WO2024110720A1 - Propulsion unit for an aircraft - Google Patents
Propulsion unit for an aircraft Download PDFInfo
- Publication number
- WO2024110720A1 WO2024110720A1 PCT/FR2023/051803 FR2023051803W WO2024110720A1 WO 2024110720 A1 WO2024110720 A1 WO 2024110720A1 FR 2023051803 W FR2023051803 W FR 2023051803W WO 2024110720 A1 WO2024110720 A1 WO 2024110720A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- axis
- propulsion assembly
- fluid
- panel
- tube
- Prior art date
Links
- 239000012530 fluid Substances 0.000 claims abstract description 77
- 238000004891 communication Methods 0.000 claims description 8
- 239000002826 coolant Substances 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 3
- 210000000056 organ Anatomy 0.000 claims 2
- 238000005461 lubrication Methods 0.000 description 10
- 238000005516 engineering process Methods 0.000 description 7
- 239000003921 oil Substances 0.000 description 6
- 230000007613 environmental effect Effects 0.000 description 4
- 238000012423 maintenance Methods 0.000 description 4
- 238000011161 development Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 210000003462 vein Anatomy 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 239000002551 biofuel Substances 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000005431 greenhouse gas Substances 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000001483 mobilizing effect Effects 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 230000002459 sustained effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/06—Attaching of nacelles, fairings or cowlings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
Definitions
- the present invention relates to a propulsion assembly for an aircraft.
- Figure 1 illustrates a propulsion assembly 10 for an aircraft.
- propulsion assembly 10 for an aircraft means an assembly comprising a reactor mast 12, a turbomachine 14 and its cowling 16.
- the reactor mast 12 is a massive part which makes it possible to attach a turbomachine 14 to an aircraft, and for example to a wing of the aircraft.
- the reactor mast 12 therefore comprises elements for fixing to the aircraft and elements for fixing the turbomachine 14.
- the reactor mast 12 has a generally elongated shape and extends along a first axis A.
- the turbomachine 14 is located under the reactor mast 12 or next to the reactor mast.
- the turbomachine can be suspended from the reactor mast 12 under the wing of the aircraft.
- the turbomachine can be installed at the rear of the aircraft fuselage.
- the turbomachine 14 has a generally elongated shape 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 by relative to the vertical.
- the turbomachine 14 includes a lubrication system 18 which makes it possible in particular to lubricate the bearings of the turbomachine by circulation of lubricating oil.
- the cowling 16 surrounds the turbomachine 14 and extends along the second axis B.
- the cowling 16 can 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 reactor mast 12 and arranged on either side of the plane P, near the position 12 o'clock, and lower longitudinal edges 24 which are generally fixed one to another. the other and are therefore located at the 6 o'clock position.
- These panels 20 are articulated 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 reactor mast 12.
- Each of the panels 20 is articulated around a third axis C which can be parallel to the second axis B for example, from a position closed in which its lower edge 24 is at the 6 o'clock position, up to an open position in which its lower edge 24 is away from the 6 o'clock position.
- the cover 16 can 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 at Figure 1.
- At least part of the cowling 16 can internally define an annular vein for the flow of an air flow around the turbomachine 14, such as as a flow vein of a secondary flow or other.
- the exchange surface of the surface exchanger 26 is therefore swept by this air flow.
- the exchanger 26 carried by the cowling 16 is connected to the lubrication system 18 by fluid connection means which must authorize the opening of the panels 20 and in particular their pivoting, without necessarily requiring disconnecting the exchanger 26 from lubrication system screw 18.
- connection means are flexible and flexible pipes 28, as illustrated in Figure 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.
- the oil circuit 26' of the exchanger 26 remains connected to the lubrication system 18 thanks to the flexibility of the pipes 28.
- Figure 2 shows two distinct states of deformation of the same pipe 28 for two different positions of a panel 20.
- the present invention proposes a simple, effective and economical solution to at least part of the aforementioned problems of the prior art.
- the invention is the result of technological research aimed at very significantly improving the performance of aircraft and, in this sense, contributes to reducing the environmental impact of aircraft.
- the invention relates to a propulsion assembly for an aircraft, this propulsion assembly comprising:
- turbomachine fixed to the reactor mast, this turbomachine extending along a second axis, the first and second axes extending in the same plane, the turbomachine comprising a fluidic system
- cowling which extends along and around the second axis, the cowling comprising at least one panel of generally semi-circular shape which extends around said second axis, said at least one panel comprising a longitudinal edge which is fixed to the reactor mast by hinges which define a third 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 is connected to the fluid system by at least one rotating joint which is centered on the third axis and which is connected by a first rigid tube to the fluid circuit and by a second rigid tube to the fluid system, this rotating joint comprising a first member rigidly fixed to the first tube, and a second member rigidly fixed to the second tube, the first and second members being assembled so as to be able to rotate relative to each other around the third axis and to ensure fluid communication between the first and second tubes
- the invention thus proposes to connect the fluid circuit of the panel exchanger to the fluid system of the turbomachine, via at least one rotating joint.
- a first specificity of this rotating articulation is that it is centered on the third axis, that is to say on the articulation axis of the corresponding panel. There is therefore no particular force undergone by the joint insofar as it follows the movements of the panel during its movements.
- Another specificity of the rotating joint is that it is formed of rigid elements unlike the pipes of the prior art. It comprises rigid tubes and connection and articulation members of these rigid tubes. The fluid connection between the fluid circuit and the fluid system is ensured continuously regardless of the position of the panel.
- the propulsion assembly according to the invention may comprise one or more of the following characteristics, taken in isolation from each other, or in combination with each other:
- each of the first and second members comprises an internal L-shaped passage, a first end of which is connected to the corresponding tube, and a second end of which is connected to the other member;
- one of the first and second members comprises a male end which is engaged along the third axis in a female end of the other of the first and second members;
- the fluid circuit is connected to the fluid system by two rotating joints centered on the third axis, a first of these rotating joints being connected to an inlet of said fluid circuit, and a second of these rotating joints being connected to a fluid outlet of said circuit;
- At least one valve is mounted between the fluid system and the second rigid tube of the or each rotating joint;
- said at least one panel comprises an internal concave surface on which said at least one exchanger is located; - said plane in which the first and second axes extend is vertical or inclined relative to the vertical;
- said fluid circuit is an oil circuit or a coolant circuit
- the fluid circuit is connected to the fluid system by at least one double rotating joint which comprises:
- the cowling surrounds at least part of the turbomachine
- the cowling comprises two panels of generally semi-circular shape which extend on either side of said main axis,
- each of these panels has an upper and lower longitudinal edge
- the other of the panels carries another heat exchanger or another type of fluidic equipment
- the turbomachine extends under the reactor mast or next to the reactor mast, -- the or each panel has a general semi-circular shape.
- Figure 1 is a partial schematic perspective view of a propulsion assembly for an aircraft
- Figure 2 is a schematic perspective view of fluid connection means of a heat exchanger to a fluid system, according to the technique prior to the invention
- FIG. 3 is a schematic perspective view of the technology used for the fluid connection means in the context of the present invention.
- Figure 4 is a schematic view in axial section of fluid connection means in the context of the present invention.
- Figure 5 is a half schematic view in axial section of a propulsion assembly for an aircraft, and illustrates a first embodiment of the invention
- Figure 6 is a half schematic view in axial section of a propulsion assembly for an aircraft, and illustrates a second embodiment of the invention.
- Figure 7 is a half schematic view in axial section of a propulsion assembly for an aircraft, and illustrates a third embodiment of the invention.
- Figure 1 can be considered as illustrating a propulsion assembly 10 within the meaning of the invention therefore the preceding description in relation to this Figure 1 can be considered as also relating to the invention.
- the propulsion assembly 10 can be located under the wing of the aircraft or at the rear of the fuselage of the aircraft for example. Furthermore, the propulsion assembly 10 can be of any type and for example of the double or triple flow turbojet type, turbomachine with ducted or non-ducted fan, turboprop, open rotor, etc.
- Figure 2 illustrates the connection means of the prior art, between the fluid or fluid circuit 26' of a heat exchanger 26 carried by a cowling panel 20, and the lubrication system 18 of the turbomachine 14.
- These means connection include flexible pipes 28 and have the disadvantages described above.
- the present invention proposes a different technology for connecting the fluid circuit 26' of an exchanger 26 to a fluid system 18 of the turbomachine 14.
- 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.
- Figure 3 The principle of this technology is illustrated in Figure 3 and consists of using one or more rotating joints 30.
- Figure 3 shows three rotating joints 30a, 30b, 30c which are connected together by rigid tubes.
- a first rigid tube 32 extends between a valve 33 or tap and a first joint 30a.
- a second rigid tube 34 extends between the first joint 30a and a second joint 30b.
- a third rigid tube 36 extends between the second articulation 30b and a third articulation 30c.
- a fourth rigid tube 38 extends between the third articulation 30c and a fluid outlet 40.
- Each of the joints 30a, 30b, 30c comprises two members which are rigidly fixed to the corresponding tubes and which are coupled to one another to on the one hand ensure fluid connection between the tubes, and on the other hand allow rotation tubes relative to each other around an axis D.
- the member 42 fixed to the end of the first tube 32 is thus coupled to the member 44 fixed to the end of the second tube 34.
- the members 42, 44 form the first rotating joint 30a around a first axis D1, and are capable of ensuring fluid communication between the tubes 32, 34 whatever the position of the members 42, 44 and the tubes 32, 34 with respect to the axis D1.
- the member 46 fixed to the other end of the second tube 34 is coupled to the member 48 fixed to the end of the third tube 36.
- the members 46, 48 form the second rotating joint 30b around a second axis D2, and are capable of ensuring fluid communication between the tubes 34, 36 whatever the position of the members 46, 48 and the tubes 34, 36 with respect to the axis D2.
- the member 50 fixed to the other end of the third tube 36 is coupled to the member 52 fixed to the end of the fourth tube 38.
- the members 50, 52 form the third rotating joint 30c around a second axis D3, and are capable of ensuring fluid communication between the tubes 36, 38 whatever the position of the members 50, 52 and the tubes 36, 38 with respect to the axis D3.
- the axes D1, D2, D3 are parallel.
- FIG 4 shows the rotating joint 30a in section, the other rotating joints 30b, 30c being similar.
- the tube 32 comprises an internal passage 32a for the circulation of a fluid, which extends over its entire length and is connected to one end of an internal passage 42a of the member 42.
- the internal passage 42a of the member 42 has a general L-shaped shape and its end, opposite the tube 32, is connected to one end of the L-shaped internal passage 44a of the other member 44.
- the tube 34 comprises an internal passage 34a which extends over the entire its length and is connected to the opposite end of the internal passage 42a of the member 42.
- An L-shaped passage has two perpendicular portions, namely a first portion which extends in one direction and a second portion which extends in a direction perpendicular to the first, the two portions being in fluid communication.
- the members 42, 44 can be assembled by a male-female type interlocking for example, as illustrated in the drawing. The interlocking is carried out along the axis D1 and makes it possible to form the articulation 30a around this axis.
- the member 42 comprises a female end piece 42b which is crossed by the passage 42a and which receives a male end piece 44b of the member 44, this male end piece 44b also being crossed by the passage 44a of this member 44 .
- Sealing means such as one or more annular seals 54, can be mounted at the end pieces 42b, 44b.
- FIG. 5 illustrates a first embodiment of a propulsion assembly 10 according to the invention.
- this propulsion assembly 10 includes:
- turbomachine 14 comprising a fluid system 18,
- cowling 16 which can surround the turbomachine 14, as in the example shown.
- the cowling 16 comprises two panels 20 of generally semi-circular shape which extend on either side of the aforementioned plane P and which comprise upper longitudinal edges 22 which are fixed to the reactor mast 12 by means of hinges 25. These upper edges 22 are located substantially in a 12 o'clock position being separated from each other by the reactor mast 12.
- the hinges 25 are three in number and are arranged one behind the other along the axis C. We can therefore consider that there is an upstream hinge, an intermediate hinge and a downstream hinge. . Preferably, two of these hinges are mounted fixed and the third is mounted floating so as to have perfect alignment.
- Each of the panels 20 is articulated around a third axis C (defined by the hinges 25) which can be parallel to the second axis B for example, from a closed position in which its lower edge (not visible) is substantially at the 6 o'clock position , to an open position in which its lower edge is away from the 6 o'clock position.
- the angular movement between the two positions is for example greater than 30° around the axis C.
- Each of the panels 20 carries at least one surface heat exchanger 26 which comprises a fluid circuit 26' connected to the fluidic system 18, and an exchange surface which is exposed to a flow of cooling gas 4.
- the exchanger 26 is located on a concave curved surface of the panel 20, which is oriented towards the axis B, and which is therefore an internal surface of the panel. This position is not restrictive. Alternatively, the exchanger 26 could for example be on an external convex surface of the panel 20.
- the panel 20 can be an internal or external panel of the turbomachine and the propulsion assembly, and can be swept by a flow of gas passing inside or outside of the panel (in particular a secondary flow or flow external to the turbomachine).
- 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.
- the fluid connection means of the fluid circuit 26' of each exchanger 26 to the fluid system 18 comprise at least one rotating joint 30 as described in the above.
- the fluid circuit 26' comprises a fluid inlet 26a and a fluid outlet 26b.
- the fluid system 18 includes a fluid inlet 18a and a fluid outlet 18b.
- the fluid inlet 26a of the circuit 26' is connected to the fluid outlet 18b of the system 18 by a first articulation 30 which is centered on the pivot axis C of the panel 20 which carries the exchanger 26 with this circuit 26' .
- This first articulation 30 is connected by rigid tubes 32, 34 respectively to the inlet 26a and the outlet 18b or to pipes connected to this inlet and this outlet.
- the first articulation is located next to one of the hinges 25, which is the intermediate hinge 25a in the example shown.
- a valve 33 is advantageously inserted between the joint 30 and the outlet 18b therefore just upstream of the joint 30. This valve 33 can also be centered on the axis C.
- the hinge 25a is located between the valve 33 and joint 30.
- the fluid outlet 26b of the circuit 26' is connected to the fluid inlet 18a of the system 18 by a second articulation 30' which is centered on the pivot axis C of the panel 20 which carries the exchanger 26 with this circuit 26 '.
- This second articulation 30' is connected by rigid tubes 32, 34 respectively to the outlet 26b and the inlet 18a or to pipes connected to this outlet and this inlet.
- the second articulation is located next to another of the hinges 25, which is the downstream hinge in the example shown.
- a valve 33 is advantageously inserted between the joint 30' and the inlet 18a, therefore just downstream of the joint 30'. This valve 33 can also be centered on axis C.
- the hinge 25b is located between the valve 33 and the articulation 30'.
- the joints 30, 30' are therefore at a distance from each other, along the axis C.
- the valve(s) 33 make it possible to isolate the fluid circuit for example with a view to dismantling the exchanger 26 or the panel 20 during a maintenance operation.
- the member 42 of the first joint 30 is inserted between the member 44 of this joint 30 and the member 42' of the second joint 30'.
- the joints 30, 30' are here arranged at the level of the first hinge 25a, on one side of this hinge 25a.
- the valve 33 associated with the first joint 30 is located on the other side of the hinge 25a, and the joints are located between the hinge 25a and the other valve 33.
- the alternative embodiment of Figure 7 differs from the previous variant in that it uses not a simple rotating articulation, for each fluid connection, but a double rotating articulation which makes it possible to avoid the obligation to align on the same axis of rotation as the hinges 25.
- the fluid inlet 26a of the circuit 26' is connected to the fluid outlet 18b of the system 18 by a double articulation which comprises joints 30a and 30b of the type of that of Figure 3 for example.
- the first articulation 30a is centered on the axis C and the second 30b is centered on an axis parallel to the axis C.
- the tubes are rigid, which is advantageous in terms of cost, mass and maintenance,
- the diameter of the tubes is optimized and does not need to be oversized, which facilitates the integration of the rotating joint into the environment,
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Joints Allowing Movement (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
The invention relates to a propulsion unit (10) for an aircraft, said propulsion unit (10) comprising: - an engine pylon (12), - a turbine engine (14) fixed to the engine pylon (12) and comprising a fluidic system (18), - a cowling (16) which comprises at least one panel (20) pivotably connected to the engine pylon (14) and carrying at least one surface heat exchanger (26) which comprises a fluid circuit (26') connected to the fluidic system (18), characterised in that the fluid circuit (26') is connected to the fluidic system (18) by at least one swivel joint (30, 30') which is centred on the swivel axis of the corresponding panel (20).
Description
DESCRIPTION DESCRIPTION
TITRE : ENSEMBLE PROPULSIF POUR UN AERONEF TITLE: PROPULSIVE ASSEMBLY FOR AN AIRCRAFT
Domaine technique de l'invention Technical field of the invention
La présente invention concerne un ensemble propulsif pour un aéronef. The present invention relates to a propulsion assembly for an aircraft.
Arrière-plan technique Technical background
L’état de l’art comprend notamment le document FR-A1 -3 094 750, US-A1- 2020/049028, US-A1 -2021/078380, FR-A1-2 567 081 et CN-U,207 854 371. La figure 1 illustre un ensemble propulsif 10 pour un aéronef. The state of the art includes in particular document FR-A1 -3 094 750, US-A1-2020/049028, US-A1 -2021/078380, FR-A1-2 567 081 and CN-U,207 854 371 Figure 1 illustrates a propulsion assembly 10 for an aircraft.
Dans la présente demande, on entend par ensemble propulsif 10 pour un aéronef, un ensemble comportant un mât réacteur 12, une turbomachine 14 et son capotage 16. In the present application, the term propulsion assembly 10 for an aircraft means an assembly comprising a reactor mast 12, a turbomachine 14 and its cowling 16.
Le mât réacteur 12 est une pièce massive qui permet de fixer une turbomachine 14 à un aéronef, et par exemple à une voilure de l’aéronef. Le mât réacteur 12 comprend donc des éléments de fixation à l’aéronef et des éléments de fixation de la turbomachine 14. Le mât réacteur 12 a une forme générale allongée et s’étend le long d’un premier axe A. The reactor mast 12 is a massive part which makes it possible to attach a turbomachine 14 to an aircraft, and for example to a wing of the aircraft. The reactor mast 12 therefore comprises elements for fixing to the aircraft and elements for fixing the turbomachine 14. The reactor mast 12 has a generally elongated shape and extends along a first axis A.
Dans la présente demande, la turbomachine 14 est située sous le mât réacteur 12 ou à côté du mât réacteur. La turbomachine peut être suspendue au mât réacteur 12 sous la voilure de l’aéronef. En variante, la turbomachine peut être installée à l’arrière du fuselage de l’aéronef. In the present application, the turbomachine 14 is located under the reactor mast 12 or next to the reactor mast. The turbomachine can be suspended from the reactor mast 12 under the wing of the aircraft. Alternatively, the turbomachine can be installed at the rear of the aircraft fuselage.
La turbomachine 14 a une forme générale allongée le long d’un second axe B qui peut être parallèle au premier axe A. Les premier et second axes A, B sont situés dans un même plan P. Ce plan P peut être vertical ou incliné par rapport à la verticale. The turbomachine 14 has a generally elongated shape 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 by relative to the vertical.
On désigne par 12h (pour 12 heures) et 6h (pour 6 heures) des positions de pièces autour du second axe B, par analogie avec le cadran d’une horloge en regardant l’ensemble par l’arrière. La position 12h est située dans le plan
P et au niveau du mât réacteur 12, et la position 6h est située dans le plan P sous la turbomachine 14. We designate by 12 o'clock (for 12 hours) and 6 o'clock (for 6 o'clock) the positions of parts around the second axis B, by analogy with the dial of a clock when looking at the whole from the rear. The 12 o'clock position is located in the plane P and at the level of the reactor mast 12, and the 6 o'clock position is located in the plane P under the turbomachine 14.
La turbomachine 14 comporte un système de lubrification 18 qui permet notamment de lubrifier des paliers de la turbomachine par circulation d’huile de lubrification. The turbomachine 14 includes a lubrication system 18 which makes it possible in particular to lubricate the bearings of the turbomachine by circulation of lubricating oil.
Le capotage 16 entoure la turbomachine 14 et s’étend le long du second axe B. Le capotage 16 peut comprendre plusieurs morceaux et comporte deux panneaux 20 de forme générale semi-circulaire qui s’étendent de part et d’autre du plan P précité. Ces panneaux 20 comprennent des bords longitudinaux supérieurs 22 qui sont fixés au mât réacteur 12 et disposés de part et d’autre du plan P, à proximité de la position 12h, et des bords longitudinaux inférieurs 24 qui sont fixés en général l’un à l’autre et sont donc situés à la position 6h. The cowling 16 surrounds the turbomachine 14 and extends along the second axis B. The cowling 16 can 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 reactor mast 12 and arranged on either side of the plane P, near the position 12 o'clock, and lower longitudinal edges 24 which are generally fixed one to another. the other and are therefore located at the 6 o'clock position.
Ces panneaux 20 sont articulés par leurs bords supérieurs 22 pour pouvoir ouvrir le capotage 16 et intervenir dans la turbomachine 14 lors d’une opération de maintenance au sol par exemple. Cette articulation est rendue possible par des charnières 25 de fixation des bords supérieurs 22 des panneaux 20 au mât réacteur 12. Chacun des panneaux 20 est articulé autour d’un troisième axe C qui peut être parallèle au second axe B par exemple, depuis une position fermée dans laquelle son bord inférieur 24 est à la position 6h, jusqu’à une position ouverte dans laquelle son bord inférieur 24 est éloigné de la position 6h. These panels 20 are articulated 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 reactor mast 12. Each of the panels 20 is articulated around a third axis C which can be parallel to the second axis B for example, from a position closed in which its lower edge 24 is at the 6 o'clock position, up to an open position in which its lower edge 24 is away from the 6 o'clock position.
Le capotage 16 peut porter au moins un échangeur surfacique 26 de chaleur. Un échangeur 26 de ce type comprend un circuit d’huile 26’ raccordé au système de lubrification 18, et une surface d’échange qui est exposée à un flux d’air de refroidissement. Un échange de calories entre la surface et le circuit d’huile 26’ de l’échangeur permet de refroidir l’huile provenant du système de lubrification 18 avant de la renvoyer à ce système de lubrification 18, comme illustré par les flèches en pointillés à la figure 1 . The cover 16 can 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 at Figure 1.
Au moins une partie du capotage 16 peut définir intérieurement une veine annulaire d’écoulement d’un flux d’air autour de la turbomachine 14, telle
qu’une veine d’écoulement d’un flux secondaire ou autre. Dans ce cas, la surface d’échange de l’échangeur surfacique 26 est donc balayée par ce flux d’air. At least part of the cowling 16 can internally define an annular vein for the flow of an air flow around the turbomachine 14, such as as a flow vein of a secondary flow or other. In this case, the exchange surface of the surface exchanger 26 is therefore swept by this air flow.
L’échangeur 26 porté par le capotage 16 est relié au système de lubrification 18 par des moyens de raccordement fluidique qui doivent autoriser l’ouverture des panneaux 20 et en particulier leur pivotement, sans forcément nécessiter de déconnecter l’échangeur 26 vis-à-vis du système de lubrification 18. The exchanger 26 carried by the cowling 16 is connected to the lubrication system 18 by fluid connection means which must authorize the opening of the panels 20 and in particular their pivoting, without necessarily requiring disconnecting the exchanger 26 from lubrication system screw 18.
Dans la technique actuelle, ces moyens de raccordement sont des tuyaux 28 souples et flexibles, comme illustré à la figure 2. Chacun de ces tuyaux 28 comprend une extrémité 28a solidaire d’un panneau 20 et destinée à être reliée à l’échangeur 26 porté par ce panneau 20, et une extrémité 28b opposée solidaire du mât réacteur 12 et destinée à être raccordée au système de lubrification 18 de la turbomachine 14. Quelle que soit la position du panneau 20, le circuit d’huile 26’ de l’échangeur 26 reste raccordé au système de lubrification 18 grâce à la souplesse des tuyaux 28. La figure 2 montre deux états distincts de déformation d’un même tuyau 28 pour deux positions différentes d’un panneau 20. In the current technique, these connection means are flexible and flexible pipes 28, as illustrated in Figure 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. Figure 2 shows two distinct states of deformation of the same pipe 28 for two different positions of a panel 20.
Cette technologie présente des inconvénients. Tout d’abord, il est nécessaire que l’environnement autour des tuyaux 28 restent libres pour ne pas gêner le débattement des tuyaux 28 lors de l’ouverture et de la fermeture des panneaux 20. Les tuyaux 28 ont de plus une longueur relativement importante pour permettre leur flexion sans entrainer des contraintes conduisant à la rupture ou à une déformation permanente. Cette technologie est ainsi relativement encombrante. Par ailleurs, ces tuyaux 28 sont surdimensionnés pour être suffisamment résistants et ont en particulier un diamètre important du fait de la présence d’une couche épaisse de protection autour de ces tuyaux 28 afin de résister au feu et aux autres agressions. Enfin, cette technologie est relativement coûteuse et de masse importante. Par ailleurs, le changement climatique est une préoccupation majeure pour de nombreux organes législatifs et de régulation à travers le monde. En effet,
diverses restrictions sur les émissions de carbone ont été, sont ou seront adoptées par divers états. En particulier, une norme ambitieuse s’applique à la fois aux nouveaux types d’avions mais aussi ceux en circulation nécessitant de devoir mettre en œuvre des solutions technologiques afin de les rendre conformes aux réglementations en vigueur. L’aviation civile se mobilise depuis maintenant plusieurs années pour apporter une contribution à la lutte contre le changement climatique. Les efforts de recherche technologique ont déjà permis d’améliorer de manière très significative les performances environnementales des avions. La Déposante prend en considération les facteurs impactant dans toutes les phases de conception et de développement pour obtenir des composants et des produits aéronautiques moins énergivores, plus respectueux de l’environnement et dont l’intégration et l’utilisation dans l’aviation civile ont des conséquences environnementales modérées dans un but d’amélioration de l'efficacité énergétique des avions. Par voie de conséquence, la Déposante travaille en permanence à la réduction de son incidence climatique négative par l’emploi de méthodes et l’exploitation de procédés de développement et de fabrication vertueux et minimisant les émissions de gaz à effet de serre au minimum possible pour réduire de l'empreinte environnementale de son activité. Ces travaux de recherche et de développement soutenus portent à la fois sur les nouvelles générations de moteurs d’avions, l’allègement des appareils, notamment par les matériaux employés et les équipements embarqués allégés, le développement de l’emploi des technologies électriques pour assurer la propulsion, et, indispensables compléments aux progrès technologiques, les biocarburants aéronautiques. This technology has drawbacks. First of all, it is necessary that the environment around the pipes 28 remains 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 stress leading to rupture or permanent deformation. This technology is therefore relatively bulky. Furthermore, these pipes 28 are oversized to be sufficiently resistant and in particular have a large diameter due to the presence of a thick layer of protection around these pipes 28 in order to resist fire and other attacks. Finally, this technology is relatively expensive and has a large 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 but also to 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 made it possible to very significantly improve the environmental performance of aircraft. The Applicant takes into consideration the impacting factors in all phases of design and development to obtain aeronautical components and products that consume less energy, are more respectful of the environment and 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 through the use of methods and the exploitation of virtuous development and manufacturing processes and minimizing greenhouse gas emissions to the minimum possible for reduce the environmental footprint of its activity. This sustained research and development work concerns new generations of aircraft engines, the reduction of aircraft weight, particularly through the materials used and lightweight on-board equipment, and the development of the use of electrical technologies to ensure propulsion, and, essential complements to technological progress, aeronautical biofuels.
La présente invention propose une solution simple, efficace et économique à au moins une partie des problèmes précités de la technique antérieure. The present invention proposes a simple, effective and economical solution to at least part of the aforementioned problems of the prior art.
Résumé de l'invention
L'invention est le résultat des recherches technologiques visant à améliorer de manière très significative les performances des avions et, en ce sens, contribue à la réduction de l’impact environnemental des avions. Summary of the invention The invention is the result of technological research aimed at very significantly improving the performance of aircraft and, in this sense, contributes to reducing the environmental impact of aircraft.
L’invention concerne un ensemble propulsif pour un aéronef, cet ensemble propulsif comportant : The invention relates to a propulsion assembly for an aircraft, this propulsion assembly comprising:
- un mât réacteur s’étendant le long d’un premier axe, - a reactor mast extending along a first axis,
- une turbomachine fixée au mât réacteur, cette turbomachine s’étendant le long d’un second axe, les premier et second axes s’étendant dans un même plan, la turbomachine comportant un système fluidique, - a turbomachine fixed to the reactor mast, this turbomachine extending along a second axis, the first and second axes extending in the same plane, the turbomachine comprising a fluidic system,
- un capotage qui s’étend le long et autour du second axe, le capotage comportant au moins un panneau de forme générale semi-circulaire qui s’étend autour dudit second axe, ledit au moins un panneau comportant un bord longitudinal qui est fixé au mât réacteur par des charnières qui définissent un troisième axe de pivotement du panneau, depuis une position fermée dans laquelle il s’étend autour de la turbomachine jusqu’à une position ouverte dans laquelle il est écarté de la turbomachine, ledit au moins un panneau portant au moins un échangeur surfacique de chaleur qui comprend un circuit de fluide raccordé audit système fluidique, caractérisé en ce que le circuit de fluide est raccordé au système fluidique par au moins une articulation tournante qui est centrée sur le troisième axe et qui est reliée par un premier tube rigide au circuit de fluide et par un second tube rigide au système fluidique, cette articulation tournante comportant un premier organe fixé rigidement au premier tube, et un second organe fixé rigidement au second tube, les premier et second organes étant assemblés de façon à pouvoir tourner l’un par rapport à l’autre autour du troisième axe et à assurer une communication fluidique entre les premier et second tubes quelle que soit la position des premier et second organes autour du troisième axe. - a cowling which extends along and around the second axis, the cowling comprising at least one panel of generally semi-circular shape which extends around said second axis, said at least one panel comprising a longitudinal edge which is fixed to the reactor mast by hinges which define a third 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 is connected to the fluid system by at least one rotating joint which is centered on the third axis and which is connected by a first rigid tube to the fluid circuit and by a second rigid tube to the fluid system, this rotating joint comprising a first member rigidly fixed to the first tube, and a second member rigidly fixed to the second tube, the first and second members being assembled so as to be able to rotate relative to each other around the third axis and to ensure fluid communication between the first and second tubes whatever the position of the first and second members around the third axis.
L’invention propose ainsi de raccorder le circuit de fluide de l’échangeur du panneau au système fluidique de la turbomachine, par l’intermédiaire d’au moins une articulation tournante. Une première spécificité de cette
articulation tournante est qu’elle est centrée sur le troisième axe, c’est-à-dire sur l’axe d’articulation du panneau correspondant. Il n’y a donc pas d’effort particulier subi par l’articulation dans la mesure où elle suit les débattements du panneau lors de ses déplacements. Une autre spécificité de l’articulation tournante est qu’elle est formée d’éléments rigides au contraire des tuyaux de la technique antérieure. Elle comprend des tubes rigides et des organes de raccordement et d’articulation de ces tubes rigides. Le raccordement fluidique entre le circuit de fluide et le système fluidique est assurée en continu quelle que soit la position du panneau. The invention thus proposes to connect the fluid circuit of the panel exchanger to the fluid system of the turbomachine, via at least one rotating joint. A first specificity of this rotating articulation is that it is centered on the third axis, that is to say on the articulation axis of the corresponding panel. There is therefore no particular force undergone by the joint insofar as it follows the movements of the panel during its movements. Another specificity of the rotating joint is that it is formed of rigid elements unlike the pipes of the prior art. It comprises rigid tubes and connection and articulation members of these rigid tubes. The fluid connection between the fluid circuit and the fluid system is ensured continuously regardless of the position of the panel.
L’ensemble propulsif selon l’invention peut comprendre une ou plusieurs des caractéristiques suivantes, prises isolément les unes des autres, ou en combinaison les unes avec les autres : The propulsion assembly according to the invention may comprise one or more of the following characteristics, taken in isolation from each other, or in combination with each other:
- chacun des premier et second organes comprend un passage interne en L dont une première extrémité est reliée au tube correspondant, et dont une seconde extrémité est reliée à l’autre organe ; - each of the first and second members comprises an internal L-shaped passage, a first end of which is connected to the corresponding tube, and a second end of which is connected to the other member;
- l’un des premier et second organes comprend un embout mâle qui est engagé selon le troisième axe dans un embout femelle de l’autre des premier et second organes ; - one of the first and second members comprises a male end which is engaged along the third axis in a female end of the other of the first and second members;
- au moins un joint ou moyen d’étanchéité est monté entre les embouts mâle et femelle ; - at least one seal or sealing means is mounted between the male and female ends;
- le circuit de fluide est raccordé au système fluidique par deux articulations tournantes centrées sur le troisième axe, une première de ces articulations tournantes étant reliée à une entrée dudit circuit de fluide, et une seconde de ces articulations tournantes étant reliée à une sortie de fluide dudit circuit ;- the fluid circuit is connected to the fluid system by two rotating joints centered on the third axis, a first of these rotating joints being connected to an inlet of said fluid circuit, and a second of these rotating joints being connected to a fluid outlet of said circuit;
- les première et seconde articulations tournantes sont à distance l’une de l’autre ; - the first and second rotating joints are at a distance from each other;
- les première et seconde articulations tournantes sont accolées ; - the first and second rotating joints are joined together;
- au moins une vanne est montée entre le système fluidique et le second tube rigide de la ou de chaque articulation tournante ; - at least one valve is mounted between the fluid system and the second rigid tube of the or each rotating joint;
- ledit au moins un panneau comprend une surface concave interne sur laquelle est situé ledit au moins un échangeur ;
- ledit plan dans lequel s’étendent les premier et second axes est vertical ou incliné par rapport à la verticale ; - said at least one panel comprises an internal concave surface on which said at least one exchanger is located; - said plane in which the first and second axes extend is vertical or inclined relative to the vertical;
- ledit circuit de fluide est un circuit d’huile ou un circuit de liquide de refroidissement ; - said fluid circuit is an oil circuit or a coolant circuit;
- le circuit de fluide est raccordé au système fluidique par au moins une double articulation tournante qui comprend : - the fluid circuit is connected to the fluid system by at least one double rotating joint which comprises:
- le premier tube rigide s’étendant entre le circuit de fluide et le premier organe d’une première articulation, - the first rigid tube extending between the fluid circuit and the first member of a first joint,
- le second tube rigide s’étendant entre le second organe de la première articulation et un troisième organe fixé rigidement à une extrémité de ce second tube, - the second rigid tube extending between the second member of the first articulation and a third member rigidly fixed to one end of this second tube,
- un troisième tube rigide s’étendant entre le système fluidique et un quatrième organe fixé rigidement à une extrémité de ce troisième tube, les troisième et quatrième organes formant une seconde articulation tournante et étant assemblés de façon à pouvoir tourner l’un par rapport à l’autre autour d’un quatrième axe parallèle au troisième axe et à assurer une communication fluidique entre les second et troisième tubes quelle que soit la position des troisième et quatrième organes autour du quatrième axe,- a third rigid tube extending between the fluidic system and a fourth member rigidly fixed to one end of this third tube, the third and fourth members forming a second rotating joint and being assembled so as to be able to rotate relative to each other the other around a fourth axis parallel to the third axis and to ensure fluid communication between the second and third tubes whatever the position of the third and fourth members around the fourth axis,
- le capotage entoure au moins une partie de la turbomachine, - the cowling surrounds at least part of the turbomachine,
- le capotage comprend deux panneaux de forme générale semi-circulaire qui s’étendent de part et d’autre dudit axe principal, - the cowling comprises two panels of generally semi-circular shape which extend on either side of said main axis,
- chacun de ces panneaux comporte un bord longitudinal supérieur et inférieur, - each of these panels has an upper and lower longitudinal edge,
- le bord longitudinal supérieur du ou de chaque panneau est fixé par les charnières, - the upper longitudinal edge of the or each panel is fixed by the hinges,
- l’autre des panneaux porte un autre échangeur de chaleur ou un autre type d’équipement fluidique, - the other of the panels carries another heat exchanger or another type of fluidic equipment,
- la turbomachine s’étend sous le mât réacteur ou à côté du mât réacteur, -- le ou chaque panneau a une forme générale semi-circulaire. - the turbomachine extends under the reactor mast or next to the reactor mast, -- the or each panel has a general semi-circular shape.
Brève description des figures
D’autres caractéristiques et avantages ressortiront de la description qui suit d’un mode de réalisation non limitatif de l’invention en référence aux dessins annexés sur lesquels : Brief description of the figures 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:
[Fig. 1] la figure 1 est une vue schématique partielle en perspective d’un ensemble propulsif pour un aéronef, [Fig. 1] Figure 1 is a partial schematic perspective view of a propulsion assembly for an aircraft,
[Fig. 2] la figure 2 est une vue schématique en perspective de moyens de raccordement fluidique d’un échangeur de chaleur à un système fluidique, selon la technique antérieure à l’invention, [Fig. 2] Figure 2 is a schematic perspective view of fluid connection means of a heat exchanger to a fluid system, according to the technique prior to the invention,
[Fig. 3] la figure 3 est vue schématique en perspective de la technologie utilisée pour les moyens de raccordement fluidique dans le cadre de la présente invention, [Fig. 3] Figure 3 is a schematic perspective view of the technology used for the fluid connection means in the context of the present invention,
[Fig. 4] la figure 4 est une vue schématique en coupe axiale de moyens de raccordement fluidique dans le cadre de la présente invention, [Fig. 4] Figure 4 is a schematic view in axial section of fluid connection means in the context of the present invention,
[Fig. 5] la figure 5 est une demi vue schématique en coupe axiale d’un ensemble propulsif pour un aéronef, et illustre un premier mode de réalisation de l’invention, [Fig. 5] Figure 5 is a half schematic view in axial section of a propulsion assembly for an aircraft, and illustrates a first embodiment of the invention,
[Fig. 6] la figure 6 est une demi vue schématique en coupe axiale d’un ensemble propulsif pour un aéronef, et illustre un deuxième mode de réalisation de l’invention, et [Fig. 6] Figure 6 is a half schematic view in axial section of a propulsion assembly for an aircraft, and illustrates a second embodiment of the invention, and
[Fig. 7] la figure 7 est une demi vue schématique en coupe axiale d’un ensemble propulsif pour un aéronef, et illustre un troisième mode de réalisation de l’invention. [Fig. 7] Figure 7 is a half schematic view in axial section of a propulsion assembly for an aircraft, and illustrates a third embodiment of the invention.
Description détaillée de l'invention Detailed description of the invention
Les figures 1 et 2 ont déjà été décrites dans ce qui précède. Figures 1 and 2 have already been described in the above.
La figure 1 peut être considérée comme illustrant un ensemble propulsif 10 au sens de l’invention donc la description qui précède en relation avec cette figure 1 peut être considérée comme concernant également l’invention.Figure 1 can be considered as illustrating a propulsion assembly 10 within the meaning of the invention therefore the preceding description in relation to this Figure 1 can be considered as also relating to the invention.
L’ensemble propulsif 10 peut être situé sous la voilure de l’aéronef ou à l’arrière du fuselage de l’aéronef par exemple.
Par ailleurs, l’ensemble propulsif 10 peut être de n’importe quel type et par exemple du type turboréacteur à double ou triple flux, turbomachine à soufflante carénée ou non carénée, turbopropulseur, open rotor, etc. The propulsion assembly 10 can be located under the wing of the aircraft or at the rear of the fuselage of the aircraft for example. Furthermore, the propulsion assembly 10 can be of any type and for example of the double or triple flow turbojet type, turbomachine with ducted or non-ducted fan, turboprop, open rotor, etc.
La figure 2 illustre les moyens de raccordement de la technique antérieure, entre le circuit fluidique ou de fluide 26’ d’un échangeur de chaleur 26 porté par un panneau 20 de capotage, et le système de lubrification 18 de la turbomachine 14. Ces moyens de raccordement comprennent des tuyaux 28 souples et présentent des inconvénients décrits plus haut. Figure 2 illustrates the connection means of the prior art, between the fluid or fluid circuit 26' of a heat exchanger 26 carried by a cowling panel 20, and the lubrication system 18 of the turbomachine 14. These means connection include flexible pipes 28 and have the disadvantages described above.
La présente invention propose une technologie différente pour raccorder le circuit de fluide 26’ d’un échangeur 26 à un système fluidique 18 de la turbomachine 14. The present invention proposes a different technology for connecting the fluid circuit 26' of an exchanger 26 to a fluid system 18 of the turbomachine 14.
Le système fluidique 18 est par exemple un système de lubrification mais pourrait en variante être un système de refroidissement. Le circuit de fluide 26’ est par exemple un circuit d’huile mais pourrait en variante être un circuit de liquide de refroidissement. 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.
Le principe de cette technologie est illustré à la figure 3 et consiste à utiliser une ou plusieurs articulations tournantes 30. La figure 3 montre trois articulations tournantes 30a, 30b, 30c qui sont reliées entre elles par des tubes rigides. The principle of this technology is illustrated in Figure 3 and consists of using one or more rotating joints 30. Figure 3 shows three rotating joints 30a, 30b, 30c which are connected together by rigid tubes.
Un premier tube rigide 32 s’étend entre une vanne 33 ou robinet et une première articulation 30a. Un second tube rigide 34 s’étend entre la première articulation 30a et une seconde articulation 30b. Un troisième tube rigide 36 s’étend entre la seconde articulation 30b et une troisième articulation 30c. Enfin, un quatrième tube rigide 38 s’étend entre la troisième articulation 30c et une sortie de fluide 40. A first rigid tube 32 extends between a valve 33 or tap and a first joint 30a. A second rigid tube 34 extends between the first joint 30a and a second joint 30b. A third rigid tube 36 extends between the second articulation 30b and a third articulation 30c. Finally, a fourth rigid tube 38 extends between the third articulation 30c and a fluid outlet 40.
Chacune des articulations 30a, 30b, 30c comprend deux organes qui sont fixés rigidement aux tubes correspondants et qui sont accouplés l’un à l’autre pour d’une part assurer le raccordement fluidique entre les tubes, et d’autre part permettre une rotation des tubes l’un par rapport à l’autre autour d’un axe D.
L’organe 42 fixé à l’extrémité du premier tube 32 est ainsi accouplé à l’organe 44 fixé à l’extrémité du second tube 34. Les organes 42, 44 forment la première articulation tournante 30a autour d’un premier axe D1 , et sont aptes à assurer une communication fluidique entre les tubes 32, 34 quelle que soit la position des organes 42, 44 et des tubes 32, 34 vis-à-vis de l’axe D1 .Each of the joints 30a, 30b, 30c comprises two members which are rigidly fixed to the corresponding tubes and which are coupled to one another to on the one hand ensure fluid connection between the tubes, and on the other hand allow rotation tubes relative to each other around an axis D. The member 42 fixed to the end of the first tube 32 is thus coupled to the member 44 fixed to the end of the second tube 34. The members 42, 44 form the first rotating joint 30a around a first axis D1, and are capable of ensuring fluid communication between the tubes 32, 34 whatever the position of the members 42, 44 and the tubes 32, 34 with respect to the axis D1.
L’organe 46 fixé à l’autre extrémité du second tube 34 est accouplé à l’organe 48 fixé à l’extrémité du troisième tube 36. Les organes 46, 48 forment la seconde articulation tournante 30b autour d’un second axe D2, et sont aptes à assurer une communication fluidique entre les tubes 34, 36 quelle que soit la position des organes 46, 48 et des tubes 34, 36 vis-à-vis de l’axe D2.The member 46 fixed to the other end of the second tube 34 is coupled to the member 48 fixed to the end of the third tube 36. The members 46, 48 form the second rotating joint 30b around a second axis D2, and are capable of ensuring fluid communication between the tubes 34, 36 whatever the position of the members 46, 48 and the tubes 34, 36 with respect to the axis D2.
L’organe 50 fixé à l’autre extrémité du troisième tube 36 est accouplé à l’organe 52 fixé à l’extrémité du quatrième tube 38. Les organes 50, 52 forment la troisième articulation tournante 30c autour d’un second axe D3, et sont aptes à assurer une communication fluidique entre les tubes 36, 38 quelle que soit la position des organes 50, 52 et des tubes 36, 38 vis-à-vis de l’axe D3. The member 50 fixed to the other end of the third tube 36 is coupled to the member 52 fixed to the end of the fourth tube 38. The members 50, 52 form the third rotating joint 30c around a second axis D3, and are capable of ensuring fluid communication between the tubes 36, 38 whatever the position of the members 50, 52 and the tubes 36, 38 with respect to the axis D3.
Les axes D1 , D2, D3 sont parallèles. The axes D1, D2, D3 are parallel.
La figure 4 montre l’articulation tournante 30a en coupe, les autres articulations tournantes 30b, 30c étant similaires. Figure 4 shows the rotating joint 30a in section, the other rotating joints 30b, 30c being similar.
Le tube 32 comprend un passage interne 32a pour la circulation d’un fluide, qui s’étend sur toute sa longueur et est relié à une extrémité d’un passage interne 42a de l’organe 42. Le passage interne 42a de l’organe 42 a une forme générale en L et son extrémité, opposée au tube 32, est reliée à une extrémité du passage interne 44a en forme de L de l’autre organe 44. Le tube 34 comprend un passage interne 34a qui s’étend sur toute sa longueur et est relié à l’extrémité opposée du passage interne 42a de l’organe 42.The tube 32 comprises an internal passage 32a for the circulation of a fluid, which extends over its entire length and is connected to one end of an internal passage 42a of the member 42. The internal passage 42a of the member 42 has a general L-shaped shape and its end, opposite the tube 32, is connected to one end of the L-shaped internal passage 44a of the other member 44. The tube 34 comprises an internal passage 34a which extends over the entire its length and is connected to the opposite end of the internal passage 42a of the member 42.
Un passage en L comporte deux portions perpendiculaires, à savoir une première portion qui s’étend dans une direction et une deuxième portion qui s’étend dans une direction perpendiculaire à la première, les deux portions étant en communication fluidique.
Les organes 42, 44 peuvent être assemblés par un emboîtement du type mâle femelle par exemple, comme illustré dans le dessin. L’emboîtement est réalisé suivant l’axe D1 et permet de former l’articulation 30a autour de cet axe. Dans l’exemple représenté, l’organe 42 comprend un embout femelle 42b qui est traversé par le passage 42a et qui reçoit un embout mâle 44b de l’organe 44, cet embout mâle 44b étant également traversé par le passage 44a de cet organe 44. An L-shaped passage has two perpendicular portions, namely a first portion which extends in one direction and a second portion which extends in a direction perpendicular to the first, the two portions being in fluid communication. The members 42, 44 can be assembled by a male-female type interlocking for example, as illustrated in the drawing. The interlocking is carried out along the axis D1 and makes it possible to form the articulation 30a around this axis. In the example shown, the member 42 comprises a female end piece 42b which is crossed by the passage 42a and which receives a male end piece 44b of the member 44, this male end piece 44b also being crossed by the passage 44a of this member 44 .
Des moyens d’étanchéité, tels qu’un ou plusieurs joints annulaires 54, peuvent être montés au niveau des embouts 42b, 44b. Sealing means, such as one or more annular seals 54, can be mounted at the end pieces 42b, 44b.
La figure 5 illustre un premier mode de réalisation d’un ensemble propulsif 10 selon l’invention. Comme évoqué dans ce qui précède, cet ensemble propulsif 10 comprend : Figure 5 illustrates a first embodiment of a propulsion assembly 10 according to the invention. As mentioned in the above, this propulsion assembly 10 includes:
- un mât réacteur 12, - a reactor mast 12,
- une turbomachine 14 comportant un système fluidique 18, et - a turbomachine 14 comprising a fluid system 18, and
- un capotage 16 qui peut entourer la turbomachine 14, comme dans l’exemple représenté. - a cowling 16 which can surround the turbomachine 14, as in the example shown.
Dans l’exemple représenté, le capotage 16 comprend deux panneaux 20 de forme générale semi-circulaire qui s’étendent de part et d’autre du plan P précité et qui comprennent des bords longitudinaux supérieurs 22 qui sont fixés au mât réacteur 12 par des charnières 25. Ces bords supérieurs 22 sont situés sensiblement dans une position 12h en étant séparés l’un de l’autre par le mât réacteur 12. In the example shown, the cowling 16 comprises two panels 20 of generally semi-circular shape which extend on either side of the aforementioned plane P and which comprise upper longitudinal edges 22 which are fixed to the reactor mast 12 by means of hinges 25. These upper edges 22 are located substantially in a 12 o'clock position being separated from each other by the reactor mast 12.
Dans l’exemple représenté, les charnières 25 sont au nombre de trois et sont disposées les unes derrière les autres le long de l’axe C. On peut donc considérer qu’il y a une charnière amont, une charnière intermédiaire et une charnière aval. De préférence, deux de ces charnières sont montées fixes et la troisième est montée flottante de manière à avoir un alignement parfait.In the example shown, the hinges 25 are three in number and are arranged one behind the other along the axis C. We can therefore consider that there is an upstream hinge, an intermediate hinge and a downstream hinge. . Preferably, two of these hinges are mounted fixed and the third is mounted floating so as to have perfect alignment.
Chacun des panneaux 20 est articulé autour d’un troisième axe C (défini par les charnières 25) qui peut être parallèle au second axe B par exemple, depuis une position fermée dans laquelle son bord inférieur (non visible) est sensiblement à la position 6h, jusqu’à une position ouverte dans laquelle son
bord inférieur est éloigné de la position 6h. Le débattement angulaire entre les deux positions est par exemple supérieur à 30° autour de l’axe C. Each of the panels 20 is articulated around a third axis C (defined by the hinges 25) which can be parallel to the second axis B for example, from a closed position in which its lower edge (not visible) is substantially at the 6 o'clock position , to an open position in which its lower edge is away from the 6 o'clock position. The angular movement between the two positions is for example greater than 30° around the axis C.
Chacun des panneaux 20 porte au moins un échangeur surfacique 26 de chaleur qui comprend un circuit de fluide 26’ raccordé au système fluidique 18, et une surface d’échange qui est exposée à un flux de gaz de refroidissement 4. Each of the panels 20 carries at least one surface heat exchanger 26 which comprises a fluid circuit 26' connected to the fluidic system 18, and an exchange surface which is exposed to a flow of cooling gas 4.
Dans l’exemple représenté, l’échangeur 26 est situé sur une surface incurvée concave du panneau 20, qui est orientée vers l’axe B, et qui est donc une surface interne du panneau. Cette position n’est pas limitative. En variante, l’échangeur 26 pourrait par exemple être sur une surface convexe externe du panneau 20. In the example shown, the exchanger 26 is located on a concave curved surface of the panel 20, which is oriented towards the axis B, and which is therefore an internal surface of the panel. This position is not restrictive. Alternatively, the exchanger 26 could for example be on an external convex surface of the panel 20.
En effet, dans le cadre de la présente invention, le panneau 20 peut être un panneau interne ou externe de la turbomachine et de l’ensemble propulsif, et peut être balayé par un flux de gaz passant à l’intérieur ou à l’extérieur du panneau (notamment un flux secondaire ou flux externe à la turbomachine). L’échangeur 26 est donc situé à l’intérieur ou à l’extérieur du panneau 20, et donc positionné sur une surface interne ou externe de ce panneau 20. Indeed, in the context of the present invention, the panel 20 can be an internal or external panel of the turbomachine and the propulsion assembly, and can be swept by a flow of gas passing inside or outside of the panel (in particular a secondary flow or flow external to the turbomachine). 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.
Les moyens de raccordement fluidique du circuit de fluide 26’ de chaque échangeur 26 au système fluidique 18 comprennent au moins une articulation tournante 30 telle que décrite dans ce qui précède. The fluid connection means of the fluid circuit 26' of each exchanger 26 to the fluid system 18 comprise at least one rotating joint 30 as described in the above.
Dans l’exemple représenté, le circuit de fluide 26’ comprend une entrée de fluide 26a et une sortie de fluide 26b. Le système fluidique 18 comprend une entrée de fluide 18a et une sortie de fluide 18b. In the example shown, the fluid circuit 26' comprises a fluid inlet 26a and a fluid outlet 26b. The fluid system 18 includes a fluid inlet 18a and a fluid outlet 18b.
L’entrée de fluide 26a du circuit 26’ est reliée à la sortie de fluide 18b du système 18 par une première articulation 30 qui est centrée sur l’axe C de pivotement du panneau 20 qui porte l’échangeur 26 avec ce circuit 26’. Cette première articulation 30 est reliée par des tubes rigides 32, 34 respectivement à l’entrée 26a et à la sortie 18b ou à des conduites reliées à cette entrée et cette sortie. Dans l’exemple représenté, on constate que la première articulation est située à côté d’une des charnières 25, qui est la charnière intermédiaire 25a dans l’exemple représenté. Une vanne 33 est
avantageusement intercalée entre l’articulation 30 et la sortie 18b donc juste en amont de l’articulation 30. Cette vanne 33 peut également être centrée sur l’axe C. Dans le dessin, on constate que la charnière 25a est située entre la vanne 33 et l’articulation 30. The fluid inlet 26a of the circuit 26' is connected to the fluid outlet 18b of the system 18 by a first articulation 30 which is centered on the pivot axis C of the panel 20 which carries the exchanger 26 with this circuit 26' . This first articulation 30 is connected by rigid tubes 32, 34 respectively to the inlet 26a and the outlet 18b or to pipes connected to this inlet and this outlet. In the example shown, we see that the first articulation is located next to one of the hinges 25, which is the intermediate hinge 25a in the example shown. A valve 33 is advantageously inserted between the joint 30 and the outlet 18b therefore just upstream of the joint 30. This valve 33 can also be centered on the axis C. In the drawing, we see that the hinge 25a is located between the valve 33 and joint 30.
La sortie de fluide 26b du circuit 26’ est reliée à l’entrée de fluide 18a du système 18 par une seconde articulation 30’ qui est centrée sur l’axe C de pivotement du panneau 20 qui porte l’échangeur 26 avec ce circuit 26’. Cette seconde articulation 30’ est reliée par des tubes rigides 32, 34 respectivement à la sortie 26b et à l’entrée 18a ou à des conduites reliées à cette sortie et à cette entrée. Dans l’exemple représenté, on constate que la seconde articulation est située à côté d’une autre des charnières 25, qui est la charnière aval dans l’exemple représenté. Une vanne 33 est avantageusement intercalée entre l’articulation 30’ et l’entrée 18a donc juste en aval de l’articulation 30’. Cette vanne 33 peut également être centrée sur l’axe C. Dans le dessin, on constate que la charnière 25b est située entre la vanne 33 et l’articulation 30’. The fluid outlet 26b of the circuit 26' is connected to the fluid inlet 18a of the system 18 by a second articulation 30' which is centered on the pivot axis C of the panel 20 which carries the exchanger 26 with this circuit 26 '. This second articulation 30' is connected by rigid tubes 32, 34 respectively to the outlet 26b and the inlet 18a or to pipes connected to this outlet and this inlet. In the example shown, we see that the second articulation is located next to another of the hinges 25, which is the downstream hinge in the example shown. A valve 33 is advantageously inserted between the joint 30' and the inlet 18a, therefore just downstream of the joint 30'. This valve 33 can also be centered on axis C. In the drawing, we see that the hinge 25b is located between the valve 33 and the articulation 30'.
Les articulations 30, 30’ sont donc à distance l’une de l’autre, le long de l’axe C. The joints 30, 30' are therefore at a distance from each other, along the axis C.
La ou les vannes 33 permettent d’isoler le circuit de fluide en vue par exemple du démontage de l’échangeur 26 ou du panneau 20 lors d’une opération de maintenance. The valve(s) 33 make it possible to isolate the fluid circuit for example with a view to dismantling the exchanger 26 or the panel 20 during a maintenance operation.
La variante de réalisation de la figure 6 diffère du précédent mode de réalisation notamment par le fait que les deux articulations 30, 30’ sont ici accolées et non plus à distance l’une de l’autre. The alternative embodiment of Figure 6 differs from the previous embodiment in particular in that the two joints 30, 30' are here next to each other and no longer at a distance from each other.
Comme illustré dans le dessin, l’organe 42 de la première articulation 30 est intercalé entre l’organe 44 de cette articulation 30 et l’organe 42’ de la seconde articulation 30’. As illustrated in the drawing, the member 42 of the first joint 30 is inserted between the member 44 of this joint 30 and the member 42' of the second joint 30'.
Les articulations 30, 30’ sont ici disposées au niveau de la première charnière 25a, d’un côté de cette charnière 25a. La vanne 33 associée à la première articulation 30 est située de l’autre côté de la charnière 25a, et les articulations sont situées entre la charnière 25a et l’autre vanne 33.
La variante de réalisation de la figure 7 diffère de la précédente variante en ce qu’elle utilise non pas une simple articulation tournante, pour chaque liaison fluidique, mais une double articulation tournante ce qui permet de n’avoir pas l’obligation de s’aligner sur le même axe de rotation que les charnières 25. The joints 30, 30' are here arranged at the level of the first hinge 25a, on one side of this hinge 25a. The valve 33 associated with the first joint 30 is located on the other side of the hinge 25a, and the joints are located between the hinge 25a and the other valve 33. The alternative embodiment of Figure 7 differs from the previous variant in that it uses not a simple rotating articulation, for each fluid connection, but a double rotating articulation which makes it possible to avoid the obligation to align on the same axis of rotation as the hinges 25.
L’entrée de fluide 26a du circuit 26’ est reliée à la sortie de fluide 18b du système 18 par une double articulation qui comprend des articulations 30a et 30b du type de celle de la figure 3 par exemple. La première articulation 30a est centrée sur l’axe C et la seconde 30b est centrée sur un axe parallèle à l’axe C. The fluid inlet 26a of the circuit 26' is connected to the fluid outlet 18b of the system 18 by a double articulation which comprises joints 30a and 30b of the type of that of Figure 3 for example. The first articulation 30a is centered on the axis C and the second 30b is centered on an axis parallel to the axis C.
L’invention présente de nombreux avantages parmi lesquels : The invention has numerous advantages including:
- les tubes sont rigides, ce qui est avantageux en termes de coût, de masse et de maintenance, - the tubes are rigid, which is advantageous in terms of cost, mass and maintenance,
- le diamètre des tubes est optimisé et n’a pas besoin d’être surdimensionné, ce qui facilite l’intégration de l’articulation tournante dans l’environnement, - the diameter of the tubes is optimized and does not need to be oversized, which facilitates the integration of the rotating joint into the environment,
- il n’y a pas de déplacements relatifs des articulations sauf dans le cas de la dernière variante et de l’utilisation d’une double articulation tournante,- there are no relative movements of the joints except in the case of the last variant and the use of a double rotating joint,
- la longueur de l’articulation tournante est également optimisée, - the length of the rotating joint is also optimized,
- la maintenance est simplifiée et moins coûteuse car le démontage du circuit de fluide est plus simple et rapide, - maintenance is simplified and less costly because dismantling the fluid circuit is simpler and faster,
- la dernière variante permet d’avoir des désalignements par rapport à l’axe- the last variant allows for misalignments in relation to the axis
C des charnières.
C hinges.
Claims
1. Ensemble propulsif (10) pour un aéronef, cet ensemble propulsif (10) comportant : 1. Propulsion assembly (10) for an aircraft, this propulsion assembly (10) comprising:
- un mât réacteur (12) s’étendant le long d’un premier axe (A), - a reactor mast (12) extending along a first axis (A),
- une turbomachine (14) fixée au mât réacteur (12), cette turbomachine (14) s’étendant le long d’un second axe (B), les premier et second axes (A, B) s’étendant dans un même plan (P), la turbomachine (14) comportant un système fluidique (18), - a turbomachine (14) fixed to the reactor mast (12), this turbomachine (14) extending along a second axis (B), the first and second axes (A, B) extending in the same plane (P), the turbomachine (14) comprising a fluidic system (18),
- un capotage (16) qui s’étend le long et autour du second axe (B), le capotage (16) comportant au moins un panneau (20) qui s’étend autour dudit second axe, ledit au moins un panneau (20) comportant un bord longitudinal (22) qui est fixé au mât réacteur (14) par des charnières (25) qui définissent un troisième axe (C) de pivotement du panneau, depuis une position fermée dans laquelle il s’étend autour de la turbomachine (14) jusqu’à une position ouverte dans laquelle il est écarté de la turbomachine (14), ledit au moins un panneau (20) portant au moins un échangeur surfacique de chaleur (26) qui comprend un circuit de fluide (26’) raccordé audit système fluidique (18), caractérisé en ce que le circuit de fluide (26’) est raccordé au système fluidique (18) par au moins une articulation tournante (30, 30’) qui est centrée sur le troisième axe (C) et qui est reliée par un premier tube rigide (32) au circuit de fluide (26’) et par un second tube rigide (34) au système fluidique (18), cette articulation tournante (30, 30’) comportant un premier organe (42) fixé rigidement au premier tube (32), et un second organe (44) fixé rigidement au second tube (34), les premier et second organes (42, 44) étant assemblés de façon à pouvoir tourner l’un par rapport à l’autre autour du troisième axe (C) et à assurer une communication fluidique entre les premier et second tubes (32, 34) quelle que soit la position des premier et second organes (42, 44) autour du troisième axe (C). - a cowling (16) which extends along and around the second axis (B), the cowling (16) comprising at least one panel (20) which extends around said second axis, said at least one panel (20) ) comprising a longitudinal edge (22) which is fixed to the reactor mast (14) by hinges (25) which define a third pivot axis (C) of the panel, from a closed position in which it extends around the turbomachine (14) up 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 fluidic system (18), characterized in that the fluid circuit (26') is connected to the fluidic system (18) by at least one rotating joint (30, 30') which is centered on the third axis (C) and which is connected by a first rigid tube (32) to the fluid circuit (26') and by a second rigid tube (34) to the fluid system (18), this rotating joint (30, 30') comprising a first member ( 42) rigidly fixed to the first tube (32), and a second member (44) rigidly fixed to the second tube (34), the first and second members (42, 44) being assembled so as to be able to rotate one relative to the other around the third axis (C) and to ensure fluid communication between the first and second tubes (32, 34) whatever the position of the first and second members (42, 44) around the third axis (C).
2. Ensemble propulsif (10) selon la revendication 1 , dans lequel chacun des premier et second organes (42, 44) comprend un passage interne (42a,
44a) en L dont une première extrémité est reliée au tube (32, 34) correspondant, et dont une seconde extrémité est reliée à l’autre organe (44, 42). 2. Propulsion assembly (10) according to claim 1, in which each of the first and second members (42, 44) comprises an internal passage (42a, 44a) L-shaped, a first end of which is connected to the corresponding tube (32, 34), and a second end of which is connected to the other member (44, 42).
3. Ensemble propulsif (10) selon la revendication 1 ou 2, dans lequel l’un des premier et second organes (42, 44) comprend un embout mâle (44b) qui est engagé selon le troisième axe (C) dans un embout femelle (42b) de l’autre des premier et second organes (44, 42). 3. Propulsion assembly (10) according to claim 1 or 2, in which one of the first and second members (42, 44) comprises a male tip (44b) which is engaged along the third axis (C) in a female tip (42b) of the other of the first and second organs (44, 42).
4. Ensemble propulsif (10) selon la revendication 3, dans lequel au moins un joint ou moyen d’étanchéité (54) est monté entre les embouts mâle et femelle (42b, 44b). 4. Propulsion assembly (10) according to claim 3, wherein at least one seal or sealing means (54) is mounted between the male and female ends (42b, 44b).
5. Ensemble propulsif (10) selon l’une des revendications précédentes, dans lequel le circuit de fluide (26’) est raccordé au système fluidique (18) par deux articulations tournantes (30, 30’) centrées sur le troisième axe (C), une première de ces articulations tournantes (30) étant reliée à une entrée (26a) dudit circuit de fluide (26’), et une seconde (30’) de ces articulations tournantes étant reliée à une sortie de fluide (26b) dudit circuit (26’). 5. Propulsion assembly (10) according to one of the preceding claims, in which the fluid circuit (26') is connected to the fluidic system (18) by two rotating joints (30, 30') centered on the third axis (C ), a first of these rotating joints (30) being connected to an inlet (26a) of said fluid circuit (26'), and a second (30') of these rotating joints being connected to a fluid outlet (26b) of said circuit (26').
6. Ensemble propulsif (10) selon la revendication 5, dans lequel les première et seconde articulations tournantes (30, 30’) sont à distance l’une de l’autre. 6. Propulsion assembly (10) according to claim 5, wherein the first and second rotating joints (30, 30') are spaced apart from each other.
7. Ensemble propulsif (10) selon la revendication 5, dans lequel les première et seconde articulations tournantes (30, 30’) sont accolées. 7. Propulsion assembly (10) according to claim 5, in which the first and second rotating joints (30, 30') are joined together.
8. Ensemble propulsif (10) selon l’une des revendications précédentes, dans lequel au moins une vanne (33) est montée entre le système fluidique (18) et le second tube rigide (34) de la ou de chaque articulation tournante (30, 30’). 8. Propulsion assembly (10) according to one of the preceding claims, in which at least one valve (33) is mounted between the fluid system (18) and the second rigid tube (34) of the or each rotating joint (30). , 30').
9. Ensemble propulsif (10) selon l’une des revendications précédentes, dans lequel le circuit de fluide (26’) est raccordé au système fluidique (18) par au moins une double articulation tournante (30a, 30b) qui comprend :9. Propulsion assembly (10) according to one of the preceding claims, in which the fluid circuit (26') is connected to the fluid system (18) by at least one double rotating joint (30a, 30b) which comprises:
- le premier tube rigide (32) s’étendant entre le circuit de fluide (26’) et le premier organe (42) d’une première articulation (30a),
- le second tube rigide (34) s’étendant entre le second organe (44) de la première articulation (30a) et un troisième organe (46) fixé rigidement à une extrémité de ce second tube (34), et - the first rigid tube (32) extending between the fluid circuit (26') and the first member (42) of a first articulation (30a), - the second rigid tube (34) extending between the second member (44) of the first articulation (30a) and a third member (46) rigidly fixed to one end of this second tube (34), and
- un troisième tube rigide (36) s’étendant entre le système fluidique (18) et un quatrième organe (48) fixé rigidement à une extrémité de ce troisième tube (36), les troisième et quatrième organes (46, 48) formant une seconde articulation tournante (30b) et étant assemblés de façon à pouvoir tourner l’un par rapport à l’autre autour d’un quatrième axe parallèle au troisième axe (C) et à assurer une communication fluidique entre les second et troisième tubes (34, 36) quelle que soit la position des troisième et quatrième organes (46, 48) autour du quatrième axe. - a third rigid tube (36) extending between the fluid system (18) and a fourth member (48) rigidly fixed to one end of this third tube (36), the third and fourth members (46, 48) forming a second rotating joint (30b) and being assembled so as to be able to rotate relative to each other around a fourth axis parallel to the third axis (C) and to ensure fluid communication between the second and third tubes (34 , 36) whatever the position of the third and fourth organs (46, 48) around the fourth axis.
10. Ensemble propulsif (10) selon la revendication 5, dans lequel ledit au moins un panneau (20) comprend une surface concave interne sur laquelle est situé ledit au moins un échangeur (26). 10. Propulsion assembly (10) according to claim 5, wherein said at least one panel (20) comprises an internal concave surface on which said at least one exchanger (26) is located.
11. Ensemble propulsif (10) selon l’une des revendications précédentes, dans lequel ledit plan (P) dans lequel s’étendent les premier et second axes est vertical ou incliné par rapport à la verticale. 11. Propulsion assembly (10) according to one of the preceding claims, wherein said plane (P) in which the first and second axes extend is vertical or inclined relative to the vertical.
12. Ensemble propulsif (10) selon l’une des revendications précédentes, dans lequel ledit circuit de fluide (26’) est un circuit d’huile ou un circuit de liquide de refroidissement. 12. Propulsion assembly (10) according to one of the preceding claims, wherein said fluid circuit (26') is an oil circuit or a coolant circuit.
13. Ensemble propulsif (10) selon l’une des revendications précédentes, dans lequel le capotage (16) comprend deux panneaux (20) de forme générale semi-circulaire qui s’étendent de part et d’autre dudit axe principal, chacun de ces panneaux comporte un bord longitudinal supérieur (22) et inférieur (24), le bord longitudinal supérieur du ou de chaque panneau est fixé par les charnières (25). 13. Propulsion assembly (10) according to one of the preceding claims, wherein the cowling (16) comprises two panels (20) of generally semi-circular shape which extend on either side of said main axis, each of these panels have an upper (22) and lower (24) longitudinal edge, the upper longitudinal edge of the or each panel is fixed by the hinges (25).
14. Ensemble propulsif (10) selon la revendication précédente, dans lequel l’autre des panneaux (20) porte un autre échangeur de chaleur ou un autre type d’équipement fluidique.
14. Propulsion assembly (10) according to the preceding claim, wherein the other of the panels (20) carries another heat exchanger or another type of fluidic equipment.
15. Ensemble propulsif (10) selon l’une des revendications précédentes, dans lequel le ou chaque panneau (20) a une forme générale semi-circulaire
15. Propulsion assembly (10) according to one of the preceding claims, in which the or each panel (20) has a general semi-circular shape
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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FRFR2212297 | 2022-11-24 | ||
FR2212297A FR3142456A1 (en) | 2022-11-24 | 2022-11-24 | PROPULSIVE ASSEMBLY FOR AN AIRCRAFT |
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WO2024110720A1 true WO2024110720A1 (en) | 2024-05-30 |
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PCT/FR2023/051803 WO2024110720A1 (en) | 2022-11-24 | 2023-11-15 | Propulsion unit for an aircraft |
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FR (1) | FR3142456A1 (en) |
WO (1) | WO2024110720A1 (en) |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2567081A1 (en) | 1984-07-03 | 1986-01-10 | Sueddeutsche Kuehler Behr | Hot water pipe for vehicle heating systems |
CN207854371U (en) | 2017-12-26 | 2018-09-11 | ***通信集团广东有限公司 | A kind of heat pipe back board system for cabinet |
US20200049028A1 (en) | 2017-04-24 | 2020-02-13 | Safran Aircraft Engines | Aircraft propulsion assembly comprising air-liquid heat exchangers |
FR3094750A1 (en) | 2019-04-03 | 2020-10-09 | Safran Nacelles | Aircraft turbojet cooling system |
US20210078380A1 (en) | 2018-05-18 | 2021-03-18 | Bayerische Motoren Werke Aktiengesellschaft | Liquid System and Motor Vehicle Comprising such a Liquid System |
-
2022
- 2022-11-24 FR FR2212297A patent/FR3142456A1/en active Pending
-
2023
- 2023-11-15 WO PCT/FR2023/051803 patent/WO2024110720A1/en unknown
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2567081A1 (en) | 1984-07-03 | 1986-01-10 | Sueddeutsche Kuehler Behr | Hot water pipe for vehicle heating systems |
US20200049028A1 (en) | 2017-04-24 | 2020-02-13 | Safran Aircraft Engines | Aircraft propulsion assembly comprising air-liquid heat exchangers |
CN207854371U (en) | 2017-12-26 | 2018-09-11 | ***通信集团广东有限公司 | A kind of heat pipe back board system for cabinet |
US20210078380A1 (en) | 2018-05-18 | 2021-03-18 | Bayerische Motoren Werke Aktiengesellschaft | Liquid System and Motor Vehicle Comprising such a Liquid System |
FR3094750A1 (en) | 2019-04-03 | 2020-10-09 | Safran Nacelles | Aircraft turbojet cooling system |
Also Published As
Publication number | Publication date |
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FR3142456A1 (en) | 2024-05-31 |
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