FORWARD ENGINE MOUNTING SYSTEM FOR AN AIRCRAFT COMPRISING AN ENGINE PISTON AND AN ENGINE CASING
The front engine attachment system with orthogonal yokes and connecting rods addresses the challenge of reducing the engine height, allowing the nacelle to be positioned closer to the wing, enhancing stability and safety.
Patent Information
- Application Number
- FR2023007061
- Authority / Receiving Office
- FR · FR
- Patent Type
- Patents
- Current Assignee / Owner
- Filing Date
- 2023-07-03
- Publication Date
- 2025-07-18
- Estimated Expiration
- 2043-07-03
AI Technical Summary
The increasing size of aircraft engine fans necessitates a reduction in the height of the front engine attachment to move the nacelle closer to the wing, reducing the distance between the nacelle cowls and the ground.
A front engine attachment system with a reactor pylon and engine casing, featuring orthogonal yokes and connecting rods, which reduces the vertical footprint and allows for a compact aircraft engine mounting system.
The system achieves a reduced vertical footprint, enabling the nacelle to be positioned closer to the wing, while providing isostatic stability and fail-safe mechanisms for force transmission.
Smart Images
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Abstract
Description
Title of the invention: FRONT ENGINE ATTACHMENT SYSTEM FOR AN AIRCRAFT COMPRISING A JET MASTS AND A CRANKCASE Technical field
[0001] The present invention relates to an aircraft attachment system comprising a reactor mast and an engine casing, where the attachment system is compact, as well as an aircraft comprising at least one such attachment system. STATE OF THE PRIOR ART
[0002] An aircraft conventionally comprises at least one engine, in particular a turbojet. Under each wing and for each engine, the aircraft comprises a reactor mast which is fixed to the wing structure and which extends below the wing and the engine is suspended under the reactor mast.
[0003] The engine is housed in a nacelle and attached to the engine pylon via an engine attachment system comprising a front engine suspension attachment on a first interface plane, a rear engine suspension attachment on a second interface plane and a thrust recovery path, which can either be integrated into one of the two aforementioned engine suspension interface planes, or integrated independently into a third interface plane.
[0004] There are many types of front engine mounts that are satisfactory from the point of view of their current use. But the fans of new engines are increasingly larger to improve engine performance, which reduces the distance between the nacelle cowls and the ground.
[0005] It is then necessary to define a new arrangement making it possible to reduce the height of the front engine attachment to move the nacelle away from the ground and consequently to bring the nacelle closer to the wing. Statement of the invention
[0006] An object of the present invention is to provide a front engine attachment system for an aircraft engine comprising a reactor pylon and an engine casing, where the integration ensures a reduction in the height of the assembly.
[0007] For this purpose, a front engine attachment system is proposed for an aircraft engine, the front engine attachment system having a vertical median plane and comprising:
[0008] - a reactor mast comprising at a front part, a nose presenting at level of the vertical median plane and in front of the nose, a front male yoke having a first front bore extending in a transverse direction which is orthogonal to the vertical median plane, and at the level of the vertical median plane and under the nose, a lower male yoke having a first lower bore extending in the transverse direction, and on either side of the vertical median plane, a first port male yoke extending orthogonally to the vertical median plane and having a first port bore coaxial with a first port axis parallel to a longitudinal direction and a first starboard male yoke extending orthogonally to the vertical median plane and having a first starboard bore coaxial with a first starboard axis parallel to the longitudinal direction,
[0009] - an engine casing comprising a front female yoke having a second front bore extending in the transverse direction, a lower female yoke having a second lower bore extending in the transverse direction, a second port male yoke having a second port bore extending in the longitudinal direction, and a second starboard male yoke having a second starboard bore extending in the longitudinal direction,
[0010] - at least a first port connecting rod having a first and a second bores,
[0011] - at least a first starboard connecting rod having a third and a fourth bores,
[0012] - a front axle extending in the transverse direction mounted in the first front bore and in the second front bore,
[0013] - a lower axis extending in the transverse direction mounted in the first lower bore and the second lower bore,
[0014] - a first port axle mounted in the first port bore and the first bore of the first port connecting rod,
[0015] - a second port axle mounted in the second port bore and the second bore of the first port connecting rod,
[0016] - a first starboard axis mounted in the first starboard bore and the first bore of the first starboard connecting rod, and
[0017] - a second starboard axle mounted in the second starboard bore and the second bore of the first starboard connecting rod.
[0018] Such an attachment system has a reduced vertical footprint.
[0019] Advantageously, the casing takes the form of a crown and each front and lower female yoke of the casing is constituted by walls of the casing arranged on either side of the vertical median plane and constituting protrusions of the casing between which the front and lower male yokes are arranged.
[0020] Advantageously, the front male yoke is made up of two front fittings, where each front fitting has a front sub-bore, where the two front sub-bores extend and form the first front bore.
[0021] Advantageously, the lower male yoke is made up of two fittings in lower, where each lower fitting has a lower underbore, where the two lower underbores extend and form the first lower bore.
[0022] Advantageously, said front engine attachment system also comprises a second port connecting rod having a first and a second bore, where the first port pin is also mounted in the first bore of the second port connecting rod, where the second port pin is also mounted in the second bore of the second port connecting rod, the first and second port connecting rods being mounted in parallel around the first and second port male yokes, and said front engine attachment system also comprises a second starboard connecting rod having a third and a fourth bore, where the first starboard pin is also mounted in the third bore of the second starboard connecting rod, where the second starboard pin is also mounted in the fourth bore of the second starboard connecting rod, the first and second starboard connecting rods being mounted in parallel around the first and second starboard male yokes.
[0023] According to a particular embodiment, the axes of one of the pairs among the pair comprising the first port axis and the second port axis and the pair comprising the first starboard axis and the second starboard axis, are mounted adjusted in the associated bores, the axes of the other of the pairs are mounted with a radial clearance in the associated bores, the lower axis is mounted adjusted in the associated bores and the front axis is mounted with a radial clearance in the associated bores.
[0024] According to a particular embodiment, the axes of one of the pairs among the pair comprising the first port axis and the second port axis and the pair comprising the first starboard axis and the second starboard axis, are mounted adjusted in the associated bores, the axes of the other of the pairs are mounted with a radial clearance in the associated bores, the lower axis is mounted with a radial clearance in the associated bores and the front axis is mounted adjusted in the associated bores.
[0025] The invention also proposes an aircraft comprising a structure, an engine and a front engine attachment system according to one of the preceding variants, where the reactor mast is fixed to the structure and where the casing is an engine casing. Brief description of the drawings
[0026] The above-mentioned features of the invention, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made in relation to the attached drawings, among which:
[0027] [Fig-1] is a side view of an aircraft according to the invention, and
[0028] [Fig.2] is a perspective view of a fastening system according to the invention.
[0029] DETAILED DESCRIPTION OF EMBODIMENTS
[0030] In the following description, terms relating to a position are taken with reference to an aircraft in forward position, that is to say as shown in [Fig.l], where the arrow F represents the direction of forward movement.
[0031] [Fig.l] shows an aircraft 100 which has an engine 102, in particular a turbojet which is fixed under a reactor mast 104 itself fixed under a wing 106.
[0032] In the following description, and by convention, X refers to the longitudinal direction of the engine 102 oriented positively in the direction of advance of the aircraft 100, Y refers to the transverse direction of the engine 102 which is horizontal when the aircraft 100 is on the ground, and Z refers to the vertical direction or vertical height when the aircraft 100 is on the ground, these three directions X, Y and Z being orthogonal to each other.
[0033] The motor 102 generally has a shape of revolution around the longitudinal axis X.
[0034] In the embodiment of the invention shown in [Fig.l], the aircraft 100 comprises an engine 102 under each wing 106 of the aircraft 100, but it is possible to provide several engines under each wing 106.
[0035] [Fig.2] shows the port portion of a front engine attachment system 150 for the engine 102 according to the invention, the starboard portion being generally symmetrical to the port portion with respect to a vertical median plane XZ of the attachment system 150.
[0036] The attachment system 150 comprises a casing 102a of the engine 102 fixed to the engine pylon 104 and the engine pylon 104 fixed to the structure of the wing 106 and, more generally, to a structure of the aircraft 100.
[0037] The casing 102a is a casing of the motor 102 and here it generally takes the form of a cylinder around the longitudinal direction X. The motor 102 is not described in more detail because it can take any form known to those skilled in the art.
[0038] The attachment system 150 is fixed to the structure of the aircraft 100, here the structure of the wing 106, and extends under the wing 106 and supports the engine 102 via the casing 102a of the engine 102.
[0039] Conventionally, a rear engine attachment is fixed between the engine pylon 104 and a rear part of the engine 102 and it can take any form known to those skilled in the art.
[0040] The reactor mast 104 takes the form of a box which here comprises an upper wall 104a, a lower wall 104b and two side walls 104c-d. The different walls 104a-d are integral with each other so as to form a box whose vertical section is generally trapezoidal.
[0041] The reactor mast 104 comprises, at a front part 163 of the box, a nose 110 fixed at the front part 163 by any known means, such as by welding or by installing bolts. The front part 163 corresponds to the front ends of the walls 104a-d.
[0042] In the following description, only the elements which are on the port side are visible on the [Fig.2], but the elements which are to starboard are symmetrical with respect to the vertical median plane XZ.
[0043] The nose 110 has at the level of the vertical median plane XZ and at the front of the nose 110, a frontal male yoke 112 which is crossed by a first frontal bore coaxial with a frontal axis 112a.
[0044] The nose 110 also has at the level of the vertical median plane XZ and under the nose 110, a lower male yoke 114 which is crossed by a first lower bore coaxial with a lower axis 114a. The lower axis 114a is here parallel to the front axis 112a and they both extend in the transverse direction Y perpendicular to the vertical median plane XZ, and they therefore extend here generally parallel to the transverse direction Y.
[0045] On either side of the vertical median plane XZ, the nose 110 has a lateral stiffener 111 which extends perpendicularly to the vertical median plane XZ. There is thus a port lateral stiffener 111 which comprises a first port male yoke 107 extending orthogonally to the vertical median plane XZ and crossed by a first port bore coaxial with a first port axis 116a and a starboard lateral stiffener which comprises a first starboard male yoke extending orthogonally to the vertical median plane XZ and crossed by a first starboard bore coaxial with a first starboard axis.
[0046] The casing 102a here takes the form of a crown and it comprises a front female yoke 113 crossed by a second front bore coaxial with the front axis 112a.
[0047] The casing 102a also has a lower female yoke 115 which is crossed by a second lower bore coaxial with the lower axis 114a.
[0048] Each female yoke 113, 115 is made up of two walls 113a (only one is visible in [Fig.2]), 115a-b which are on either side of the vertical median plane XZ. The front male yoke 112 and the lower male yoke 114 are arranged between the two walls 113a, 115a-b to form a yoke-type connection.
[0049] The two walls 113a, 115a-b forming each female yoke 113, 115 are thus generally parallel to the vertical median plane XZ and each is crossed by a bore which forms with the bore of the other wall, the second front bore or the second lower bore.
[0050] On either side of the vertical median plane XZ, the casing 102a has a lateral flange 117 which extends perpendicular to the vertical median plane XZ. There is thus a port lateral flange 117 which comprises a second port male yoke 109 which is crossed by a second port bore coaxial with a second port axis 116b and a starboard lateral flange which comprises a second starboard male yoke which is crossed by a second starboard bore coaxial with a second starboard axis. The second port / starboard bore is outside relative to the first bore port / starboard of the port lateral stiffener 111.
[0051] The first port axis 116a is parallel to the second port axis 116b and distinct from the latter. Similarly, the first starboard axis is parallel to the second starboard axis and distinct from the latter.
[0052] The attachment system 150 also comprises a pair of port connecting rods 118 comprising a first port connecting rod 118a having a first and a second bore and a second port connecting rod 118b having a first and a second bore, as well as a pair of starboard connecting rods comprising first and second starboard connecting rods each having a third and a fourth bore. The pairs of connecting rods 118 are arranged on either side of the vertical median plane XZ and each connecting rod 118 here lies in a lateral plane YZ.
[0053] For safety reasons, the first and second port connecting rods 118a-b are mounted in parallel to each other, around the first and second port male yokes 107, 109, between the associated first axis 124 and second axis 126. Each first and second port connecting rod 118a-b is thus pierced with a bore allowing the reception of the corresponding axis 124, 126. Thus, in the event of breakage of one of the first and second port connecting rods 118a-b, the pair of starboard connecting rods takes over.
[0054] Each pair of connecting rods 118 forms a female yoke in which the lateral stiffener 111 of the nose 110 and the lateral flange 117 of the casing 102a are arranged.
[0055] The attachment system 150 also comprises a front axis 120 (also called front shaft) extending in the transverse direction Y and mounted in the first front bore and in the second front bore, to produce a yoke-type assembly between the front male yoke 112 and the front female yoke 113, i.e. a pivot connection around the front axis 112a.
[0056] The attachment system 150 also comprises a lower axis 122 (also called lower shaft) extending in the transverse direction Y and mounted in the first lower bore and the second lower bore, to produce a yoke-type assembly between the lower male yoke 114 and the lower female yoke 115, i.e. a pivot connection around the lower axis 114a.
[0057] The attachment system 150 also comprises a first port axle 124 (also called the first port shaft) mounted in the first port bore, in the first bore of the first port connecting rod 118a and in the first bore of the second port connecting rod 118b, to provide a pivot connection between the first port bore and the pair of port connecting rods 118 around the first port axle 116a.
[0058] The attachment system 150 also comprises a second port axle 126 (also called second port shaft) mounted in the second port bore, in the second bore of the first port connecting rod 118a and in the second bore of the second port connecting rod 118b, to provide a pivot connection between the second port bore and the pair of port connecting rods 118 around the second port axis 116b.
[0059] A symmetrical mounting is provided for the starboard connecting rod, with a first starboard pin (also called a first starboard shaft) mounted in the first starboard bore and the first bore of the first and second connecting rods of the starboard connecting rod pair to provide a pivot connection about the first starboard pin, and a second starboard pin (also called a second starboard shaft) mounted in the second starboard bore and the second bore of the first and second connecting rods of the starboard connecting rod pair to provide a pivot connection about the second starboard pin.
[0060] In this assembly, on the one hand, the front axis 112a and the lower axis 114a extend in the transverse direction Y and they are perpendicular to the median plane XZ and, on the other hand, the first port axis 116a, the first starboard axis, the second port axis 116b and the second starboard axis are parallel to the median plane XZ, and here generally parallel to the longitudinal direction X.
[0061] Such an assembly makes it possible to reduce the height of the casing 102a and it also makes it possible to reduce the height of the upper aerodynamic line of the secondary vein of the engine 102, called the “crest line”, i.e. the vein around the nose 110.
[0062] The different axes are blocked in translation by any appropriate means known to those skilled in the art such as nuts, and each shaft is coaxial with the axis considered.
[0063] With such an attachment system 150 and an appropriate rear engine attachment, the overall engine attachment system is said to be 'isostatic', that is to say that the translations in the three directions X, Y and Z and the three rotations around these same axes (Mx, My, Mz) are blocked.
[0064] The attachment system 150 makes it possible to control the shear forces in the three directions X, Y and Z and by combination with an appropriate rear engine attachment, the moments My and Mz.
[0065] The X and Z forces are governed by means of the front axis 120 and the lower axis 122 and the Y forces are governed by means of the connecting rods 118.
[0066] In the embodiment of the invention shown in [Fig.2], the casing 102a takes the form of a continuous crown over 360° and comprises the central female yoke 113, which comprises the walls 113a, forming protrusions of the casing 102a, and the lower female yoke 115, which comprises the walls 115a-b, forming protrusions of the casing 102a. Each female yoke 113, 115 of the casing 102a is thus constituted by the walls 113a, 115a-b of the casing 102a. The walls 113a, 115a-b are integrated into the casing 102a, and form protrusions of the casing 102a. The walls 113a, 115a-b can be made by any process, for example these walls can be molded, cast, welded or machined in the mass. The front 112 and lower 114 male yokes are thus respectively housed between the walls 113a of the central female yoke 113 and between the walls 115a-b of the lower female yoke 115. The walls 113a, 115a-b thus form ears, located on either side of the vertical median plane XZ, and between which the front 112 and lower 114 male yokes are arranged.
[0067] In the same way, for safety reasons, the front male yoke is composed of two front fittings 110a-b, which are here symmetrical with respect to the vertical median plane XZ. The two front fittings 110a-b are arranged on either side of the vertical median plane XZ and they are fixed to each other and to the engine mast 104 by any suitable fixing means such as screw elements, welding points, etc. The two front fittings HOa-b can be machined from the mass.
[0068] Each front fitting 110a-b has a front sub-bore, and the two front sub-bores extend and form the first front bore.
[0069] Similarly, for safety reasons, the lower male yoke 114 is composed of two lower fittings 134a-b, which are here symmetrical with respect to the vertical median plane XZ. The two lower fittings 134a-b are arranged on either side of the vertical median plane XZ and they are fixed to each other and to the engine mast 104 by any suitable fixing means such as screw elements, weld points, etc. The two lower fittings 134a-b can be machined from a solid.
[0070] Each lower fitting 134a-b has a lower sub-bore, and the two lower sub-bores extend and form the first lower bore.
[0071] When the engine 102 is in operation, forces are generated and they are transmitted to the structure of the wing through the attachment system 150, that is to say, among others, the casing 102a and the engine pylon 104, through a primary force path.
[0072] Thus, certain elements of the attachment system 150 provide the primary force path while other elements provide secondary force paths which compensate for a failure of the primary force path, these other elements constituting waiting fail-safe means.
[0073] According to a first embodiment of the invention, the axes of one of the pairs among the pair comprising the first port axis 124 and the second port axis 126 and the pair comprising the first starboard axis and the second starboard axis, are fitted in the associated bores. That is to say that either the port axes 124 and 126 and the associated pair of connecting rods 118 provide the primary force path, or the starboard axes and the associated pair of connecting rods provide the primary force path.
[0074] According to this first embodiment, the axes of the other pair are mounted with radial play in the associated bores, that is to say, the axes of the other pair ensure the secondary path of efforts.
[0075] Still in this first embodiment, the lower axis 122 is mounted adjusted in the associated bores to ensure the primary force path and the front axis 120 is mounted with radial play in the associated bores to ensure the secondary force path.
[0076] According to a second embodiment of the invention, and as for the first embodiment, the axes of one of the pairs among the pair comprising the first port axis 124 and the second port axis 126 and the pair comprising the first starboard axis and the second starboard axis, are fitted in the associated bores. That is to say that either the port axes 124 and 126 and the associated pair of connecting rods 118 provide the primary force path, or the starboard axes and the associated pair of connecting rods provide the primary force path.
[0077] According to this second embodiment, the axes of the other pair are mounted with radial play in the associated bores to ensure the secondary force path.
[0078] In this second embodiment, the lower axis 122 is mounted with radial clearance in the associated bores to ensure the secondary force path and the front axis 120 is mounted adjusted in the associated bores to ensure the primary force path.
[0079] Adjusted assemblies allow a transfer of forces directly from one part to another, while the presence of a clearance does not allow the transfer of forces directly. This transfer of forces becomes possible only if an element of the primary path of forces is defective and two elements which are mounted with clearance relative to each other move to cancel the clearance and come into contact, and thus ensure the transfer of forces.
Claims
Claims
1. A front engine attachment system (150) for an aircraft engine (100), the front engine attachment system (150) having a vertical median plane (XZ) and comprising: - a reactor mast (104) comprising at a front part (163), a nose (110) having at the vertical median plane (XZ) and at the front of the nose (110), a front male yoke (112) having a first front bore extending in a transverse direction (Y) which is orthogonal to the vertical median plane (XZ), and at the vertical median plane (XZ) and under the nose (110), a lower male yoke (114) having a first lower bore extending in the transverse direction (Y), and on either side of the vertical median plane (XZ), a first port male yoke (107) extending orthogonally to the vertical median plane (XZ) and having a first port bore coaxial with a first port axis (116a) parallel to a longitudinal direction (X) and a first starboard male yoke extending orthogonally to the vertical median plane (XZ) and having a first starboard bore coaxial with a first starboard axis parallel to the longitudinal direction (X), - a casing (102a) of the engine (102) comprising a front female yoke (113) having a second front bore extending in the transverse direction (Y), a lower female yoke (115) having a second lower bore extending in the transverse direction (Y), a second port male yoke (109) having a second port bore extending in the longitudinal direction (X), and a second starboard male yoke having a second starboard bore extending in the longitudinal direction (X), - at least a first port connecting rod (118a) having a first and a second bore, - at least a first starboard connecting rod having a third and a fourth bore, - a front axle (120) extending in the transverse direction (Y) mounted in the first front bore and in the second front bore, - a lower axle (122) extending in the transverse direction (Y) mounted in the first lower bore and the second lower bore, - a first port axle (124) mounted in the first port bore and the first bore of the first port connecting rod (118a), - a second port pin (126) mounted in the second port bore and the second bore of the first port connecting rod (118a), - a first starboard pin mounted in the first starboard bore and the first bore of the first starboard connecting rod, and - a second starboard pin mounted in the second starboard bore and the second bore of the first starboard connecting rod.
2. Front engine attachment system (150) according to claim 1, characterized in that the casing (102a) takes the form of a crown and in that each front and lower female yoke (113, 115) of the casing (102a) is constituted by walls (113a, 115a-b) of the casing (102a) arranged on either side of the vertical median plane (XZ) and constituting protrusions of the casing (102a) between which the front (112) and lower (114) male yokes are arranged.
3. Front engine attachment system (150) according to one of claims 1 or 2, characterized in that the front male yoke (112) consists of two front fittings (HOa-b), where each front fitting (HOa-b) has a front sub-bore, where the two front sub-bores extend and form the first front bore.
4. Front engine attachment system (150) according to one of claims 1 to 3, characterized in that the lower male yoke (114) consists of two lower fittings (134a-b), where each lower fitting (134a-b) has a lower sub-bore, where the two lower sub-bores extend and form the first lower bore.
5. Front engine attachment system (150) according to one of claims 1 to 4, characterized in that said front engine attachment system (150) also comprises a second port connecting rod (118b) having a first and a second bore, where the first port pin (124) is also mounted in the first bore of the second port connecting rod (118b), where the second port pin (126) is also mounted in the second bore of the second port connecting rod (118b), the first and second port connecting rods (118a, 118b) being mounted in parallel around the first and second port male yokes (107, 109), and in that said front engine attachment system (150) also comprises a second starboard connecting rod having a third and a fourth bore, where the first starboard pin is also mounted in the third bore of the second starboard connecting rod, where the second starboard pin is also mounted in the fourth bore of the second starboard connecting rod, the first and second starboard connecting rods being mounted in parallel around the first and second starboard male yokes.
6. Front engine attachment system (150) according to one of claims 1 to 5, characterized in that the axes of one of the pairs among the pair comprising the first port axis (124) and the second port axis (126) and the pair comprising the first starboard axis and the second starboard axis, are mounted adjusted in the associated bores, in that the axes of the other of the pairs are mounted with a radial clearance in the associated bores, in that the lower axis (122) is mounted adjusted in the associated bores and in that the front axis (120) is mounted with a radial clearance in the associated bores.
7. Front engine attachment system (150) according to one of claims 1 to 5, characterized in that the axes of one of the pairs among the pair comprising the first port axis (124) and the second port axis (126) and the pair comprising the first starboard axis and the second starboard axis, are mounted adjusted in the associated bores, in that the axes of the other of the pairs are mounted with a radial clearance in the associated bores, in that the lower axis (122) is mounted with a radial clearance in the associated bores and in that the front axis (120) is mounted adjusted in the associated bores.
8. An aircraft (100) comprising a structure, an engine (102) and a forward engine attachment system (150) according to one of the preceding claims, wherein the engine pylon (104) is fixed to the structure and wherein the casing (102a) is a casing of the engine (102).