AIRCRAFT PROPELLER ASSEMBLY COMPRISING A TURBOJET ENGINE, A MAST AND MEANS OF ATTACHING THE TURBOJET ENGINE TO THE MAST
The propulsion assembly with articulated connecting rods and pivot connections addresses the challenge of managing axial forces and moments in turbojet engine mounting, improving stability and access within the propulsion system.
Patent Information
- Authority / Receiving Office
- FR · FR
- Patent Type
- Applications
- Current Assignee / Owner
- AIRBUS OPERATIONS (SAS)
- Filing Date
- 2024-12-23
- Publication Date
- 2026-06-26
AI Technical Summary
Existing turbojet engine mounting systems do not effectively manage axial moments and forces, leading to the need for improved mounting masts that alleviate stress and facilitate easier access to the propulsion assembly.
A propulsion assembly comprising a turbojet engine, a mast, and a hooking device with articulated connecting rods that distribute axial forces and moments, utilizing pivot connections and clevis-type joints to align connection points, ensuring stability and ease of access.
The solution effectively distributes axial forces and moments, providing stability and ease of access to the propulsion assembly, enhancing the safety and functionality of the turbojet engine mounting system.
Smart Images
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Abstract
Description
Title of the invention: PROPULSION ASSEMBLY FOR AN AIRCRAFT COMPRISING A TURBOJET ENGINE, A MAST AND MEANS FOR ATTACHING THE TURBOJET ENGINE TO THE MAST technical field
[0001] The present invention relates to the general field of attaching a turbojet engine under the wing of an aircraft. It relates in particular to a propulsion system comprising a turbojet engine, for example of the unfaired fan type, a pylon, and a mounting system for attaching the turbojet engine under the pylon. It also relates to an aircraft equipped with such a propulsion system. PREVIOUS STATE OF THE ART
[0002] An aircraft conventionally comprises wings and at least one fixed propulsion unit under each of these wings. Each propulsion unit comprises a towing pylon and an engine. The towing pylon has a rigid structure called the "primary structure" which is fixed between the wing and the engine by means of towing assemblies, namely a first towing assembly between the wing and the towing pylon and a second towing assembly between the pylon and the engine.
[0003] Although such an engine assembly is efficient, the evolution of turbojets leads to the need to develop different mounting masts which, in particular, allow the turbojet to be unloaded. Description of the invention
[0004] An object of the present invention is to provide a propulsion assembly comprising a turbojet, a mast and a hooking device for hooking the turbojet under the mast.
[0005] To this end, a propulsion system for an aircraft is proposed, said propulsion system having a longitudinal axis and a vertical median plane passing through the longitudinal axis and comprising:
[0006] - a turbojet engine comprising a front casing extending between a front face and a rear face perpendicular to the longitudinal axis,
[0007] - a mounting mast having a primary structure with a front wall,
[0008] - an engine mount comprising a first connecting rod and a second connecting rod which are arranged on either side of the median plane, where one of the connecting rods is mounted articulated by a first point of connection to the front wall and by a second point of connection to the front crankcase, where the other connecting rod is mounted articulated by a third and a fourth connection points to the front wall and by a fifth connection point to the front casing, and where the connection points are in the front third of the front casing, and
[0009] - connecting rods mounted articulated between the mounting mast and the turbojet engine.
[0010] With such an arrangement, the turbojet is relieved of the fact that the axial moment is introduced as far forward as possible.
[0011] Advantageously, the three connection points ensuring the connection between a connecting rod and the front wall are aligned along a direction perpendicular to the median plane.
[0012] According to a particular embodiment, the propulsion assembly further comprises:
[0013] - two external connecting rods arranged on either side of the median plane, where each The outer connecting rod has a rear end mounted and hinged to a lower longitudinal member of the primary structure by a first rear connection point, and a front end mounted and hinged to the rear face by a first front connection point, and
[0014] - two internal connecting rods arranged on either side of the median plane, where each The inner connecting rod has a rear end mounted articulated to the lower side member by a second rear connection point and a front end mounted articulated to the rear face by a second front connection point.
[0015] Advantageously, each front and rear connection point takes the form of a pivot connection whose axis is perpendicular to the median plane.
[0016] According to a particular embodiment, the turbojet engine comprises a rear casing, where the longitudinal axis constitutes an axis of rotation of the turbojet engine, and the propulsion assembly further comprises:
[0017] - two external connecting rods arranged on either side of the median plane, where each The outer connecting rod has a rear end mounted and hinged to the lower side member by a first rear connection point, and a front end mounted and hinged to the rear face by a first front connection point, and
[0018] - two internal connecting rods arranged on either side of the median plane, where each the inner connecting rod has a rear end mounted articulated to the lower side member by a second rear connection point and a front end mounted articulated to the rear face or rear casing by a second front connection point, and where the axes of the inner connecting rods converge towards the longitudinal axis.
[0019] Advantageously, the propulsion assembly further comprises a propeller at the front of the front casing and convergence on the longitudinal axis takes place at the center of the propeller.
[0020] Advantageously, the front connection points of the outer connecting rods are aligned along a horizontal transverse line.
[0021] Advantageously, each front and rear connection point of the outer connecting rods takes the form of a pivot joint whose axis is perpendicular to the median plane.
[0022] The invention also proposes an aircraft comprising a wing and a propulsion assembly according to one of the preceding variants, the primary structure of which is fixed under the wing. Brief description of the drawings
[0023] The features of the invention mentioned above, as well as others, will become clearer upon reading the following description of an exemplary embodiment, said description being made in relation to the accompanying drawings, among which:
[0024] [Fig-1] represents a side view of an aircraft according to the invention,
[0025] [Fig.2] is a schematic representation of a propulsion assembly according to a first embodiment of the invention in side view,
[0026] [Fig.3] is a perspective view of a propulsion assembly according to the first embodiment of the invention,
[0027] [Fig.4] is a schematic representation of a propulsion assembly according to a second embodiment of the invention in side view,
[0028] [Fig. 5] is a perspective view of a propulsion assembly according to the second embodiment of the invention, and
[0029] [Fig.6] is a front view of a motor attachment implemented in the invention.
[0030] DETAILED STATEMENT OF IMPROVEMENTS
[0031] With reference to [Fig.1], an aircraft 50 comprises a fuselage 51 to which is fixed, on each side, a wing 52 under which is mounted at least one propulsion assembly 100 according to the invention.
[0032] The propulsion assembly 100, 200 includes a mounting mast 104 fixed under the wing 52 and a turbojet 102 fixed under the mounting mast 104. The turbojet 102 is of the unfaired fan turbojet type.
[0033] By convention, X is called the longitudinal axis of the turbojet 102 and therefore of the propulsion assembly 100, 200, this longitudinal axis X being parallel to a longitudinal direction of this turbojet 102. On the other hand, Y is called the transverse axis of the turbojet 102 which is horizontal when the aircraft is on the ground, and Z is called the vertical axis or vertical height when the aircraft is on the ground, these three directions X, Y and Z being orthogonal to each other.
[0034] On the other hand, the terms "forward" and "rear" are to be considered in relation to a direction of advance of the aircraft 50 during the operation of the turbojet 102, this direction being schematically represented by the arrow 107 on the [Fig.1].
[0035] Figures 2 and 3 show the propulsion assembly 100 according to a first embodiment of the invention, and Figures 4 and 5 show the propulsion assembly 200 according to a second embodiment of the invention. Figure 6 shows a detail of an engine attachment 150 which ensures a fixing between the mounting mast 104 and the turbojet 102.
[0036] The turbojet 102 comprises, from front to rear, a propeller 53, a nacelle 54 in which the other elements of the turbojet 102 are housed, and which takes the form of a core having a front casing 112a and a rear casing 112b, which is fixed to the rear of the front casing 112a and in which the other elements of the turbojet 102 are housed, such as compression stages, a combustion chamber, turbine stages, and an exhaust cone. The rear casing 112b and the front casing 112a are coaxial with the longitudinal axis X, and the rear casing 112a has a smaller diameter than the front casing 112a. The rear casing 112b extends here from a rear face 113b of the front casing 112a which is perpendicular to the longitudinal axis X which constitutes an axis of rotation of the turbojet 102.
[0037] The attachment mast 104 is represented here by its primary structure 106, which is fixed to the wing structure 52 by any suitable fastening means known to those skilled in the art. The front casing 112a extends between a front face 113a and a rear face 113b, which are perpendicular to the longitudinal axis X.
[0038] The primary structure 106 is in the form of a box extending along the longitudinal direction X and comprising a front wall 106e, located at the front of the primary structure 106, a lower stringer 106a extending below the primary structure 106 and an upper stringer 106b extending above the primary structure 106. The primary structure 106 also comprises two side walls 106c-d on each side of the vertical median plane P. These various stringers and walls are fixed to each other to form the primary structure 106.
[0039] The mooring mast 104 and the turbojet 102 are globally symmetrical with respect to a vertical median plane XZ of the propulsion assembly 100 which passes through the longitudinal axis X, which is hereafter called the median plane P and which separates the mooring mast 104 and the turbojet 102 into two port-starboard parts.
[0040] In each of the two embodiments of the invention represented here, the propulsion assembly 100, 200 includes a motor attachment 150 which ensures a fixing between the front wall 106e of the primary structure 106 and the front casing 112a.
[0041] The engine attachment 150 comprises a first connecting rod 152a and a second connecting rod 152b and they are arranged on either side of the median plane P with here, the first connecting rod 152 on the port side and the second connecting rod 152b on the starboard side, but the reverse arrangement is possible.
[0042] One of the two connecting rods 152a (here on the port side) is mounted articulated by a first connection point 602a to the front wall 106e and by a second connection point 602b to the front casing 112a. The other of the connecting rods 152b (here on the starboard side) is mounted articulated by a third 604a and a fourth 604b connection points to the front wall 106e and by a fifth connection point 604c to the front casing 112a.
[0043] The connection points 602a-b and 604a-c relating to the first connecting rod 152a and the second connecting rod 152b are in the front third of the front housing 112a. That is to say, considering that the front housing 112a has a length L parallel to the longitudinal axis X between the front face 113a and the rear face 113b, the connection points 602a-b and 604a-c are at most at a distance L / 3 from the front face 113a.
[0044] With such an arrangement, the axial moment Mx and the forces transmitted vertically parallel to the vertical axis Z and transversely parallel to the transverse axis Y are transmitted to the hooking mast 104 without completely traversing the front casing 112a.
[0045] In the embodiment of the invention shown in [Fig.6], the three connection points 602a and 604a-b ensuring the connection between a connecting rod 152a-b and the front wall 106e are aligned along a direction perpendicular to the median plane P in order to block rotation around the longitudinal axis X.
[0046] Each connection point 602a-b, 604a-c ensures at least one pivot connection around an axis parallel to the longitudinal axis X, but according to a preferred embodiment, each connection point 602a-b, 604a-c ensures a ball joint.
[0047] The two specific arrangements described below employ two external connecting rods 120, 220 and two internal connecting rods 122, 222, which together provide a first-degree statically indeterminate system that ensures safety, for example, in the event of the failure of a connecting rod 120, 122, 220, or 222. Each connecting rod 120, 122, 220, or 222 also provides load transfer along its axis. The connecting rods 120, 122, 220, and 222 are mounted with hinges between the mounting mast 104 and the turbojet engine 102.
[0048] In the first embodiment of the invention shown in Figs. 2 and 3, the propulsion assembly 100 thus comprises two external connecting rods 120 which are arranged on either side of the median plane P. Each external connecting rod 120 has a rear end 120a which is mounted articulated to the lower longitudinal member 106a by a first rear connection point 121a and a front end 120b which is mounted articulated to the rear face 113b of the front casing 112a by a first front connection point 121b.
[0049] Similarly, in the first embodiment of the invention, the propulsion assembly 100 comprises the two inner connecting rods 122 which are arranged on either side of the median plane P. Each inner connecting rod 122 has a rear end 122a which is mounted articulated to the lower spar 106a by a second rear connection point 123a and a front end 122b which is mounted articulated to the rear face 113b by a second front connection point 123b.
[0050] The inner connecting rods 122 are located inside the propulsion assembly 100 relative to the outer connecting rods 120, which are on the outside of the inner connecting rods 122 and extend further back relative to the inner connecting rods 122.
[0051] The second rear connection point 123a is arranged in front of the first rear connection point 121a.
[0052] With such an arrangement, the connecting rods 120 and 122 are moved away from the rear casing 112b allowing easier access to the interior of the propulsion assembly 100.
[0053] In the embodiment of the invention presented here, the two front connection points 121b of the outer connecting rods 120 are aligned along a transverse line D which is horizontal and therefore here parallel to the transverse axis Y.
[0054] The transverse line D is also here perpendicular to the median plane P and therefore parallel to the transverse axis Y.
[0055] In the embodiment of the invention presented here, each connection point 121a-b, 123a-b takes the form of a pivot connection whose axis is perpendicular to the median plane P, but a different orientation is possible.
[0056] To this end, each connection point 121a-b, 123a-b takes the form of a clevis-type connection, with a male clevis mounted movable in rotation in a female clevis via an axis.
[0057] For each front connection point 121b, 123b, the female clevis is integral with the rear face 113b and the male clevis is constituted by the front end 120b, 122b of the connecting rod 120, 122 concerned.
[0058] For each rear connection point 121a, 123a, the female clevis is integral with the lower longitudinal member 106a and the male clevis is formed by the rear end 120a, 122a of the relevant connecting rod 120, 122. Here, the female clevises of the rear connection points 123a of the inner connecting rods 122 are fixed to a beam 125 integral with the lower longitudinal member 106a and which here extends laterally beyond the primary structure 106.
[0059] In the second embodiment of the invention shown in Figs. 4 and 5, the propulsion assembly 200 thus comprises two external connecting rods 220 which are arranged on either side of the median plane P. Each external connecting rod 220 has a rear end 220a which is mounted articulated to the lower longitudinal member 106a by a first rear connection point 221a and a front end 220b which is mounted articulated to the rear face 113b of the front casing 112a by a first front connection point 221b.
[0060] Similarly, in the second embodiment of the invention, the propulsion assembly 200 also comprises the two inner connecting rods 222 which are arranged on either side of the median plane P. Each inner connecting rod 222 has a rear end 222a which is mounted articulated to the lower spar 106a by a second rear connection point 223a and a front end 222b which is mounted articulated to the rear face 113b or to the rear casing 112b by a second front connection point 223b.
[0061] The inner connecting rods 222 are located inside the propulsion assembly 100 relative to the outer connecting rods 220, which are on the outside of the inner connecting rods 222 and extend further back relative to the inner connecting rods 222.
[0062] The second rear connection point 223a is arranged in front of the first rear connection point 221a.
[0063] Furthermore, the axes of the inner connecting rods 222 converge towards the longitudinal axis X. The axis of a connecting rod is the axis connecting the two ends of the connecting rod and is represented here by the reference 'd' in [Fig. 3]. According to a preferred embodiment, the convergence on the longitudinal axis X takes place at the center of the propeller 53, which is at the front of the front housing 112a, that is to say, at the intersection between the longitudinal axis X and the plane of the propeller 53.
[0064] With such an arrangement, the inner connecting rods 222 converge towards the axis of rotation X of the turbojet 102 to minimize stresses.
[0065] In the embodiment of the invention presented here, the two front connection points 221b of the outer connecting rods 220 are aligned along a transverse line D which is horizontal and therefore here parallel to the transverse axis Y.
[0066] The transverse line D is also here perpendicular to the median plane P and therefore parallel to the transverse axis Y.
[0067] In the embodiment of the invention presented here, each connection point 221a-b, 223a-b takes the form of a pivot joint, and for the external connecting rods 220, the axis of the pivot joint is perpendicular to the median plane P, but a different orientation is possible.
[0068] To this end, each connection point 221a-b, 223a-b takes the form of a clevis-type connection, with a male clevis mounted movable in rotation in a female clevis via an axis.
[0069] For each front connection point 221b of an outer connecting rod 220, the female yoke is integral with the rear face 113b and the male yoke is formed by the front end 220b of the relevant connecting rod 220. For each front connection point 223b of an inner connecting rod 222, the female yoke is integral with the rear face 113b or the rear housing 112b and the male yoke is formed by the front end 222b of the relevant connecting rod 222.
[0070] For each rear connection point 221a, 223a, the female clevis is integral with the lower longitudinal member 106a and the male clevis is formed by the rear end 220a, 222a of the relevant connecting rod 220, 222. Here, the female clevises of the rear connection points 223a of the inner connecting rods 222 are fixed to a beam 225 integral with the lower longitudinal member 106a and which here extends laterally beyond the primary structure 106.
Claims
Demands
1. Propulsion assembly (100, 200) of an aircraft (50), said propulsion assembly (100, 200) having a longitudinal axis (X) and a vertical median plane (P) passing through the longitudinal axis (X) and comprising: - a turbojet engine (102) having a front casing (112a) extending between a front face (113a) and a rear face (113b) perpendicular to the longitudinal axis (X), - a mounting mast (104) having a primary structure (106) with a front wall (106e), - an engine mount (150) having a first connecting rod (152a) and a second connecting rod (152b) which are arranged on either side of the median plane (P), where one of the connecting rods (152a) is mounted articulated by a first connection point (602a) to the front wall (106e) and by a second connection point (602b) to the front casing (112a),where the other connecting rod (152b) is mounted articulated by a third (604a) and a fourth (604b) connection points to the front wall (106e) and by a fifth connection point (604c) to the front casing (112a), and where the connection points (602a-b, 604a-c) are in the front third of the front casing (112a) and - connecting rods (120, 122, 220, 222) mounted articulated between the mounting mast (104) and the turbojet (102).
2. Propulsive assembly (100, 200) according to claim 1, characterized in that the three connection points (602a, 604a-b) ensuring the connection between a connecting rod (152a-b) and the front wall (106e) are aligned along a direction perpendicular to the median plane (P).
3. Propulsion assembly (100) according to claim 1 or 2, characterized in that it further comprises: - two outer connecting rods (120) arranged on either side of the median plane (P), where each outer connecting rod (120) has a rear end (120a) mounted articulated to a lower spar (106a) of the primary structure (106) by a first rear connection point (121a) and a front end (120b) mounted articulated to the rear face (113b) by a first front connection point (121b), and - two inner connecting rods (122) arranged on either side of the median plane (P), where each inner connecting rod (122) has a rear end (122a) mounted articulated to the lower spar (106a) by a second rear connection point (123a) and a front end (122b) articulated mounting on the rear face (113b) by a second front connection point (123b).
4. Propulsive assembly (100) according to claim 3, characterized in that each front and rear connection point (121a-b, 123a-b) takes the form of a pivot connection whose axis is perpendicular to the median plane (P).
5. Propulsion assembly (200) according to claim 1 or 2, characterized in that the turbojet (102) comprises a rear casing (112b), where the longitudinal axis (X) constitutes an axis of rotation of the turbojet (102), and in that the propulsion assembly (200) further comprises: - two outer connecting rods (220) arranged on either side of the median plane (P), where each outer connecting rod (220) has a rear end (220a) mounted articulated to the lower spar (106a) by a first rear connection point (221a) and a front end (220b) mounted articulated to the rear face (113b) by a first front connection point (221b), and - two inner connecting rods (222) arranged on either side of the median plane (P),where each inner connecting rod (222) has a rear end (222a) mounted articulated to the lower side member (106a) by a second rear connection point (223a) and a front end (222b) mounted articulated to the rear face (113b) or to the rear housing (112b) by a second front connection point (223b) and where the axes of the inner connecting rods (222) converge towards the longitudinal axis (X).
6. Propulsion assembly (200) according to claim 5, characterized in that it further comprises a propeller (53) at the front of the front casing (112a) and in that the convergence on the longitudinal axis (X) takes place at the center of the propeller (53).
7. Propulsive assembly (200) according to any one of claims 5 or 6, characterized in that the forward connection points (221b) of the outer connecting rods (220) are aligned along a horizontal transverse line (D).
8. Propulsive assembly (200) according to any one of claims 5 to 7, characterized in that each front and rear connection point (221a-b) of the outer connecting rods (220) takes the form of a pivot connection whose axis is perpendicular to the median plane (P). 10
9. Aircraft (50) comprising a wing (52) and a propulsion assembly (100, 200) according to any one of the preceding claims, the primary structure (106) of which is fixed under the wing (52).