FR3101615A1 - Thruster assembly comprising an engine attachment having at least one connecting pin equipped with a translation and aircraft locking system comprising at least one such propellant assembly - Google Patents

Abstract

Thruster assembly comprising an engine attachment having at least one connecting pin equipped with a translation and aircraft locking system comprising at least one such propellant assembly The subject of the invention is a propulsion assembly for an aircraft comprising a connecting pin ( 76) of an engine attachment connecting first and second parts and comprising: a first hollow tube (88), housed in bores (86) provided in the first and second parts in operation and comprising at least one groove (90.1) near at least one of its first and second ends (88.1, 88.2), at least one locking plate (100.1, 100.2) comprising at least one locking hole (102) having a first part (104.1), delimited by a first edge (B104.1) configured to fit in the groove (90.1), and a second part (104.2), delimited by a second edge (B104.2) and configured to allow the introduction of the first hollow tube (88 ) in the blocking hole (1 02), the locking plate (100.1, 100.2) being movable between a first position in which the first edge (B104.1) of the first part (104.1) is accommodated, at least partially, in the groove (90.1) and a second position in which no edge of the locking hole (102) is positioned in the groove (90.1) of the first hollow tube (88), a locking system (106) making it possible to immobilize the locking plate (100.1) , 100.2) in the first position. Figure 7

Description

Propulsion assembly comprising an engine attachment having at least one connecting pin equipped with a system for locking in translation and aircraft comprising at least one such propulsion assembly

The present application relates to a propulsion assembly comprising an engine attachment having at least one connecting pin equipped with a translation locking system as well as to an aircraft comprising at least one such propulsion assembly.

According to one embodiment visible in Figures 1 and 2, an aircraft 10 comprises several thruster assemblies 12 positioned under each of the wings 14 of the aircraft. Each thruster assembly 12 comprises an engine 16, a nacelle (not shown in FIG. 2) positioned around the engine 16 as well as a mast 18 connecting the engine 16 and the wing 14. The mast 18 comprises a primary structure 20 which is connected to the engine 16 by an engine attachment 22 and to the wing 14 by an wing attachment 24.

For the present invention, a longitudinal direction X is parallel to the axis of rotation A16 of the motor 16, a horizontal transverse direction Y is horizontal and perpendicular to the axis of rotation A16 of the motor 16, a vertical transverse direction Z is vertical and perpendicular to the axis of rotation A16 of the engine 16. A transverse plane is perpendicular to the longitudinal direction X. The notions front and rear refer to the direction of flow of the gases, the front corresponding to the admission of the gases (air ) in the engine and the rear corresponding to the exhaust gases (combustion gases).

The engine attachment 22 comprises a front engine attachment 26, a rear engine attachment 28 and a pair of push rods 30 ensuring the recovery of the thrust forces.

1. une poutre transversale 32 reliée à la structure primaire 20 par des éléments de liaison 34 verticaux et au moteur 16 par un axe de liaison de sécurité 36,
2. une première bielle 38 reliée au moteur 16 par un premier axe de liaison moteur latéral 40 et à la poutre transversale 32 par deux axes de liaison poutre 42
3. une deuxième bielle 44 reliée au moteur 16 par un deuxième axe de liaison moteur latéral 46 et à la poutre transversale 32 par un axe de liaison poutre 48.

According to one embodiment visible in Figures 3 and 4, the rear engine mount 28 comprises:

1. a transverse beam 32 connected to the primary structure 20 by vertical connecting elements 34 and to the motor 16 by a safety connecting pin 36,
2. a first connecting rod 38 connected to the motor 16 by a first lateral motor connecting pin 40 and to the transverse beam 32 by two beam connecting pins 42
3. a second connecting rod 44 connected to the motor 16 by a second lateral motor connecting pin 46 and to the transverse beam 32 by a beam connecting pin 48.

Each beam connecting axis 42, 48 comprises a hollow tube 50 configured to be housed in bores 52, approximately parallel to the longitudinal direction, provided in the transverse beam 32 and the first or second connecting rod 38, 44, as well as a system locking in translation to hold the hollow tube 50 in the bores 52. According to one embodiment, the locking system in translation comprises first and second washers 54.1, 54.2 arranged at each of the ends of the hollow tube 50, resting respectively against end faces F32, F32' of the transverse beam 32 provided at each end of the bores 52, as well as a bolt 56 passing through the first and second washers 54.1, 54.2 and the hollow tube 50. This bolt 56 has a head 56.1 bearing against the first washer 54.1 and a nut 56.2 bearing against the second washer 54.2. To prevent the bolt 56 from unscrewing, the nut 56.2 is a slotted nut which cooperates with a pin 58 lodged in a hole passing through the threaded rod 56.3 of the bolt 56.

Each beam connecting axis 42, 48 comprises a large number of parts, which complicates the assembly/disassembly operations of the motor and lengthens the intervention time.

During the operation of the aircraft, each hollow tube 50 must be regularly inspected. To do this, it is necessary to dismantle the bolt 56, the first and second washers 54.1, 54.2, to inspect the hollow tube 50 and then to reassemble the bolt 56 and the first and second washers 54.1, 54.2. These different operations make inspection operations more complex and increase intervention time.

The present invention aims to remedy all or part of the drawbacks of the prior art.

To this end, the subject of the invention is a propulsion assembly for an aircraft comprising a primary structure of a mast, an engine as well as an engine attachment connecting the primary structure and the engine. The engine attachment comprises at least a first connecting pin connecting a first part which corresponds to a part of the engine or which is connected to the engine and a second part which corresponds to a part of the primary structure or which is connected to the primary structure . The first connecting pin comprises a first hollow tube, being housed in bores provided in the first and second parts and emerging at the first and second end faces, as well as a first translation locking system configured to immobilize the first hollow tube in the bores.

According to the invention, the first hollow tube comprises at least one groove, close to at least one of the first and second ends of the first hollow tube, positioned outside the bores and having a side approximately coplanar with one of the first and second end faces in operation. In addition, the first translation blocking system comprises at least one blocking plate having a thickness substantially equal to or slightly less than a width of the groove, configured to face one of the first or second end faces in operation , comprising at least one locking orifice having a first part, delimited by a first edge, and a second part, delimited by a second edge and configured to allow the introduction of the first hollow tube into the locking orifice, the locking being movable between a first position in which the first edge of the first part is housed at least partially in the groove and a second position in which no edge of the locking orifice is positioned in the groove. The first translation locking system also comprises a locking system making it possible to immobilize the locking plate in the first position.

The number of parts of the first connecting shaft being reduced, the assembly/disassembly of the motor is simplified and the intervention time reduced.

Since the first hollow tube is not blocked by the first translation locking system, it is possible to inspect it during operation of the aircraft without having to dismantle the first translation locking system.

According to another characteristic, the first hollow tube comprises a first groove positioned close to the first end of the first hollow tube as well as a second groove positioned close to the second end of the first hollow tube, the first and second grooves being separated by a distance substantially equal to a distance separating the first and second end faces. In parallel, the first translation blocking system comprises a first blocking plate cooperating with the first end of the first hollow tube as well as a second blocking plate cooperating with the second end of the first hollow tube.

According to another characteristic, the first part of the blocking orifice is a semicircle, positioned at a first end of the blocking orifice, having a diameter substantially equal to a diameter of the groove and the second part of the blocking orifice is a semi-circle, positioned at a second end of the blocking orifice, having a diameter greater than or equal to a diameter of the first or second end of the first hollow tube.

According to another characteristic, the locking system comprises a locking orifice, passing through the blocking plate, as well as a rod connected to the first or second part, passing through the locking orifice to immobilize the blocking plate in operation.

According to another characteristic, when the motor attachment comprises a second connecting pin comprising a second hollow tube and a second translation locking system having a bolt that is housed in the second hollow tube, the rod of the locking system is a threaded rod of the bolt.

According to another characteristic, the first hollow tube has, at least one of the first and second ends, at least one shape allowing it to be pivoted on itself manually.

The invention also relates to an aircraft comprising at least one propulsion unit according to one of the preceding characteristics.

Other characteristics and advantages will emerge from the description of the invention which follows, description given by way of example only, with regard to the appended drawings, among which:

is a side view of an aircraft,

is a side view of a podless thruster assembly,

is a front view of a rear engine mount which illustrates an embodiment of the prior art,

is a perspective view of part of the rear engine mount visible in Figure 3 illustrating a beam connecting pin in the disassembled state,

is a perspective view of a rear engine mount which illustrates one embodiment of the invention,

is a perspective view of part of the rear engine attachment visible in FIG. 5 illustrating a translation locking system in the locked state,

is a perspective view of part of the rear engine mount visible in Figure 5 illustrating two connecting pins in the disassembled state,

is a perspective view of a connecting pin and a translation locking system in the unlocked state,

is a section along line IX-IX of Figure 8 of a connecting axis,

is a perspective view of one end of a link pin which illustrates one embodiment of the invention, and

is a perspective view of a hollow tube of the connecting axis visible in Figure 10.

1. une poutre transversale 66 reliée à la structure primaire 62 par des éléments de liaison 68 verticaux et au moteur 64 par un axe de liaison de sécurité 70,
2. une première bielle 72 reliée au moteur 64 par un premier axe de liaison moteur 74 et à la poutre transversale 66 par des premier et deuxième axes de liaison poutre 76, 76’,
3. une deuxième bielle 78 reliée au moteur 64 par un deuxième axe de liaison moteur 80 et à la poutre transversale 66 par des premier et deuxième axes de liaison poutre 82, 82’.

According to an embodiment illustrated by FIG. 3, a rear engine attachment 60, connecting a primary structure 62 of a mast and an engine 64 of an aircraft, comprises:

1. a transverse beam 66 connected to the primary structure 62 by vertical connecting elements 68 and to the motor 64 by a safety connecting pin 70,
2. a first connecting rod 72 connected to the motor 64 by a first motor connecting pin 74 and to the transverse beam 66 by first and second beam connecting pins 76, 76',
3. a second connecting rod 78 connected to the motor 64 by a second motor connecting pin 80 and to the transverse beam 66 by first and second beam connecting pins 82, 82'.

According to another embodiment, the second connecting rod 78 is connected to the transverse beam 66 by a single beam connecting axis 82, as for the prior art visible in Figure 3.

For the rest of the description, the invention is described applied to the first connecting rod 72. However, it can be applied to the second connecting rod 78.

For each of the first and second beam connecting axes 76, 76', the first connecting rod 72 comprises at least one first bore 84 and the transverse beam 66 comprises at least one second bore 86. According to the configuration visible in FIGS. 5 to 7 and 9, the second bore 86 comprises two sections arranged on either side of the first bore 84 of the first connecting rod 72. When the transverse beam 66 and the first connecting rod 72 are connected by the first and second beam connecting axes 76, 76 ', the first and second bores 84, 86 are aligned and oriented approximately parallel to the longitudinal direction X.

The transverse beam 66 comprises first and second end faces F66, F66' at the level of which open the second bores 86 intended for the first and second beam connecting axes 76, 76'. The first and second end faces F66, F66' are approximately parallel to each other and approximately perpendicular to the longitudinal direction X.

The first beam connecting axis 76 comprises a first hollow tube 88 configured to be housed in the first and second bores 84 and 86. This hollow tube 88 is cylindrical, has an outer diameter substantially equal to that of the first and second bores 84, 86 This hollow tube 88 is positioned in the first and second bores 84 and 86 in operation.

The first hollow tube 88 comprises first and second ends 88.1, 88.2, at least one of the first and second ends 88.1, 88.2 projecting with respect to one of the first and second end faces F66, F66' of the beam transverse 66 in operation. According to an embodiment visible in particular in Figure 9, the first and second ends 88.1, 88.2 project relative to the first and second end faces F66, F66' of the transverse beam 66 in operation.

The first hollow tube 88 comprises at least one groove 90.1, 90.2 close to at least one of the first and second ends 88.1, 88.2, positioned outside the first and second bores 84, 86 in operation. According to a configuration visible in particular in Figure 9, the first hollow tube 88 comprises a first groove 90.1 positioned close to the first end 88.1 of the hollow tube 88 and a second groove 90.2 close to a second end 88.2 of the hollow tube 88. These first and second grooves 90.1, 90.2 extend over the entire circumference of the hollow tube.

Each of the first and second grooves 90.1, 90.2 comprises a first flank 94.1, 94.2 close to the first or second end 88.1, 88.2, a second flank 96.1, 96.2 parallel to the first flank 94.1, 94.2 and more distant from the first or second end 88.1 , 88.2 as the first flank 94.1, 94.2 as well as a bottom 98.1, 98.2 connecting the first and second flanks 94.1, 96.1/94.2, 96.2. Each of the first and second grooves 90.1, 90.2 has a width which corresponds to the distance separating the first and second sides 94.1, 96.1/94.2, 96.2 as well as a diameter which corresponds to the diameter of the bottom 98.1, 98.2.

In operation, the second flanks 96.1, 96.2 of the first and second grooves 90.1, 90.2 are approximately coplanar with the first and second end faces F66, F66' of the transverse beam 66. Thus, the second flanks 96.1, 96.2 of the first and second grooves 90.1, 90.2 of the hollow tube 88 are separated by a distance substantially equal to the distance separating the first and second end faces F66, F66' of the transverse beam 66.

According to one configuration, the hollow tube 88 has a first diameter between the first and second grooves 90.1, 90.2 as well as a second diameter smaller than the first diameter between each of the first and second grooves 90.1, 90.2 and the first or second end 88.1, 88.2 the closest.

According to one embodiment visible in Figures 10 and 11, the hollow tube 88 has, at least one of its first and second ends 88.1, 88.2, at least one shape allowing it to be pivoted on itself manually. According to one configuration, the hollow tube 88 comprises, at a first end 88.1, two diametrically opposed lugs 99, projecting with respect to the first end 88.1.

The first beam connection axis 76 comprises at least one translation blocking system configured to occupy a blocked state in which it cooperates with the hollow tube 88 and immobilizes it in translation in a direction parallel to the longitudinal direction X as well as a unlocked state in which it no longer immobilizes the hollow tube 88 in translation.

The translation blocking system comprises at least one blocking plate 100.1, 100.2 which has a thickness substantially equal to or slightly less than the width of the first or second groove 90.1, 90.2. Each blocking plate 100.1, 100.2 has first and second faces F1, F2, one of them being configured to face one of the first and second end faces F66, F66' of the transverse beam 66 in functioning. Each blocking plate 100.1, 100.2 also comprises at least one blocking orifice 102, opening at the level of the first and second faces F1, F2, comprising a first part 104.1, delimited by a first edge B104.1 and a second part 104.2 delimited by a second edge B104.2 and configured to allow the introduction of the hollow tube 88 into the blocking orifice 102. Each blocking plate 100.1, 100.2 is movable between a first position, corresponding to the blocked state visible in Figure 6 , in which the first edge B104.1 of the first part 104.1 is, at least partially, housed in the first or second groove 90.1, 90.2, as well as a second position, corresponding to the unlocked state visible in FIG. 8, wherein no edge of the blocking hole 102 is positioned in the first or second groove 90.1, 90.2

According to one configuration, the locking orifice 102 is oblong. The first part 104.1 of the locking orifice 102 is a semicircle, positioned at a first end of the locking orifice 102, having a diameter substantially equal to the diameter of the first or second groove 90.1, 90.2 and the second part 104.2 of the locking orifice 102 is a semicircle, positioned at a second end of the locking orifice 102, having a diameter greater than or equal to the second diameter of the first or second end 88.1, 88.2 of the hollow tube 88. Thus, in the first position, the first or second end 88.1, 88.2 of the hollow tube 88 is coaxial with the first part 104.1 of the locking orifice 102 and, in the second position, the first or second end 88.1, 88.2 of the tube hollow 88 is coaxial with the second part 104.2 of the locking orifice 102. According to this configuration, to pass from the first position to the second position and vice versa, each locking plate 100.1, 100.2 translates according to a direction of displacement parallel to a straight line passing through the center of the semicircle forming the first part 104.1 and the center of the semicircle forming the second part 104.2.

The blocking system also includes a locking system 106 making it possible to immobilize the blocking plate 100.1, 100.2 in the first position corresponding to the blocked state. This locking system 106 comprises a locking hole 108 passing through the first or second locking plate 100.1, 100.2, as well as a rod 110 connected directly or indirectly to the transverse beam 66 and being housed in the locking hole 108 to immobilize the first or second blocking plate 100.1, 100.2 in operation, the locking orifice 108 and the rod 110 having identical substantial diameters to immobilize the blocking plate 100.1, 100.2 in a plane perpendicular to the longitudinal direction X.

According to a first configuration, the rod 110 corresponds to the rod of a screw, exclusively dedicated to the locking function of the blocking plate 100.1, 100.2, which is screwed into a threaded bore of the transverse beam 66.

According to another configuration visible in Figures 5 to 7, the rod 110 corresponds to the rod of a bolt 112 of a second locking system in translation of a second connecting pin according to the prior art.

The translation locking system may comprise a single locking plate 100.1 which cooperates with a single end 88.1 of at least one hollow tube 88 or, as illustrated in FIGS. 7 and 9, a first locking plate 100.1 which cooperates with the first end 88.1 of at least one hollow tube 88 and a second blocking plate 100.2 which cooperates with the second end 88.2 of at least one hollow tube 88.

According to an embodiment visible in Figures 5 to 7, each locking plate 100.1, 100.2 comprises a locking hole 102 and a locking hole 108.

According to another embodiment, each locking plate 110.1, 100.2 comprises several locking holes 102, each cooperating with a hollow tube 88 provided with grooves 90.1, 90.2, and a locking hole 108.

To reduce its mass and increase its rigidity, each locking plate 100.1, 100.2 is perforated between the locking hole(s) 102 and the locking hole 108.

According to an embodiment visible in Figures 5 to 7, the connection between the transverse beam 66 and a first connecting rod 72 comprises first and second connecting pins 76, 76 ', the first connecting pin 76 comprising a hollow tube 88 having first and second grooves 90.1, 90.2, according to the invention, and the second connecting pin 76' comprising a second hollow tube 114, without groove, according to the prior art. The first locking system in translation of the first connecting pin 76 comprises at least one locking plate 100.1, 100.2, according to the invention, and the second locking system in translation of the second connecting pin 76' comprises a bolt 112 housed in the second hollow tube 114, in accordance with the prior art, each blocking plate 100.1, 100.2 performing the function of a washer. According to this embodiment, the first connecting axis 76 is located as close as possible to the safety connecting axis 70 which corresponds to a less accessible zone.

As illustrated in Figure 5, the connection connecting the transverse beam 66 and the second connecting rod 78 is identical to that connecting the transverse beam 66 and the first connecting rod 72. Alternatively, it could be identical to that of the prior art.

Although described applied to the connection between a connecting rod 72, 78 and a transverse beam 66 of a rear engine attachment 60, the invention is in no way limited to this application. Thus, it can apply to any connecting axis connecting a first part which corresponds to a part of an aircraft engine 64 or which is connected to an aircraft engine 64 and a second part which corresponds to a part of a primary structure 62 of an aircraft mast or which is connected to a primary structure 62 of an aircraft mast, the connecting pin comprising a hollow tube being housed in bores provided in the first and second parts and emerging at first and second end faces.

According to one embodiment, the hollow tubes 88 and the first and second blocking plates 100.1, 100.2 are made of the same material, such as for example a superalloy marketed under the "Inconel" brand.

The translation locking system of the invention makes it possible to reduce the number of parts, which tends to simplify the assembly/disassembly of the motor 64 and to reduce the intervention time.

The translation locking system does not require the use of a tool in line with at least one connecting pin, which limits the risk of damage in this area.

According to another advantage, it can be installed on existing engine mounts by replacing only the hollow axles.

Finally, the translation locking system not being positioned in the hollow tube 88 or not blocking it, it is possible to inspect the hollow tube during operation of the aircraft without having to disassemble the translation lock.

Claims (7)

Aircraft thruster assembly comprising a primary structure (62) of a mast, an engine (64) and an engine attachment (60) connecting the primary structure (62) and the engine (64) and comprising at least one first connecting pin (76, 82) connecting a first part (72, 78) which corresponds to a part of the motor (64) or which is connected to the motor (64) and a second part (66) which corresponds to a part of the primary structure (62) or which is connected to the primary structure (62), the first connecting pin (76, 82) comprising a first hollow tube (88), being housed in bores (84, 86) provided in the first and second parts (66, 72, 78) and emerging at the level of first and second end faces (F66, F66'), as well as a first translation locking system configured to immobilize the first hollow tube (88) in the bores (84, 86), characterized in that the first hollow tube (88) comprises at least one groove (90.1, 90.2), close to at least one of the first and second ends (88.1, 88.2) of the first hollow tube (88), positioned outside the bores (84, 86) and having a flank (96.1, 96.2) approximately coplanar with one of the first and second end faces (F66, F66') in operation, and in that the first translation blocking system comprises at least one blocking plate (100.1, 100.2) having a thickness substantially equal to or slightly less than a width of the groove (90.1, 90.2), configured to face one of the first or second end faces (F66, F66') in operation and comprising at least one locking orifice (102) having a first part (104.1), delimited by a first edge (B104.1), and a second part (104.2), delimited by a second edge (B104.2) and configured to allow the introduction of the first hollow tube (88) into the blocking orifice (102), the blocking plate (100.1, 100.2) being movable between a first position in which the first edge (B104.1) of the first part (104.1) is housed at least partially in the groove (90.1, 90.2) and a second position in which no edge of the locking orifice (102 ) is positioned in the groove (90.1, 90.2) and in that the first translation locking system comprises a locking system (106) making it possible to immobilize the locking plate (100.1, 100.2) in the first position. Propellant assembly according to the preceding claim, characterized in that the first hollow tube (88) comprises a first groove (90.1) positioned close to the first end (88.1) of the first hollow tube (88) as well as a second groove (90.2 ) positioned close to the second end (88.2) of the first hollow tube (88), the first and second grooves (90.1, 90.2) being separated by a distance substantially equal to a distance separating the first and second end faces ( F66, F66'), and in that the first translation locking system comprises a first locking plate (100.1) cooperating with the first end (88.1) of the first hollow tube (88) as well as a second locking plate ( 100.2) cooperating with the second end (88.2) of the first hollow tube (88). Propellant assembly according to one of the preceding claims, characterized in that the first part (104.1) of the blocking orifice (102) is a semi-circle, positioned at a first end of the blocking orifice (102), having a diameter substantially equal to a diameter of the groove (90.1, 90.2), and the second part (104.2) of the locking orifice (102) is a semicircle, positioned at a second end of the locking orifice (102), having a diameter greater than or equal to a diameter of the first or second end (88.1, 88.2) of the first hollow tube (88). Propulsion unit according to one of the preceding claims, characterized in that the locking system (106) comprises a locking orifice (108), passing through the locking plate (100.1, 100.2), as well as a rod (110), connected to the first or second part (66, 72, 78), passing through the locking hole (108) to immobilize the blocking plate (100.1, 100.2) in operation. Propulsion assembly according to the preceding claim, the engine attachment comprising a second connecting pin (76', 82') comprising a second hollow tube (114) and a second translation locking system having a bolt (112) lodged in the second hollow tube (114), characterized in that the rod (110) of the locking system (106) is a threaded rod of the bolt (112). Propellant assembly according to one of the preceding claims, characterized in that the first hollow tube (88) has, at at least one of the first and second ends (88.1, 88.2), at least one shape allowing it to be pivoted on itself. even manually. Aircraft comprising at least one propulsion unit according to one of the preceding claims.