Propulsion unit for an aircraft
By adopting plug-in connectors and self-closing valves in the aircraft propulsion unit, the high weight, high cost and environmental regulations of the flexible hose connection device are solved, and a lightweight, economical and convenient maintenance fluid connection is achieved.
Patent Information
- Application Number
- CN202380081477.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Priority Date
- 2022-11-24
- Filing Date
- 2023-11-15
- Publication Date
- 2025-07-08
AI Technical Summary
In existing aircraft propulsion units, flexible hose connection devices lead to high weight, high cost, susceptible to climate change restrictions, and do not comply with environmental regulations.
The plug-in connector and self-closing valve design provide fluid communication in the closed position through the plug-in connector and disconnect the fluid passage in the open position. The connector is equipped with a self-closing valve to automatically control the opening and closing of the fluid passage.
Reduces weight and cost, simplifies component integration and installation, optimizes fluid circuit connection length, improves maintenance ease, and complies with environmental regulations.
Smart Images
Figure CN120282913A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to a propulsion unit for an aircraft. Background Art
[0002] The prior art particularly includes the documents FR-A1-3 094 750, KR-A1-2019 0071093, US-A1-2020 / 182389 and FR-A1-3 098 289.
[0003] Figure 1 A propulsion unit 10 for an aircraft is shown.
[0004] For the purposes of the present application, the propulsion unit 10 for an aircraft is considered to mean an assembly including an engine pylon 12, a turbomotor 14 and its nacelle 16.
[0005] The engine pylon 12 is a solid part for fixing the turbomotor 14 to the aircraft (e.g., to the wing of the aircraft). Thus, the engine pylon 12 includes elements for fixing to the aircraft and fixing elements of the turbomotor 14. The engine pylon 12 has a generally elongated shape and extends along a first axis A.
[0006] In the present application, the turbomotor 14 is located below the engine pylon 12 or beside the engine pylon. The turbomotor can be suspended from the engine pylon 12 below the wing of the aircraft. Alternatively, the turbomotor can be installed at the rear of the fuselage of the aircraft.
[0007] The turbomotor 14 has a generally elongated shape along a second axis B, and the second axis B can be parallel to the first axis A. The first axis A and the second axis B are located in the same plane P. The plane P can be vertical or inclined with respect to the vertical direction.
[0008] When observing the assembly from the rear, by analogy with the face of a clock, the 12 o'clock position (12h) and the 6 o'clock position (6h) are the positions of the components around the second axis B. The 12 o'clock position is located in the plane P and at the engine pylon 12, while the 6 o'clock position is located in the plane P and below the turbomotor 14.
[0009] The turbomotor 14 includes a lubrication system 18, and the lubrication system 18 particularly lubricates the bearings of the turbomotor by circulating lubricating oil.
[0010] The fairing 16 surrounds the turbomachine 14 and extends along a second axis B. The fairing 16 may include several parts and includes two panels 20 of a generally semi-circular shape extending on either side of the aforementioned plane P. These panels 20 include an upper longitudinal edge 22 and a lower longitudinal edge 24, the upper longitudinal edge 22 being fixed to the engine mount 12 and arranged on either side of the plane P, near the 12 o'clock position, and the lower longitudinal edge 24 being generally fixed to each other and thus located at the 6 o'clock position.
[0011] These panels 20 are hinged at their upper edges 22 such that the fairing 16 can be opened to allow access to the turbomachine 14, for example during ground maintenance operations. This hinging is made possible by hinges 25 for fixing the upper edges 22 of the panels 20 to the engine mount 12. Each panel 20 is hinged about a third axis C that may be parallel to the second axis B, for example moving from a closed position where the lower edge 24 of each panel 20 is at the 6 o'clock position to an open position where the lower edge 24 of each panel 20 is away from the 6 o'clock position.
[0012] The fairing 16 may carry at least one surface heat exchanger 26. This type of exchanger 26 includes an oil circuit 26' connected to the lubrication system 18 and an exchange surface exposed to a cooling air flow. Heat exchange between the surface of the exchanger and the oil circuit 26' cools the oil from the lubrication system 18 and then returns the oil from the lubrication system 18 to the lubrication system 18, as Figure 1 shown by the dashed arrows.
[0013] At least a part of the fairing 16 may delimit internally an annular duct for the flow of air around the turbomachine 14, such as a flow duct for a secondary flow, etc. In this case, the exchange surface of the surface heat exchanger 26 is swept by this air flow.
[0014] The exchanger 26 carried by the fairing 16 is connected to the lubrication system 18 by fluid connection means that must allow the panels 20 to be opened, in particular pivoted, without requiring the exchanger 26 to be disconnected from the lubrication system 18.
[0015] In the current state of the art, these connection means are flexible hoses 28, as Figure 2 shown. Each of these hoses 28 includes an end 28a and an opposite end 28b, the end 28a being fixed to the panel 20 and configured to be connected to the exchanger 26 carried by this panel 20, and the opposite end 28b being fixed to the engine mount 12 and configured to be connected to the lubrication system 18 of the turbomachine 14. Due to the flexibility of the hoses 28, the oil circuit 26' of the exchanger 26 remains connected to the lubrication system 18 regardless of the position of the panel 20. Figure 2 Two different deformed states of the same hose 28 are shown for two different positions of the panel 20.
[0016] This technology has its drawbacks. First, the environment around the hose 28 needs to be unconstrained so as not to impede the movement of the hose 28 when the panel 20 is opened and closed. The hose 28 also needs to be relatively long so that the hose 28 can be bent without causing stresses that would lead to rupture. As a result, this technology is relatively cumbersome. In addition, due to the thick protective layer around these hoses 28, these hoses 28 are oversized to have sufficient resistance, particularly with a large diameter. Finally, this technology is relatively expensive and of high quality. Climate change is also a major concern for many legislative and regulatory bodies around the world. In fact, various restrictions on carbon emissions have been, are being, or will be adopted in different places. In particular, an ambitious standard applies to both new types of aircraft and those already in service, which requires the implementation of technical solutions to make the aircraft comply with the current regulations. For several years, the civil aviation industry has been working to help address climate change. Technical research work has led to a significant improvement in the environmental performance of aircraft. The applicant has taken into account the influencing factors at all stages of design and development to obtain aviation components and products that consume less energy, are more environmentally friendly, and have moderate environmental consequences for their integration and use in civil aviation, with the aim of improving the energy efficiency of the aircraft. Therefore, the applicant has been working to reduce its negative impact on the climate by adopting benign methods and using benign development and manufacturing methods, and to minimize greenhouse gas emissions as much as possible to reduce the environmental footprint of the applicant's business. This ongoing research and development work focuses on a new generation of aircraft engines, particularly on making the aircraft lighter through the use of materials and lighter on-board equipment, developing propulsion using electric technology, and developing aviation biofuels as a necessary complement to technological progress.
[0017] The present invention provides a simple, effective and economical solution to at least some of the foregoing problems of the prior art. Summary of the Invention
[0018] The present invention is the result of a technical research aimed at significantly improving the performance of an aircraft and, in this way, contributing to reducing the environmental impact of the aircraft.
[0019] The present invention relates to a propulsion unit for an aircraft, the propulsion unit comprising:
[0020] - a turbomachine that extends along a main axis and includes a fluid system,
[0021] - A fairing that extends along and around the main axis. The fairing includes at least one panel that extends around the main axis. The at least one panel includes a first longitudinal edge that is fixed by a hinge. The hinge defines an axis for pivoting the panel from a closed position to an open position. In the closed position, the panel extends around the turbomachine, and in the open position, the panel moves away from the turbomachine. The at least one panel carries at least one surface area heat exchanger. The at least one surface area heat exchanger includes a fluid circuit connected to the fluid system.
[0022] It is characterized in that the fluid circuit of each panel in the panels is connected to the fluid system through at least one first plug connector carried by the panel. The first plug connector engages in or on a second plug connector of the propulsion unit to provide fluid communication between the connectors when the panel is in the closed position, and disengages from the second connector when the panel is in the open position to interrupt the fluid communication. Each of the first connector and the second connector is equipped with a self-closing valve.
[0023] Therefore, the present invention proposes to connect the fluid circuit of the exchanger of the panel to the fluid system of the turbomachine by plug connection. It should be understood that in the closed position, the first connector and the second connector are installed in each other and provide fluid communication between the fluid circuit of the exchanger and the fluid system. In the open position, the first connector and the second connector are disassembled from each other, and the fluid circuit of the exchanger is no longer in fluid communication with the fluid system. Therefore, it is sufficient to close the panel to install the connectors together and open the panel to disassemble the connectors. Each of these connectors is equipped with a self-closing valve. In this application, a valve refers to a system for automatically closing the connector. When one connector is installed in another connector, the valve of each of these connectors is in a position where a fluid passage can be achieved between the connectors. When a connector is disassembled, the valve of that connector is in a position to block the fluid passage.
[0024] The propulsion unit according to the present invention may include one or more of the following features adopted individually or in combination with each other:
[0025] - The at least one first plug connector is located on one of the edges of the panel, for example, on the first edge of the panel or on the second edge opposite to the first edge.
[0026] - The fluid circuit is an oil circuit or a liquid coolant circuit.
[0027] - The turbomachine includes a longitudinal structure which is at the level of the second longitudinal edge of the panel opposite the first edge, and when the panel is in the closed position, at least some of the second connectors are carried by this structure.
[0028] - The propulsion unit includes an engine pylon which extends along an axis parallel to the main axis of the turbomachine, to which the turbomachine is fixed and extends below or beside this engine pylon, and when the panel is in the closed position, the engine pylon is at the first longitudinal edge of the panel, and at least a portion of the second connectors are carried by this engine pylon.
[0029] - At least a portion of the second connectors are carried by another panel in the panels.
[0030] - Each of the first connectors is configured to engage in or on one of the second connectors in a direction tangential to the circumference centered on the main axis of the turbomachine.
[0031] - The first connectors and the second connectors are in a plane perpendicular to the main axis of the turbomachine.
[0032] - Each of the panels includes at least two first connectors, one of these first connectors being connected to the fluid inlet of the circuit and the other of these first connectors being connected to the fluid outlet of the circuit.
[0033] - The propulsion unit includes at least two second connectors, one of these second connectors being connected to the fluid inlet of the fluid system and the other of these second connectors being connected to the fluid outlet of the system.
[0034] - Each of the panels includes a concave surface on which the at least one exchanger is located.
[0035] -- Each of the first connectors and the second connectors is equipped with a ball valve or a piston valve.
[0036] - The propulsion unit includes devices for locking the panel in the closed position, which can be operated from an unlocked position to a locked position, and which are configured such that when these devices are brought from their unlocked position to their locked position, the first connectors are inserted into or onto the second connectors.
[0037] - These devices are located beside the first connectors.
[0038] -- The fairing surrounds at least a portion of the turbomachine.
[0039] - The fairing includes two panels of a generally semi-circular shape extending on either side of the main axis,
[0040] - Each of these panels includes an upper longitudinal edge and a lower longitudinal edge,
[0041] - The upper longitudinal edge of the panel or each panel is fixed by a hinge,
[0042] - The other panel of the panels carries another heat exchanger or another type of fluid device,
[0043] -- The first connector and the second connector cooperate with each other by male-female insertion,
[0044] -- The panel or each panel is generally semi-circular in shape. Description of the Drawings
[0045] Further features and advantages will become apparent from the following description of non-limiting embodiments of the invention with reference to the drawings, in which:
[0046] Figure 1 Figure 1 is a partial schematic perspective view of a propulsion unit for an aircraft,
[0047] Figure 2 Figure 2 is a schematic perspective view of a connecting device for fluidly connecting a heat exchanger to a fluid system according to the prior art of the invention, with its fairing panels in the open position,
[0048] Figure 3 Figure 3 is a schematic front perspective view of a propulsion unit according to an embodiment of the invention,
[0049] Figure 4 Figure 4 is Figure 3 a very schematic view of the propulsion unit in
[0050] Figure 5 Figure 5 showing Figure 3 a very schematic view of the propulsion unit in
[0051] Figure 6 Figure 6 is a schematic perspective view of a first plug connector and a second plug connector that can be used in the context of the invention,
[0052] Figure 7 Figure 7 is a schematic half - view of an axial cross - section of a propulsion unit according to a variant embodiment of the present invention,
[0053] Figure 8 Figure 8 is Figure 7 a schematic perspective view of connectors of the propulsion unit, which are inserted one inside the other,
[0054] Figure 9 Figure 9 is Figure 7 a schematic perspective view of connectors of the propulsion unit, which are detachable from each other,
[0055] Figure 10 Figure 10 is Figure 7 a schematic perspective view of the female connector of the propulsion unit,
[0056] Figure 11 Figure 11 is Figure 7 a schematic perspective view of the male connector of the propulsion unit shown in,
[0057] Figure 12 Figure 12 is a schematic half - view of an axial cross - section of a propulsion unit according to another variant embodiment of the present invention,
[0058] Figure 13 Figure 13 is Figure 12 a schematic cross - sectional half - view of the propulsion unit in, where one of its fairing panels is in the open position and the other fairing panel is in the closed position,
[0059] Figure 14 Figure 14 is for Figure 12 a schematic cross - sectional view of connectors of the propulsion unit shown in, which are inserted one inside the other,
[0060] Figure 15 Figure 15 is Figure 12 a schematic cross - sectional view of connectors of the propulsion unit, which are detachable from each other,
[0061] Figure 16 Figure 16 is a schematic half - view of an axial cross - section of a propulsion unit according to another variant embodiment of the present invention,
[0062] Figure 17 Figure 17 is Figure 16 Schematic cross-sectional half view of the propulsion unit, in which one of the fairing panels is in the open position and the other fairing panel is in the closed position,
[0063] Figure 18 Figure 18 is Figure 16 Schematic cross-sectional view of the connectors of the propulsion unit shown, these connectors being inserted one inside the other,
[0064] Figure 19 Figure 19 is Figure 16 Schematic cross-sectional view of the connectors of the propulsion unit, these connectors being detachable from each other,
[0065] Figure 20 Figure 20 is Figure 16 Schematic cross-sectional view of the connectors of the propulsion unit shown, these connectors being inserted one inside the other,
[0066] Figure 21 Figure 21 is Figure 16 Schematic cross-sectional view of the connectors of the propulsion unit, these connectors being detachable from each other, and
[0067] [Figures 22 to 23] Figures 22 and 23 are schematic cross-sectional views similar to Figure 20 and Figure 21 and show another variant embodiment. Detailed description
[0068] has been described above Figure 1 and Figure 2 .
[0069] Reference Figures 3 to 6 shows an embodiment of the propulsion unit 10 according to the present invention.
[0070] For example, the propulsion unit 10 can be located under the wing of an aircraft or at the rear of the fuselage of an aircraft.
[0071] The propulsion unit 10 can be any type of propulsion unit, such as a turbojet engine with two or three streams, a turbofan engine with a ducted fan or a ductedless fan, a turboprop engine, an open rotor, etc.
[0072] The propulsion unit 10 is similar to the propulsion unit described above in connection with Figure 1 and includes:
[0073] - An engine mount 12, although the engine mount 12 is optional,
[0074] - A turbomachine 14, the turbomachine 14 comprising a fluid system 18, in particular a fluid system 18 for the bearings and rotating elements of the turbomachine 14, and
[0075] - A cowling 16, the cowling 16 being able to surround the turbomachine 14, as in the example shown.
[0076] The engine mount 12 has an elongated shape along a first axis A.
[0077] The turbomachine 14 has an elongated shape along a second axis B, the second axis B being substantially parallel to the first axis A. The turbomachine 14 is preferably located below the engine mount 12 such that the axes A and B are contained in the same vertical plane P.
[0078] Thus, by analogy with the face of a clock, the engine mount 12 is located at the 12 o'clock position (12 h).
[0079] At the 6 o'clock position (6 h), the turbomachine 14 includes a longitudinal mount 17, the longitudinal mount 17 forming part of the cowling 16 of the turbomachine 14.
[0080] In the example shown, the cowling 16 may include several parts and includes at least two panels 20 of substantially semi-circular shape. These panels 20 extend on either side of a vertical plane.
[0081] In the example shown, the panels 20 include longitudinal upper edges 22, the longitudinal upper edges 22 being fixed to the turbomachine 14 or the engine mount 12 by hinges 25. In the example shown, the upper edges 22 of the panels 20 are separated from one another by the engine mount 12.
[0082] Each of the panels 20 is hinged about a third axis C which may be parallel to the axis B, for example from a closed position to an open position, in the closed position, the lower edge 24 of each panel bears against the structure 17, as Figure 4 in the case of the panel on the left hand side in Figure 3 and in the open position, the lower edge 24 of each panel is spaced apart from the structure 17, as Figure 5 in the case of the panel 20 in
[0083] The angular deflection between these two positions ( Figure 5 arrow F1) about the axis C is for example greater than 30°.
[0084] Each of the panels 20 includes a substantially curved wall 25, the wall 25 having a convex outer surface 25a and a concave inner surface 25b. At least one of these surfaces 25a, 25b is configured to be swept by a gas flow.
[0085] Each panel in the panel 20 also includes at least one hot surface exchanger 26.
[0086] In the example shown, the exchanger 26 is located on the concave surface 25b of the wall 25 and includes a fluid circuit 26' configured to be connected to the fluid system 18 and an exchange surface exposed to the cooling gas flow. However, the position of the exchanger 26 is not restrictive. Alternatively, the exchanger 26 can be located, for example, on the convex outer surface of the panel 20.
[0087] In fact, in the context of the present invention, the panel 20 can be an internal or external panel of a turbine engine and a propulsion unit and can be swept by a gas flow passing inside or outside the panel. Therefore, the exchanger 26 is located inside or outside the panel 20 and thus on the inner or outer surface of the panel 20.
[0088] The fluid system 18 is, for example, a lubrication system, but alternatively, it can be a cooling system. The fluid circuit 26' is, for example, an oil circuit, but alternatively, it can be a cooling circuit.
[0089] The fluid circuit 26' includes a fluid inlet 26a and a fluid outlet 26b, and the fluid inlet and the fluid outlet are connected to the fluid system 18 through fluid connection means.
[0090] In the context of the present invention, the connection means for connecting the exchanger 26 are carried by the panel 20 that carries the exchanger. More specifically, the wall 25 of each panel in the panel 20 carries at least one plug connector 30 for fluidly connecting the circuit 26' to the fluid system 18.
[0091] In the example shown, the connector 30 is located on the lower edge 24 of the panel 20. Figure 3 It is shown that each panel 20 includes two plug connectors 30 of the male type, and these two plug connectors 30 are axially spaced from each other along the axis B. Each of these connectors 30 is configured to cooperate with a complementary connector 30' carried by the mount 17 through male-female insertion. Therefore, it should be understood that in the example shown, the mount 17 carries four connectors, two connectors 30' are located on one side of the structure and are configured to cooperate with the connectors 30 of the first panel 20, while the other two connectors 30' are located on the other side of the structure and are configured to cooperate with the connectors 30 of the second panel 20.
[0092] One of the connectors 30 in each panel 20 of the connectors is connected to the inlet 26a of the circuit 26' of the exchanger 26 of the panel, while the other connector 30 of the panel 20 is connected to the outlet of the circuit 26'. This connection can be achieved through a rigid pipe 32.
[0093] On each side of structure 17, one of the connectors 30' in the connector is connected to the inlet 18a of the fluid system 18, and the other connector 30' is connected to the outlet 18b of the system 18. This connection can be achieved through a rigid pipe 34.
[0094] Figure 6 A non-limiting example of an embodiment of connectors 30, 30' is shown. Connectors 30, 30' are preferably configured to mate with each other by male-female insertion. The panel 20 can carry the male connector, or conversely the female connector, and the structure 17 can carry the female connector, or conversely the male connector.
[0095] For example Figure 6 The male connector shown on the left in, for example, includes a cylindrical protruding end 30a and an opposite end 30b for connecting to one of the pipes 32 in the pipe.
[0096] The end 30a may include an annular groove 30d for receiving a seal (such as an O-ring).
[0097] For example Figure 6 The female connector shown on the right in, for example, includes a cylindrical hollow end 30c and an opposite end 30b for connecting to one of the pipes 34 in the pipe. The ends 30a, 30c are configured to engage with each other. Each of these connectors 30, 30' includes an internal channel that extends between the two ends of the connector and enables fluid circulation between these ends.
[0098] As can be seen in Figure 4 and Figure 5 , the engagement direction (arrow F2) of the connectors is tangent to the circumference centered on axis B.
[0099] Connectors 30, 30' are equipped with self-sealing valves 36. The self-sealing valves 36 automatically close the internal channels of the connectors (see Figure 6 ). Each valve 36 can simply be moved from the position of closing the channel to the position of opening the channel by inserting the connectors together. Each valve 36 can simply be moved from the position of opening the channel to the position of closing the channel by separating the connectors from each other.
[0100] When the panel 20 is in the closed position, the connector 30 of the panel 20 engages in the connector 30' of the structure 17, and this insertion ensures fluid communication between the connectors and the connection of the loop 26' to the fluid system 18. The valves 36 on the connectors are located in positions that do not obstruct the fluid channels between the connectors.
[0101] When the panel 20 is in the open position, the connector 30 of the panel 20 disengages from the connector 30', and the valves 36 close the fluid channels of these connectors.
[0102] In the example shown, the propulsion unit 10 includes a device 40 for locking the panel 20 in the closed position( Figure 4 and Figure 5 ). The lower edge 24 of each panel 20 or the lower edge 24 of one of the panels 20 is equipped with a locking device 40 that cooperates with the structure 17 or the lower edge 24 of another panel 20.
[0103] Figures 7 to 11 An alternative embodiment of the propulsion unit 10 according to the invention is shown, in which the elements previously described in connection with Figures 3 to 6 are designated by the same reference numerals.
[0104] One difference between this variant and the previous embodiment is that the connector 30 of the panel 20 is located on the upper edge 22 of the panel 20, near the hinge 25 of these panels 20.
[0105] Another difference related to the first embodiment is that the connector 30' that cooperates with the connector 30 on the panel 20 is carried by the engine mount 12.
[0106] One of the connectors 30 in each panel 20 is connected to the inlet 26a of the circuit 26' of the exchanger 26 of this panel, while the other connector 30 of this panel 20 is connected to the outlet 26b of the circuit 26'. This connection can be achieved through a rigid pipe 32.
[0107] On each side of the engine mount 12, one of the connectors 30' is connected to the inlet 18a of the fluid system 18, while the other connector 30' is connected to the outlet 18b of this system 18. This connection can be achieved through a rigid pipe 34.
[0108] Figures 8 to 11 Another non - limiting example of an embodiment of the connectors 30, 30' is shown. The connectors 30, 30' are preferably configured to mate with each other by male - female insertion, such that the panel 20 can carry the male connector or, conversely, the female connector, and the engine mount 12 can carry the female connector or, conversely, the male connector.
[0109] For example Figure 11 the male connector shown includes, for example, a cylindrical protruding end 30a and an opposite end 30b for connection to one of the pipes 32.
[0110] The protruding end 30a can carry a seal 31, such as an O - ring.
[0111] For example Figure 10The female connector shown on the right includes, for example, a hollow end portion 30c in the shape of a cylinder and an opposite end portion 30b for connection to one of the conduits 34 in the conduit. The end portions 30a, 30c are configured to engage with each other. Each of these connectors 30, 30' includes an internal passage extending between the two ends of the connector and capable of fluid communication between these ends.
[0112] Figures 8 to 11 The connectors 30, 30' in [[]] are in the form of a housing.
[0113] As can be Figure 8 and Figure 9 seen in Figure 9 , the engagement direction of the connectors (
[0114] arrow F2 of
[0115] Figures 12 to 15 is tangent to the circumference centered on the axis B.
[0116] As Figures 3 to 6 in the embodiment of
[0117] Figure 14 and Figure 15 shows a more specific example of an embodiment of the device 40 for locking the panels 20 together.
[0118] At least one of the panels 20 may include one or more of these devices 40. Each device 40 includes a hook 42 and a lever 44 for actuating the hook 42. One of the panels 20 carries the device 40, while the other panel 20 includes a finger 46 or the like opposite the device and configured to cooperate with the hook 42. When the edges 24 of the panels are brought together, the hook 42 engages on the finger 46, and actuation of the lever 44 causes the hook 42 to be pulled away from the finger 46, thereby clamping the panels 20 together and locking the panels 20.
[0119] Figure 14 and Figure 15 also shows a more specific example of an embodiment of the end caps 30, 30'. In this example, the end cap 30 is straight, while the end cap 30' is angled.
[0120] The connector 30 is a male - type connector, and the valve 36 is a ball - valve - type valve. The ball 50 is received in the connector 30 and can be moved from a closed position of the connector to an open position of the connector. In the closed position of the connector, the ball 50 is supported on the seat 52 of the connector 30, while in the open position of the connector, the ball 50 moves away from the seat 52. The ball 50 is loaded in the closed position by a spring 54.
[0121] The connector 30' is a female - type connector, and the valve 36 of the connector 30' is a piston - valve - type valve. The piston 60 is received in the connector 30' and can be moved from a closed position of the connector to an open position of the connector. In the closed position of the connector, the piston 60 is supported on the seat 62 of the connector 30', while in the open position of the connector, the piston 60 moves away from the seat 62. The piston 60 is biased in the closed position by a spring 64. Further, the piston 60 includes an extension 66 which is configured to support on the ball 50 of the corresponding connector 30 and push the ball 50 into its open position (arrow F2) when the connectors 30, 30' are engaged with each other.
[0122] Either of the connectors 30, 30' carries a seal 31, such as an O - ring.
[0123] Figures 16 to 21 An alternative embodiment of the propulsion unit 10 according to the present invention is shown, in which the elements described above are labeled with the same reference numerals.
[0124] The connector 30 on the panel 20 is located on the lower edge 24 and the upper edge 22 of the panel 20. Thus, the upper edge 22 of the panel 20 includes the connector 30, and the connector 30 is similar to Figures 7 to 11 the connector in, and cooperates with the connector 30' carried by the engine mount 12. These connectors 30 are connected, for example, to the inlets 26a and outlets 26b of the circuits 26' of one or more exchangers 26.
[0125] The lower edge 24 of one of the panels 20 includes the connector 30, and the connector 30 is similar to Figures 3 to 6 the connector in, and cooperates with the connector 30' carried by another panel of the panel 20. The direct connection of the connectors 30, 30' on the panel 20 enables the circuits 26' of the panel 20 to be interconnected, and these circuits 26' are connected to the fluid system 18 through the connectors 30 located on the upper edge 22 of the panel 20.
[0126] In Figure 18 and Figure 19 the example shown, the connector 30 located on the upper edge 22 of the panel 20 is straight and cooperates with the angled connector 30' of the engine mount 12.
[0127] InFigure 20 and Figure 21 In the example shown, the connectors 30, 30' of the lower edge 24 of the panel 20 are straight.
[0128] The locking device 40 is located at these edges 24 so that the connectors 30, 30' are inserted when locked.
[0129] Figures 22 and 23 show another example of an embodiment of the connectors 30, 30' located at the lower edge 24 of the panel 20.
[0130] Each lower edge 24 of the panels 20 is provided with two connectors 30 or 30', which are arranged adjacent to each other, for example, one connector is arranged above the other.
[0131] The locking device 40 is located at these edges 24 so that the connectors 30, 30' are inserted when locked.
[0132] The present invention has several advantages, including:
[0133] - The connectors 30, 30' are rigid, which represents a saving in weight and cost compared to the connection devices of the prior art,
[0134] - The connectors can be combined or installed near the hinge 25,
[0135] - The diameter of the connectors can be reduced relative to the diameter of the connection devices of the prior art, thus also limiting the overall size,
[0136] - The pipes connected to these connectors do not deflect, which simplifies the integration and installation of the components,
[0137] - The connection length of the fluid circuit to the fluid system is optimized to reduce its overall size and cost,
[0138] - The maintenance of the propulsion unit is improved by optimizing the disassembly of the fluid circuit of the exchanger on each panel,
[0139] - The quick connection and disconnection of the connectors, without the risk of leakage,
[0140] - No special tools are required to close or open the connectors and the fluid circuit, etc.
Claims
1. A propulsion unit (10) for an aircraft, the propulsion unit (10) comprising: - a turbomachine (14) extending along a main axis (B) and including a fluid system (18), - a nacelle (16) extending along and around the main axis (B), the nacelle (16) including at least one panel (20) extending around the main axis (B), the at least one panel (20) including a first longitudinal edge (22) fixed by a hinge (25), the hinge (25) defining an axis (C) for pivoting the panel from a closed position, in which the panel extends around the turbomachine (14), to an open position, in which the panel moves away from the turbomachine (14), the at least one panel (20) carrying at least one surface area heat exchanger (26), the at least one surface area heat exchanger including a fluid circuit (26') connected to the fluid system (18), characterized in that the fluid circuit (26')(20) is connected to the fluid system (18) by at least one first plug connector (30, 30') carried by the panel (20), the first plug connector (30) engaging in or on a second plug connector (30') of the propulsion unit (10) to provide fluid communication between the connectors (30, 30') when the panel (20) is in the closed position and disengaging from the second connector (30') when the panel (20) is in the open position to disconnect the fluid communication, each of the first connector and the second connector (30, 30') being equipped with a self-closing valve.
2. The propulsion unit (10) according to claim 1, wherein, The turbomachine (14) includes a longitudinal structure (17) located at a second longitudinal edge (24) of the panel (20) opposite the first edge (22), at least some of the second connectors in the second connector (30') being carried by the structure (17) when the panel (20) is in the closed position.
3. The propulsion unit (10) according to claim 1 or 2, wherein, The propulsion unit (10) includes an engine pylon (12) extending along an axis (A) parallel to the main axis (B) of the turbomachine (14), the turbomachine (14) being fixed to the engine pylon (12) and extending below or beside the engine pylon, the engine pylon being at the level of the first longitudinal edge (22) of the panel (20) when the panel (20) is in the closed position, at least a part of the second connector (30') being carried by the engine pylon (12).
4. The propulsion unit (10) according to any one of the preceding claims, wherein, At least a part of the second connector (30') is carried by another panel in the panel (20).
5. The propulsion unit (10) according to any one of the preceding claims, wherein, Each first connector in the first connectors (30, 30') is configured to engage in or on one of the second connectors in the second connector (30') along a direction (F2) that is tangent to a circumference centered on the main axis (B) of the turbomachine (14).
6. The propulsion unit (10) according to any one of the preceding claims, wherein, The first connector and the second connectors (30, 30') are located in a plane perpendicular to the main axis (B) of the turbomachine (14).
7. The propulsion unit (10) according to any one of the preceding claims, wherein, Each panel in the panels (20) includes at least two first connectors (30), one of these first connectors (30) being connected to the fluid inlet (26a) of the circuit (26') and the other of these first connectors (30) being connected to the fluid outlet (26b) of this circuit (26').
8. The propulsion unit (10) according to claim 7, wherein The propulsion unit includes at least two second connectors (30'), one of these second connectors (30') being connected to the fluid inlet (18a) of the fluid system (18) and the other of these second connectors (30') being connected to the fluid outlet (18b) of this system (18).
9. The propulsion unit (10) according to any one of the preceding claims, wherein, Each panel in the panels (20) includes a concave surface on which the at least one exchanger (26) is located.
10. The propulsion unit (10) according to any one of the preceding claims, wherein, The propulsion unit includes devices (50) for locking the panel (20) in the closed position, these devices (50) being able to operate from an unlocked position to a locked position and being configured to cause the first connector (30) to be inserted into or onto the second connector (30') when these devices are brought from their unlocked position to their locked position.
11. The propulsion unit (10) according to the preceding claim, wherein, The locking devices (50) are located next to the first connector.
12. The propulsion unit (10) according to any one of the preceding claims, wherein, The at least one first plug connector is located on one of the edges of the panel, for example on the first edge of the panel or on the second edge opposite the first edge.
13. The propulsion unit (10) according to any one of the preceding claims, wherein, The fluid circuit is an oil circuit or a cooling circuit.
14. The propulsion unit (10) according to any one of the preceding claims, wherein, The fairing includes two panels of a generally semi-circular shape extending on either side of the main axis, the upper longitudinal edges of the panel or each panel being fixed by the hinge. The propulsion unit (10) according to any one of the preceding claims, wherein, The other panel in the panels carries another heat exchanger or another type of fluid device.