Front engine attachment system with compact structure for aircraft engine
By designing a system that combines the engine mount and front engine attachment, the main rod, spindle and annular linear connections are used to solve the problem of high height of the front engine attachment, and the engine performance improvement and nacelle and engine The effect of increasing wing distance.
Patent Information
- Application Number
- CN202410845513.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Priority Date
- 2023-06-28
- Filing Date
- 2024-06-27
- Publication Date
- 2024-12-31
AI Technical Summary
The existing aircraft engine front engine attachment system is high, resulting in a decrease in the distance between the nacelle and the ground, affecting the engine performance. A new arrangement is needed to reduce the height of the front engine attachment to bring the nacelle closer to the wings. .
A front engine attachment system is designed, combining the engine mount and the front engine attachment, through the main rod, spindle, outer cylinder and annular linear connection, the tight bonding of the components and the vertical intermediate plan design are achieved, reducing the Component height.
It effectively reduces the height of the front engine attachment, improves engine performance, ensures stable engine suspension, increases the distance between the nacelle and the wing, and improves the tightness and safety of the overall system.
Smart Images
Figure CN119222046A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to a front engine attachment system for an aircraft engine, wherein the front engine attachment system is compact, and to an aircraft having at least one such front engine attachment. Background Art
[0002] Aircraft usually have at least one engine, in particular a jet engine. Under each wing, the aircraft has an engine pylon (suspension) for each engine, which is fastened to the wing structure and extends under the wing, the engine being suspended under the engine pylon.
[0003] The engine is housed in the nacelle and is fastened to the engine pylon by means of an engine attachment system comprising a front engine attachment and a rear engine attachment.
[0004] Many types of front engine attachments are satisfactory from the point of view of their current use. However, in order to increase the performance of the engine, the fans of new engines are getting bigger and bigger, which correspondingly reduces the distance between the nacelle and the ground.
[0005] It was then necessary to define a new arrangement that would allow reducing the height of the front engine attachment, moving the nacelle further away from the ground and, in turn, bringing the nacelle closer to the wing. Summary of the invention
[0006] The object of the present invention is to propose a front engine attachment system which combines an engine pylon and a front engine attachment to reduce the height of the assembly.
[0007] To this end, a front engine attachment system for an engine of an aircraft is proposed, the front engine attachment system having a vertical mid-plane and having:
[0008] - an engine pylon having, at the front part, a nose with a main female clamping piece and a cylindrical shell around a vertical axis;
[0009] - a main rod intended to be fastened to the front casing of the engine by means of a secondary shaft through a secondary ball joint connection about a secondary axis perpendicular to the median plane;
[0010] - a main axis which is perpendicular to the median plane and which realizes a main ball joint connection of the main rod about the main axis in the main female clamping piece, wherein the main axis and the secondary axis are in the same vertical plane perpendicular to the median plane; and
[0011] An outer cylinder coaxial with the vertical axis, a first end of which is fastened in the cylindrical shell and a second end of which is intended to be mounted so as to be movable about the vertical axis relative to the front shell via an annular linear connection.
[0012] Such a front engine attachment system has a reduced vertical bulk because the front engine attachment is integrated into the engine pylon.
[0013] Advantageously, the main axis is arranged in front of the vertical axis.
[0014] According to one particular embodiment, the front engine attachment system has an inner cylinder inserted and fastened in an outer cylinder.
[0015] According to another particular embodiment, the nose has two lateral stops, respectively arranged on the port and starboard sides of the outer cylinder, which are intended to be located between two lateral counter-stops of the front casing.
[0016] Advantageously, the front engine attachment system has two lateral rods, which are respectively arranged on the port and starboard sides of the main rod and each lateral rod is mounted with a tight fit on the main shaft and with clearance on the secondary shaft.
[0017] Advantageously, the main shaft is composed of a hollow outer peripheral shaft and an inner shaft received in the outer peripheral shaft.
[0018] Advantageously, the secondary shaft is composed of a hollow outer peripheral shaft and an inner shaft received in the outer peripheral shaft.
[0019] The invention also proposes an aircraft having an engine with a front casing and a front engine attachment system according to one of the aforementioned variants, wherein the main rod is fastened to the front casing by a secondary spherical joint connection, and wherein the second end of the outer cylinder is mounted so as to be movable relative to the front casing about a vertical axis via an annular linear connection. BRIEF DESCRIPTION OF THE DRAWINGS
[0020] The above and other features of the present invention will become more apparent upon reading the following description of an exemplary embodiment given with reference to the accompanying drawings, in which:
[0021] Figure 1 is a side view of an aircraft according to the present invention;
[0022] Figure 2 is a perspective view of a front engine attachment system according to the present invention;
[0023] Figure 3 The front engine attachment system according to the present invention is along Figure 2 A sectional perspective view taken along line III in FIG.
[0024] Figure 4 The front engine attachment system according to the present invention is along Figure 2 A sectional perspective view taken along line IV in FIG.
[0025] Figure 5 is a variant embodiment similar to Figure 4 of the view. DETAILED DESCRIPTION
[0026] In the following description, position-related terms are considered relative to an aircraft in a forward motion position, i.e., Figure 1 As shown, where arrow F indicates the direction of forward movement.
[0027] Figure 1 An aircraft 100 is shown having an engine 102 , in particular a jet engine, fastened beneath an engine pylon 104 , which is itself fastened beneath a wing 106 .
[0028] In the following description, and by convention, the X direction is the longitudinal direction of the engine 102, which is oriented positively in the direction of the forward motion of the aircraft 100; the Y direction is the lateral direction of the engine 102, which is horizontal when the aircraft 100 is on the ground; and the Z direction is the vertical direction or vertical height when the aircraft 100 is on the ground, and these three directions X, Y and Z are orthogonal to each other.
[0029] The engine 102 has a general shape exhibiting rotational symmetry about the longitudinal axis X.
[0030] exist Figure 1 In the illustrated embodiment of the present invention, the aircraft 100 has one engine 102 beneath each wing 106 of the aircraft 100 , but multiple engines may be disposed beneath each wing 106 .
[0031] Figure 2 A forward engine attachment system 150 is shown, which is secured to the structure of the aircraft 100 , in this case to the structure of the wing 106 , and extends beneath the wing 106 and supports the engine 102 , and in particular the forward portion of the engine 102 . Figures 2 to 4 Various views of the front engine attachment system 150 are shown.
[0032] The front engine attachment system 150 comprises an engine pylon 104 fastened to the structure of the wing 106 and a front engine attachment 160 fastened between the engine pylon 104 and a front casing 103 integral with the engine 102. The front engine attachment system 150 has a vertical median plane XZ.
[0033] The rear engine attachment is conventionally 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.
[0034] The engine pylon 104 is in the form of a box having, in particular at the front portion 163, a nose 110 having a main female clevis 111 consisting of two walls 110a-110b parallel to one another and vertical, i.e. parallel to the median plane XZ and therefore perpendicular to the transverse direction Y. As will be described below, the main female clevis 111 makes it possible to place in place a rod mounted so as to rotate freely in the main female clevis 111 about a main axis 10 oriented transversely, i.e. perpendicular to the median plane XZ and therefore horizontally, thus achieving a spherical joint connection called a main spherical joint connection, the main axis of rotation of which is the main axis 10 and in which the rotations about the other two axes have reduced amplitudes.
[0035] exist Figures 2 to 5 In the embodiment of the invention shown, the nose 110 is constituted by two assembly parts 109a-109b fastened to each other in the middle plane XZ, and each wall 110a-110b constituting the main female clamping part 111 belongs to one of the assembly parts 109a-109b and, in this case, the two walls 110a-110b are symmetrical relative to the middle plane XZ.
[0036] Figure 3 A cross section is shown at the primary female clamping member 111 and the secondary female clamping member 103a.
[0037] The engine pylon 104 has an upper wall 104a, a lower wall 104b and two lateral walls 104c-104d. The walls 104a-104d are integral with each other to form a box having a substantially trapezoidal vertical cross section. The nose 110 is fastened to the front region 163 of the engine pylon 104 by any known means, such as by welding or bolts. The front region 163 corresponds to the front ends of the walls 104a-104d.
[0038] The front engine attachment 160 has a main rod 162 which is fastened to the nose 110 in the main female clamping piece 111. The main ball joint connection of the main rod 162 in the main female clamping piece 111 is realized by a main shaft 165 which is equipped with a boss 171 on which the main rod 162 is mounted in an articulated manner. The main shaft 165 passes through the two walls 110a-110b forming the main female clamping piece 111 and the main rod 162 through a hole provided for this purpose. The main shaft 165 is therefore perpendicular to the median plane XZ. The main axis 10 constitutes the axis of the main shaft 165.
[0039] The main rod 162 is also fastened in an articulated manner to the front housing 103 by means of a secondary ball joint connection, the main axis of rotation of which is the secondary axis 12, which is perpendicular to the middle plane XZ and is therefore horizontal, and wherein the rotations about the other two axes have a reduced amplitude. To this end, the front housing 103 has a female chuck piece 103a, which is also composed of two walls that are parallel and vertical to each other, i.e. parallel to the middle plane XZ and in this case symmetrical with respect to the middle plane XZ. The main rod 162 is fastened to the secondary female chuck piece 103a by means of a secondary axis 167, which passes through the two walls forming the secondary female chuck piece 103a and the main rod 162 through a hole provided for this purpose. The secondary axis 167 is therefore perpendicular to the middle plane XZ. The secondary axis 12 constitutes the axis of the secondary axis 167. The secondary ball joint connection between the main rod 162 and the front housing 103 is realized by a secondary shaft 167, and the secondary shaft 167 is equipped with a boss 174, and the main rod 162 is mounted on the boss 174 in an articulated manner.
[0040] The secondary axis 12 is vertically aligned with the main axis 10 and is below the main axis 10, i.e. the axis of the secondary axis 167 and the axis of the main axis 165 are in the same vertical plane perpendicular to the longitudinal direction X and therefore perpendicular to the middle plane XZ, or in other words, the main axis of the main spherical joint connection, i.e. the main axis 10, and the main axis of the secondary spherical joint connection, i.e. the secondary axis 12, are in the same vertical plane perpendicular to the middle plane XZ.
[0041] exist Figure 3 In the embodiment of the invention shown, the main rod 162 is mounted in a close-fitting manner on the main shaft 165 and the secondary shaft 167 via bosses 171 and 174. The main shaft 165 is mounted inside the hole of the main female chuck member 111 by means of a rotary bearing. The secondary shaft 167 is mounted in a close-fitting manner inside the hole of the secondary female chuck member 103a.
[0042] Figure 4A cross section is shown at an annular linear connection, also called a “socket connection” 169 , in which the translation axis is the vertical axis 20 .
[0043] The nose 110 has a cylindrical shell 502 coaxial with the vertical axis 20 and therefore oriented vertically and in this case in a vertical median plane XZ.
[0044] The front engine attachment 160 also has an outer cylinder 504 , a first end of which is fastened in the cylindrical shell 502 , such that the outer cylinder 504 is coaxial with the vertical axis 20 .
[0045] The second end of the outer cylinder 504 is mounted so as to be movable relative to the front housing 103 via an annular linear connection about the vertical axis 20. Thus, between the outer cylinder 504 and the front housing 103, and therefore between the nose 110 and the front housing 103, there is a ball joint connection about a main axis, which is the vertical axis 20. There is also a sliding connection, the direction of which is parallel to the vertical axis 20.
[0046] exist Figure 4 In the embodiment of the present invention shown in , the ball joint connection is realized by placing in place a boss 506 mounted around the outer cylinder 504, on which the front housing 103 is hingedly mounted. The boss 506 is between the outer cylinder 504 and the front housing 103, and a through hole 508 is realized in the front housing 103, thereby allowing the boss 506 and the second end of the outer cylinder 504 to be placed in place.
[0047] A sliding connection is achieved between the cylindrical shell 502 and the boss 506 , so that the boss 506 is mounted so as to be free to move in translation along the cylindrical shell 502 parallel to the vertical axis 20 .
[0048] exist Figure 4 In the embodiment of the invention shown, the outer cylinder 504 is hollow, and the front engine attachment 160 also has an inner cylinder 505 inserted and fastened in the outer cylinder 504. The inner cylinder 505 is therefore also coaxial with the vertical axis 20. The outer diameter of the inner cylinder 505 is smaller than the inner diameter of the outer cylinder 504, so that a space 507 is created between them, i.e. between the inside of the outer cylinder 504 and the outside of the inner cylinder 505. The difference in diameter is, for example, of the order of 0.6 mm to 2 mm, and preferably 1 mm.
[0049] exist Figure 4In the embodiment of the invention shown, the first end of the outer cylinder 504 and the inner cylinder 505 are secured by placing a pin 503 in place, which is driven into a hole through the outer cylinder 504, the inner cylinder 505 and the nose 110. In this example, the axis of the pin 503 is perpendicular to the vertical axis 20.
[0050] exist Figure 5 In the illustrated embodiment of the invention, only the outer cylinder 504 is present, which in this example is solid.
[0051] The main female clamping piece 111 is arranged in front of the socket connection 169 with respect to the longitudinal direction X, ie the main axis 10 of the main ball joint connection is in front of the vertical axis 20 .
[0052] With this arrangement, the pylon 104 directly incorporates the elements ensuring the fastening of the engine 102 , in order to reduce the height necessary for such fastening.
[0053] When the engine 102 is running, forces are generated and transmitted to the structure of the wing through the front shell 103 and the front engine attachment system 150, that is, through the main rods 162a-162b, secondary shafts 167, main shafts 165, socket connections 169 and engine pylons 104 that form the main force path.
[0054] Therefore, the forces in the Z direction are transmitted through the secondary ball joint connection and the primary ball joint connection, ie vertically through the main rod 162 .
[0055] The forces in the X-direction and the Y-direction are transmitted via the socket connection 169 .
[0056] For safety reasons, the front engine attachment system 150 also has means for ensuring a secondary force path for compensating for the failure of the main force path, these means constituting backup safety means (or “wait-for-fail-safe” means).
[0057] exist Figure 5 In the embodiment of the invention shown, if the spigot connection 169 fails, it is necessary to continue to transmit the force in the Y direction. Therefore, according to a particular embodiment of the invention, the nose 110 then has two lateral stops 512a-512b, which are respectively arranged on the port side and the starboard side of the outer cylinder 504, and for each lateral stop 512a-512b, the front shell 103 has a lateral mating stop 510a-510b, which are also respectively arranged on the starboard side and the port side of the outer cylinder 504, and the lateral stops 512a-512b are arranged between the lateral mating actuators 510a-510b.
[0058] In the normal position, i.e. in the absence of a fault in the main force path, each lateral stop 512a-512b is at a distance from the associated lateral mating stop 510a-510b, and in the event of a fault, one of the lateral stops 512a-512b abuts against the associated lateral mating stop 510a-510b.
[0059] exist Figure 4 In the embodiment of the invention shown, in the event of a rupture at the outer cylinder 504, the inner cylinder 505 takes over and thus forms a backup safety device (or "fail-safe" device).
[0060] In the event of a failure, it is necessary to continue to transmit force in the Z direction. Therefore, according to a specific embodiment of the present invention, the front engine attachment system 150 has two lateral rods 170a-170b, which are respectively arranged on the port side and the starboard side of the main rod 162, and Figure 2 and Figure 3 In the embodiment of the invention shown, they are respectively arranged on the port side or starboard side of the walls 110a-110b forming the main female clamping member 111 and are symmetrical with respect to the median plane XZ.
[0061] Each lateral rod 170a-170b is mounted in a close-fitting manner on the main shaft 165 and with clearance on the secondary shaft 167. Therefore, in the event of certain failures, at least one lateral rod 170a-170b and / or the secondary shaft 167 will move so that the inner wall of the hole of the at least one lateral rod 170a-170b abuts against the secondary shaft 167.
[0062] exist Figure 2 and Figure 3 In the embodiment of the present invention shown, the main shaft 165 is composed of a cylindrical and hollow outer peripheral shaft 165a and an inner shaft 165b accommodated in the outer peripheral shaft 165a. This arrangement can compensate for any breakage of the outer peripheral shaft 165a.
[0063] exist Figure 2 and Figure 3 In the embodiment of the present invention shown, the secondary shaft 167 is composed of a cylindrical and hollow outer peripheral shaft 167a and an inner shaft 167b received in the outer peripheral shaft 167a. This arrangement can compensate for any breakage of the outer peripheral shaft 167a.
Claims
1. A front engine attachment system (150) for an engine (102) of an aircraft (100), the front engine attachment system (150) having a vertical mid-plane (XZ) and having: - an engine pylon (104) having, at the front part, a nose (110) with a main female clamping piece (111) and a cylindrical shell (502) around a vertical axis (20); - a main rod (162) intended to be fastened to the front casing (103) of the engine (102) by means of a secondary shaft (167) through a secondary ball joint connection about a secondary axis (12) perpendicular to the median plane (XZ); - a main axis (165) which is perpendicular to the middle plane (XZ) and realizes a main ball joint connection of the main rod (162) about a main axis (10) in the main female clamping piece (111), wherein The major axis (10) and the minor axis (12) are in the same vertical plane perpendicular to the median plane (XZ); as well as - an outer cylinder (504) coaxial with the vertical axis (20), a first end of which is fastened in the cylindrical shell (502) and a second end of which is intended to be mounted so as to be movable around the vertical axis (20) relative to the front shell (103) via an annular linear connection.
2. The front engine attachment system (150) of claim 1, characterized in that: The main axis (10) is arranged in front of the vertical axis (20).
3. The front engine attachment system (150) of claim 1, characterized in that: The front engine attachment system has an inner cylinder (505) inserted and fastened into the outer cylinder (504).
4. The front engine attachment system (150) of claim 1, characterized in that: The nose (110) has two lateral stops (512a-512b), which are respectively arranged on the port side and the starboard side of the outer cylinder (504), and the lateral stops are intended to be located between the two lateral matching stops (510a-510b) of the front shell (103).
5. The front engine attachment system (150) of claim 1, characterized in that: The front engine attachment system has two lateral rods (170a-170b), which are respectively arranged on the port side and the starboard side of the main rod (162), and wherein each of the lateral rods (170a-170b) is mounted on the main shaft (165) in a close-fitting manner and is mounted on the secondary shaft (167) with clearance.
6. The front engine attachment system (150) of claim 1, characterized in that: The main shaft (165) includes a hollow outer peripheral shaft (165a) and an inner shaft (165b) received in the outer peripheral shaft (165a).
7. The front engine attachment system (150) of claim 1, characterized in that: The auxiliary shaft (167) includes a hollow outer peripheral shaft (167a) and an inner shaft (167b) received in the outer peripheral shaft (167a).
8. An aircraft (100) having an engine (102) with a front housing (103) and a front engine attachment system (150) according to claim 1, wherein: The main rod (162) is fastened to the front housing (103) via the secondary spherical joint connection, and wherein the second end of the outer cylinder (504) is mounted to be movable relative to the front housing (103) around the vertical axis (20) via the annular linear connection.