Assembly for attaching pylon to aircraft engine

Abstract

The invention relates to an assembly for attaching a pylon (104) to an aircraft engine (102), the assembly comprising an engine front mount (150) comprising a front tang (112) and a front clevis (113), a lower tang (114) and a lower clevis (115), and a port / starboard link (118), the front tang and the front clevis connect the attachment pylon and the engine via a front pin (120) mounted in the front tang and the front clevis, and the lower tang and the lower clevis connect the attachment pylon and the engine via a lower pin (122) mounted in the lower tang and the lower clevis, and a port / starboard link mounted between the attachment pylon and the engine via a mounting pin, where the front pin and the lower pin are orthogonal to the mid-plane (XZ), and where the mounting pin of the link is parallel to the mid-plane (XZ). The vertical occupied space of the assembly is reduced.

Description

Technical Field

[0001] The invention relates to an assembly of an attachment pylon to an aircraft engine, comprising a mounting system in the form of an engine front mount, wherein the mounting system is compact, and to an aircraft comprising at least one such assembly. Background Art

[0002] An aircraft generally comprises at least one engine, in particular a turbojet engine. Under each wing and for each engine, the aircraft comprises an engine pylon, which is fastened to the structure of the wing and extends under the wing, and under which the engine is suspended.

[0003] The engine is housed in the nacelle and secured to the engine pylon by an engine mounting system comprising an engine front suspension mount on a first interface plane, an engine rear suspension mount on a second interface plane, and a thrust absorbing path which may be incorporated into one of the two engine suspension interface planes or separately into a third interface plane.

[0004] The various types of engine front mountings currently used are all satisfactory. However, in order to improve the performance of the engine, the fans of new engines are getting bigger and bigger, which correspondingly reduces the distance between the fairing of the nacelle and the ground.

[0005] This means that a new type of arrangement has to be defined which makes it possible to reduce the height of the front engine mounting in order to move the nacelle further away from the ground and therefore the nacelle has to be moved closer to the wing. Summary of the invention

[0006] An object of the present invention is to propose an engine front mounting system for an aircraft engine, the engine front mounting system comprising an engine pylon and an engine casing, the combination of which ensures a reduced overall height.

[0007] To this end, an assembly of an attachment pylon and an aircraft engine is proposed, the attachment pylon comprising a primary structure including an upper spar, a lower spar, a port side panel and a starboard side panel, and a front transverse reinforcement, the assembly having a vertical midplane and comprising an engine front mounting fastened to the attachment pylon and to the outer casing of the engine and comprising:

[0008] - a front tang in the vertical midplane and on one of the front transverse reinforcement of the pylon and the casing of the engine,

[0009] - a front connecting fork centered on the vertical midplane and on the other of the front transverse reinforcement of the pylon and the casing of the engine,

[0010] - and a lower tang in the vertical midplane and on one of the lower spar to which the pylon is attached and the casing of the engine,

[0011] - a lower connecting fork centered on the vertical midplane and on the other of the lower spar to which the pylon is attached and the casing of the engine,

[0012] - a first port tang and a first starboard tang extending orthogonally to the vertical median plane, for each port and starboard lateral panel, or on the forward transverse stiffener,

[0013] - a second port tang and a second starboard tang for the casing of the engine,

[0014] - at least the first port link and the first starboard link,

[0015] - a front pin, which connects the front tang to the front connecting fork,

[0016] - a lower pin connecting the lower tang to the lower connecting fork,

[0017] - a first port pin connecting the first port tang with the first port connecting rod and a first starboard pin connecting the first starboard tang with the first starboard connecting rod,

[0018] - a second port pin connecting the second port tang with the first port link and a second starboard pin connecting the second starboard tang with the first starboard link.

[0019] According to one embodiment, the front tang is arranged on the front transverse reinforcement of the attachment pylon and the front connecting fork is arranged on the outer casing of the engine.

[0020] According to one embodiment, the front connecting fork is arranged on the front transverse reinforcement of the attachment pylon and the front tang is arranged on the outer casing of the engine.

[0021] According to one embodiment, the lower tang is arranged on the lower spar of the attachment pylon and the lower clevis is arranged on the casing of the engine.

[0022] According to one embodiment, the lower clevis is arranged on the lower spar of the attachment pylon and the lower tang is arranged on the casing of the engine.

[0023] According to one embodiment, the casing of the engine is in the form of a ring, and each front and lower connecting fork of the casing of the engine is formed by walls of the casing, which are positioned on both sides of a vertical midplane and form protrusions protruding from the casing, and the front and lower tangs of the attachment pylon are positioned between these walls.

[0024] According to one embodiment, the front tang is constituted by two front plates.

[0025] According to one embodiment, the lower tang is constituted by two lower plates.

[0026] According to one embodiment, the engine front mounting member further includes a second port link and a second starboard link, the first port pin also connects the first port tang with the second port link, the first starboard pin also connects the first starboard tang with the second starboard link, the second port pin also connects the second port tang with the second port link, the second starboard pin also connects the second starboard tang with the second starboard link, the first and second port links are installed in parallel around the first and second port tangs, and the first and second starboard links are installed in parallel around the first and second starboard tangs.

[0027] According to one embodiment, the pins of one of the pair of pins including a first port pin and a second port pin and the pins of one of the pair of pins including a first starboard pin and a second starboard pin connect the attachment pylon to the outer casing of the engine without play, wherein the pins of the other pair of pins connect the attachment pylon to the outer casing of the engine with play, the lower pin connects the attachment pylon to the outer casing of the engine without play, and the front pin connects the attachment pylon to the outer casing of the engine with play.

[0028] According to one embodiment, the pins of one of the pair of pins including a first port pin and a second port pin and the pins of the pair of pins including a first starboard pin and a second starboard pin connect the attachment pylon to the outer casing of the engine without play, wherein the pins of the other pair of pins connect the attachment pylon to the outer casing of the engine with play, the lower pin connects the attachment pylon to the outer casing of the engine with play, and the front pin connects the attachment pylon to the outer casing of the engine without play.

[0029] An aircraft is also proposed, comprising an assembly of an attachment pylon and an aircraft engine according to the invention.

[0030] The present invention therefore relates to an engine front mounting system for an aircraft engine, the engine front mounting system having a vertical mid-plane and comprising:

[0031] - an engine pylon comprising: a nose on the front part, the nose being in a vertical midplane and having a front tang at the front of the nose, the front tang having a first front hole extending in a transverse direction orthogonal to the vertical midplane; a lower tang being in the vertical midplane and below the nose and having a first lower hole extending in the transverse direction; and a first port tang and a first starboard tang on either side of the vertical midplane, the first port tang extending orthogonally to the vertical midplane and having a first port hole coaxial with a first port pin parallel to the longitudinal direction, the first starboard tang extending orthogonally to the vertical midplane and having a first starboard hole coaxial with a first starboard pin parallel to the longitudinal direction,

[0032] - a housing of the engine, comprising: a front clevis having a second front hole extending in the transverse direction; a lower clevis having a second lower hole extending in the transverse direction; a second port tang having a second port hole extending in the longitudinal direction; and a second starboard tang having a second starboard hole extending in the longitudinal direction,

[0033] - at least a first port link having a first hole and a second hole,

[0034] - at least a first starboard link having a third hole and a fourth hole,

[0035] - a front pin extending in the transverse direction and mounted in the first front hole and the second front hole,

[0036] - a lower pin extending in the transverse direction and mounted in the first lower hole and the second lower hole,

[0037] - a first port pin mounted in the first port hole and in the first hole of the first port link,

[0038] - a second port pin mounted in the second port hole and in the second hole of the first port link,

[0039] - a first starboard pin mounted in the first starboard hole and in the third hole of the first starboard link, and

[0040] - A second starboard pin mounted in the second starboard hole and in the fourth hole of the first starboard link.

[0041] Such a mounting system has a reduced vertical footprint.

[0042] Advantageously, the housing is in the form of a ring and each front and lower fork of the housing is formed by walls of the housing positioned on either side of a vertical midplane and forming a projection from the housing, between which walls the front and lower tangs are positioned.

[0043] Advantageously, the front tang consists of two front plates, wherein each front plate has a front sub-aperture, wherein the two front sub-apertures continue with one another and form the first front aperture.

[0044] Advantageously, the lower tang is composed of two lower plates, wherein each lower plate has a lower sub-hole, wherein the two lower sub-holes continue with one another and form the first lower hole.

[0045] Advantageously, the engine front mounting system further comprises a second port link having a first hole and a second hole, wherein the first port pin is also mounted in the first hole of the second port link, wherein the second port pin is also mounted in the second hole of the second port link, the first port link and the second port link being mounted in parallel around the first port tang and the second port tang, and the engine front mounting system further comprises a second starboard link having a third hole and a fourth hole, wherein the first starboard pin is also mounted in the third hole of the second starboard link, wherein the second starboard pin is also mounted in the fourth hole of the second starboard link, the first starboard link and the second starboard link being mounted in parallel around the first starboard tang and the second starboard tang.

[0046] According to a particular embodiment, the pins of one of the pair of pins comprising a first port pin and a second port pin and the pair of pins comprising a first starboard pin and a second starboard pin are mounted without play in associated holes, wherein the pins of the other pair of pins are mounted with radial play in associated holes, the lower pin is mounted without play in the associated hole, and the front pin is mounted with radial play in the associated hole.

[0047] According to a particular embodiment, the pins of one of the pair of pins comprising a first port pin and a second port pin and the pair of pins comprising a first starboard pin and a second starboard pin are mounted without play in associated holes, wherein the pins of the other pair of pins are mounted with radial play in associated holes, the lower pin is mounted with radial play in the associated hole, and the front pin is mounted without play in the associated hole.

[0048] The invention also proposes an aircraft comprising a structure, an engine and an engine front mounting system according to one of the aforementioned variants, wherein the engine pylon is fastened to the structure and wherein the outer shell is the outer shell of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0049] The foregoing and other features of the present invention will become more apparent upon reading the following description of an exemplary embodiment, which description is given with reference to the accompanying drawings, in which:

[0050] Figure 1 is a side view of an aircraft according to the invention, and

[0051] Figure 2 is a perspective view of an assembly of an attachment pylon and an aircraft engine according to the present invention. DETAILED DESCRIPTION

[0052] In the following description, position-related terms are given with reference to the aircraft in a forward-travel position, i.e. Figure 1 An aircraft is shown with arrow F indicating the direction of forward travel.

[0053] Figure 1 An aircraft 100 is shown having an engine 102 , in particular a turbojet engine, which is fastened under an attachment pylon, also referred to as engine pylon 104 , and in turn under a wing 106 .

[0054] In the following description, by convention, the longitudinal direction of the engine 102 oriented forward in the direction of travel of the aircraft 100 is referred to as X, the lateral direction of the engine 102 that is horizontal when the aircraft 100 is on the ground is referred to as Y, and the vertical direction or vertical height when the aircraft 100 is on the ground is referred to as Z, and these three directions X, Y and Z are orthogonal to each other.

[0055] The engine 102 generally has a shape that exhibits rotational symmetry about a longitudinal axis X.

[0056] exist Figure 1 In the illustrated embodiment of the present invention, the aircraft 100 includes one engine 102 beneath each wing 106 of the aircraft 100 , although multiple engines may be disposed beneath each wing 106 .

[0057] Figure 2 The port portion of an assembly of an attachment pylon 104 and an aircraft engine 102 according to the invention is shown, the port portion comprising an engine front mounting system 150 (also referred to as engine front mounting) for the engine 102 , the starboard portion being generally symmetrical with the port portion about a vertical midplane XZ of the assembly.

[0058] The assembly includes the outer shell 102 a of the engine 102 fastened to the engine pylon 104 and the engine pylon 104 fastened to the structure of the wing 106 , and more generally to the structure of the aircraft 100 .

[0059] The housing 102a is the outer shell of the engine 102 and here has the general form of a cylinder around the longitudinal direction X. The engine 102 will not be described in more detail, as the engine may take any form known to a person skilled in the art.

[0060] The assembly is fastened to the structure of the aircraft 100 , here the structure of the wing 106 , and extends underneath the wing 106 , and supports the engine 102 by means of its outer casing 102 a.

[0061] Typically, the rear engine mount is secured between the engine pylon 104 and the rear portion of the engine 102 and may take any form known to those skilled in the art.

[0062] The engine pylon 104 is in the form of a box, which here comprises an upper wall 104a (also referred to as an upper spar), a lower wall 104b (also referred to as a lower spar) and two lateral walls 104c-d (also referred to as a port lateral panel and a starboard lateral panel). The walls 104a-d are rigidly connected to each other to form a box, the vertical section of which is generally trapezoidal.

[0063] The engine pylon 104 comprises, on the front portion 163 of the box, a front transverse reinforcement, also called nose 110, fastened to the front portion 163 by any known means, such as welding or bolting. The front portion 163 corresponds to the front end of the walls 104a-d.

[0064] In the following description, Figure 2 Only the elements on the port side are visible in , but the elements on the starboard side are symmetrical about the vertical midplane XZ.

[0065] The nose 110 has a front tang 112 which is in the vertical midplane XZ and through which passes a first front hole coaxial with the front pin 112a at the front of the nose 110. In other words, the front transverse reinforcement 110 comprises a front tang 112 in the vertical midplane XZ. According to another embodiment, the front transverse reinforcement 110 comprises a front connecting fork centred on the vertical midplane XZ.

[0066] The lower wall 104b (or below the nose 110) has a lower tang 114, in the vertical midplane XZ, through which passes a first lower hole coaxial with the lower pin 114a. Here, the lower pin 114a is parallel to the front pin 112a. Both the lower pin 114a and the front pin 112a extend in a transverse direction Y perpendicular to the vertical midplane XZ and therefore extend generally parallel to the transverse direction Y. In other words, the lower spar 104b comprises a lower tang 114 in the vertical midplane XZ. According to another embodiment, the lower spar 104b comprises a lower connecting fork centered on the vertical midplane XZ. According to another embodiment, the transverse reinforcement 110 comprises a lower tang 114 in the vertical midplane XZ, below said front transverse reinforcement 110. According to another embodiment, the transverse reinforcement 110 comprises a lower connecting fork centered on the vertical midplane XZ, arranged below the transverse reinforcement 110.

[0067] On both sides of the vertical midplane XZ, the nose 110 has lateral reinforcements 111 extending perpendicularly to the vertical midplane XZ. Thus, there is: a port lateral reinforcement 111 comprising a first port tang 107 extending orthogonally to the vertical midplane XZ and through which passes a first port hole coaxial with the first port pin 116a; and a starboard lateral reinforcement comprising a first starboard tang extending orthogonally to the vertical midplane XZ and through which passes a first starboard hole coaxial with the first starboard pin. In other words, the front transverse reinforcement 110 comprises a first port tang 107 and a first starboard tang extending orthogonally to the vertical midplane XZ. According to one embodiment, the port lateral wall or lateral panel and the starboard lateral wall or lateral panel 104c-d each comprise a first port tang 107 and a first starboard tang extending orthogonally to the vertical midplane XZ.

[0068] Here, the housing 102a is in the form of a ring and comprises a front connecting fork 113 through which passes a second front hole coaxial with the front pin 112a. According to one embodiment, the housing 102a of the engine 102 comprises a front tang.

[0069] The housing 102a also has a lower connecting fork 115 through which passes a second lower hole coaxial with the lower pin 114a. According to one embodiment, the housing 102a of the engine 102 comprises a lower tang.

[0070] Each connecting fork 113, 115 of the housing 102a of the engine 102 is composed of two walls 113a ( Figure 2 The front tang 112 and the lower tang 114 of the attachment pylon 104 are arranged between the two walls 113a, 115a-b of the casing 102a of the engine 102 so as to form a fork connection.

[0071] Thus, the two walls 113a, 115a-b forming each connecting fork 113, 115 are generally parallel to the vertical midplane XZ and each wall is passed through by a hole which, together with the hole of the other wall, forms a second front hole or a second lower hole.

[0072] On either side of the vertical midplane XZ, the housing 102a has lateral flanges 117 extending perpendicularly to the vertical midplane XZ. Thus, there is a port lateral flange 117 comprising a second port tang 109 through which passes a second port hole coaxial with the second port pin 116b, and a starboard lateral flange comprising a second starboard tang through which passes a second starboard hole coaxial with the second starboard pin. The second port / starboard hole is outboard relative to the first port / starboard hole of the port lateral reinforcement 111.

[0073] The first port pin 116a is parallel to and spaced apart from the second port pin 116b. Similarly, the first starboard pin is parallel to and spaced apart from the second starboard pin.

[0074] The engine front mount 150 further includes: a pair of port links 118, the pair of port links including a first port link 118a having a first hole and a second hole and a second port link 118b having a first hole and a second hole; and a pair of starboard links including a first starboard link and a second starboard link, the first starboard link and the second starboard link each having a third hole and a fourth hole. The paired links 118 are positioned on both sides of the vertical midplane XZ, and here, each link 118 is contained in the lateral plane YZ.

[0075] For safety reasons, the first and second port links 118a, 118b are mounted parallel to each other around the first and second port tangs 107, 109 between the associated first and second pins 124, 126. Thus, the first and second port links 118a, 118b are each pierced with a hole making it possible to receive the corresponding pin 124, 126. In the event of a failure of one of the first and second port links 118a, 118b, the pair of starboard links thus takes over.

[0076] Each pair of links 118 forms a connecting fork in which the lateral reinforcements 111 of the nose 110 and the lateral flanges 117 of the casing 102a are positioned.

[0077] The engine front mount 150 also includes a front pin 120 (also called a front axle) extending in the transverse direction Y and mounted in the first and second front holes so as to create a fork assembly between the front tang 112 and the front fork 113, i.e. a pivot connection around the front pin 112a. In other words, the front pin 120 connects the front tang 112 and the front fork 113.

[0078] The engine front mount 150 also includes a lower pin 122 (also referred to as a lower shaft) extending in the transverse direction Y and mounted in the first lower hole and the second lower hole to create a connecting fork assembly between the lower tang 114 and the lower connecting fork 115, i.e., a pivot connection around the lower pin 114a. In other words, the lower pin 122 connects the lower tang 114 and the lower connecting fork 115.

[0079] The engine front mount 150 also includes a first port pin 124 (also referred to as a first port shaft) mounted in the first port hole, the first hole of the first port link 118a, and the first hole of the second port link 118b to create a pivot connection about the first port pin 116a between the first port hole and the pair of port links 118. In other words, the first port pin 124 connects the first port tang 107 and the first port link 118a.

[0080] The engine front mount 150 further includes a second port pin 126 (also referred to as a second port shaft) mounted in the second port hole, the second hole of the first port link 118a, and the second hole of the second port link 118b to create a pivot connection about the second port pin 116b between the second port hole and the pair of port links 118. In other words, the second port pin 126 connects the second port tang 109 and the first port link 118a.

[0081] A symmetrical installation of the starboard links is envisioned, wherein a first starboard pin (also referred to as a first starboard shaft) is installed in a first starboard hole and a first hole of a first link and a first hole of a second link in a pair of starboard links so as to form a pivot connection about the first starboard pin, and a second starboard pin (also referred to as a second starboard shaft) is installed in a second starboard hole and a second hole of the first link and a second hole of the second link in the pair of starboard links so as to create a pivot connection about the second starboard pin. In other words, the first starboard pin connects the first starboard tang and the first starboard link, and the second starboard pin connects the second starboard tang and the first starboard link.

[0082] In this assembly, the front pin 112a and the lower pin 114a extend in the transverse direction Y and perpendicular to the midplane XZ, and the first port pin 116a, the first starboard pin, the second port pin 116b and the second starboard pin are parallel to the midplane XZ and generally parallel to the longitudinal direction X.

[0083] Such an assembly makes it possible to reduce the height of the casing 102 a and also makes it possible to reduce the height of the upper aerodynamic line of the secondary flow of the engine 102 , known as the spine, ie the flow around the nose 110 .

[0084] Each pin is prevented from translation by any suitable means known to those skilled in the art, such as a nut, and each shaft is coaxial with the axis in question.

[0085] With such a front engine mount 150 and an appropriate rear engine mount, the entire engine mounting system is said to be "isostatic", ie it prevents translations in the three directions X, Y and Z and the three rotations about these axes (Mx, My, Mz).

[0086] The engine front mount 150 makes it possible to control the shear loads in three directions X, Y and Z and, in combination with an appropriate engine rear mount, to control the moments My and Mz.

[0087] The loads in the directions X and Z are managed by the front pin 120 and the lower pin 122 , and the load in the direction Y is managed by the connecting rod 118 .

[0088] exist Figure 2 In the embodiment of the invention shown, the housing 102a is in the form of a 360° continuous ring and comprises: a central connecting fork 113, which includes a wall 113a, thereby forming a protrusion protruding from the housing 102a; and a lower connecting fork 115, which includes walls 115a-b, thereby forming a protrusion protruding from the housing 102a. Each connecting fork 113, 115 of the housing 102a is thus formed by the walls 113a, 115a-b of the housing 102a. The walls 113a, 115a-b are incorporated into the housing 102a and form a protrusion protruding from the housing 102a. The walls 113a, 115a-b can be produced by any method, for example, these walls can be molded, cast, welded or machined from a single piece. Therefore, the front tang 112 and the lower tang 114 are respectively accommodated between the walls 113a of the central connecting fork 113 and between the walls 115a-b of the lower connecting fork 115. The walls 113a, 115a-b thus form lugs situated on either side of the vertical mid-plane XZ and between which the front tang 112 and the lower tang 114 are arranged.

[0089] Similarly, for safety reasons, the front tang is formed by two front plates 110a-b, which are symmetrical here with respect to the vertical midplane XZ. The two front plates 110a-b are positioned on either side of the vertical midplane XZ and are fastened to each other and to the engine pylon 104 by any suitable fastening means, such as screw elements, welds, etc. The two front plates 110a-b can be machined from a single piece.

[0090] Each front plate 110a - b has a front sub-aperture, and the two front sub-apertures are continuous with each other and form a first front aperture.

[0091] Similarly, for safety reasons, the lower tang 114 is formed by two lower plates 134a-b, which are symmetrical here with respect to the vertical midplane XZ. The two lower plates 134a-b are positioned on either side of the vertical midplane XZ and are fastened to each other and to the engine pylon 104 by any suitable fastening means, such as screw elements, welds, etc. The two lower plates 134a-b can be machined from a single piece.

[0092] Each lower plate 134a-b has a lower sub-hole, and the two lower sub-holes are continuous with each other and form a first lower hole.

[0093] When the engine 102 is operating, loads are generated and are transferred to the structure of the wing through the primary load path through the engine forward mount 150 (ie, specifically the outer shell 102 a and the engine pylon 104 ).

[0094] Thus, some elements of the engine front mount 150 create a primary load path, while other elements provide a secondary load path that compensates for failure of the primary load path, these other elements forming a standby fail-safe device.

[0095] According to the first embodiment of the present invention, the pins of the pair of pins including the first port pin 124 and the second port pin 126 and the pins of one of the pair of pins including the first starboard pin and the second starboard pin are mounted in the associated holes without play. In other words, the pins of the pair of pins including the first port pin 124 and the second port pin 126 and the pins of one of the pair of pins including the first starboard pin and the second starboard pin connect the attachment pylon 104 to the housing 102a of the engine 102 without play. That is, the port pins 124 and 126 and the associated pair of connecting rods 118 provide the main load path, or the starboard pins and the associated pair of connecting rods provide the main load path.

[0096] According to this first embodiment, the pins of the other pair of pins are mounted with radial play in the associated holes, i.e. the pins of the other pair of pins provide a secondary load path. In other words, the pins of the other pair of pins connecting the attachment pylon 104 to the casing 102a of the engine 102 are mounted with play.

[0097] Still according to the first embodiment, the lower pin 122 is mounted in the associated hole without play to provide a primary load path, and the front pin 120 is mounted in the associated hole with radial play to provide a secondary load path. In other words, the lower pin 122 connects the attachment pylon 104 to the outer casing 102a of the engine 102 without play, and the front pin 120 connects the attachment pylon 104 to the outer casing 102a of the engine 102 with play.

[0098] According to the second embodiment of the present invention, and as in the first embodiment, the pair of pins including the first port pin 124 and the second port pin 126 and the pins in one of the pair of pins including the first starboard pin and the second starboard pin are mounted without play in the associated holes. That is, the port pins 124 and 126 and the associated pair of connecting rods 118 provide the main load path, or the starboard pin and the associated pair of connecting rods provide the main load path.

[0099] According to this second embodiment, the pins of the other pair of pins are mounted with radial play in the associated holes so as to provide a secondary load path.

[0100] In this second embodiment, the lower pin 122 is mounted in an associated hole with radial play to provide a secondary load path, and the front pin 120 is mounted in an associated hole without play to provide a primary load path. In other words, the lower pin 122 connects the attachment pylon 104 to the outer casing 102a of the engine 102 with play, and the front pin 120 connects the attachment pylon 104 to the outer casing 102a of the engine 102 without play.

[0101] Mounting without play allows a direct transfer of load from one part to another, whereas the presence of play does not allow a direct transfer of load. Such a load transfer is only possible if an element of the main load path is defective and two elements mounted with play relative to each other move to compensate for the play and come into contact and thus provide load transfer.

Claims

1. An assembly of an attachment pylon (104) and an engine of an aircraft (100), the attachment pylon (104) comprising a main structure, the main structure comprising an upper spar (104a), a lower spar (104b), port and starboard lateral panels (104c-d), and a front transverse reinforcement (110), the assembly having a vertical midplane (XZ) and comprising an engine front mounting (150), the engine front mounting being fastened to the attachment pylon (104) and to a casing (102a) of the engine (102), and comprising: - a front tang (112) in the vertical midplane (XZ) and on one of the front transverse reinforcement (110) of the attachment pylon (104) and the casing (102a) of the engine (102), - a front connecting fork (113) centered on the vertical midplane (XZ) and on the other of the front transverse reinforcement (110) of the attachment pylon (104) and the casing (102a) of the engine (102), - a lower tang (114) in the vertical mid-plane (XZ) and on one of a lower spar (104b) of the attachment pylon (104) and a casing (102a) of the engine (102), - a lower connecting fork (115) centered on the vertical midplane (XZ) and on the other of the lower spar (104b) of the attachment pylon (104) and the casing (102a) of the engine (102), - a first port tang (107) and a first starboard tang extending orthogonally to said vertical midplane (XZ), said first port tang and said first starboard tang being used for each port and starboard lateral panel (104c-d) or on said forward transverse stiffener (110), - a second port tang (109) and a second starboard tang, the second port tang and the second starboard tang being for a housing (102a) of the engine (102), - at least a first port link (118a) and a first starboard link, - a front pin (120) connecting the front tang (112) and the front connecting fork (113), - a lower pin (122) connecting the lower tang (114) and the lower connecting fork (115), - a first port pin (124) and a first starboard pin, the first port pin connecting the first port tang (107) with the first port connecting rod (118a), the first starboard pin connecting the first starboard tang with the first starboard connecting rod, - a second port pin (126) connecting the second port tang (109) to the first port link (118a) and a second starboard pin connecting the second starboard tang to the first starboard link.

2. The assembly of the attachment pylon (104) and the aircraft (100) engine according to claim 1, characterized in that: The front tang (112) is arranged on a front transverse reinforcement (110) of the attachment pylon (104), and the front connecting fork (113) is arranged on a housing (102a) of the engine (102).

3. The assembly of the attachment pylon (104) and the aircraft (100) engine according to claim 1, characterized in that: The front connecting fork (113) is arranged on the front transverse reinforcement (110) of the attachment pylon (104), and the front tang (112) is arranged on the outer casing (102a) of the engine (102).

4. The assembly of the attachment pylon (104) and the aircraft (100) engine according to any one of claims 1 to 3, characterized in that: The lower tang (114) is arranged on a lower spar (104b) of the attachment pylon (104), and the lower connecting fork (115) is arranged on a casing (102a) of the engine (102).

5. The assembly of the attachment pylon (104) and the aircraft (100) engine according to any one of claims 1 to 3, characterized in that: The lower connecting fork (115) is arranged on the lower spar (104b) of the attachment pylon (104), and the lower tang (114) is arranged on the casing (102a) of the engine (102).

6. The assembly of the attachment pylon (104) and the aircraft (100) engine according to claims 2 and 4, characterized in that: The housing (102a) of the engine (102) is in the form of a ring, and each front connecting fork and lower connecting fork (113, 115) of the housing (102a) of the engine (102) is formed by walls (113a, 115a-b) of the housing (102a), the walls are positioned on both sides of the vertical midplane (XZ) and form protrusions protruding from the housing (102a), and the front tang foot (112) and the lower tang foot (114) of the attachment pylon (104) are positioned between the walls.

7. Assembly of an attachment pylon (104) and an aircraft (100) engine according to one of the preceding claims, characterized in that The front tang (112) is formed by two front plates (110a-b).

8. Assembly of an attachment pylon (104) and an aircraft (100) engine according to one of the preceding claims, characterized in that The lower tang (114) is formed from two lower plates (134a-b).

9. Assembly of an attachment pylon (104) and an aircraft (100) engine according to one of the preceding claims, characterized in that: The engine front mounting member (150) further comprises a second port link (118b) and a second starboard link, the first port pin (124) further connects the first port tang (107) with the second port link (118b), the first starboard pin further connects the first starboard tang with the second starboard link, the second port pin (126) further connects the second port tang (109) with the second port link (118b), the second starboard pin further connects the second starboard tang with the second starboard link, the first and second port links (118a, 118b) are installed in parallel around the first and second port tangs (107, 109), and the first and second starboard links are installed in parallel around the first and second starboard tangs.

10. An assembly of an attachment pylon (104) and an aircraft (100) engine according to any one of claims 1 to 9, characterized in that: A pair of pins including the first port pin (124) and the second port pin (126) and a pin in one of a pair of pins including the first starboard pin and the second starboard pin connect the attachment pylon (104) to the housing (102a) of the engine (102) without play, wherein the pin in the other pair of pins connects the attachment pylon (104) to the housing (102a) of the engine (102) with play, the lower pin (122) connects the attachment pylon (104) to the housing (102a) of the engine (102) without play, and the front pin (120) connects the attachment pylon (104) to the housing (102a) of the engine (102) with play.

11. An assembly of an attachment pylon (104) and an aircraft (100) engine according to any one of claims 1 to 9, characterized in that: A pair of pins including the first port pin (124) and the second port pin (126) and a pin in one of a pair of pins including the first starboard pin and the second starboard pin connect the attachment pylon (104) to the housing (102a) of the engine (102) without play, wherein the pin in the other pair of pins connects the attachment pylon (104) to the housing (102a) of the engine (102) with play, the lower pin (122) connects the attachment pylon (104) to the housing (102a) of the engine (102) with play, and the front pin (120) connects the attachment pylon (104) to the housing (102a) of the engine (102) without play.

12. An aircraft (100) comprising an assembly of an attachment pylon (104) according to one of the preceding claims and an engine of the aircraft (100).

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