly fastened to the movable cover 20 and will participate in the rigidity of said movable cover.

[0072] Although the present disclosure has been described relating to a various forms, it is obvious that it is in no way limited thereto and that it comprises all the technical equivalents of the described means as well as the combinations thereof.

[0073] The description of the disclosure is merely exemplary in nature and, thus, variations that do not depart from the substance of the disclosure are intended to be within the scope of the disclosure. Such variations are not to be regarded as a departure from the spirit and scope of the disclosure.