Propulsion unit for an aircraft
Patent Information
- Application Number
- EP2023822431
- Authority / Receiving Office
- EP · EP
- Patent Type
- Applications
- Current Assignee / Owner
- Priority Date
- 2022-11-24
- Filing Date
- 2023-11-15
- Publication Date
- 2025-10-01
AI Technical Summary
Current propulsion assembly technologies for aircraft are bulky, expensive, and environmentally inefficient due to the use of flexible, oversized fluid connection pipes, which hinder movement and contribute to high carbon emissions.
The propulsion assembly features a turbomachine with a cowling that uses interlocking connectors with self-sealing valves for fluid communication, allowing for plug-in fittings that disconnect when panels open, reducing the need for flexible pipes and optimizing fluid circuit connections.
This solution reduces the mass and cost of the propulsion assembly, minimizes environmental impact, and simplifies maintenance by enabling rapid connection and disconnection without tools, while enhancing energy efficiency and compliance with environmental regulations.
Smart Images
Figure 1.1
Abstract
Description
[0001] DESCRIPTION
[0002] TITLE: PROPULSION UNIT FOR AN AIRCRAFT
[0003] Technical field of the invention
[0004] The present invention relates to a propulsion assembly for an aircraft.
[0005] Technical background
[0006] The state of the art includes in particular document FR-A1 -3 094 750, KR-A1- 2019 0071093, US-A1 -2020 / 182389 and FR-A1-3 098 289.
[0007] Figure 1 illustrates a propulsion assembly 10 for an aircraft.
[0008] In the present application, the term propulsion unit 10 for an aircraft means an assembly comprising a reactor mast 12, a turbomachine 14 and its cowling 16.
[0009] The engine pylon 12 is a solid part that allows a turbomachine 14 to be attached to an aircraft, and for example to a wing of the aircraft. The engine pylon 12 therefore comprises elements for attachment to the aircraft and elements for attachment to the turbomachine 14. The engine pylon 12 has a generally elongated shape and extends along a first axis A.
[0010] In the present application, the turbomachine 14 is located under the engine pylon 12 or next to the engine pylon. The turbomachine may be suspended from the engine pylon 12 under the wing of the aircraft. Alternatively, the turbomachine may be installed at the rear of the fuselage of the aircraft.
[0011] The turbomachine 14 has a general shape elongated along a second axis B which can be parallel to the first axis A. The first and second axes A, B are located in the same plane P. This plane P can be vertical or inclined relative to the vertical.
[0012] The positions of parts around the second axis B are designated by 12h (for 12 hours) and 6h (for 6 hours), by analogy with the dial of a clock when looking at the assembly from the rear. The 12h position is located in the plane P and at the level of the engine pylon 12, and the 6h position is located in the plane P under the turbomachine 14.
[0013] The turbomachine 14 comprises a lubrication system 18 which in particular makes it possible to lubricate bearings of the turbomachine by circulating lubricating oil.
[0014] The cowling 16 surrounds the turbomachine 14 and extends along the second axis B. The cowling 16 may comprise several pieces and comprises two panels 20 of generally semi-circular shape which extend on either side of the aforementioned plane P. These panels 20 comprise upper longitudinal edges 22 which are fixed to the engine pylon 12 and arranged on either side of the plane P, close to the 12 o'clock position, and lower longitudinal edges 24 which are generally fixed to each other and are therefore located at the 6 o'clock position.
[0015] These panels 20 are hinged by their upper edges 22 to be able to open the cowling 16 and intervene in the turbomachine 14 during a ground maintenance operation for example. This articulation is made possible by hinges 25 for fixing the upper edges 22 of the panels 20 to the engine mast 12. Each of the panels 20 is hinged around a third axis C which can be parallel to the second axis B for example, from a closed position in which its lower edge 24 is at the 6 o'clock position, to an open position in which its lower edge 24 is away from the 6 o'clock position.
[0016] The cowling 16 may carry at least one surface heat exchanger 26. An exchanger 26 of this type comprises an oil circuit 26' connected to the lubrication system 18, and an exchange surface which is exposed to a flow of cooling air. An exchange of calories between the surface and the oil circuit 26' of the exchanger makes it possible to cool the oil coming from the lubrication system 18 before returning it to this lubrication system 18, as illustrated by the dotted arrows in FIG. 1.
[0017] At least a portion of the cowling 16 may internally define an annular flow vein for an air flow around the turbomachine 14, such as a flow vein for a secondary flow or other. In this case, the exchange surface of the surface exchanger 26 is therefore swept by this air flow.
[0018] The exchanger 26 carried by the cowling 16 is connected to the lubrication system 18 by fluid connection means which must allow the opening of the panels 20 and in particular their pivoting, without necessarily requiring the exchanger 26 to be disconnected from the lubrication system 18.
[0019] In the current technique, these connection means are flexible and supple pipes 28, as illustrated in FIG. 2. Each of these pipes 28 comprises an end 28a secured to a panel 20 and intended to be connected to the exchanger 26 carried by this panel 20, and an opposite end 28b secured to the reactor mast 12 and intended to be connected to the lubrication system 18 of the turbomachine 14. Whatever the position of the panel 20, the oil circuit 26' of the exchanger 26 remains connected to the lubrication system 18 thanks to the flexibility of the pipes 28. FIG. 2 shows two distinct states of deformation of the same pipe 28 for two different positions of a panel 20.
[0020] This technology has drawbacks. First, it is necessary for the environment around the pipes 28 to remain free so as not to hinder the movement of the pipes 28 when opening and closing the panels 20. The pipes 28 also have a relatively long length to allow their bending without causing stresses leading to rupture. This technology is therefore relatively bulky. Furthermore, these pipes 28 are oversized to be sufficiently strong and have in particular a large diameter due to the presence of a thick protective layer around these pipes 28. Finally, this technology is relatively expensive and of significant mass. Furthermore, climate change is a major concern for many legislative and regulatory bodies around the world. Indeed, various restrictions on carbon emissions have been, are being or will be adopted by various states.In particular, an ambitious standard applies both to new types of aircraft and those in circulation requiring the implementation of technological solutions in order to make them compliant with current regulations. Civil aviation has been mobilizing for several years now to make a contribution to the fight against climate change. Technological research efforts have already led to very significant improvements in the environmental performance of aircraft. The Applicant takes into consideration the impact factors in all phases of design and development to obtain less energy-intensive, more environmentally friendly aeronautical components and products whose integration and use in civil aviation have moderate environmental consequences with the aim of improving the energy efficiency of aircraft.Consequently, the Applicant is constantly working to reduce its negative climate impact by using methods and operating virtuous development and manufacturing processes that minimize greenhouse gas emissions to the minimum possible in order to reduce the environmental footprint of its activity. This sustained research and development work focuses on new generations of aircraft engines, the weight reduction of aircraft, in particular through the materials used and lighter onboard equipment, the development of the use of electric technologies to provide propulsion, and, as essential complements to technological progress, aeronautical biofuels.
[0021] The present invention provides a simple, effective and economical solution to at least some of the above-mentioned problems of the prior art.
[0022] Summary of the invention
[0023] The invention is the result of technological research aimed at significantly improving aircraft performance and, in this sense, contributes to reducing the environmental impact of aircraft. The invention relates to a propulsion unit for an aircraft, this propulsion unit comprising:
[0024] - a turbomachine extending along a main axis and comprising a fluidic system,
[0025] - a cowling which extends along and around said main axis, the cowling comprising at least one panel which extends around said main axis, said at least one panel comprising a first longitudinal edge which is fixed by hinges which define a pivot axis of the panel, from a closed position in which it extends around the turbomachine to an open position in which it is spaced from the turbomachine, said at least one panel carrying at least one surface heat exchanger which comprises a fluid circuit connected to said fluid system, characterized in that the fluid circuit of each of the panels is connected to the fluid system by at least one first push-fit connector which is carried by the panel, this first push-fit connector being engaged in or on a second push-fit connector of the propulsion unit to ensure fluid communication between the connectors when the panel is in the closed position,and being disengaged from this second connection to break this fluid communication when the panel is in the open position, each of the first and second connections being equipped with a self-sealing valve.,
[0026] The invention thus proposes to connect the fluid circuit of the panel exchanger to the fluid system of the turbomachine, by means of interlocking connectors. It is understood that in the closed position, the first and second connectors are interlocked and ensure fluid communication between the fluid circuit of the exchanger and the fluid system. In the open position, the first and second connectors are disassembled from each other and the fluid circuit of the exchanger is no longer in fluid communication with the fluid system. It is therefore sufficient to close the panel to interlock the connectors and open the panel to disassemble the connectors. Each of these connectors is equipped with a self-sealing valve. In the present application, the term "valve" means an automatic closing system of the connector.When a fitting is fitted into another fitting, the valve of each of these fittings is in a position that allows fluid flow between the fittings. When a fitting is disassembled, the valve of this fitting is in a position that prevents fluid flow.
[0027] The propulsion 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:
[0028] - said at least one first interlocking connection is located on one of the edges of the panel, such as its first edge or a second edge opposite the first edge,
[0029] - said fluid circuit is an oil circuit or a coolant circuit,
[0030] - the turbomachine comprises a longitudinal structure which is located at a second longitudinal edge of the panel, opposite said first edge, when it is in the closed position, at least part of the second connections being carried by this structure,
[0031] - the propulsion unit comprises a reactor mast extending along an axis parallel to the main axis of the turbomachine, the turbomachine being fixed to the reactor mast and extending under or beside this reactor mast which is located at the level of said first longitudinal edge of the panel when it is in the closed position, at least part of the second connections being carried by this reactor mast,
[0032] - at least part of the second connections is carried by another of the panels,
[0033] - each of the first fittings is configured to be engaged in or on one of the second fittings in a direction which is tangent to a circumference centered on the main axis of the turbomachine, - the first and second fittings are located in planes perpendicular to the main axis of the turbomachine,
[0034] - each of the panels comprises at least two first connections, one of these first connections being connected to a fluid inlet of said circuit, and the other of these first connections being connected to a fluid outlet of this circuit,
[0035] - the propulsion unit comprises at least two second connections, one of these second connections being connected to a fluid inlet of said fluid system, and the other of these second connections being connected to a fluid outlet of this system,
[0036] - each of the panels comprises an internal concave surface on which said at least one exchanger is located,
[0037] -- each of the first and second connections is equipped with a ball or piston valve,
[0038] - the propulsion assembly comprises devices for locking the panels in the closed position, these devices being operable from an unlocking position to a locking position, these devices being configured to cause the first fittings to engage in or on the second fittings when they are brought from their unlocking position to their locking position,
[0039] - these devices are located next to said first connections,
[0040] -- the cowling surrounds at least part of the turbomachine,
[0041] - the cowling comprises two panels of generally semi-circular shape which extend on either side of said main axis,
[0042] - each of these panels has an upper and lower longitudinal edge,
[0043] - the upper longitudinal edge of the or each panel is fixed by the hinges,
[0044] - the other of the panels carries another heat exchanger or another type of fluidic equipment, -- said first and second fittings cooperate with each other by male-female interlocking,
[0045] -- the or each panel has a general semi-circular shape.
[0046] Brief description of the figures
[0047] Other characteristics and advantages will emerge from the following description of a non-limiting embodiment of the invention with reference to the appended drawings in which:
[0048] [Fig. 1] Figure 1 is a partial schematic perspective view of a propulsion unit for an aircraft,
[0049] [Fig. 2] Figure 2 is a schematic perspective view of means for fluidic connection of a heat exchanger to a fluidic system, according to the technique prior to the invention, its cover panels being in the open position,
[0050] [Fig. 3] Figure 3 is a schematic perspective and front view of a propulsion unit according to one embodiment of the invention,
[0051] [Fig. 4] Figure 4 is a very schematic view of the propulsion unit of Figure 3, its cowling panels being in the closed position,
[0052] [Fig. 5] Figure 5 is a very schematic view of the propulsion unit of Figure 3, one of its cowling panels being in the open position and the other being in the closed position,
[0053] [Fig. 6] Figure 6 is a schematic perspective view of a first plug-in connector and a second plug-in connector usable in the context of the present invention,
[0054] [Fig. 7] Figure 7 is a schematic half-view in axial section of a propulsion unit according to an alternative embodiment of the invention,
[0055] [Fig. 8] Figure 8 is a schematic perspective view of connections of the propulsion assembly of Figure 7, these connections being fitted into one another, [Fig. 9] Figure 9 is a schematic perspective view of the connections of the propulsion assembly of Figure 7, these connections being disassembled from one another,
[0056] [Fig. 10] Figure 10 is a schematic perspective view of a female connector of the propulsion assembly of Figure 7,
[0057] [Fig. 11] Figure 11 is a schematic perspective view of a male connector of the propulsion assembly of Figure 7,
[0058] [Fig. 12] Figure 12 is a schematic half-view in axial section of a propulsion unit according to another alternative embodiment of the invention, [Fig. 13] Figure 13 is a schematic half-view in cross-section of the propulsion unit of Figure 12, one of its cowling panels being in the open position and the other being in the closed position,
[0059] [Fig. 14] Figure 14 is a schematic sectional view of connections of the propulsion unit of Figure 12, these connections being fitted into each other,
[0060] [Fig. 15] Figure 15 is a schematic sectional view of the connections of the propulsion assembly of Figure 12, these connections being disassembled from each other,
[0061] [Fig. 16] Figure 16 is a schematic half-view in axial section of a propulsion unit according to another alternative embodiment of the invention, [Fig. 17] Figure 17 is a schematic half-view in cross-section of the propulsion unit of Figure 16, one of its cowling panels being in the open position and the other being in the closed position,
[0062] [Fig. 18] Figure 18 is a schematic sectional view of connections of the propulsion unit of Figure 16, these connections being fitted into each other,
[0063] [Fig. 19] Figure 19 is a schematic sectional view of the connections of the propulsion assembly of Figure 16, these connections being disassembled from each other, [Fig. 20] Figure 20 is a schematic sectional view of connections of the propulsion assembly of Figure 16, these connections being fitted into each other,
[0064] [Fig. 21] Figure 21 is a schematic sectional view of the connections of the propulsion assembly of Figure 16, these connections being disassembled from each other, and
[0065] [Fig. 22-23] Figures 22 and 23 are schematic sectional views similar to those of Figures 20 and 21 and illustrating another alternative embodiment.
[0066] Detailed description of the invention
[0067] Figures 1 and 2 have already been described in the above.
[0068] Reference is made to Figures 3 to 6 which illustrate an embodiment of a propulsion assembly 10 according to the invention.
[0069] The propulsion unit 10 may be located under the wing of the aircraft or at the rear of the fuselage of the aircraft, for example.
[0070] Furthermore, the propulsion unit 10 may be of any type and for example of the double or triple flow turbojet type, turbomachine with ducted or unducted fan, turboprop, open rotor, etc.
[0071] The propulsion assembly 10 is similar to that described above in relation to Figure 1 and comprises:
[0072] - a reactor mast 12 although this is optional,
[0073] - a turbomachine 14 which comprises a fluidic system 18, in particular its bearings and rotating elements, and
[0074] - a cowling 16 which can surround the turbomachine 14, as in the example shown.
[0075] The reactor mast 12 has an elongated shape along a first axis A.
[0076] The turbomachine 14 has an elongated shape along a second axis B substantially parallel to the first axis A. The turbomachine 14 is preferably located under the reactor mast 12 so that the axes A, B are contained in the same vertical plane P. The reactor mast 12 is thus located at 12 o'clock (12 hours) by analogy with the dial of a clock.
[0077] At 6 o'clock (6 hours), the turbomachine 14 comprises a longitudinal mast 17 which forms part of the cowling 16 of the turbomachine 14.
[0078] The cowling 16 may comprise several pieces and comprises at least two panels 20 of generally semi-circular shape in the example shown. These panels 20 extend on either side of the vertical plane P.
[0079] In the example shown, the panels 20 comprise upper longitudinal edges 22 which are fixed to the turbomachine 14 or to the reactor mast 12 by hinges 25. The upper edges 22 of the panels 20 are separated from each other by the reactor mast 12 in the example shown.
[0080] Each of the panels 20 is articulated around a third axis C which can be parallel to the axis B for example, from a closed position in which its lower edge 24 is applied against the structure 17, as is the case of the left panel in figure 4, to an open position in which its lower edge 24 is spaced from the structure 17, as is the case of the panels 20 of figure 3 and the left panel of figure 5.
[0081] The angular movement (arrow F1 - figure 5) between the two positions is for example greater than 30° around the C axis.
[0082] Each of the panels 20 comprises a wall 25 of generally curved shape which comprises an external convex surface 25a and an internal concave surface 25b. At least one of these surfaces 25a, 25b is intended to be swept by a flow of gas.
[0083] Each of the panels 20 further comprises at least one surface heat exchanger 26.
[0084] In the example shown, the exchanger 26 is located on the internal concave surface 25b of the wall 25 and comprises a fluid circuit 26' intended to be connected to the fluid system 18, and an exchange surface which is exposed to the flow of cooling gas. This position of the exchanger 26 is however not limiting. Alternatively, the exchanger 26 could for example be on an external convex surface of the panel 20.
[0085] Indeed, in the context of the present invention, the panel 20 may be an internal or external panel of the turbomachine and of the propulsion assembly, and may be swept by a flow of gas passing inside or outside the panel. The exchanger 26 is therefore located inside or outside the panel 20, and therefore positioned on an internal or external surface of this panel 20.
[0086] The fluid system 18 is for example a lubrication system but could alternatively be a cooling system. The fluid circuit 26' is for example an oil circuit but could alternatively be a coolant circuit.
[0087] The fluid circuit 26' comprises a fluid inlet and outlet 26a, 26b which are connected to the fluid system 18 by fluid connection means.
[0088] In the context of the present invention, the means for connecting an exchanger 26 are carried by the panel 20 which carries this exchanger. More precisely, the wall 25 of each of the panels 20 carries at least one interlocking connector 30 for fluid connection of the circuit 26' to the fluid system 18.
[0089] In the example shown, the connectors 30 are located on the lower edges 24 of the panels 20. Figure 3 shows that each panel 20 comprises two male-type interlocking connectors 30 which are axially spaced from each other along the axis B. Each of these connectors 30 is intended to cooperate by male-female interlocking with a complementary connector 30' carried by the mast 17. It is therefore understood that the mast 17 carries four connectors in the example shown, two connectors 30' are located on one side of the structure and intended to cooperate with the connectors 30 of a first panel 20, and two other connectors 30' are located on the other side of the structure and intended to cooperate with the connectors 30 of the second panel 20.
[0090] One of the connections 30 of each panel 20 is connected to the inlet 26a of the circuit 26' of the exchanger 26 of this panel, and the other connection 30 of this panel 20 is connected to the outlet of the circuit 26'. This connection can be made by rigid pipes 32.
[0091] On each side of the structure 17, one of the connections 30' is connected to the inlet 18a of the fluidic system 18, and the other connection 30' is connected to the outlet 18b of this system 18. This connection can be made by rigid pipes 34.
[0092] Figure 6 shows a non-limiting example of embodiment of the connectors 30, 30'. The connectors 30, 30' are preferably intended to cooperate with each other by male-female interlocking, the panels 20 being able to carry the male connectors, or conversely female connectors, and the structure 17 being able to carry the female connectors, or conversely male connectors.
[0093] A male connector, such as that illustrated on the left in Figure 6, comprises a projecting end 30a, for example cylindrical, and an opposite end 30b for connection to one of the pipes 32.
[0094] The end 30a may comprise an annular groove 30d for housing a seal such as an O-ring for example.
[0095] A female connector, such as that illustrated on the right in Figure 6, comprises a hollow end 30c, for example cylindrical, and an opposite end 30b for connection to one of the pipes 34. The ends 30a, 30c are intended to engage one into the other. Each of these connectors 30, 30' comprises an internal passage extending between the two ends of the connector and allowing fluid circulation between these ends.
[0096] As seen in Figures 4 and 5, the engagement directions of the fittings (arrow F2) are tangent to circumferences centered on the B axis.
[0097] The fittings 30, 30' are equipped with self-sealing valves 36, i.e. valves which allow the internal passages of the fittings to be closed automatically (see figure 6). Each valve 36 is able to move from a position for closing the passage to a position for opening this passage, simply by fitting the fittings into each other. Each valve 36 is able to move from a position for opening the passage to a position for closing this passage, simply by separating the fittings from each other.
[0098] When a panel 20 is in the closed position, its fittings 30 are engaged in the fittings 30' of the structure 17 and this interlocking ensures fluid communication between the fittings and the connection of the circuit 26' to the fluid system 18. The valves 36 of the fittings are in a position where they do not hinder the fluid passage between the fittings.
[0099] When a panel 20 is in the open position, its connections 30 are disengaged from the connections 30' and the valves 36 close the fluid passages of these connections.
[0100] In the example shown, the propulsion assembly 10 comprises devices 40 for locking the panels 20 in the closed position (Figures 4 and 5). The lower edge 24 of each panel 20 or of one of the panels 20 is equipped with a locking device 40 which cooperates with the structure 17 or the lower edge 24 of the other panel 20.
[0101] Figures 7 to 11 illustrate an alternative embodiment of a propulsion assembly 10 according to the invention in which the elements already described above in relation to Figures 3 to 6 are designated by the same references.
[0102] One of the differences between this variant and the previous embodiment is that the connections 30 of the panels 20 are located on their upper edges 22, therefore in the vicinity of the hinges 25 of these panels 20.
[0103] Another difference related to the first is that the connections 30' which cooperate with the connections 30 of the panels 20 are carried by the reactor mast 12. One of the connections 30 of each panel 20 is connected to the inlet 26a of the circuit 26' of the exchanger 26 of this panel, and the other connection 30 of this panel 20 is connected to the outlet 26b of the circuit 26'. This connection can be made by rigid pipes 32.
[0104] On each side of the reactor mast 12, one of the connections 30' is connected to the inlet 18a of the fluidic system 18, and the other connection 30' is connected to the outlet 18b of this system 18. This connection can be made by rigid pipes 34.
[0105] Figures 8 to 11 show another non-limiting example of embodiment of the connectors 30, 30'. The connectors 30, 30' are preferably intended to cooperate together by male-female interlocking, the panels 20 being able to carry the male connectors, or conversely female, and the reactor mast 12 being able to carry the female connectors, or conversely male.
[0106] A male connector, such as that illustrated in Figure 11, comprises a projecting end 30a, for example cylindrical, and an opposite end 30b for connection to one of the pipes 32.
[0107] The projecting end 30a may carry a seal 31 such as an O-ring.
[0108] A female connector, such as that illustrated on the right in Figure 10, comprises a hollow end 30c, for example cylindrical, and an opposite end 30b for connection to one of the pipes 34. The ends 30a, 30c are intended to engage one into the other. Each of these connectors 30, 30' comprises an internal passage extending between the two ends of the connector and allowing fluid circulation between these ends.
[0109] The connections 30, 30' of figures 8 to 11 are in the form of boxes.
[0110] As seen in Figures 8 and 9, the engagement directions of the fittings (arrow F2 - Figure 9) are tangent to circumferences centered on the B axis.
[0111] The connections 30, 30' are equipped with valves 36 as mentioned above. Figures 12 to 15 illustrate an alternative embodiment of a propulsion unit 10 according to the invention in which the elements already described above are designated by the same references.
[0112] As in the embodiment of Figures 3 to 6, the connections 30 of the panels 20 are located on their lower edges 24.
[0113] Figures 14 and 15 show a more concrete example of the embodiment of the devices 40 for locking the panels 20 together.
[0114] At least one of the panels 20 may comprise one or more of these devices 40. Each device 40 comprises a hook 42 and a lever 44 for actuating this hook 42. A first of the panels 20 carries this device 40 and the other panel 20 comprises, opposite this device, a finger 46 or the like intended to cooperate with this hook 42. When the edges 24 of the panels are brought closer to each other, the hook 42 engages on the finger 46 and the actuation of the lever 44 causes a tensile force of the hook 42 on the side opposite the finger 46, which causes the panels 20 to be clamped against each other and locked.
[0115] Figures 14 and 15 also show a more concrete example of the embodiment of the end pieces 30, 30'. The end pieces 30 are straight and the end pieces 30' are bent in this example.
[0116] Furthermore, the connectors 30 are of the male type and their valves 36 are here of the ball type. A ball 50 is housed in the connector 30 and movable from a closed position of the connector, in which it rests on a seat 52 of the connector 30, to an open position of the connector, in which it is moved away from this seat 52. The ball 50 is urged into the closed position by a spring 54.
[0117] The connectors 30' are of the female type and their valves 36 are here of the piston type. A piston 60 is housed in the connector 30' and movable from a closed position of the connector, in which it bears on a seat 62 of the connector 30', to an open position of the connector, in which it is moved away from this seat 62. The piston 60 is urged into the closed position by a spring 64. Furthermore, the piston 60 comprises an extension 66 which is intended to bear on the ball 50 of the corresponding connector 30 and urge it into its open position, when the connectors 30, 30' are engaged in one another (arrow F2).
[0118] Either of the fittings 30, 30' carries a seal 31 such as an O-ring.
[0119] Figures 16 to 21 illustrate an alternative embodiment of a propulsion assembly 10 according to the invention in which the elements already described in the above are designated by the same references.
[0120] The connections 30 of the panels 20 are here located both on their lower edges 24 and their upper edges 22. The upper edges 22 of the panels 20 thus comprise connections 30 which are similar to those of figures 7 to 11 and which cooperate with connections 30' carried by the reactor mast 12. These connections 30 are for example connected to an inlet 26a and to an outlet 26b of the circuit 26' of one or more exchangers 26.
[0121] The lower edge 24 of one of the panels 20 comprises connectors 30 which are similar to those of figures 3 to 6 and which cooperate with connectors 30' carried by the other of the panels 20. The direct connection of the connectors 30, 30' of the panels 20 makes it possible to connect their circuits 26' together, these circuits 26' being connected to the fluidic system 18 by the connectors 30 located on the upper edges 22 of the panels 20.
[0122] The connections 30 located on the upper edges 22 of the panels 20 are straight and cooperate with elbow connections 30' of the reactor mast 12, in the example illustrated in figures 18 and 19.
[0123] The connections 30, 30' of the lower edges 24 of the panels 20 are straight in the example illustrated in figures 20 and 21.
[0124] A locking device 40 is located at these edges 24 to cause the fittings 30, 30' to fit together during locking. Figures 22 and 23 show another example of the construction of the fittings 30, 30' at the lower edges 24 of the panels 20.
[0125] The lower edge 24 of each of the panels 20 is equipped with two connectors 30 or 30' which are arranged next to each other, and for example one above the other.
[0126] A locking device 40 is located at these edges 24 to cause the fittings 30, 30' to fit together during locking.
[0127] The present invention has several advantages including:
[0128] - the connections 30, 30' are rigid, which represents a gain in mass and cost compared to the connection means of the prior art;
[0129] - the fittings can be associated or mounted near the hinges 25,
[0130] - the diameter of the connections can be reduced compared to that of the connection means of the prior art, thus also limiting their size,
[0131] - there is no movement of the pipes connected to these fittings, which simplifies the integration and assembly of the different parts,
[0132] - the connection length of the fluid circuit to the fluid system is optimized to reduce its size and cost,
[0133] - the maintenance of the propulsion unit is improved by optimizing the dismantling of the fluid circuit of the exchanger of each panel,
[0134] - quick connection of fittings and quick disconnection of fittings without risk of leakage,
[0135] - no need for specific tools to close or open fittings as well as fluid circuits, etc.
Claims
CLAIMS 1. Propulsion assembly (10) for an aircraft, this propulsion assembly (10) comprising: - a turbomachine (14) extending along a main axis (B) and comprising a fluidic system (18), - a cowling (16) which extends along and around said main axis (B), the cowling (16) comprising at least one panel (20) which extends around said main axis (B), said at least one panel (20) comprising a first longitudinal edge (22) which is fixed by hinges (25) which define an axis (C) for pivoting the panel, from a closed position in which it extends around the turbomachine (14) to an open position in which it is spaced from the turbomachine (14), said at least one panel (20) carrying at least one surface heat exchanger (26) which comprises a fluid circuit (26') connected to said fluid system (18), characterized in that the fluid circuit (26') (20) is connected to the fluid system (18) by at least one first push-fit connector (30, 30') which is carried by the panel (20),this first push-fit connection (30) being engaged in or on a second push-fit connection (30') of the propulsion assembly (10) to ensure fluid communication between the connections (30, 30') when the panel (20) is in the closed position, and being disengaged from this second connection (30') to break this fluid communication when the panel (20) is in the open position, each of the first and second connections (30, 30') being equipped with a self-sealing valve., 2. Propulsion assembly (10) according to claim 1, in which the turbomachine (14) comprises a longitudinal structure (17) which is located at a second longitudinal edge (24) of the panel (20), opposite said first edge (22), when it is in the closed position, at least a portion of the second connections (30') being carried by this structure (17).
3. A propulsion assembly (10) according to claim 1 or 2, wherein the propulsion assembly (10) comprises a reactor mast (12) extending along of an axis (A) parallel to the main axis (B) of the turbomachine (14), the turbomachine (14) being fixed to the reactor mast (12) and extending under or beside this reactor mast which is located at the level of said first longitudinal edge (22) of the panel (20) when it is in the closed position, at least a part of the second connections (30') being carried by this reactor mast (12).
4. Propulsion assembly (10) according to one of the preceding claims, in which at least part of the second connections (30') is carried by another of the panels (20).
5. Propulsion assembly (10) according to one of the preceding claims, in which each of the first connections (30, 30') is configured to be engaged in or on one of the second connections (30') in a direction (F2) which is tangent to a circumference centered on the main axis (B) of the turbomachine (14).
6. Propulsion assembly (10) according to one of the preceding claims, in which the first and second connections (30, 30') are located in planes perpendicular to the main axis (B) of the turbomachine (14).
7. Propulsion assembly (10) according to one of the preceding claims, in which each of the panels (20) comprises at least two first connectors (30), one of these first connectors (30) being connected to a fluid inlet (26a) of said circuit (26'), and the other of these first connectors (30) being connected to a fluid outlet (26b) of this circuit (26').
8. Propulsion assembly (10) according to claim 7, in which it comprises at least two second connections (30'), one of these second connections (30') being connected to a fluid inlet (18a) of said fluid system (18), and the other of these second connections (30') being connected to a fluid outlet (18b) of this system (18).
9. Propulsion assembly (10) according to one of the preceding claims, in which each of the panels (20) comprises an internal concave surface on which said at least one exchanger (26) is located.
10. Propulsion assembly (10) according to one of the preceding claims, in which it comprises devices (50) for locking the panels (20) in the closed position, these devices (50) being operable from an unlocking position to a locking position, these devices (50) being configured to cause the first fittings (30) to engage in or on the second fittings (30') when they are brought from their unlocking position to their locking position.
11. Propulsion assembly (10) according to the preceding claim, wherein said locking devices (50) are located next to said first connections 12. Propulsion assembly (10) according to one of the preceding claims, wherein said at least one first interlocking connection is located on one of the edges of the panel, such as its first edge or a second edge opposite the first edge.
13. Propulsion assembly (10) according to one of the preceding claims, in which said fluid circuit is an oil circuit or a coolant circuit.
14. Propulsion assembly (10) according to one of the preceding claims, in which the cowling comprises two panels of generally semi-circular shape which extend on either side of said main axis, the upper longitudinal edge of the or each panel is fixed by the hinges. Propulsion assembly (10) according to one of the preceding claims, in which the other of the panels carries another heat exchanger or another type of fluidic equipment.