Rear assembly of an aircraft turbojet engine nacelle comprising a thrust reverser with sliding cascades

Abstract

A nacelle rear assembly of a nacelle of a turbojet engine of an aircraft extends along a longitudinal central axis (A) and includes a sliding cascade thrust reverser. The cascade thrust reverser includes at least one sliding cowl, a deflection cascade including a plurality of rows of vanes that each extend around the longitudinal central axis (A) and that are longitudinally arranged from a first front row of vanes up to a last rear row of vanes, each row of vanes including at least one deflection vane for deflecting the airflow toward the outside of the rear assembly of the nacelle, the deflection cascade being movably integral with the sliding cowl, wherein the deflection cascade includes at least one additional neutral row of vanes that is interposed between the last row of vanes and the sliding cowl and that includes at least one neutral vane.

Claims

1. A nacelle rear assembly of a nacelle of an aircraft turbojet engine, the nacelle rear assembly extending along a longitudinal central axis (A), and the nacelle rear assembly including a thrust reverser with sliding cascades, the nacelle rear assembly comprising: a sliding cowl axially mounted movable in longitudinal translation from front to back, between a closing position in which the sliding cowl provides aerodynamic continuity of the nacelle, and an opening position in which the sliding cowl opens a passage for directing an air flow coming from a cold air flow path of the nacelle; and a cascade of vanes comprising a plurality of blading rows each extending about the longitudinal central axis (A) and arranged longitudinally from a first front blading row to a last rear blading row, each blading row, except the last rear blading row, including at least one deflection blade having a curved shape and defined by a concave front face and a convex rear face to direct the air flow forward and toward an outside of the nacelle rear assembly of the nacelle, the cascade of vanes being secured in displacement to the sliding cowl, wherein the sliding cowl includes a front end and an overhang extending forwardly from the front end, the overhang of the sliding cowl provides aerodynamic continuity with the nacelle when the sliding cowl is in the closing position, the overhang and the front end defining a recessed portion, and wherein the cascade of vanes include at least one neutral blading row interposed between the last rear blading row and the front end of the sliding cowl and including at least one neutral blade disposed in the recessed portion and surrounded by the overhang, the at least one neutral blading row and the last rear blading row jointly delimiting a leakage passage toward the outside of the nacelle rear assembly and a force exerted on the at least one neutral blade by the air flow through the leakage passage is devoid of an axial component oriented backward.

2. The nacelle rear assembly according to claim 1, wherein the leakage passage is adapted to direct the air flow perpendicular to the longitudinal central axis (A) of the nacelle rear assembly.

3. The nacelle rear assembly according to claim 1, wherein the leakage passage is delimited by a first rear face which extends radially and which belongs to the at least one neutral blade and by a second front face which extends radially and which belongs to a blade of the last rear blading row.

4. The nacelle rear assembly according to claim 3, wherein the first rear face is parallel to the second front face.

5. The nacelle rear assembly according to claim 1, wherein the overhang extends longitudinally to radially cap, at least in part, the leakage passage.

6. The nacelle rear assembly according to claim 1, wherein the sliding cowl carries flaps pivotally mounted in the cold air flow path, between a rest position and a thrust reversal position corresponding to the opening position of the sliding cowl, the flaps configured to direct the air flow toward the blading rows, from the first front blading row to the last rear blading row and to limit a flow rate of the air flow passing through the neutral blading row, when the flaps are in the thrust reversal position.

7. A nacelle of an aircraft turbojet engine including a nacelle rear assembly according to claim 1.

8. The nacelle rear assembly according to claim 1, wherein the overhang includes a front end that is disposed upstream from the at least one neutral blading row.

9. The nacelle rear assembly according to claim 1, wherein the overhang includes a front end that is disposed upstream from the leakage passage.

10. The nacelle rear assembly according to claim 1, wherein the air flow through the leakage passage is first directed upstream toward a front end of the overhang and then outside the sliding cowl.

11. The nacelle rear assembly according to claim 1, wherein the plurality of blading rows and the at least one neutral blading row are disposed radially and inwardly from the overhang.

12. The nacelle rear assembly according to claim 1, wherein the overhang has a front end that is disposed upstream from the leakage passage defined between the last rear blading row and the at least one neutral blading row.

13. The nacelle rear assembly according to claim 1, wherein the sliding cowl further includes a flap, when the sliding cowl is in the closing position, the flap abuts against a deflection edge of a fan casing to inhibit the air flow coming from the cold air flow path from entering a cavity that houses the cascade of vanes.

14. The nacelle rear assembly according to claim 13, wherein when the sliding cowl is in a substantially retracted position, a gap is defined between the flap and the deflection edge and the air flow coming from the cold air flow path flows through the gap between the flap and the deflection edge, and then through the leakage passage toward the outside of the nacelle rear assembly.

Description

DRAWINGS

(1) 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:

(2) FIG. 1 is a schematic longitudinal sectional view illustrating a cascade vane of a thrust reverser, according to the prior art;

(3) FIG. 2 is an overall schematic view illustrating a turbojet engine nacelle comprising a rear assembly of a nacelle equipped with a thrust reverser which comprises a substantially retracted sliding cowl, according to the present disclosure;

(4) FIG. 3 is a detailed perspective view illustrating a clearance for the passage of an air leakage through the cascades of the thrust reverser of FIG. 2;

(5) FIG. 4 is a longitudinal cross-sectional view illustrating the sliding cowl in the direct jet position, and a cascade vane with neutral blading, according to the present disclosure;

(6) FIG. 5 is a longitudinal cross-sectional view illustrating the sliding cowl of FIG. 4 in the substantially retracted position; and

(7) FIG. 6 is a longitudinal cross-sectional view illustrating the sliding cowl of FIG. 4 in the thrust reversal position.

(8) 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

(9) 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.

(10) In the description and the claims, the longitudinal, vertical and transverse terminology will be adopted without limitation, with reference to the trihedron L, V, T indicated in the figures, whose axis L is parallel to the central axis A of the nacelle.

(11) The terms “axial” and “radial” will also be used with reference to the longitudinal central axis (A) of the nacelle, the term “radial” designating a direction perpendicular to the central axis A of the nacelle.

(12) In all these figures, identical or analogous references represent identical or analogous organs or sets of organs.

(13) Note that in the present patent application, the terms “upstream” and “downstream” must be understood relative to the circulation of the air flow inside the propulsion unit formed by the nacelle and the turbojet engine, that is to say from the left toward the right in FIG. 2.

(14) In the present application, the terms “upper,” “lower” and their derivatives refer to the position or the orientation of an element or of a component, this position or this orientation being considered when the nacelle is in configuration of service on an aircraft on the ground.

(15) FIG. 2 represents a nacelle 10 of a turbojet engine which has a substantially tubular structure about a longitudinal central axis (A).

(16) The nacelle 10 comprises an air inlet 12 upstream from the turbojet engine 14, a median section 16 intended to surround a fan of the turbojet engine, a nacelle rear assembly 18 intended to surround the combustion chamber of the turbojet engine 14, the nacelle 10 being terminated by an ejection nozzle 20, whose outlet is located downstream of the turbojet engine 14.

(17) The median section 16 includes an outer fan cowl 24 and a fan casing 26 which delimits a deflection edge 27 visible in FIGS. 4 to 6.

(18) The nacelle rear assembly 18 of the nacelle 10 includes a thrust reverser 22 which supports cascade vanes 28.

(19) The thrust reverser 22 includes a sliding thrust reversal cowl 30 which has a generally cylindrical shape about the axis A of the nacelle 10.

(20) As can be seen in FIG. 6, the sliding cowl 30 comprises an outer cowl 32, and an inner wall 34 which delimits a cold air flow path 36 with an inner structure 38 which surrounds the turbojet engine 14.

(21) The sliding thrust reversal cowl 30 is axially mounted movable in longitudinal translation from front to back, between a closing position illustrated in FIGS. 2 and 4, in which the sliding cowl 30 provides aerodynamic continuity of the nacelle 10, and an opening position illustrated in FIG. 6, in which the sliding cowl 30 opens a passage 40 for the redirection of an air flow coming from the cold air flow path 36 of the nacelle 10.

(22) To this end, as can be seen in FIG. 2, the thrust reverser 22 comprises cylinders 42, which are designed to drive the assembly formed by the cascades 28 and the sliding thrust reversal cowl 30 in sliding between its opening position and its closing position.

(23) Also, the cascades 28 are secured to a rear frame 44 which is connected to the sliding cowl 30, so that the cascades 28 are slidably driven with the sliding cowl 30 by the cylinders 42.

(24) The sliding cowl 30 carries flaps 46 which are pivotally mounted in the cold air flow path 36, between a rest position illustrated in FIGS. 4 and 5, which corresponds to the direct jet closing position of the sliding cowl 30, and a thrust reversal position illustrated in FIG. 6, which corresponds to the thrust reversal opening position of the sliding cowl 30, in which the flaps 46 direct the air flow toward the cascades 28 as illustrated by the arrows in FIG. 6.

(25) With reference to FIG. 4, it will be noted that when the sliding cowl 30 occupies its closing position, the cascades 28 are housed in a cavity 48 which is delimited radially by the outer fan cowl 24 and the fan casing 26.

(26) In addition, a front portion 50 of the sliding cowl 30 is in longitudinal bearing on the deflection edge 27 of the fan casing 26 via a seal 52, to inhibit the air flowing in the cold air flow path 36 to enter the cavity 48 which houses the cascade vanes 28.

(27) The cascade vanes 28 each comprise a plurality of blading rows 54 which each extend in a circular manner about the central axis A and which are arranged longitudinally in a regular manner from a first front blading row 54a to a last rear blading row 54b.

(28) Each blading row 54 includes a plurality of blades 56 which are each adapted to divert the air flow coming from the cold air flow path 36 forward, outside the nacelle 10, so as to exert a counter-thrust.

(29) As can be seen in FIG. 4, the blades 56 of the blading rows 54 have a curved shape and are each delimited by a concave front face 58 and by a convex rear face 60, to direct the air flow forward.

(30) In accordance with the present disclosure, the cascade 28 includes an additional neutral blading row 62 which is interposed longitudinally between the last blading row 54b and the sliding cowl 30.

(31) The neutral blading row 62 extends circularly about the central axis A and it includes a plurality of neutral blades 64.

(32) In addition, the neutral blading row 62 delimits a leakage passage 66 toward the outside of the nacelle rear assembly 18 of the nacelle 10, the leakage passage 66 being designed so that the force exerted on each neutral blade 64 by the leakage air through the leakage passage 66 is devoid of an axial component oriented backward.

(33) According to the form of the present disclosure described here, the leakage passage 66 is adapted to radially orient the leakage air, that is to say perpendicular to the central axis A of the nacelle rear assembly 18 of the nacelle 10.

(34) To this end, the leakage passage 66 is delimited by a first rear face 68 which extends radially and which belongs to the neutral blade 64 and by a second front face 70 which extends radially and which belongs to the blade 56 of the last blading row 54b.

(35) Thus, when the sliding cowl 30 adopts a substantially retracted position illustrated in FIGS. 3 and 5, for example in the case of non-functioning of the holding locks for holding the sliding cowl 30 in the closed position, a leakage air flow flows from the fresh air flow path 36, by passing successively between the deflection edge 27 and the front portion 50 of the sliding cowl 30, then through the leakage passage 66. In this configuration, the leakage air flow does not exert axial force backward due to its strictly radial orientation.

(36) According to another aspect of the present disclosure illustrated in FIG. 5, the sliding cowl 30 includes a front overhang 72 which extends longitudinally so as to radially cap the leakage passage 66 and the neutral blade 64.

(37) The front overhang 72 is arranged opposite a rear end edge 74 of the fan cowl 24, so as to provide aerodynamic continuity of the nacelle 10 in the closed sliding cowl 30 configuration.

(38) The description of the present disclosure is given by way of non-limiting example.

(39) It will be understood in particular that the leakage passage 66 can be adapted to orient the leakage air substantially backward, the leakage passage 66 then being designed so that the force exerted on each neutral blade 64 by the leakage air through the leakage passage 66 has an axial component oriented forward which tends to close the sliding cowl 30.

(40) In this type of configuration in which the leakage passage 66 directs the leakage air substantially backward, the flaps 46 are designed to direct the air flow toward the blading rows 54 which redirect the air flow forward, to limit the flow rate of the air flow passing through the neutral blading row 62, when the flaps 46 are in thrust reversal position, as can be seen in FIG. 6.

(41) To this end, the leading edge of each flap 46, which is arranged in the vicinity of the pivot point of the associated flap 46, is arranged substantially at the level of the last blading row 54b in a longitudinal direction.

(42) Unless otherwise expressly indicated herein, all numerical values indicating mechanical/thermal properties, compositional percentages, dimensions and/or tolerances, or other characteristics are to be understood as modified by the word “about” or “approximately” in describing the scope of the present disclosure. This modification is desired for various reasons including industrial practice, material, manufacturing, and assembly tolerances, and testing capability.

(43) As used herein, the phrase at least one of A, B, and C should be construed to mean a logical (A OR B OR C), using a non-exclusive logical OR, and should not be construed to mean “at least one of A, at least one of B, and at least one of C.”

(44) 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.