Assembly for an aircraft comprising a turbomachine, a cradle and an attachment system
Patent Information
- Authority / Receiving Office
- WO · WO
- Patent Type
- Applications
- Current Assignee / Owner
- SAFRAN AIRCRAFT ENGINES SAS
- Filing Date
- 2026-01-21
- Publication Date
- 2026-07-30
Smart Images
Figure FR2026050058_30072026_PF_FP_ABST
Abstract
Description
DESCRIPTION TITLE: Aircraft assembly comprising a turbomachine, a cradle and a mounting system TECHNICAL FIELD OF THE INVENTION
[0001] The invention relates to the field of turbomachine attachments to an aircraft. In particular, the invention relates to an aircraft assembly comprising a turbomachine, a cradle, and a system for attaching the turbomachine to the cradle. STATE OF PRIOR ART
[0002] Existing systems for attaching a turbomachine to a pylon or aircraft cradle are described, for example, in documents CA2958686, WO2022 / 245363, WO2022 / 248791 or WO2023 / 198962.
[0003] A turbomachine typically comprises, in one flow direction, an inlet section, a compressor section, a combustion section, a turbine section, and an exhaust section. During operation, air enters through the inlet section and flows to the compressor section, where one or more axial compressors progressively compress the air until it reaches the combustion section, where combustion gases are generated. These combustion gases then flow from the combustion section along a defined hot gas path in the turbine section and exit the combustion section through the exhaust section. Such a turbomachine produces thrust capable of propelling a motor vehicle, such as an aircraft.On an aircraft, the thrust generated by the turbomachine produces thrust forces transmitted to a support, such as a pylon or cradle, and similarly, the aircraft applies equal and opposite reaction forces to the support. This load induces a pitching moment or a yaw moment in the turbomachine. It is therefore necessary to reduce these pitching and yaw moments applied to the turbomachine so that it does not deform to the point of degrading its operating performance.
[0004] Indeed, when the turbomachine produces thrust and is subjected to maneuvering loads (aerodynamic forces on a nacelle or propeller associated with the turbomachine), the turbomachine itself is subjected to loads, e.g., thrust, gravity, etc. The bending (or "back-bone bending" according to Anglo-Saxon terminology) of a turbomachine casing, induced by these stresses, creates clearance closures, or even wear, degrading the turbomachine's performance, thus increasing fuel consumption and accelerating the turbomachine's aging.
[0005] In the case of unfaired turbomachinery typically used on short- or medium-range aircraft, the turbomachine's mounting is critical because the turbomachine's large-diameter propeller induces significant axial moment loads. Furthermore, to achieve high performance, the turbomachine has a small, high-pressure body, making it susceptible to various stresses such as gravitational loads, aircraft maneuvers, and axial moments.
[0006] A conventional turbomachine suspension with an upstream attachment on an upstream casing and a downstream attachment on a turbine casing or exhaust casing does not allow for optimization of the performance of the turbomachine assembly and aircraft cradle or pylon.
[0007] Another known solution, from document WO2022 / 245363, is to position a downstream suspension on the casing upstream of a high-pressure body (cantilevered high-pressure body solution). The bending moments induced by aerodynamic forces upstream of the turbomachine and the thrust will no longer be transmitted through the high-pressure body. Furthermore, this solution can create significant displacements between the tower and the turbomachine at the high-pressure body not supported by suspensions, particularly when the turbomachine is subjected to acceleration factors, such as gravitational acceleration and aircraft maneuvers, resulting in significant clearance loss and displacement between the turbomachine and the tower. Moreover, since the two suspension planes are close together, it is difficult to achieve a good compromise in stiffness between the tower and the upstream casing, which also leads to significant clearance loss between the turbomachine and the tower under load. PRESENTATION OF THE INVE TO
[0008] One aim of the invention is to provide an aircraft assembly comprising a turbomachine, a cradle and a system for attaching the turbomachine to the cradle which allows for a compromise in attachment that limits the consumption of play in the high-pressure body.
[0009] To this end, the invention provides an assembly for an aircraft comprising a turbomachine, a cradle including an upstream frame and a system for attaching the turbomachine to the cradle, the turbomachine extending along a longitudinal axis oriented in a direction of a flow generated by the turbomachine, the turbomachine comprising, along the longitudinal axis, a propeller extending in a plane P orthogonal to the longitudinal axis, an upstream casing, an intermediate casing, a turbine casing and an exhaust casing, the attachment system comprising upstream attachment means for attaching the turbomachine to the upstream frame of the cradle fixed at the level of the upstream casing of the turbomachine,in which the upstream fastening means comprise a series of three coupling means for connecting the upstream casing to the upstream frame of the cradle extending towards the propeller from the upstream frame and arranged such that each resultant force of the coupling means has a direction intersecting the longitudinal axis at the level of the plane P of the propeller, and in which the fastening system comprises means for resisting an axial torque, and means for resisting vertical and lateral forces between the cradle and at least one of the intermediate, turbine and exhaust casings.
[0010] Advantageously, but optionally, the assembly according to the invention has at least one of the following technical characteristics: - each coupling means comprises a ball-and-socket connecting rod extending along the direction of the resultant of the associated recovery force; - the coupling means are equally distributed over a circumference of the upstream casing; - the fixing system includes rear fixing means of the turbomachine to the cradle fixed at the level of one of the turbine and exhaust casings of the turbomachine, the rear fixing means including the means for taking up vertical and lateral forces; - the rear fixing means include means for taking up an axial torque; - the rear fixing means include a "yoke" type fixing comprising a ball joint and a boomerang link; - the fastening system further includes intermediate fastening means for the turbomachine to the cradle fixed at the level of the intermediate housing of the turbomachine, the intermediate fastening means including means for taking up an axial torque; - the intermediate fastening means are fixed to the upstream frame of the cradle; -- the intermediate fastening means comprise a pair of connecting rods mounted to slide along a horizontal direction orthogonal to the longitudinal axis on the cradle; and, - the intermediate fixing means include a ball-joint connecting rod mounted tangentially on the intermediate housing. BRIEF DESCRIPTION OF THE FIGURES
[0011] Other features and advantages of the invention will become apparent from the following description of an embodiment of the invention. See the attached drawings.
[0012] [Fig.1] is a schematic three-dimensional view of a first embodiment of an aircraft assembly comprising a turbomachine, a cradle and a system for linking the turbomachine to the cradle according to the invention;
[0013] [Fig.2] is a schematic three-dimensional view of a second embodiment of an aircraft assembly comprising a turbomachine, a cradle, and a system for connecting the turbomachine to the cradle according to invention i and,
[0014] [Fig.3] is a schematic three-dimensional view of a third embodiment of an aircraft assembly comprising a turbomachine, a cradle and a turbomachine-to-cradle connection system according to the invention.
[0015] For clarity, identical or similar elements are identified by identical reference symbols across all figures. DETAILED DESCRIPTION OF A METHOD OF IMPLEMENTATION
[0016] With reference to figure 1, we will describe a first embodiment of an assembly according to the invention.
[0017] This first embodiment of an assembly according to the invention comprises a turbomachine 1, a cradle 2, and a fastening system 24, 27 for attaching the turbomachine 1 to the cradle 2. As is known per se, the cradle 2 is generally itself attached to an aircraft wing. The turbomachine 1 comprises, in the direction of the flow, a propeller 3, rotating in a plane P, an upstream casing 4, an intermediate casing 5, a turbine casing 6, and an exhaust casing 7. The turbomachine 1 extends along a longitudinal axis XX, the plane P being perpendicular to the longitudinal axis XX. It should be noted that generally the turbine casing 6 (also called "Turbine Vane Frame" according to Anglo-Saxon terminology) is equipped with arms forming stator blades, and the exhaust casing 7 (also called "Turbine Rear Frame" according to Anglo-Saxon terminology) is the last casing of the turbomachine 1.
[0018] The cradle 2 extends parallel to the longitudinal axis XX and is generally located above the turbomachine 1. Here, it includes an upstream frame 21 in the shape of an arch, partially surrounding the turbomachine 1, generally at the level of the intermediate casing 5.
[0019] The fixing system 240,270,271 here includes upstream fixing means 240 of the turbomachine 1 to the upstream frame 21 of the cradle 2 fixed at the upstream casing 4 of the turbomachine 1 and rear fixing means 270,271 of the turbomachine 1 to the cradle 2 fixed at the level of one of the turbine casings 6 and exhaust casing 7 of the turbomachine 1.
[0020] The upstream fastening means here comprise a series of three coupling means 240 connecting the upstream housing 4 to the upstream frame 21 of the cradle 2, extending towards the propeller 3 from the upstream frame 21 and arranged such that each resultant force of the coupling means 24 has a direction D intersecting the longitudinal axis XX at the plane P of the propeller 3. Each coupling means 240 includes a ball-and-socket joint extending, along the convergent direction D of the associated resultant force, between the upstream housing 4 and the upstream frame 21 of the cradle 2. The series of three coupling means 240 is equally distributed around a circumference or periphery of the upstream housing 4. This allows for optimal absorption of axial moment forces without transmitting them to the high-pressure body of the turbomachine 1.
[0021] The rear mounting means here include means for resisting vertical and lateral forces and means for resisting axial torque. To this end, the rear mounting means comprise a "yoke" type mounting 270, 271 including a ball-and-socket joint 270 and a boomerang joint 271. The boomerang joint 271 includes a boomerang-shaped component fixed by three kinematic links: a ball joint with the turbine housing 6 or exhaust housing 7 of the turbomachine 1 and two ball joints with the cradle 2. The "yoke" type mounting allows for the resisting of both vertical and lateral forces as well as engine torque, while preventing deflection of the cantilevered high-pressure body. Alternatively, the rear mounting means are any other conceivable means for resisting vertical and lateral forces and axial torque.
[0022] With reference now to figure 2, we will describe a second embodiment of an assembly according to the invention.
[0023] This second embodiment of an assembly according to the invention differs from the first embodiment previously described by the fact that the fixing system 240,270,255 of the turbomachine 1 to the cradle 2 further comprises intermediate fixing means 255 of the turbomachine 1 to the cradle 2 fixed at the level of the intermediate casing 5 of the turbomachine 1. Here, the intermediate fixing means 255 are fixed to the upstream frame 21 of the cradle 2.
[0024] The intermediate mounting means comprise a pair of connecting rods 255 slidably mounted in a horizontal lateral direction orthogonal to the longitudinal axis XX on the cradle 2. The pair of connecting rods 255 provides pure engine torque transfer and forms axial torque transfer means. Thus, the axial torque transfer means are positioned between the intermediate housing 5 of the turbomachine 1 and the cradle 2. In other words, in this second embodiment, the engine torque transfer occurs upstream of the turbomachine 1, thereby limiting the deflections related to torque transmission in the high-pressure housing.
[0025] Furthermore, this second embodiment of an assembly according to the invention differs from the first embodiment described above in that the rear fastening means here include vertical and lateral load transfer elements 270 comprising two inclined ball-and-socket connecting rods 270. This allows the vertical and lateral loads to be transferred downstream of the turbomachine 1 and prevents deflection of the cantilevered high-pressure body.
[0026] With reference to figure 3, we will describe a third embodiment of an assembly according to the invention.
[0027] This third embodiment differs from the second embodiment previously described in that the intermediate fixing means comprise, instead of the previous pair of connecting rods 255, a ball joint connecting rod 251 positioned tangentially with respect to the intermediate housing 5 so as to provide means for axial torque transfer at the level of said intermediate housing 5. In addition, the ball joint connecting rod 251 allows for the transfer of lateral forces.
[0028] The implementation of one of the previously described embodiments of an assembly according to the invention has the advantage of being isostatic and of allowing effective protection of the high-pressure body from axial moment forces while preventing it from being cantilevered and minimizing the mass of the turbomachine attachment.
[0029] This allows control of the high-pressure body clearances to ensure its performance / operability in a new engine and a removal time compatible with short and medium-haul operation of the aircraft thus equipped.
[0030] Naturally, the invention described above is by way of example. It is understood that a person skilled in the art is capable of carrying out different embodiments of the invention without departing from the scope of the invention.
[0031] It is emphasized that all features, as they are apparent to a person skilled in the art from this description, the drawings and the attached claims, even if in practice they have only been described in relation to other specific features, both individually and in any combinations, may be combined with other features or groups of features disclosed herein, provided that this has not been expressly excluded or that technical circumstances render such combinations impossible or meaningless.
Claims
DEMANDS 1. Assembly for an aircraft comprising a turbomachine (1), a cradle (2) including an upstream frame (21) and a fastening system (240, 251, 255, 270, 271) of the turbomachine (1) to the cradle (2), the turbomachine extending along a longitudinal axis (XX) oriented in a direction of a flow generated by the turbomachine, the turbomachine comprising, along the longitudinal axis (XX), a propeller (3) extending in a plane P orthogonal to the longitudinal axis (XX), an upstream casing (4), an intermediate casing (5), a turbine casing (6) and an exhaust casing (7), the fastening system including upstream fastening means of the turbomachine to the upstream frame of the cradle fixed at the level of the upstream casing (4) of the turbomachine,in which the upstream fastening means comprise a series of three coupling means (240) of the upstream casing to the upstream frame of the cradle extending towards the propeller from the upstream frame and arranged such that each resultant force of the coupling means has a direction (D) intersecting the longitudinal axis (XX) at the level of the plane P of the propeller, and in which the fastening system comprises means for resisting an axial couple (251, 255, 271), and means for resisting vertical and lateral forces (251, 270) between the cradle and at least one of the intermediate, turbine and exhaust casings.
2. Assembly according to claim 1, wherein each coupling means comprises a ball-and-socket connecting rod extending along the direction (D) of the resultant associated recovery force.
3. Assembly according to any one of claims 1 to 2, wherein the coupling means are evenly distributed over a circumference of the upstream casing.
4. Assembly according to any one of claims 1 to 3, wherein the fastening system comprises rear fastening means for the turbomachine to the cradle fixed at the level of one of the turbine and exhaust casings of the turbomachine, the rear fastening means comprising means for taking up vertical and lateral forces (270).
5. Assembly according to claim 4, wherein the rear fixing means comprise the means for taking up an axial torque (271).
6. Assembly according to claim 5, wherein the rear fastening means comprise a "yoke" type fastening comprising a ball-to-ball joint (270) and a boomerang link (271).
7. Assembly according to any one of claims 1 to 3, wherein the fastening system further comprises intermediate fastening means of the turbomachine to the cradle fixed at the level of the intermediate housing of the turbomachine, the intermediate fastening means comprising means for taking up an axial torque (251,255).
8. Assembly according to claim 7, wherein the intermediate fastening means are fixed to the upstream frame of the cradle.
9. Assembly according to any one of claims 7 to 8, wherein the intermediate fastening means comprise a pair of connecting rods (255) mounted to slide along a horizontal direction orthogonal to the longitudinal axis (XX) on the cradle.
10. Assembly according to any one of claims 7 to 8, wherein the intermediate fastening means comprise a ball-joint connecting rod (251) mounted tangentially on the intermediate housing (5).