Assembly comprising an aircraft turbine engine and mounting pylon for same

Abstract

The invention relates to an assembly (101) that comprises an aircraft turbine engine (103) and a pylon (105) for mounting the turbine engine (103). The turbine engine (103) extends longitudinally along an axis (X), and comprises, from upstream to downstream, a propeller, an upstream structural casing (109), an intermediate structural casing (111), a core (113) and a downstream structural casing (115). The assembly (101) comprises a first and a second suspension member (117, 119) located upstream of the core (113) and a third suspension member (121) located downstream of the core (113). This third suspension member (121) comprises an extension system (123) which is configured to automatically vary its length (L) according to loads to which the turbine engine (103) is subjected, and to automatically and rigidly connect the pylon (105) to the downstream structural casing (115), for specific loads.

Description

[0001] Description

[0002] TITLE: SET COMPRISING AN AIRCRAFT TURBOMACHINE AND ITS MOUNTING PYLON

[0003] TECHNICAL FIELD

[0004] The invention relates to the field of turbomachine suspension systems in an aircraft. It relates in particular to an assembly comprising an aircraft turbomachine and its suspension pylon.

[0005] PRIOR ART

[0006] The state of the art includes in particular documents EP-B1-2082961, FR-A1-3118992 and US-A1-2021261263.

[0007] There are currently several solutions for suspending a turbomachine from an aircraft component.

[0008] A first solution consists of the use, on the one hand, of two suspension planes, one upstream of the core (or in English "core" which notably includes a compressor and a high pressure turbine) of the turbomachine, the other downstream of the core of the turbomachine, and on the other hand, of a thrust recovery.

[0009] A second solution consists of the use of structural nacelles, which allow the turbomachine suspensions to be rigidly connected. This solution makes it possible to counter the problem of clearance consumption (i.e. clearance is present in an initial / rest position, and is consumed in an active position) induced by gravity loads. The splint principle that applies in this case results in hyperstaticity of the connection, which makes the core sensitive to aerodynamic and thrust loads while reducing weight effects.

[0010] Finally, a third solution consists of maintaining the core in a cantilever. In this approach, two suspension planes are placed upstream of the core, which reduces the consumption of clearances linked to aerodynamic loads, but in return increases the consumption of clearances linked to gravity loads.

[0011] A disadvantage of these solutions is that it is not possible to reduce clearance consumption due to gravity loads while simultaneously reducing clearance consumption due to aerodynamic loads. The performance of the turbomachine is therefore degraded accordingly.

[0012] This problem applies to all turbomachines, but more specifically to turbomachines with a so-called unducted architecture (i.e. in which the propeller is unducted), due to the IP-type aerodynamic loads (i.e. loads for which the turbomachine undergoes a tilting force called IP mode) which are greater than on a ducted architecture. For this type of architecture, it is possible to suspend the turbomachine from the first two structural casings (i.e. the most upstream relative to the flow of the flow in the turbomachine) which results in maintaining a part of the mass of the turbomachine (including the core) in cantilever.

[0013] This approach protects the core from permanent IP-type loads and thrust forces, but significantly degrades clearance consumption at core level (particularly in the high-pressure core stages) under gravity loads. This clearance consumption then leads to a degradation in the performance of the turbomachine.

[0014] SUMMARY OF THE INVENTION

[0015] The present invention provides a solution to these drawbacks.

[0016] Thus, one objective of the invention is to propose a suspension solution making it possible to reduce both the consumption of clearances linked to gravity loads and that linked to aerodynamic loads.

[0017] To this end, the invention according to a first aspect relates to an assembly comprising an aircraft turbomachine and a pylon for attaching the turbomachine to an element of the aircraft, the turbomachine extending longitudinally along an axis and comprising from upstream to downstream, in the direction of gas flow, a propeller, an upstream structural casing, an intermediate structural casing, a core and a downstream structural casing, said assembly further comprising, in a first suspension plane, a first suspension member connected on the one hand to the pylon and on the other hand to the upstream structural casing, in a second suspension plane, a second suspension member connected on the one hand to the pylon and on the other hand to the intermediate structural casing, and, in a third suspension plane, a third suspension member connected on the one hand to the pylon and on the other hand to the downstream structural casing, said assembly being characterized in that the third suspension member comprises an extension system,configured to vary its length automatically depending on the loads to which the turbomachine is subjected and to automatically, rigidly connect said pylon to said downstream structural casing, for determined loads, and in that the extension system comprises a sliding pivot or slide connection making it possible to vary the length of said extension system, the sliding pivot or slide connection being connected, via an articulation system, to a mobile element located in an enclosure.,

[0018] The assembly according to the invention may comprise one or more of the following characteristics, taken in isolation from one another or in combination with one another: the sliding pivot or slide connection is connected, via the articulation system, to the mobile element on the one hand, and to a weight, integral with said mobile element, and a return spring for said weight on the other hand, the mobile element, the articulation system, the weight and the spring being configured so that said mobile element is free in said enclosure for a range of determined load values ​​and is blocked by said enclosure outside of said range, so that the sliding pivot or slide connection is also blocked.the extension system further comprising an electric motor, located at the interface between the articulation system and the mobile element, configured to drive the movement of said mobile element in the enclosure, and coupled to an accelerometer, the electric motor and the accelerometer being configured so that the mobile element is free in the enclosure for a range of determined load values ​​and is blocked by said enclosure outside of said range, so as to block the sliding pivot or slide connection.the sliding pivot or slide connection is connected, via the articulation system, to the movable element on the one hand, and to a weight and a return spring of said weight on the other hand, the extension system further comprising a pneumatic motor, located at the interface between the articulation system and the movable element, configured to drive the movement of said movable element in the enclosure, and coupled to a compressed air inlet duct, the weight being coupled to a valve of the compressed air inlet duct and configured so that the opening or closing of said valve depends on the position of said weight and causes the movable element to be free in the enclosure for a range of determined load values ​​and is blocked by said enclosure outside of said range, so that the sliding pivot or slide connection is also blocked.the extension system comprises a sliding pivot connection or slide making it possible to vary the length of said extension system, the extension system further comprising an electromagnet, coupled on the one hand to an axis of the sliding pivot connection or slide, and on the other hand to an accelerometer, the electromagnet and the accelerometer being configured so that the axis of the sliding pivot connection or slide is free for a range of determined load values ​​and is blocked outside of said range.the extension system comprises a sliding pivot or slide connection making it possible to vary the length of said extension system, the sliding pivot or slide connection being connected, via an articulation system to a weight and a return spring of said weight on the other hand, the extension system further comprising an electromagnet coupled to an axis of the sliding pivot or slide connection, the weight being coupled to a switch of the electromagnet and configured so that the opening or closing of the switch depends on the position of said weight and causes the axis of the sliding pivot or slide connection to be free for a range of determined load values ​​and is blocked outside of said range. the extension system is configured so that the pylon is rigidly connected to the downstream structural casing for load values ​​less than 0.9G or greater than 1.1G and left free otherwise.the extension system is connected to the pylon by a first ball joint and to the downstream structural casing by a second ball joint. the variation in the length of the extension system is between 4 centimeters and 8 centimeters, preferably equal to 6 centimeters. the extension system has a response time to a variation in the load of between 0.05 seconds and 0.15 seconds, and preferably equal to 0.1 seconds.

[0019] The invention according to a second aspect further relates to an aircraft comprising an assembly according to the first aspect.

[0020] BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The invention will be better understood with the aid of the following description, given solely by way of example and with reference to the appended drawings in which: Figure 1 is a schematic representation of an assembly comprising an aircraft turbomachine and a pylon for attaching the turbomachine to an element of the aircraft according to a first embodiment of the invention; Figure 2 is a schematic representation of an assembly comprising an aircraft turbomachine and a pylon for attaching the turbomachine to an element of the aircraft according to a second embodiment of the invention; Figure 3a, Figure 3b and Figure 3c are schematic representations of an assembly comprising an aircraft turbomachine and a pylon for attaching the turbomachine to an element of the aircraft according to a third embodiment of the invention and under different loads;Figure 4 is a schematic representation of an assembly comprising an aircraft turbomachine and a pylon for attaching the turbomachine to an element of the aircraft according to a fourth embodiment of the invention; Figure 5 is a schematic representation of an assembly comprising an aircraft turbomachine and a pylon for attaching the turbomachine to an element of the aircraft according to a fifth embodiment of the invention; Figure 6 is a schematic representation of an assembly comprising an aircraft turbomachine and a pylon for attaching the turbomachine to an element of the aircraft according to a sixth embodiment of the invention; and, Figure 7 is a schematic representation of an assembly comprising an aircraft turbomachine and a pylon for attaching the turbomachine to an element of the aircraft according to a seventh embodiment of the invention.;

[0022] DESCRIPTION OF EMBODIMENTS

[0023] With reference to Figure 1 and Figure 2, we will now describe embodiments of an assembly 101 comprising an aircraft turbomachine 103 and a pylon 105 for attaching the turbomachine 103 to an element of the aircraft 100.

[0024] The turbomachine 103 extends longitudinally along an axis X and comprises from upstream to downstream, in the direction of gas flow, a propeller 107 (only shown in FIG. 1), an upstream structural casing 109, an intermediate structural casing 111, a core 113 and a downstream structural casing 115.

[0025] In the example shown, the propeller 107 is unducted. However, the invention also applies to a turbomachine in which the propeller (which is called a fan in this case) is ducted.

[0026] The assembly 101 also comprises a first suspension member 117 which is located in a suspension plane PI and which is connected on the one hand to the pylon 105 and on the other hand to the upstream structural casing 109.

[0027] The assembly 101 also comprises a second suspension member 119 which is located in a suspension plane P2 and which is connected on the one hand to the pylon 105 and on the other hand to the intermediate structural casing 111.

[0028] Finally, in addition to the first suspension member 117 and the second suspension member 119 which correspond to a known suspension system in which the turbomachine 103 is held in a cantilevered position, the assembly 101 comprises a third suspension member 121 which is located in a suspension plane P3 and which is connected on the one hand to the pylon 105 and on the other hand to the downstream structural casing 113. In other words, an additional suspension plane, downstream of the turbomachine 103, is added to its conventional cantilevered suspension obtained by two suspension planes upstream of the turbomachine 103.

[0029] Furthermore, as can be seen in particular in FIG. 2, the third suspension member 121 comprises an extension system 123 of its length L. In particular, the extension system 123 is configured to vary its length L automatically as a function of loads to which the turbomachine 103 is subjected and to automatically connect, in a rigid manner, the pylon 105 to the downstream structural casing 115, for determined loads.

[0030] The term "loads" here refers to all loads to which the turbomachine may be subjected with the exception of gravity loads. The expression "gravity loads" refers to an acceleration force to which the turbomachine is subjected. This force is expressed in G and, thus, the unit (i.e. IG) corresponds to the acceleration of gravity at the surface of the Earth. In practice, depending on the use cases of the aircraft (for example, depending on its flight phases), the turbomachine may be subjected to gravity loads greater or less than IG.

[0031] The term "automatically" implies that the action mentioned is carried out without intervention by an operator or a processing unit used to control the performance of this action. In other words, the modification of the length L and the blocking of the connection are triggered without the intervention of elements capable of processing information and generating a command on the basis of this processing. Finally, the term "rigid" implies that the pylon 105 is made integral with the downstream structural casing 115 (at the level of the third suspension member) for certain loads. Thus, for certain load values, the downstream part of the turbomachine 103 is left free to move vertically (i.e. orthogonally to the X axis) by the suspension member 121 (which corresponds to a cantilever suspension) while for other load values, the downstream part of the turbomachine 103 is held fixedly.

[0032] Furthermore, the modification of the length L of the extension system 123 can be carried out in both directions and, consequently, although the system is said to be extension, it allows in practice to carry out an elongation or a retraction of the suspension member 121 depending on the situation.

[0033] Thanks to the invention, the suspension of the turbomachine makes it possible to limit both IP type loads and thrust loads experienced by the core while reducing gravity loads (in particular vertical static gravity loads) also experienced by the core.

[0034] In the non-limiting example shown in Figure 2, the extension system 123 is connected to the pylon 105 by a first ball joint 127 and to the downstream structural casing 115 by a second ball joint 129. In other words, the extension system 123 is located between two ball joints which frame it on either side. Advantageously, the presence of ball joints on both sides makes it possible to maintain a constraint along the main axis of the extension system 123. In a particular embodiment, the variation in the length L of the extension system 123 is between 4 centimeters and 8 centimeters, and it is preferably equal to 6 centimeters. Such a variation is adapted to the dimensions of the turbomachine and to the forces undergone (such as the thrust, the IP forces, the IP moment) which are at the origin of a vertical displacement (i.e. orthogonal to the X axis) of the downstream structural casing 115.

[0035] In a particular embodiment also, the extension system 123 has a response time to a variation in the load (to which the turbomachine 103 is subjected) of between 0.05 seconds and 0.15 seconds, and preferably equal to 0.1 seconds. Advantageously, such a response time is adapted to allow the system to react to a variation in the load of approximately 0.1G.

[0036] With reference to figures 3a to 7 we will now describe different embodiments of the invention.

[0037] In the example shown in Figure 3a, Figure 3b and Figure 3c, the extension system 123 comprises a sliding pivot connection or slide 131 which allows its length L to be varied.

[0038] The sliding pivot connection or slide 131 is connected to a mobile element 135 via an articulation system 133. The mobile element 135 is located in an enclosure 137. The sliding pivot connection or slide 131 is also connected, via the articulation system 133, to a weight 139 and to a spring 141 for returning the weight 139. The weight 139 is integral with the mobile element 135 and the calibration of the mass of the weight 139 and the return force of the spring 141 makes it possible to determine in advance the displacement (or absence of displacement) of the weight 139 as a function of the loads to which the turbomachine 103 is subjected.

[0039] Furthermore, the movable element 135, the articulation system 133, the weight 139 and the spring 141 are configured so that the movable element 135 is free in the enclosure 137 for a range of determined load values ​​and is blocked by the enclosure 137 outside this range of values. The sliding pivot or slide connection 131 is thus blocked outside this range of values. Here and in what follows, the term “free” implies that the axis of the sliding pivot or slide connection can slide which causes the pivot 105 to move closer to or further away (along a vertical axis orthogonal to the X axis) from the downstream structural casing 115. Conversely, the term “blocked” implies that the axis of the sliding pivot or slide connection can no longer slide and the connection thus becomes rigid (it is also said that the connection is engaged).

[0040] In this example, Figure 3a represents a configuration in which the link is free, for example for a range of load values ​​between 0.9G and 1.1G. Figure 3b represents a configuration in which the link is engaged, for example for a range of load values ​​greater than 1.1G. And Figure 3c represents a configuration in which the link is engaged, for example for a range of load values ​​less than 0.9G.

[0041] As a non-limiting example, the spring 141 and the weight 139 can be calibrated so that the connection is disengaged under a vertical load of IG, and that it engages in less than 0.1s under a vertical load of 1.5G or 0.5G. In the example shown in Figure 4, the extension system 123 also comprises a sliding pivot connection or slide 131 allowing its length L to be varied.

[0042] The sliding pivot connection or slide 131 is also connected, via an articulation system 133, to a mobile element 135 located in an enclosure 137. On the other hand, in this case, the extension system 123 further comprises an electric motor 143 (for example a servomotor), located at the interface between the articulation system 133 and the mobile element 135, configured to drive the movement of the mobile element 135 in the enclosure 137, and coupled to an accelerometer 145. The coupling here is an electrical coupling which implies that the motor 143 can be activated or not depending on an electrical signal from the accelerometer 145.

[0043] The electric motor 143 and the accelerometer 145 are thus configured so that the mobile element 135 is free in the enclosure 137 for a range of determined load values ​​and is blocked by the enclosure 137 outside of said range, so as to block the sliding pivot or slide connection 131. As for the previous embodiment, and in general, the extension system 123 can be configured so that the pylon 105 is rigidly connected to the downstream structural casing 115 for load values ​​less than 0.9G or greater than 1.1G and left free otherwise.

[0044] In another embodiment not shown, the electric motor can be replaced by a hydraulic motor. In this case, the energy supplying the hydraulic motor comes either from an oil pump of a propulsion unit of the turbomachine, or from a hydraulic system of the aircraft. The activation of the system is done by a system of valves, electronically controlled. Advantageously, such a system makes it possible to use hydraulic energy which is available nearby (at the aircraft).

[0045] In another embodiment, also not shown, the motor may be pneumatic. The motor's energy comes, for example, from a reservoir supplied by an independent compressor.

[0046] In the example shown in Figure 5, the extension system 123 also includes a sliding pivot connection or slide 131 allowing its length L to be varied.

[0047] The sliding pivot connection or slide 131 is connected, by means of an articulation system 133, to a mobile element 135 located in an enclosure 137 on the one hand, and to a weight 139 and a spring 141 for returning the weight 139 on the other hand.

[0048] The extension system 123 further comprises a pneumatic motor 147, located at the interface between the articulation system 133 and the mobile element 135, configured to drive the movement of the mobile element 135 in the enclosure 137, and coupled to a compressed air inlet duct 149. The coupling here designates a pneumatic coupling allowing the pneumatic motor 147 to be supplied with compressed air by the compressed air inlet duct 149.

[0049] In this embodiment, the weight 139 is coupled to a valve 151 of the compressed air inlet duct 149 and configured so that the opening or closing of the valve 151 depends on its position. In other words, the movement of the weight 139 causes the pneumatic motor 147 to be supplied with compressed air or not.

[0050] Furthermore, the opening or closing of the valve 151 by the movement of the weight 139 causes the movable element 135 to be free in the enclosure 137 for a range of determined load values ​​and is blocked by the enclosure 137 outside this range, so that the sliding pivot or slide connection 131 is also blocked.

[0051] Advantageously, this embodiment makes it possible to reduce the reaction time of the extension system 123.

[0052] Furthermore, as for the embodiment described with reference to Figure 4, the pneumatic motor can be replaced by a hydraulic motor which can be powered by energy available nearby.

[0053] In the example shown in Figure 6, the extension system 123 also comprises a sliding pivot connection or slide 131 which allows its length L to be varied.

[0054] The extension system 123 further comprises an electromagnet 153, coupled on the one hand to an axis 155 of the sliding pivot connection or slide 131, and on the other hand to an accelerometer 145. The coupling to the axis 155 is a mechanical coupling implying that the electromagnet can cause the displacement (i.e. the sliding) of this axis 155 while the coupling to the accelerometer is an electrical coupling implying that the electromagnet 153 can be activated by a signal from the accelerometer 155. In this embodiment, the electromagnet 153 and the accelerometer 145 are configured so that the axis 155 of the sliding pivot connection or slide 131 is free for a range of determined load values ​​and is blocked outside this range.

[0055] Finally, in the example shown in Figure 7, the extension system 123 always comprises a sliding pivot connection or slide 131 which allows its length L to be varied. The sliding pivot connection or slide 131 is connected, via an articulation system 133 to a weight 139 and a spring 141 for returning the weight 139 on the other hand.

[0056] The extension system 123 further comprises an electromagnet 153 coupled to an axis 155 of the sliding pivot connection or slide 131.

[0057] In this embodiment, the weight 139 is coupled to a switch 157 of the electromagnet 153 and configured so that the opening or closing of the switch 157 depends on the position of the weight 139 and causes the axis 155 of the sliding pivot connection or slide 131 to be free for a range of determined load values ​​and is blocked outside this range.

Claims

CLAIMS 1. Assembly (101) comprising an aircraft turbomachine (103) and a pylon (105) for attaching the turbomachine (103) to an element of the aircraft (100), the turbomachine (103) extending longitudinally along an axis (X) and comprising from upstream to downstream, in the direction of gas flow, a propeller (107), an upstream structural casing (109), an intermediate structural casing (111), a core (113) and a downstream structural casing (115), said assembly (101) further comprising, in a first suspension plane (PI), a first suspension member (117) connected on the one hand to the pylon (105) and on the other hand to the upstream structural casing (109), in a second suspension plane (P2), a second suspension member (119) connected on the one hand to the pylon (105) and on the other hand to the intermediate structural casing (111), and, in a third suspension plane (P3), a third suspension member (121) connected on the one hand to the pylon (105) and on the other hand to the downstream structural casing (115),said assembly (101) being characterized in that the third suspension member (121) comprises an extension system (123), configured to vary its length (L) automatically as a function of loads to which the turbomachine (103) is subjected and to automatically, rigidly connect said pylon (105) to said downstream structural casing (115), for determined loads, and in that the extension system (123) comprises a sliding pivot or slide connection (131) making it possible to vary the length (L) of said extension system (123), the sliding pivot or slide connection (131) being connected, via an articulation system (133), to a mobile element (135) located in an enclosure., 2. Assembly (101) according to claim 1, in which the sliding pivot or slide connection (131) is connected, via the articulation system (133), to the movable element (135) on the one hand, and to a weight (139), integral with said movable element (135), and a spring (141) for returning said weight (139) on the other hand, the movable element (135), the articulation system (133), the weight (139) and the spring (141) being configured so that said movable element (135) is free in said enclosure (137) for a range of determined load values ​​and is blocked by said enclosure (137) outside of said range, so that the sliding pivot or slide connection (131) is also blocked.

3. Assembly (101) according to claim 1, wherein the extension system (123) further comprises an electric motor (143), located at the interface between the articulation system (133) and the movable element (135), configured to drive the movement of said movable element (135) in the enclosure (137), and coupled to an accelerometer (145), the electric motor (143) and the accelerometer (145) being configured so that the movable element (135) is free in the enclosure (137) for a range of determined load values ​​and is blocked by said enclosure (137) outside of said range, so as to block the sliding pivot or slide connection (131).

4. Assembly (101) according to claim 1, wherein the sliding pivot or slide connection (131) is connected, via the articulation system (133), to the movable element (135) on the one hand, and to a weight (139) and a spring (141) for returning said weight (139) on the other hand, the extension system (123) further comprising a pneumatic motor (147), located at the interface between the articulation system (133) and the movable element (135), configured to drive the movement of said movable element (135) in the enclosure (137), and coupled to a compressed air inlet duct (149),the weight (139) being coupled to a valve (151) of the compressed air inlet duct (149) and configured so that the opening or closing of said valve (151) depends on the position of said weight (139) and causes the movable element (135) to be free in the enclosure (137) for a range of determined load values ​​and is blocked by said enclosure (137) outside of said range, so that the sliding pivot or slide connection (131) is also blocked., 5. Assembly (101) according to any one of the preceding claims, in which the extension system (123) is configured so that the pylon (105) is rigidly connected to the downstream structural casing (115) for load values ​​less than 0.9G or greater than 1.1G and left free otherwise.

6. Assembly (101) according to any one of the preceding claims, in which the extension system (123) is connected to the pylon (105) by a first ball joint (127) and to the downstream structural casing (115) by a second ball joint (129).

7. Assembly (101) according to any one of the preceding claims, in which the extension system (123) has a response time to a variation in the load of between 0.05 seconds and 0.15 seconds, and preferably equal to 0.1 seconds.

8. Aircraft (100) comprising an assembly (101) according to any one of the preceding claims.

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