Front engine attachment system for engine of aircraft and aircraft
The front engine attachment system addresses the challenge of larger engines by integrating a compact design with articulated connections and safety features, ensuring stable engine suspension and failure compensation.
Patent Information
- Application Number
- CN202410752500.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Priority Date
- 2023-06-28
- Filing Date
- 2024-06-12
- Publication Date
- 2024-12-31
AI Technical Summary
The increasing size of aircraft engine fans necessitates a reduction in the height of the front engine attachment to maintain a safe distance from the ground, as current systems are inadequate for larger engines.
A front engine attachment system integrating an engine hanger and attachment with a vertical median plane, comprising an engine suspender, primary and secondary articulated connections, and annular linear connections, reducing vertical bulk and incorporating safety mechanisms for force transmission and failure compensation.
The system effectively reduces the vertical height of the engine attachment, ensuring safe and stable engine suspension while accommodating larger engines by distributing and compensating for potential failures.
Smart Images
Figure CN119218434A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to a front engine attachment system for an aircraft engine, and to an aircraft having at least one such front engine attachment, wherein the front engine attachment system is compact. Background Art
[0002] Aircraft usually have at least one engine, in particular a turbojet engine. Under each wing and for each engine, the aircraft has an engine boom fixed to the wing structure and extending under the wing, and the engine is suspended under the engine boom.
[0003] The engine is placed in the engine compartment and secured to the engine boom by an engine attachment system including a front engine attachment and a rear engine attachment.
[0004] There are many types of front engine attachments, which 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 also makes the distance between the engine compartment and the ground shorter.
[0005] It was therefore necessary to determine a new arrangement allowing to reduce the height of the front engine attachment so as to move the nacelle away from the ground and therefore closer to the wing. Summary of the invention
[0006] An object of the present invention is to provide a front engine attachment system that integrates an engine hanger and a front engine attachment to reduce the height of the assembly.
[0007] For this purpose, a front engine attachment system for an engine of an aircraft is proposed, the front engine attachment system having a vertical median plane and comprising:
[0008] - an engine suspender, which comprises at the front a nose having a main frame and a cylindrical housing around a vertical axis,
[0009] - a primary connecting rod designed to be fixed to the front cowl of the engine via a secondary shaft by a secondary articulated connection about a secondary axis perpendicular to the median plane,
[0010] - a main axis, which is perpendicular to the median plane and about which the main articulated connection of the main connecting rod is realized in the main carrier, 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 fixed in the cylindrical housing and a second end of which is designed to be mounted relative to the front cowl by an annular linear connection about the vertical axis.
[0012] Since the front engine attachment is integrated into the engine boom, the vertical bulk of such a front engine attachment system is reduced.
[0013] Advantageously, the main axis is arranged in front of the vertical axis.
[0014] Advantageously, the main link is designed to be fixed to the second mother frame of the front hood by a pivot connection about a pivot axis perpendicular to the median plane, since the front engine attachment system includes a second shaft for realizing the pivot connection, and the second shaft is arranged to be mounted in the hole of the main link in a manner with clearance and is designed to be mounted in the hole of the second mother frame in a close-fitting manner.
[0015] According to a particular embodiment, the front engine attachment system includes an inner cylinder inserted and secured in an outer cylinder.
[0016] According to another particular embodiment, the nose comprises two lateral stops respectively arranged on the port and starboard sides of the outer cylinder and designed to be located between two lateral opposite stops of the front cowl.
[0017] Advantageously, the front engine attachment system comprises two side links, respectively arranged on the port and starboard side of the main link, and each side link is mounted on the main shaft in a close-fitting manner and on the secondary shaft in a clearance manner.
[0018] Advantageously, the main shaft is composed of a hollow outer peripheral shaft and an inner shaft received in the outer peripheral shaft.
[0019] The invention also provides an aircraft comprising a structure, an engine having a front cowl and a front engine attachment system according to at least one of the aforementioned variants, wherein the main link is fixed to the front cowl by a secondary articulated connection and wherein the second end of the outer cylinder is mounted relative to the front cowl by an annular linear connection about a vertical axis. BRIEF DESCRIPTION OF THE DRAWINGS
[0020] The above-mentioned features of the present invention, as well as other features, will become more apparent upon reading the following description of exemplary embodiments, which description is made with reference to the accompanying drawings, in which:
[0021] Figure 1 is a side view of an aircraft according to the 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 Figure 2 A perspective view of the section at line III of
[0024] Figure 4 The front engine attachment system according to the present invention is Figure 2 A perspective view of the section at line IV of
[0025] Figure 5 The front engine attachment system according to the present invention is Figure 2 A perspective view of the section at line V of
[0026] Figure 6 is a variation of the embodiment Figure 5 Similar view. DETAILED DESCRIPTION
[0027] In the following description, position-related terms refer to the aircraft in the forward position, i.e. Figure 1 As shown, arrow F indicates the forward direction.
[0028] Figure 1 An aircraft 100 is shown with an engine 102 , in particular a turbojet engine, fastened under an engine boom 104 , which in turn is fastened under a wing 106 .
[0029] In the following description, by convention, the longitudinal direction of the engine 102 oriented forward in the forward direction of the aircraft 100 is referred to as X, the lateral direction of the engine 102 which is horizontal when the aircraft 100 is on the ground is referred to as Y, and the vertical height or vertical direction 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.
[0030] The engine 102 is generally in the shape of a body of revolution about a longitudinal axis X.
[0031] exist Figure 1 In the illustrated embodiment of the invention, the aircraft 100 includes one engine 102 under each wing 106 of the aircraft 100 , although multiple engines may be provided under each wing 106 .
[0032] Figure 2 A front engine attachment system 150 is shown, which is secured to the aircraft structure 100 , here the wing structure 106 , and extends under the wing 106 and supports the engine 102 , in particular the front portion of the engine 102 . Figures 2 to 5 Different views of the front engine attachment system 150 are shown.
[0033] The front engine attachment system 150 comprises an engine boom 104 fixed to the wing structure 106 and a front engine attachment 160 fixed between the engine boom 104 and the front cowl 103 connected to the engine 102. The front engine attachment system 150 has a vertical median plane XZ.
[0034] Typically, the rear engine attachment is secured between the engine boom 104 and the rear of the engine 102 and may take any form known to those skilled in the art.
[0035] The engine boom 104 has the form of a housing which comprises, in particular, a nose 110 at the front 163, comprising a main carrier 111 consisting of two walls 110a, 110b which are parallel to each other and vertical, i.e. parallel to the median plane XZ and therefore perpendicular to the transverse direction Y. As will be described in detail below, the main carrier 111 allows the provision of a connecting rod which is mounted to rotate freely in the main carrier 111 about a main axis 10 oriented transversely, i.e. perpendicular to the median plane XZ and therefore horizontal, thereby achieving a so-called main articulated connection in which the main axis of rotation is the main axis 10 and in which the amplitude of rotation along the other two axes is reduced.
[0036] exist Figures 2 to 6 In the illustrated embodiment of the invention, the nose 110 is composed of two fittings 109a to 109b fixed to each other at the median plane XZ, and each wall 110a to 110b constituting the main mother frame 111 belongs to one of the metal fittings 109a to 109b, and here, the two walls 110a to 110b are symmetrical about the median plane XZ.
[0037] Figure 4 A cross section at the main mother frame 111 and the first mother frame 103a is shown.
[0038] The engine hanger 104 includes an upper wall 104a, a lower wall 104b and two side walls 104c, 104d. The different walls 104a to 104d are connected to each other to form a housing whose vertical cross section is generally trapezoidal. The nose 110 is fixed to the front area 163 of the engine hanger 104 by any known method, such as by welding or bolts. The front area 163 corresponds to the front ends of the walls 104a, 104d.
[0039] The front engine attachment 160 comprises a main connecting rod 162, which is fixed to the nose 110 in the main carrier 111. The main articulated connection of the main connecting rod 162 in the main carrier 111 is realized by a main shaft 165, which is equipped with a nut 171 on which the main connecting rod 162 is hingedly mounted. The main shaft 165 passes through the two walls 110a, 110b forming the main carrier 111 and the main connecting 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.
[0040] The main connecting rod 162 is also articulatedly fixed to the front cover 103 by means of a secondary articulated connection, the main axis of rotation of which is the secondary axis 12a, which is perpendicular to the median plane XZ and is therefore horizontal, and the amplitude of rotation along the other two axes is reduced. To this end, the front cover 103 has a first frame 103a, which is also composed of two walls that are parallel to each other and vertical, that is, the two walls are parallel to the median plane XZ and are symmetrical here with respect to the median plane XZ. The fixing of the main connecting rod 162 to the first frame 103a is provided by a secondary shaft 167a, which passes through the two walls forming the first frame 103a and the main connecting rod 162 through a hole provided for this purpose. The secondary shaft 167a is therefore perpendicular to the median plane XZ. The secondary axis 12a constitutes the axis of the secondary shaft 167a. The secondary articulated connection of the main connecting rod 162 to the front cowl 103 is realized by a secondary shaft 167 which is provided with a nut 174 on which the main connecting rod 162 is articulatedly mounted.
[0041] The secondary axis 12a is aligned perpendicularly with the main axis 10 and is below the main axis 10, i.e. the axis of the secondary axis 167a and the axis of the main axis 165 are in the same vertical plane perpendicular to the longitudinal direction X and therefore also perpendicular to the median plane XZ, or in other words, the main axis of the main articulated connection, i.e. the main axis 10, and the main axis of the secondary articulated connection, i.e. the secondary axis 12a, are in the same vertical plane perpendicular to the median plane XZ.
[0042] exist Figure 4 In the embodiment of the invention shown, the main connecting rod 162 is mounted in a close-fitting manner on the main shaft 165 and the secondary shaft 167a via nuts 171 and 174. The main shaft 165 is mounted in a hole of the main frame 111 through a rotating bearing. The secondary shaft 167a is mounted in a close-fitting manner in the hole of the first frame 103a.
[0043] Figure 5 A cross section of an annular linear connection is shown, wherein the translation axis is the vertical axis 20 , also referred to as a “socket connection” 169 .
[0044] The nose 110 has a cylindrical housing 502 coaxial with the vertical axis 20 and therefore oriented vertically and here in a vertical median plane XZ.
[0045] The front engine attachment 160 also includes an outer cylinder 504 , a first end of which is fixed in the cylindrical housing 502 , such that the outer cylinder 504 is coaxial with the vertical axis 20 .
[0046] exist Figure 5In the embodiment of the invention shown, the first end of the outer cylinder 504 is fixed by providing a pin 503 inserted in a hole passing through the outer cylinder 504 and the nose 110. Here, the axis of the pin 503 is perpendicular to the vertical axis 20.
[0047] The second end of the outer cylinder 504 is mounted relative to the front mask 103 by an annular linear connection around the vertical axis 20. Thus, there is an articulated connection between the outer cylinder 504 and the front mask 103, and therefore between the nose 110 and the front mask 103, around a main axis, which is the vertical axis 20. There is also a sliding connection whose direction is parallel to the vertical axis 20.
[0048] exist Figure 5 In the embodiment of the present invention shown, the hinged connection is achieved by providing a nut 506 mounted around the outer cylinder 504, and the front cover 103 is hingedly mounted on the outer cylinder 504. The nut 506 is located between the outer cylinder 504 and the front cover 103, and a bore 508 is formed in the front cover 103 to allow the nut 506 and the second end of the outer cylinder 504 to be arranged.
[0049] A sliding connection is achieved between the cylindrical socket 502 and the nut 506 , the nut 506 thus being mounted so as to be free to translate along the cylindrical socket 502 parallel to the vertical axis 20 .
[0050] exist Figure 5 In the illustrated embodiment of the invention, the outer cylinder 504 is solid.
[0051] exist Figure 6 In the embodiment of the present invention, the outer cylinder 504 is hollow, and the front engine attachment 160 further includes an inner cylinder 505 inserted and fixed in the outer cylinder 504. Therefore, the inner cylinder 505 is 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 to form a space 507 therebetween, i.e., between the inside of the outer cylinder 504 and the outside of the inner cylinder 505. The diameter difference is, for example, 0.6 mm to 2 mm, and preferably 1 mm.
[0052] exist Figure 4 In the embodiment of the invention shown, the first end of the outer cylinder 504 and the inner cylinder 505 are fixed by providing a pin 503 inserted in a hole passing through the outer cylinder 504, the inner cylinder 505 and the nose 110. Here, the axis of the pin 503 is perpendicular to the vertical axis 20.
[0053] The main carrier 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 articulated connection is in front of the vertical axis 20 .
[0054] With this arrangement, the boom 104 directly engages the elements securing the engine 102, thereby reducing the height required for this securing.
[0055] When the engine 102 is operating, forces are generated and transmitted to the wing structure through the front cowl 103 and the front engine attachment system 150, that is, through the main connecting rod 162, the secondary shaft 167a, the main shaft 165, the socket connection 169 and the engine suspension rod 104 that form the main force path.
[0056] The force in Z is therefore transmitted via the secondary articulated connection and the primary articulated connection, ie vertically via the main link 162 .
[0057] The forces on X and Y are transmitted via the socket connection 169 .
[0058] For safety reasons, the front engine attachment system 150 also comprises means ensuring a secondary force path which compensates for a failure of the primary force path, these means constituting a waiting safety device (called “waiting fail safe” in Anglo-Saxon).
[0059] Thus, according to a particular embodiment of the invention, the main link 162 is also articulatedly fixed to the front cowl 103 by a pivot connection about a pivot axis 12b perpendicular to the median plane XZ and therefore horizontal. To this end, the front cowl 103 has a second frame 103b, here formed by two walls parallel to each other and vertical, i.e. parallel to the median plane XZ, and here they are identical to the walls of the first frame 103a. The fixing of the main link 162 to the second frame 103b is ensured by a second axis 167b which passes through the two walls forming the second frame 103b and the main link 162 by passing through a hole preformed for this purpose, in order to achieve the pivot connection. The second axis 167b is perpendicular to the median plane XZ. The pivot axis 12b constitutes the axis of the second axis 167b.
[0060] Figure 3 A cross section at the second mother carrier 103b is shown.
[0061] Therefore, the main link 162 is a link fixed at three points.
[0062] The main frame 111 is arranged behind the second frame 103b with respect to the longitudinal direction X, ie the main axis 10 of the main articulated connection is located behind the pivot axis 12b of the pivot connection.
[0063] The second shaft 167b is installed in a close-fitting manner in the hole of the second mother frame 103b, and is installed in a clearance manner in the hole of the main connecting rod 162. Therefore, in certain fault conditions, the main connecting rod 162 and / or the second shaft 167b will move to make the inner wall of the hole of the main connecting rod 162 abut against the second shaft 167b.
[0064] exist Figure 5 In the embodiment of the invention shown, in the event of a failure at the socket connection 169, it is necessary to continue to transmit the force on Y. Therefore, according to a particular embodiment of the invention, the nose 110 then has two side stops 512a, 512b, respectively arranged on the port and starboard sides of the outer cylinder 504, and for each side stop 512a, 512b, the front cowl 103 has a side opposing stop 510a, 510b, and two side opposing stops 510a, 510b are also respectively arranged on the port and starboard sides of the outer cylinder 504, and the side stops 512a, 512b are arranged between the side opposing stops 510a, 510b.
[0065] In the normal position, i.e. in the absence of a fault in the main force path, each side limiter 512a, 512b is away from the associated side opposing limiter 510a, 510b, and in the event of a fault, one of the side limits 512a, 512b will press against the associated side opposing limiter 510a, 510b.
[0066] exist Figure 6 In the embodiment of the invention shown, in the event of a rupture of the outer cylinder 504, the inner cylinder 505 takes over, thereby forming a waiting safety device (called "waiting fail safe" in Anglo-Saxon).
[0067] In the event of a failure, it is necessary to continue to transmit forces in Z. Therefore, according to a particular embodiment of the invention, the front engine attachment system 150 comprises two side links 170a, 170b, respectively arranged on the port and starboard sides of the main link 162, and Figures 2 to 4 In the embodiment of the invention shown, they are respectively on the port and starboard sides of the walls 110a, 110b forming the main mother frame 111 and are symmetrical with respect to the median plane XZ.
[0068] Each lateral link 170a, 170b is mounted on the main shaft 165 in a close-fitting manner and on the secondary shaft 167a in a clearance manner. Therefore, in the event of certain failures, at least one lateral link 170a, 170b and / or the secondary shaft 167a will move so that the inner wall of the hole of the at least one lateral link 170a, 170b abuts against the secondary shaft 167a.
[0069] exist Figures 2 to 4 In the embodiment of the invention shown, the main shaft 165 is composed of a cylindrical and hollow outer peripheral shaft 165a and an inner shaft 165b placed in the outer peripheral shaft 165a. Such an arrangement allows compensating for possible breakage of the outer peripheral shaft 165a.
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 comprising: An engine boom (104) comprising at the front a nose (110) having a main frame (111) and a cylindrical receiving portion (502) around a vertical axis (20), a main connecting rod (162) designed to be fixed to the front cowl (103) of the engine (102) by a secondary articulated connection through a secondary shaft (167a), the secondary articulated connection being about a secondary axis (12a) perpendicular to the median plane (XZ), a main axis (165) which is perpendicular to the median plane (XZ) and realizes a main articulated connection of the main connecting rod (162) in the main mother frame (111) around a main axis (10), wherein the main axis (10) and the secondary axis (12a) are in the same vertical plane perpendicular to the median plane (XZ), and An outer cylinder (504), the outer cylinder (504) is coaxial with the vertical axis (20), the first end of the outer cylinder is fixed in the cylindrical receiving portion (502), and the second end of the outer cylinder is designed to be mounted relative to the front cover (103) through an annular linear connection around the vertical axis (20).
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) according to any one of claims 1 or 2, characterized in that The main connecting rod (162) is designed to be fixed to the second mother frame (103b) of the front cover (103) by a pivot connection around a pivot axis (12b) perpendicular to the median plane (XZ), and the front engine attachment system (150) includes a second shaft (167b) for realizing the pivot connection, and the second shaft (167b) is configured to be installed in the hole of the main connecting rod (162) in a manner with a gap, and is designed to be installed in the hole of the second mother frame (103b) in a close-fitting manner.
4. The front engine attachment system (150) according to any one of claims 1 to 3, characterized in that The front engine attachment system includes an inner cylinder (505) inserted and secured in the outer cylinder (504).
5. The front engine attachment system (150) according to any one of claims 1 to 3, characterized in that: The nose (110) comprises two side stoppers (512a, 512b) respectively arranged on the port side and the starboard side of the outer cylinder (504), and the two side stoppers (512a, 512b) are designed to be located between two side-facing stoppers (510a, 510b) of the front cover (103).
6. The front engine attachment system (150) according to any one of claims 1 to 5, characterized in that The front engine attachment system includes two side links (170a, 170b) respectively arranged on the port and starboard sides of the main link (162), and each side link (170a, 170b) is mounted on the main shaft (165) in a close-fitting manner and on the secondary shaft (167a) in a clearance manner.
7. The front engine attachment system (150) according to any one of claims 1 to 6, characterized in that The main shaft (165) is composed of a hollow outer peripheral shaft (165a) and an inner shaft (165b) accommodated in the outer peripheral shaft (165a).
8. An aircraft (100) comprising a structure, an engine (102) having a front cowl (103), and a front engine attachment system (150) according to any one of the preceding claims, wherein: The main connecting rod (162) is fixed to the front cover (103) by the secondary hinged connection, and wherein the second end of the outer cylinder (504) is mounted relative to the front cover (103) by the annular linear connection around the vertical axis (20).