THRUST REVERSER AT THE DOOR OF A NACELLE OF A TURBOJET ENGINE OF AN AIRCRAFT WITH A SYSTEM FOR DIVERTING FLUIDS TO THE EXTERIOR

Abstract

A thrust reverser of a nacelle of a turbojet engine of an aircraft extending about a longitudinal axis and including a fixed structure and at least one door which is rotatable between a closed position and an open position and including a downstream frame spaced axially from a downstream end edge of the door by an axial clearance parallel to the longitudinal axis. The thrust reverser includes a system for diverting fluids to the exterior including at least one projection fixed onto the door or the other fixed structure and extending into the axial clearance and towards one of the fixed structure or the door, while leaving an axial gap between a free end of said projection and one of the fixed structure or the door.

Claims

1. A thrust reverser of a nacelle of a turbojet engine of an aircraft extending about a longitudinal axis, comprising: a fixed structure and at least one door rotatable between a closed position in which said door provides aerodynamic continuity with the fixed structure for the circulation of an air flow and an open position in which the circulating air flow is diverted to the exterior and upstream of the thrust reverser, the fixed structure comprising a downstream frame comprising an upstream end spaced axially from a downstream end edge of the door by an axial clearance parallel to the longitudinal axis; at least one fluid diverter system for diverting fluids to the exterior of the thrust reverser associated with the door, wherein the fluid diverter system comprises at least one deflector group comprising at least one projection fixed onto one of the door or the fixed structure and extending locally from one of downstream end edge of the door or the upstream end of the downstream frame in the axial clearance and towards one of the upstream end of the downstream frame or the downstream end edge of the door, while leaving an axial gap between a free end of said projection and one of the upstream end of the downstream frame of the fixed structure or the downstream end edge of the door.

2. The thrust reverser according to claim 1, wherein the at least one projection includes at least one first projection fixed to the downstream end edge of the door and extending locally into the axial clearance and towards the upstream end of the downstream frame of the fixed structure and at least one second projection fixed to the upstream end of the downstream frame of the fixed structure and extending locally into the axial clearance and towards the downstream end edge of the door.

3. The thrust reverser according to claim 2, wherein the at least one first projection and the at least one second projection are in local direct radial and/or circumferential contact with one another.

4. The thrust reverser according to claim 3, wherein one of the at least one first projection or at least one the second projection is made from an elastic material capable of being deformed elastically on application of external stress and being restored to its initial form once the external stress has stopped.

5. The thrust reverser according to claim 4, wherein one of the at least one first projection or at least one the second projection is a seal made from a material that is more flexible than the other one of the at least one second projection or the at least one first projection.

6. The thrust reverser according to claim 2, wherein the at least one first projection and the at least one second projection are spaced apart circumferentially from one another by a circumferential clearance.

7. The thrust reverser according to claim 6, wherein the at least one first projection comprises an attachment portion fixed to the downstream end edge of the door and a diverting portion extending from an outer surface of the attachment portion to the exterior.

8. The thrust reverser according to claim 6, wherein the at least one second projection comprises an attachment portion fixed to the upstream end of the downstream frame of the fixed structure and a diverting portion extending from an outer surface of the attachment portion to the exterior.

9. The thrust reverser according to claim 2, wherein the number of first projections is greater than or equal to two and a number of second projections is greater than or equal to two, the number of first projections being different from the number of second projections.

10. The thrust reverser according to claim 1, wherein the at least one deflector group of the fluid diverter system comprises at least two deflector groups circumferentially spaced apart from each other.

11. The thrust reverser according to claim 2 wherein the at least one fluid diverter system includes a first fluid diverter system comprising at least one first deflector group comprising the first projection and the second projection spaced apart circumferentially from the first projection by a circumferential clearance and a second fluid diverter system comprising at least one second deflector group comprising the first projection and the second projection in local direct radial and/or circumferential contact with the first projection.

12. A nacelle of a turbojet engine of an aircraft comprising a thrust reverser with a door according to claim 1.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0060] Further aims, features and advantages of the invention will become apparent from reading the following description, given solely by way of a non-limiting example, with reference to the accompanying drawings in which:

[0061] Further aims, features and advantages of the invention will become apparent from reading the following description, given solely by way of a non-limiting example, with reference to the accompanying drawings in which:

[0062] FIG. 1 is a schematic view of a nacelle for a turbojet engine of an aircraft comprising a thrust reverser with a door in a closed position according to the prior art;

[0063] FIG. 1A is a detailed view of FIG. 1, in which the thrust reverser with a door is in an open position;

[0064] FIG. 2 is a detailed cross-sectional view of the nacelle of FIG. 1;

[0065] FIG. 2A is a detailed view of FIG. 2;

[0066] FIG. 3 is a schematic view of a thrust reverser with a door of a nacelle of a turbojet engine of an aircraft according to the invention;

[0067] FIG. 4 FIG. 5 FIG. 6 are detailed views of a fluid diverter system of the thrust reverser of FIG. 3 according to one embodiment of the invention;

[0068] FIG. 7 and FIG. 8 are detailed views of a fluid diverter system of the thrust reverser of FIG. 3 according to another embodiment of the invention.

DETAILED DESCRIPTION OF AT LEAST ONE EMBODIMENT

[0069] In the following description, the terms “upstream” and “downstream” are defined with respect to the direction of airflow in the turbomachine.

[0070] The terms “axial” and “radial” are defined relative to a longitudinal extension axis A of the thrust reverser 10.

[0071] FIG. 3 shows very schematically a thrust reverser 10 with a door of a nacelle of a turbojet engine of an aircraft (not shown).

[0072] The thrust reverser 10 extends along a longitudinal axis A corresponding to a longitudinal axis of the nacelle (not shown). The thrust reverser 10 corresponds to the downstream section of the nacelle.

[0073] The thrust reverser 10 comprises a fixed structure 12 and a door 14 which is rotatable about an axis transverse to the longitudinal axis, between a closed position, shown in FIG. 3, in which it provides aerodynamic continuity with the fixed structure 12 of the reverser and with the nacelle and an open position (not shown), in which the door 14 allows the air flow to be diverted to the exterior and upstream of the reverser 10.

[0074] The door 14 is pivotably mounted about an axis by means of an actuator. The actuation of the door is known and will not be described further.

[0075] The fixed structure 12 comprises here a housing 13 for receiving the door 14 delimited axially by an upstream frame 13a and a downstream frame 13b and transversely by two lateral beams 13c, only one of which is shown in FIG. 3. Alternatively, it could be provided that the fixed structure 12 comprises a different number of housings for receiving the door, for example greater than or equal to two.

[0076] The downstream frame 13b is spaced apart axially from a downstream end edge of the door 14 by an axial clearance J.

[0077] The thrust reverser 10 further comprises a system 20 for diverting fluids to the exterior of the thrust reverser 10.

[0078] An example of the fluid diverter system 20 is illustrated in detail in FIGS. 4 to 6. In this example, the fluid diverter system 20 comprises a first portion 22 connected to the door 14 and extending axially into axial clearance J and towards the downstream frame 13b of the fixed structure 12 of the thrust reverser 10.

[0079] An axial gap (not referenced) is left between a free end of said first portion 22 and an upstream end 15 of the downstream frame 13b of the fixed structure 12. The axial gap is smaller than the axial clearance.

[0080] As illustrated in FIG. 5, the first portion 22 comprises an attachment portion 22a fixed to the downstream end edge 14a of said door and a diverting portion 22b extending from an outer surface of the attachment portion 22a to the exterior. The diverting portion 22b is here substantially inclined at an angle of between 90° and 150°, for example equal to 135° relative to the attachment portion 22a.

[0081] The fluid diverter system 20 further comprises a second portion 24 connected to the fixed structure 12 and extending axially into the axial clearance J from the upstream end 15 of the downstream frame 13b and towards the downstream end edge 14a of the door 14 of the thrust reverser 10.

[0082] An axial gap (not referenced) is left between a free end of said second portion 24 and the downstream end edge 14a of the door 14. The axial gap is smaller than the axial clearance.

[0083] As illustrated in FIG. 6, the second portion 24 comprises an attachment portion 24a fixed to the upstream end 15 of the downstream frame 13b of the fixed structure 12 and a diverting portion 24b extending from an outer surface of the attachment portion 24a to the exterior. The deflecting portion 24b is here inclined at an angle of between 90° and 150°, for example equal to 90° relative to the attachment portion 24a.

[0084] The first and second portions 22, 24 are deflectors configured to change the direction of flow of a stream of fluids external to the thrust reverser.

[0085] The first portion 22 supported by the door 14 is not in contact with the downstream frame 13b of the fixed structure 12 and the second portion 24 supported by said downstream frame 13b is not in contact with the end edge 14a of the door 14.

[0086] The first and the second portions 22, 24 are here spaced apart circumferentially from one another by a circumferential clearance.

[0087] In other words, the first and the second portions 22, 24 of the fluid diverter system 20 are not in contact with one another. The circumferential clearance makes it possible to allow for manufacturing and installation tolerances of the door and the fixed structure, as well as displacements during aircraft flight.

[0088] The first and the second projections 22, 24 of the fluid diverter system 20 each extend locally into the axial clearance J. In other words, the first projection 22 attached to the door does not extend around the whole circumference of the end edge 14a of the door 14 and the second projection 24 attached to the fixed structure does not extend around the whole circumference of the upstream end 15 of the downstream frame 13b of the fixed structure 12.

[0089] Thus, the first and the second portions 22, 24 of the fluid diverter system 20 form a local barrier allowing external fluids to be redirected to the exterior of the thrust reverser 10 to pass along the downstream frame 13b of the fixed structure 12.

[0090] As illustrated, the fluid diverter system 20 comprises a first portion 22 and a second portion 24, forming a deflector group. Alternatively, a different number of first and second portions 22, 24 of the fluid diverter system could be provided. It could also be provided that the number of first portions 22 is different from the number of second portions 24. In the case of a plurality of first and second portions, the first and second portions can be alternated. It is also possible to provide a succession of first portions without alternating with second portions.

[0091] It could also be provided that the fluid diverter system 20 comprises a plurality of deflector groups spaced apart circumferentially from one another.

[0092] It could also be provided that the fluid diverter system 20 comprises a single projection forming a deflector group and extending into the axial clearance from either the door 14 or the fixed structure 12 towards the other fixed structure 12 or the door 14.

[0093] The first portion 22 and second portion 24 can be made from a rigid material, such as a metal material, a composite material, a plastic material. The term “rigid” means a material which is not elastically deformable under the action of an applied stress.

[0094] The embodiment illustrated in FIGS. 7 and 8, in which the same elements have the same reference numbers, differs from the embodiment illustrated in FIGS. 4 to 6 only in the system for diverting external fluids.

[0095] As illustrated in detail in FIGS. 7 and 8, the fluid diverter system 30 comprises a first portion 32 connected to the door 14 and extending axially locally into the axial clearance J and towards the downstream frame 13b of the fixed structure 12 of the thrust reverser 10.

[0096] An axial gap (not referenced) is left between a free end of said first portion 32 and the downstream frame 13b of the fixed structure 12. The axial gap is smaller than the axial clearance.

[0097] As illustrated, the first projection 32 is fixed to the downstream end edge 14a of said door 14.

[0098] The fluid diverter system 30 further comprises a second portion 34 connected to the fixed structure 12, in particular fixed to the upstream end 15 of the downstream frame 13b of the fixed structure 12 and extending axially locally into the axial clearance J and towards the downstream end edge 14a of the door 14 of the thrust reverser 10.

[0099] An axial gap (not referenced) is left between a free end of said second portion 34 and the downstream end edge 14a of the door 14. The axial gap is smaller than the axial clearance.

[0100] As illustrated, the first and the second projections 32, 34 are in point-like and direct radial contact with one another, forming a local seal between the door 14 and the downstream frame 13b. In other words, the first portion 32 is in radial abutment with the second portion 34. The contacts between the first portion 32 and the second portion 34 are shown in detail in FIG. 8. Thus, it is observed that the first portion 32 and the second portion 34 are in contact along two contact areas (not referenced).

[0101] In other words, the first projection 32 fixed to the door 14 does not extend around the whole circumference of the end edge 14a of the door 14 and the second projection 34 fixed to the fixed structure 12 does not extend around the whole circumference of the upstream end 15 of the downstream frame 13b of the fixed structure 12.

[0102] The term “direct contact” is defined as a contact without an intermediate element between two elements.

[0103] Thus, the first and the second projections 32, 34 of the fluid diverter system 30 form a local and point-like barrier allowing external fluids to be redirected to the exterior of the thrust reverser 10 to flow along the downstream frame 13b of the fixed structure 12.

[0104] In this example, the first and second projections 32, 34 are also deflectors configured to modify the flow direction of a stream of fluids external to the thrust reverser.

[0105] Alternatively, it is possible that the first and the second projections 32, 34 are in circumferential contact with one another, or that first and the second projections 32, 34 are in circumferential and radial contact with one another.

[0106] The first portion 32 may be a seal made from a more flexible material than the second portion 34. For example, the first portion 32 is made from a polymeric material such as silicone for example. Alternatively, it is possible that the first portion 32 is made in the form of a metal leaf spring. In general, the first portion 32 is made from an elastic material capable of being deformed elastically with the application of external stress and returning to its initial shape once the external stress has stopped.

[0107] The second portion 34 can be made from a rigid material, such as a metal material, a composite material or a plastic material. The term “rigid” means a material which is not elastically deformable under the action of an applied stress.

[0108] Alternatively, the first portion 32 supported by the door 14 could be more rigid than the second portion 34 supported by the fixed structure 12.

[0109] Alternatively, the first portion 32 and the second portion 34 can each be made from an elastic material capable of being elastically deformed during the application of external stress and returning to its initial shape once the external stress has stopped.

[0110] As shown, the fluid diverter system 30 comprises a first portion 32 and a second portion 34 together forming a deflector group. Alternatively, a different number of first and second portions 32, 34 of the fluid diverter system could be provided. Each deflector group comprising a first and a second portion are spaced apart circumferentially from one another.

[0111] It is also possible to combine a first fluid diverter system 20 described with reference to FIGS. 4 to 6 with a second fluid diverter system 30 described with reference to FIGS. 7 and 8, the first device 20 and the second device 30 being spaced apart circumferentially from one another.

[0112] In a manner that is in no way limiting, the thrust reverser 10 also comprises a circumferential seal 19 shown in FIG. 8 extending circumferentially around the door 14. The circumferential seal 19 is separate from the systems 20, 30 for diverting fluids.

[0113] In all of the described embodiments, the fluid diverter system 20, 30 is advantageously arranged in the axial clearance between the door 14 and the fixed structure 12 closest to the mast or fuselage of the aircraft on which the thrust reverser 10 is to be mounted.

[0114] Due to the invention, it is possible to effectively divert the external fluids circulating around the door to the exterior of the thrust reverser and thus to prevent these external fluids from entering the clearance between the downstream end edge of the door and the downstream frame of the fixed structure of the thrust reverser.