PROPULSION UNIT OF AN AIRCRAFT COMPRISING A FLUID COOLING CIRCUIT WITH QUICK NACELLE / ENGINE COUPLINGS AND AIRCRAFT EQUIPPED WITH SUCH AN ASSEMBLY

Abstract

In a propulsion assembly of an aircraft comprising a fluid cooling circuit with quick nacelle / engine couplings and aircraft provided with such an assembly The invention relates to a propulsion assembly (100) of an aircraft comprising: an engine (105); an interior structure formed by two half-shells (111), where each half-shell (111) is intended to be articulated to a mast (102) and comprises a semi-cylindrical part capable of being movable between a closed position in which the half-shell (111) is tightened around the engine (105) and an open position in which the half-shell (111) is spaced from the engine (105); a fluid circuit (C) at least one half-shell (111) being equipped with a cooling circuit (R) associated with the fluid circuit (C);a removable hydraulic junction (120) between the fluid circuit (C) and the cooling circuit (R), the removable hydraulic junction (120) comprising at least two quick connectors, where each of the quick connectors comprises a pair of male / female elements configured to fit axially into one another, with one element of the pair fixed to the half-shell (111) and the other element of the pair secured to the engine (105). Abstract figure: Figure 3b;

Description

Title of the invention: PROPULSION ASSEMBLY OF AN AIRCRAFT COMPRISING A FLUID COOLING CIRCUIT WITH QUICK NACELLE COUPLINGS / ENGINE AND AIRCRAFT EQUIPPED WITH SUCH AN ASSEMBLY

[0001] The present invention relates to a propulsion unit of an aircraft comprising a fluid cooling circuit.

[0002] In relation to figures 1a and 1b, a propulsion unit 1 mounted under a wing 2 of an aircraft using a mast 3 comprises a turbomachine comprising an engine 5 surrounded by a nacelle. During operation of the engine 5, the air enters the nacelle then divides into a primary flow (not shown) which passes through the engine 5 and into a secondary flow F2 which is channeled between the engine 5 and the nacelle 6, in a secondary vein 7. The secondary vein 7 is delimited on the outside by an external structure 6a of the nacelle and on the inside by an internal structure 6b of the nacelle, which forms a sealed compartment around the engine 5.

[0003] The internal structure 6b is formed by two half-shells 8 distributed on either side of the engine 5 (only one half-shell is shown in Figures 1a and 1b, the other half-shell not shown is a mirror image of the half-shell shown). Each half-shell 8 comprises a high bifurcation portion 19a, a low bifurcation portion 19b and a semi-cylindrical part 13, located between the two portions. Each half-shell 8 is articulated to the mast 3 at its high bifurcation portion 19a and can pivot between a closed position ([Fig.1a]) in which the half-shell 8 is tightened around the engine 5 with its semi-cylindrical part 13 which partially surrounds the engine 5 and an open position ([Fig.1b]) in which the half-shell 8 is moved away from the engine 5.

[0004] It is known, for example from patent EP3640467, to cool the oil necessary for the operation of the engine 5 by circulating it in a cooling circuit 9 arranged in one of the half-shells 8. The cooling circuit 9 uses a cold air intake in the secondary stream 7 to cool the oil heated by the operation of the engine 5. The cooling circuit 9 is connected to the oil circuit (not shown) of the engine 5 by means of hoses 11 running through the articulation of the half-shell 8 to the mast 3 and connecting the mast to the upper bifurcation portion 19a. When the half-shell 8 is in the open position, access to the hoses 11 by operators for maintenance purposes is complicated by the small gap between the half-shell 8 and the engine 5 in this area as well as by the bulk in the area of ​​different systems.

[0005] There is a need to find a solution to overcome this drawback in order to facilitate and accelerate engine maintenance operations and thereby increase the availability rate of aircraft.

[0006] For this purpose, a propulsion unit for an aircraft is proposed comprising: - an engine; - two half-shells arranged on either side of a longitudinal median plane of the engine, where each half-shell comprises a high bifurcation extended by a semi-cylindrical part, each half-shell being intended to be articulated to a mast at the level of its high bifurcation and to be movable between a closed position in which the half-shell is tightened around the engine with its semi-cylindrical part partially surrounding the engine and an open position in which the half-shell is spaced from the engine; - a fluid circuit; - at least one half-shell being equipped with a cooling circuit associated with the fluid circuit;the propulsion assembly comprising a removable hydraulic junction between the fluid circuit and the cooling circuit, the removable hydraulic junction comprising at least two quick connectors, where each of the quick connectors comprises a pair of male / female elements configured to fit axially into one another, with one element of the pair fixed to the half-cylindrical part of the half-shell and the other element of the pair secured to the engine.;

[0007] The invention meets the aforementioned need by eliminating the hoses in the area above the engine and replacing them with a removable hydraulic junction with easier access.

[0008] Other aims, characteristics and advantages will emerge from the description of the invention which follows, a description given by way of non-limiting example only, with reference to the attached drawings in which: [Fig. 1a] is a schematic front view of a propulsion unit of the prior art, one half-shell of the nacelle of which is in the closed position; [Fig. 1b] is a view similar to [Fig. 1a], representing a propulsion unit of the prior art, one half-shell of which is in the open position; [Fig. 2] is a schematic view along a longitudinal section of a propulsion unit attached to a wing of an aircraft according to the invention; [Fig. 3a] is a schematic front view of the propulsion unit of [Fig. 2] comprising a nacelle, one half-shell of which is in the closed position, according to an embodiment of the invention; [Fig.3b] is a view similar to [Fig.3a], showing the propulsion assembly of [Fig.2] of which a half-shell is in the open position, according to the same embodiment of the invention; [Fig.4] is an enlarged schematic view of the zone W shown in [Fig.3a] and showing a central distributor / collector hydraulically connected to a satellite distributor / collector according to an embodiment of the invention; [Fig.5] is a schematic plan view of the actual hydraulic connection between a central distributor / collector and a distributor / . satellite manifold according to one embodiment of the invention; [Fig.6] is a schematic perspective view of the central distributor / manifold of [Fig.4]; [Fig.7] is a schematic perspective view of the satellite distributor / manifold shown in [Fig.4]; [Fig.8] is a schematic bottom plan view showing a locking system of a central distributor / manifold with a satellite distributor / manifold in the locked position according to one embodiment of the invention; [Fig.9] is a schematic bottom plan view showing the locking system of [Fig.8] in the unlocked position; [Fig. 10] is a schematic side view of an aircraft equipped with a propulsion unit according to the present invention.

[0009] In relation to figures 2 to 3b and 10, a propulsion unit 100 is mounted under a wing 101 of an aircraft 106 using a mast 102. The propulsion unit comprises a turbomachine 103 surrounded by a nacelle 104. The turbomachine 103 comprises an engine 105 and a secondary vein 107 in which circulates a secondary air flow F2 propelled towards the rear of the engine 105 during operation of the latter.

[0010] In the following description and by convention, X is the longitudinal axis of the engine oriented positively in the direction of advance of the aircraft and which is horizontal when the aircraft is on the ground, Y is the transverse axis and Z is the vertical axis or height which is vertical when the aircraft is on the ground, these three directions X, Y and Z being orthogonal to each other.

[0011] The secondary vein 107 which extends along the X axis, is delimited on the outside by an external structure 108 of the nacelle 104 and on the inside by an internal structure 109 of the nacelle 104.

[0012] The interior structure 109 comprises a high bifurcation 109a located above the motor 105, a low bifurcation 109b located below the motor 105, and between the two bifurcations, a cylindrical part 110 which surrounds the motor 105. The two bifurcations 109a-b both extend vertically, along the X and Z axes.

[0013] The cylindrical part 110 is formed by two half-shells 111 (a single half-shell 111 is shown in FIGS. 3a and 3b) arranged on either side of a longitudinal median plane V (plane parallel to the X and Z axes) of the engine 105 and symmetrical to each other with respect to this plane. Each of the two half-shells 111 comprises a high bifurcation portion 112a, a low bifurcation portion 112b and a semi-cylindrical part 113, located between the two portions. The inner skin 113a of the semi-cylindrical part 113 is located opposite the engine 105 while the outer skin 113b of the semi-cylindrical part 113 forms a wall of the secondary vein 107.

[0014] Each half-shell 111 is articulated to the mast 102 so as to pivot around an axis parallel to the X axis between a closed position ([Fig.3a]) in which the half-shell 111 is tightened around the motor 105 with its half-cylindrical 113 which partially surrounds the motor 105 and an open position ([Fig.3b]) in which the half-shell 111 is spaced from the motor 105.

[0015] The articulation 114 of each half-shell 111 to the motor 105 is formed by at least one hinge arranged on the upper bifurcation portion 109a.

[0016] The propulsion assembly 100 comprises different fluid circuits C (only one shown in the figures) to supply the engine 105 with fluids necessary for its operation. Each fluid circuit C comprises different components (not shown) arranged in the mast 102 and / or the engine 105, such as for example a tank and pumps, connected to each other by conduits. Also in the following description, only a part of the complete fluid circuit is concerned and will be called fluid circuit C.

[0017] The propulsion unit 100 comprises a cooling circuit R connected to a fluid circuit C to regulate the temperature of the fluid. Such a cooling circuit R equips a half-shell 111 and comprises at least one air / fluid heat exchanger 115 as well as conduits (not shown) for circulating the fluid. In each of the exchangers 115, a radiant mass is brought into contact with a flow of (cold) air taken from the secondary vein 107 in order to cool the (hot) fluid during its passage through the radiant mass. The exchangers 115 and the conduits of the cooling circuit R are arranged in the thickness of the half-shell 111.

[0018] According to the invention, the propulsion assembly 100 comprises a removable hydraulic junction 120 for connecting the fluid circuit C and the cooling circuit R when the half-shell 111 carrying the cooling circuit R is in the closed position ([Fig.3a]), and disconnecting the fluid circuit C and the cooling circuit R when the half-shell 111 is moved out of its closed position ([Fig.3b]).

[0019] The removable hydraulic junction 120 between the fluid circuit C and the cooling circuit R comprises at least one fluid inlet quick connector E and at least one fluid outlet quick connector S. Particularly visible in [Fig.4], each quick connector E, S comprises a male element M and a female element F, intended to be axially fitted into one another in a fitting direction parallel to a fitting axis A and to be disengaged from one another under the action of an operator.

[0020] The number of fluid inlet quick connectors (E) and fluid outlet quick connectors (S) depends on the fluid flow rate to be passed between the fluid circuit C and the cooling circuit R.

[0021] For each quick coupling (E, S), one of its male / female elements is fixed to the internal skin 113a of the half-cylindrical part 113 of the half-shell 111, and the other of its male / female elements is fixed to the motor 105, under the latter.

[0022] In the embodiment shown in Figures 4 to 7, the removable hydraulic junction 120 comprises a single fluid inlet quick connector E and a single fluid outlet quick connector S, therefore two female elements F and two male elements M.

[0023] The female elements F are all arranged in a fluid distributor / collector 121, called the central distributor / collector, hydraulically connected to the fluid circuit C and fixed to the engine 105 by being arranged under the latter. The male elements M are all arranged in a fluid distributor / collector 122, called the satellite distributor / collector, integral with the half-cylindrical part 113 of the half-shell 111 and hydraulically connected to the cooling circuit R. More specifically, the satellite distributor / collector is fixed to the internal skin 113a of the half-cylindrical part 113 of the half-shell 111.

[0024] Each of the male elements M or female F of a quick connector E, S is in the form of an elongated and hollow body to allow, in particular, the passage of fluid therein. The longitudinal axis of the body of the female element is parallel to the fitting axis A.

[0025] The body of the male element M comprises a relief R (visible in [Fig.5]) and the body of the female element F is pierced with an opening O for fitting the male element M into the female element F. The junction 120 comprises locking means that can be disengaged by an operator described in more detail later in the description, and configured to cooperate with the relief R of the male element M to retain the male element M fitted into the female element F.

[0026] Each female element F is equipped with a sliding operating sheath 116 (shown in [Fig.5]) along the fitting axis A, and capable of cooperating with the male element M to retain the male element by engaging the male element M in the sheath of the female element F.

[0027] The operating sheath 116 is movable in translation between two positions. The axial movement of the operating sheath from one position to the other by the manipulation of a handle 124 by the operator causes the disengagement of the locking means which leads to the disengagement of the male element M from the female element F which can thus be detached (released) from the female element F.

[0028] The locking means are such as, for example, described in patent US3873062 and comprise a ring whose opening is oriented axially relative to the body of the female element F and which is integral with longitudinal claws profiled so as to come, under the effect of elastic means associated with said ring, to engage by their free end in the relief of the male element, which takes the form of an external peripheral groove.

[0029] Each of the central distributor / collector 121 and satellite 122 is in the form of a machined block of parallelepiped shape, extending longitudinally in a direction parallel to the X axis.

[0030] The central and satellite distributors / collectors 121, 122 are positioned such that the central distributor / collector 121 has a lateral face 121c, called the contact face, located opposite a lateral face 122c, also called the contact face, of the satellite distributor / collector 122 when the half-shell 111 is in its closed position. The contact faces 121c, 122c are parallel to each other when the half-shell 111 is in its closed position and are opposite each other.

[0031] The central distributor / collector 121 comprises: - on an upper face 121sup, located opposite the motor 105, means 121f (visible only in [Fig.6]) for fixing the machined block to the motor 105 as well as a fluid inlet and outlet 121e,s, called main inlets and outlets, to allow the hydraulic connection of the machined block to the fluid circuit C by means of conduits (not shown); - on its contact face 121c, a fluid inlet and outlet 121el,sl, called secondary inlet and outlet, where each secondary inlet / outlet is a female element F intended to couple with a male element M of the satellite distributor / collector 122.The fitting axes A of the female elements of the central distributor / collector are all parallel to each other, and orthogonal to the aforementioned contact face 121c and the female elements F are fully arranged in the machined block with their openings O coming flush with the contact face 121c; - an internal hydraulic path (not shown) for conveying the fluid from the main fluid inlet 121e to the secondary fluid outlet 121s 1, and from the secondary fluid inlet 121el to the main fluid outlet 121s; - a disengaging mechanism 123 operable by an operator to disengage the locking means of the female elements F by acting on the operating sleeves of the female elements F in order to move them between their first and second positions and thus allow the removal of the male elements M from the female elements F.

[0032] The fixing means 121f of the central distributor / collector 121 to the engine 105 comprise, on a first, second and third corner of the upper face of the machined block, two-branch yokes 125. The yokes are all oriented along planes perpendicular to the X axis. At each of the three yokes 125, a first end of a connecting rod 126 is mounted without play between the branches through a smooth bearing crossed by a hinge pin (not shown) fitted into each of the branches, while the second end of the connecting rod is fixed without play, via an axis, to a fitting (not shown) integral with the engine 105. The fixing of the machined block via these three yokes makes it possible to eliminate the degree of freedom in Y.

[0033] At a fourth corner of the upper face 121sup, a two-arm yoke 127 whose arms are oriented parallel to the X axis is fixed to a fitting 128 secured to the motor 105. The fitting 128 comprises a flat part arranged between the two arms of the yoke 127. A hinge pin (not shown) fitted into each of the arms of the yoke 127 and into the flat part of the fitting 128 connects the fitting 128 and the yoke 127 without play. This arrangement makes it possible to eliminate the degrees of freedom in X and Z.

[0034] In an embodiment shown in Figures 4, 5 and 7, the maneuverable clutch mechanism 123 comprises: - a handle 124 (visible in [Fig.4]) mounted to move in rotation on a lower face 121inf of the machined block with an axis perpendicular to the upper / lower faces 121sup,inf of the machined block; - a shaft F (visible in [Fig.5]) one of the ends of which is fixed to the handle 124 and to which a cam C is fixed at the other end.

[0035] The sheaths 116, whether two as in the present illustrated embodiment or more, are all connected to each other, two by two, by connecting axes L. When an operator moves the handle 124 in rotation, the shaft F pivots on itself and pivots the cam C. By pivoting, the cam pushes back the sheaths 116 of the operator connected to each other by the connecting axis L (unique in the illustrated example due to only two sheaths) and allows their movement simultaneously in a direction parallel to the fitting axes A, between a first position in which the sheaths allow connection with the male elements and a second position in which the male and female elements are disconnected. The passage from the first to the second position of the cam C triggers the release of the reliefs R and authorizes the withdrawal of the male elements M fitted into the female elements F.

[0036] The satellite distributor / collector 122 comprises: - on a lower face 122inf and on a lateral face 1221at both located opposite the internal skin 113a of the half-shell 111, means for fixing the machined block to the half-shell 111; - on its contact face 122c, located opposite the contact face 121c of the central distributor / collector 121, a fluid inlet and outlet 122el,sl, called secondary inlet and outlet, where each secondary inlet and outlet is a male element M intended to couple with a female element F of the central distributor / collector 121.The bodies of the male elements M extend at least partly outside the contact face 122c; - on a face other than the contact face 122c, for example on the lateral face 1221at opposite the contact face 122c, as illustrated in FIGS. 4 and 7, a fluid inlet and outlet 122e,s, referred to as main, to allow the hydraulic connection of the machined block to the cooling circuit R by means of conduits (not shown); - an internal hydraulic path being provided to convey the fluid from. the secondary fluid inlet 122el to the main fluid outlet 122s, and from the main fluid inlet 122e to the secondary fluid outlet 122s 1.

[0037] The half-shell 111, due in particular to its flexibility (made of composite material) exacerbated by its dimensions (diameter greater than one meter), deforms during flight. The fixing means 122f of the satellite distributor / collector 122 to the half-shell 111 are, consequently, configured so that the connection of the cooling circuit to the fluid circuit C through the removable hydraulic junction 120 remains operational during flight.

[0038] Particularly visible in figures 4 and 7, the means for fixing the satellite distributor / collector 122f to the half-shell 111 are designed so that said distributor / collector is mounted floating on the half-shell 111.

[0039] In detail: - a fitting 132 is arranged on the lateral face 1221at of the machined block located opposite the half-shell 111 and comprises a flat part extending along the transverse axis Y. The flat part extends parallel to a flat part of a fixing flange 133 fixed to the half-shell 111. The fixing flange 133 comprises a through bore 134 arranged on its flat part while the fitting 132 comprises a spigot 135 which projects out of its flat part, parallel to the axis X, and is received in the bore of the fitting 133.The spigot has a cylindrical shape and the bore 135 has a dimension greater (of the order of 2 to 5 times) than that of the spigot so as to allow a rotational movement of the machined block around an axis parallel to the X axis; - two two-armed yokes 129 are located on the lower face 122inf of the machined block, at a distance from the other yoke and two two-armed yokes 130 are located on the inner skin 113a of the half-shell 111, and each of the aforementioned yokes 129 of the machined block 129 is located opposite a two-armed yoke 130 secured to the half-shell 111. The arms of the yokes 129, 130 are all oriented along an axis perpendicular to the X axis. The yokes 129 of the machined block and the yokes of the half-shell 111 are connected two by two each time by means of a connecting rod 131 arranged, at each of its two ends, between the two arms of a yoke 129, 130.The connecting rod 131 is fixed to each of the yokes 129, 130 by means of a ball joint bearing inserted into a bore of the connecting rod and crossed by a hinge pin fitted into each of the branches of the yoke. The distance between the branches of the yoke 129, 130 is greater (for example, of the order of 2 to 5 times) than the thickness of the connecting rod 131 so as to allow a translational movement of the connecting rod 131 between the branches of the yokes 129, 130, i.e. along the X axis.

[0040] In order to facilitate the work of the operators for fitting the male elements M with the female elements F, the satellite distributor / collector 122 comprises first centering means and the central distributor / collector 121 comprises second centering means, intended to cooperate with the first centering means. when moving from the open position to the closed position of the half-shell 111 to position the contact face 122c of the satellite distributor / collector 122 in a suitable position facing the contact face 121c of the central distributor / collector 121 when the half-shell 111 is moved to its closed position.

[0041] In the example illustrated in [Fig.7], the first centering means comprise two centering pins 140 arranged on the contact face of the satellite distributor / collector 122 and the second centering means comprise two bores 141 (only one shown) arranged on the contact face 121c of the central distributor / collector 121 according to a scheme complementary to the scheme with which the centering pins 140 are placed on the contact face 122c of the satellite distributor / collector 122. Each of the centering pins 140 is intended to be inserted, during a movement of the half-shell 111 towards its closed position, into an associated bore 141 to achieve the correct positioning of the central distributors / collectors 121 and satellite 122.

[0042] The entry of the bores 141 preferably comprises a countersink to further facilitate the insertion of the centering pins 140 into the bores 141.

[0043] As shown in Figures 8 and 9, the propulsion unit 100 is equipped with a system 142 for locking the satellite distributor / collector with the central distributor / collector and which can be activated by an operator once the male elements M and female F are fitted. Activation of the locking system 142 adds a safety feature aimed at preventing the untimely uncoupling of the male elements M and female F during flight. The locking system 142 is, for example as illustrated in Figures 8 and 9, of the lever type 144 provided with a hook 146, articulated in rotation about an axis 148 of the central distributor / collector 121 perpendicular to the plane of the face 121inf. The lever 144 is intended to cooperate with another element such as a rod 150 located on the lower face 122inf of the satellite distributor / collector 122.The lever 144 is pivotally hinged about the axis 148 between a position in which the lever is hooked onto the rod 150 ([Fig.8]) and a position, after rotation through an angle a of 90 degrees, in which the hook 146 releases the rod 150 to allow the opening of the half-shell 111 ([Fig.9]). An access hatch (not shown) is in this case necessary at the level of the half-shell 111 to access the lever 144. To avoid adding a hatch, the lever function could be combined with that of the handle 124.

[0044] As shown in [Fig.7], during maintenance operations and in particular in polluted environments, caps 151 can cover the hydraulic connections not connected for the duration of the maintenance and be removed to connect the connections before closing the half-shells 111. To avoid forgetting any, the caps can be connected together in the geometric configuration connections they are intended to protect. [Fig.5] shows an example of caps linked together intended to cover the fluid inlets and outlets 122e,s.

[0045] The invention has been described in the case where only one half-shell 111 is equipped with a cooling system R. In the case where both half-shells are equipped with a cooling circuit, then the fluid circuit C and each cooling circuit R are connected to each other through a removable hydraulic junction arranged under the engine 105. A first removable hydraulic junction is intended to connect the fluid circuit C to the cooling circuit R arranged in a first half-shell 111 and a second removable hydraulic junction is intended to connect the fluid circuit C to the cooling circuit arranged in a second half-shell.

[0046] Taking up the embodiment described above, but this time applied to the case where each of the two half-shells is equipped with a cooling system R, there are two possible alternatives: - a first alternative where there are two central distributors / collectors fixed under the engine 105, with a central distributor / collector dedicated to each half-shell, itself equipped with a satellite distributor / collector.The two central and satellite distributors / collectors are as described above, and the central distributors / collectors are located under the engine 105 one after the other; - a second alternative where there are two satellite distributors / collectors as described above, with one satellite distributor / collector per half-shell, and a single central distributor / collector fixed under the engine 105, is intended to interface with each of the two satellite distributors / collectors in a manner identical to that described above. The central distributor / collector comprises secondary fluid inlets / outlets on a first and a second lateral face, opposite one another and each extending along the X axis.

Claims

1.

2.

3. Claims Propulsion assembly of an aircraft comprising: - an engine (105); - two half-shells (111) arranged on either side of a longitudinal median plane (V) of the engine (105), where each half-shell (111) comprises a high bifurcation (109a) extended by a semi-cylindrical part (110), each half-shell (111) being intended to be articulated to a mast (102) at its high bifurcation (109a) and is capable of being movable between a closed position in which the half-shell (111) is tightened around the engine (105) with its semi-cylindrical part (113) partially surrounding the engine (105) and an open position in which the half-shell (111) is spaced from the engine (105); - a fluid circuit (C); - at least one half-shell (111) being equipped with a cooling circuit (R) associated with the fluid circuit (C);characterized in that it comprises a removable hydraulic junction (120) between the fluid circuit (C) and the cooling circuit (R), the removable hydraulic junction (120) comprising at least two quick connectors (E, S), where each of the quick connectors (E, S) comprises a pair of male / female elements (M, F) configured to fit axially into one another, with one element of the couple fixed to the half-cylindrical part (113) of the half-shell (111) and the other element of the couple secured to the engine (105).; Propulsion assembly (100) according to claim 1, characterized in that each of the male (M) or female (F) elements of a quick coupling (E,S) is in the form of an elongated and hollow body and in that the body of the male element (M) comprises a relief (Ml) and the body of the female element (F) is pierced with an opening (O) for fitting the male element (M) into the female element (F), and comprises locking means disengageable by an operator, and intended to cooperate with the relief (Ml) of the male element (M) to retain the male element (M) fitted into the female element (F) after insertion of the male element (M) into the female element (F).Propulsion assembly (100) according to claim 2, characterized in that the female connectors (F) are all arranged in a fluid distributor / collector (121), called central distributor / collector, hydraulically connected to the fluid circuit (C) and fixed to the engine (105) and in that the male connectors (M) are all arranged in one. fluid distributor / collector (122), called satellite distributor / collector, hydraulically connected to the cooling circuit (R) and fixed to the circular part (111) of the half-shell (111).

4. Propulsion assembly (100) according to claim 3, characterized in that the central distributor / collector (121) takes the form of a machined block of parallelepiped shape comprising a face, called contact face (121c), on which are arranged the openings (0) of the female elements (F) of the quick couplings (E, S), the female elements (F) being integrally arranged in the block and having their fitting axes (A) orthogonal to said contact face (121c).

5. Propulsion assembly (100) according to claim 4, characterized in that the central distributor / collector (121) comprises a disengaging mechanism (123) operable by an operator to disengage the locking means of the female elements (F).

6. Propulsion assembly (100) according to claim 3, characterized in that the satellite distributor / collector (122) takes the form of a machined block of parallelepiped shape comprising a face, called contact face (122c) outside of which the male elements (M) of the quick connectors (E, S) project.

7. Propulsion assembly (100) according to claim 3, characterized in that the satellite distributor / collector (122) comprises first centering means (140) and the central distributor / collector (121) comprises second centering means (141), the first and second centering means being intended to cooperate with each other when the half-shell (111) passes from the open position to the closed position.

8. Aircraft comprising a wing (101) to which is fixed a mast (102) to which is mounted a propulsion unit according to one of claims 1 to 7 using a mast 102, each half-shell being mounted articulated to the mast (102 at its upper bifurcation (109a) so as to pivot between said two positions.

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