Air intake scoop for an aircraft

Abstract

An air intake scoop intended to be fastened on a panel of an aircraft includes an air inlet mouth having a wall, a peripheral collar intended to be fastened to the panel, and a bearing element intended to support the air circulation duct. The air inlet mouth is made of a thermoplastic material and the bearing element is fastened on the peripheral collar so as to achieve a pressure barrier in case of breakage of the wall of the air inlet mouth.

Claims

1. An air intake scoop fastened at an orifice of a panel of an aircraft and to an air circulation duct and configured to draw an air flow, the air intake scoop comprising: an air inlet mouth having a wall projecting from one side of the panel opposite the drawn air flow; a peripheral collar located at one end of the air inlet mouth, the peripheral collar separate from the panel and fastened to the panel; and a bearing element separate from the peripheral collar, the bearing element supporting the air circulation duct and extending along the peripheral collar away from the air inlet mouth, wherein the air inlet mouth, the air circulation duct, the bearing element and the peripheral collar jointly define a space therein, and wherein the air inlet mouth is made of a thermoplastic material and the bearing element is fastened on the peripheral collar such that a pressure barrier is formed by the bearing element between the peripheral collar and the air circulation duct.

2. The air intake scoop according to claim 1, wherein the bearing element includes a bearing plate supporting the air circulation duct.

3. The air intake scoop according to claim 2 further comprising a seal disposed between the bearing plate and the air circulation duct.

4. The air intake scoop according to claim 1, wherein the bearing element includes a base fastened to the peripheral collar to form the pressure barrier.

5. The air intake scoop according to claim 4, wherein the base of the bearing element is L-shaped and comprises a first branch fastened to and parallel to the peripheral collar, and a second branch that forms the pressure barrier.

6. The air intake scoop according to claim 1, wherein the bearing element includes stiffeners.

7. The air intake scoop according to claim 6, wherein the stiffeners are disposed between a bearing plate of the bearing element and a first branch of a base of the bearing element fastened to the peripheral collar, the stiffeners being perpendicular to the bearing plate and the first branch of the base.

8. The scoop according to claim 1, wherein the air inlet mouth and the peripheral collar are integrally made in one piece.

9. The scoop according to claim 1, wherein the bearing element is made of a thermoplastic material.

10. An inner fixed structure of an aircraft nacelle including an air intake scoop according to claim 1.

11. An aircraft nacelle including an air intake scoop according to claim 1.

12. An air intake scoop fastened at an orifice of a panel of an aircraft and to an air circulation duct and configured to draw an air flow, the air intake scoop comprising: an air inlet mouth having a proximal end defining a wall projecting from one side of the panel opposite the drawn air flow and a distal free end disposed away from the proximal end; a peripheral collar located at the proximal end of the air inlet mouth, the peripheral collar separate from the panel and fastened to the panel; and a bearing element separate from the peripheral collar, the bearing element supporting the air circulation duct and extending along the peripheral collar away from the air inlet mouth, wherein the air inlet mouth, the air circulation duct, the bearing element and the peripheral collar jointly define a space therein, the distal free end extending toward an end of the air circulation duct to be flush with the end of the air circulation duct, wherein the air inlet mouth is made of a thermoplastic material and the bearing element is fastened on the peripheral collar such that a pressure barrier is formed by the bearing element between the peripheral collar and the air circulation duct.

13. The scoop according to claim 12, further comprising a seal disposed between the air circulation duct and the bearing element to jointly define the space with the air inlet mouth, the air circulation duct, the bearing element and the peripheral collar.

14. The scoop according to claim 12, wherein the bearing element includes a first branch fastened to and parallel to the peripheral collar and a second branch extending from the first branch toward the air circulation duct to form the pressure barrier.

15. The scoop according to claim 12, wherein an air leakage through a junction area between the air circulation duct and the distal free end of the air inlet mouth is blocked by the bearing element and contained in the space.

16. The scoop according to claim 12, wherein the distal free end of the air inlet mouth is fastened to the air circulation duct.

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 partial view illustrating a static air intake scoop fastened on the inner face of an inner fixed structure of an aircraft nacelle according to the prior art;

(3) FIG. 2 is a schematic partial view illustrating an air intake scoop fastened on the inner face of an inner fixed structure of an aircraft nacelle according to the present disclosure; and

(4) FIG. 3 is a schematic sectional view of a scoop including stiffeners according to the present disclosure.

(5) 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

(6) 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.

(7) FIG. 1 represents an air intake scoop 1 of the prior art fastened by bolting (not represented), by its proximal end, on the inner face 2 of an inner fixed structure 3 of an aircraft nacelle, said inner fixed structure 3 defining, together with an outer structure (not represented), a flow annular channel 4, also called secondary flow path, in which a cold air flow 5, called secondary air flow, circulates, said scoop 1 being further fastened, by its distal end, to a duct 6 intended to open into a turbojet engine (not represented) of the aircraft.

(8) The scoop 1 is fastened, by its proximal end, at an orifice 7 of the inner fixed structure 3.

(9) The scoop 1 allows drawing an air flow 50, called drawn air flow, coming from the cold air flow 5 of the secondary flow path 4.

(10) The drawn air flow 50 is then channeled in the duct 6 for cooling the turbine of the turbojet engine.

(11) The scoop 1 is made of materials resistant to pressure and to impacts, such as composite materials like epoxy carbon, or metals like carbon, aluminum, titanium or alloys.

(12) The scoop 1 according to the prior art includes an air inlet mouth 8 projecting at the inner face 2 side of the inner fixed structure 3, a peripheral collar 9 which surrounds the air inlet mouth 8 at its proximal end with respect to the inner fixed structure 3, and a bearing element 10 fastened on the air inlet mouth 8 of the scoop 1 and intended to support the duct 6.

(13) The scoop 1 is fastened to the inner face 2 of the inner fixed structure 3 by the peripheral collar 9.

(14) The air inlet mouth 8 has a free distal end flush with the duct 6.

(15) The air inlet mouth 8 has a shape facilitating the entry of the drawn air flow 50 into the scoop 1, and provides aerodynamic continuity between the inner fixed structure 3 and the scoop 1.

(16) The aerodynamic continuity between the inner fixed structure 3 and the scoop 1 is provided by a step 11 with a height substantially identical to the thickness of the inner fixed structure 3, present at the juncture between the peripheral collar 9 and the air inlet mouth 8.

(17) The entry of air into the scoop is facilitated by the curved shape of the air inlet mouth 8.

(18) The peripheral collar 9 and the air inlet mouth 8 are made integrally in one piece.

(19) The bearing element 10 enables fastening of the scoop 1 to the duct 6.

(20) To this end, the duct 6 includes an interface element 12 which cooperates with the bearing element 10 via a seal 13.

(21) The bearing 10 and interface 12 elements are substantially parallel to the peripheral collar 9 of the scoop 1.

(22) At the junction area between the scoop 1 and the duct 6, a portion 50′ of the diverted air flow 50 tends to escape and seep into a space “e” between the interface element 12, the seal 13, and the bearing element 10, which has the effect of increasing the pressure in said space “e.”

(23) The bearing element 10 of the scoop 1 then achieves a tight barrier allowing inhibiting leakages of the drawn air flow 50.

(24) Moreover, the air inlet mouth 8 being subjected to impacts of debris and to high pressures of the diverted air flow, the pressure and impacts resistant materials composing the scoop, allow reducing the risk of cracks C, and at the same time air leakages 50″ through the wall of the air inlet mouth 8 of the scoop 1.

(25) FIG. 2 represents an air intake scoop 100 according to the present disclosure, fastened by bolting (not represented), by its proximal end, on the inner face 2 of an inner fixed structure 3 of an aircraft nacelle, said inner fixed structure 3 defining, together with an outer structure (not represented), a flow annular channel 4, also called secondary flow path, in which a cold air flow 5, called secondary air flow, circulates, said scoop 100 being further fastened, by its distal end, to a duct 6 intended to open into a turbojet engine (not represented) of the aircraft.

(26) The scoop 100 is fastened, by its proximal end, at an orifice 7 of the inner fixed structure 3.

(27) The scoop 100 allows drawing an air flow 50, called drawn air flow, coming from the cold air flow 5 of the secondary flow path 4.

(28) The drawn air flow 50 is then channeled in the duct 6 for cooling the turbine of the turbojet engine.

(29) The scoop 100 includes an air inlet mouth 108 projecting at the inner face 2 side of the inner fixed structure 3, a peripheral collar 109 which surrounds the air inlet mouth 108 at its proximal end with respect to the inner fixed structure 3, and a bearing element 110 fastened on the peripheral collar 109 and intended to support the duct 6.

(30) The scoop 100 is fastened to the inner face 2 of the inner fixed structure 3 by the peripheral collar 109.

(31) The air inlet mouth 108 has a free distal end flush with the duct 6.

(32) The air inlet mouth 108 is made of a thermoplastic material such as polyamide, Polyethylene terephthalate or else Polyoxymethylene, among others.

(33) The air inlet mouth 108 has a shape facilitating the entry of the drawn air flow 50 into the scoop 100, and provides aerodynamic continuity between the inner fixed structure 3 and the scoop 100.

(34) The aerodynamic continuity between the inner fixed structure 3 and the scoop 100 is provided by a step 111 with a height substantially identical to the thickness of the inner fixed structure 3, present at the juncture between the peripheral collar 109 and the air inlet mouth 108.

(35) The entry of air into the scoop is facilitated by the curved shape of the air inlet mouth 108.

(36) In one form, the peripheral collar 109 and the air inlet mouth 108 are integrally made in one piece.

(37) The bearing element 110 enables tight junction of the duct 6 to the scoop 100.

(38) The bearing element 110 enables fastening of the scoop 100 to the duct 6.

(39) To this end, the duct 6 includes an interface element 12 which cooperates with the bearing element 110 via a seal 13.

(40) The bearing element 110 is concentric with the air inlet mouth 108.

(41) The bearing element 110 advantageously includes a bearing plate 114 substantially parallel to the peripheral collar 109, the bearing plate 114 being intended to support the duct 6, via the seal 13.

(42) The bearing element further includes an L-shaped base 115 a first branch of which is fastened to the peripheral collar 109, parallel to said collar 109, and the second branch of which allows linking the first branch to the bearing plate 114.

(43) In one form, the base 115 and the bearing plate 110 are integrally made in one piece.

(44) At the junction area between the scoop 100 and the duct 6, a portion 50′ of the diverted air flow 50 tends to escape and seep into a space E between the interface element 12, the seal 13, and the bearing element 110, and the air inlet mouth 108, which has the effect of increasing the pressure in said space E.

(45) The second branch of the base 115 of the bearing element 110 of the scoop 100 then achieves a tight barrier allowing inhibiting leakages of the drawn air flow 50.

(46) Moreover, the air inlet mouth 108 being subjected to impacts of debris and to high pressures of the diverted air flow, cracks C may appear in its wall, and at the same time air leakages 50″. The second branch of the base 115 of the bearing element 110 of the scoop 100 then achieves a tight barrier allowing avoiding air flow leakages.

(47) The bearing element 110 is made of materials resistant to the forces generated by the pressure, such as reinforced thermoplastic materials such as for example polyether ether ketone, polyamide reinforced with glass, carbon, aramid fibers or any other metallic alloy like aluminum or titanium reinforcements.

(48) According to one form, the bearing element 110 is reinforced by stiffeners 116 (FIG. 3).

(49) The first branch of the base 115 of the bearing element 110 is turned towards the direction opposite to the air inlet mouth 108.

(50) FIG. 3 represents one form of a scoop 100 according to the present disclosure including stiffeners 116 disposed between the bearing plate 114 and the base 115 of the bearing element 110.

(51) The stiffeners 116 are substantially perpendicular to the bearing plate 114.

(52) The stiffeners 116 allow stiffening the bearing element 110, and thus consolidating the sealing barrier.

(53) The stiffeners 116 also allow transmitting the compressive forces of the seal 13 (FIG. 2).

(54) 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.

(55) 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.”

(56) 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.