FR3142457A1 - PROPULSIVE ASSEMBLY FOR AN AIRCRAFT - Google Patents

Abstract

Propulsion assembly (10) for an aircraft, this propulsion assembly (10) comprising: - a reactor mast (12), - a turbomachine (14) fixed to the reactor mast (12) and comprising a fluidic system (18), - a cowling (16) which comprises at least one panel (20) which is articulated by hinges (25) on the reactor mast (12), this 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 fluidic circuit (26') is connected to the fluidic system (18) by at least one of said hinges (25) which forms a rotating fluidic connection (30, 30 '). Figure for abstract: Figure 5

Description

PROPULSIVE ASSEMBLY FOR AN AIRCRAFT Technical field of the invention

The present invention relates to a propulsion assembly for an aircraft.

Technical background

The state of the art includes document FR-A1-3 094 750.

There illustrates a propulsion assembly 10 for an aircraft.

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.

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.

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.

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.

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.

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 there .

At least part of the cowling 16 can internally define an annular flow path for an air flow around the turbomachine 14, such as a flow path for a secondary flow or the like. In this case, 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.

In the current technique, these connection means are flexible and flexible pipes 28, as illustrated in . 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. shows two distinct states of deformation of the same pipe 28 for two different positions of a panel 20.

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. 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 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 comply 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.

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:

- a reactor mast extending along a first axis,

- 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,

- a cowling which extends along and around the second axis, the cowling comprising at least one panel 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 exchanger of heat which comprises a fluidic circuit connected to said fluidic system,

characterized in that the fluidic circuit is connected to the fluidic system by at least one of said hinges which forms a rotating fluidic connection, this hinge comprising a hinge axis mounted inside a hinge body, the axis and the body hinge being movable relative to each other with respect to the third axis,

said hinge pin comprising at least one internal fluid passage and an external cylindrical surface onto which opens at least one orifice in fluid communication with this internal passage,

said hinge body extending around said outer cylindrical surface and having an internal passage which is configured to be placed in fluid communication with said port when the panel is in the closed position.

Advantageously, the internal passage of the hinge body is configured to be fluidly isolated from said orifice when the panel is in the open position.

The invention thus proposes to connect the fluidic circuit of the panel exchanger to the fluidic system of the turbomachine, via at least one of the articulation hinges of the panel, this hinge thus forming a rotating fluidic connection. A first specificity of this rotating fluid connection 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 effort suffered by the connection to the extent that it follows the movement of the panel during its movements. Another specificity of the rotating link is that it is integrated into a hinge and therefore does not require separate elements. The fluid connection between the fluid circuit and the fluid system depends on the position of the panel around its articulation axis. When the panel is closed, the fluidic circuit is connected to the fluidic system by the rotating connection which is “open”. When the panel is open, the fluidic circuit is connected to the fluidic system by the rotating connection which is advantageously "closed", thus preventing in particular fluid leaks at the level of the rotating connection.

• l’axe de charnière est monté mobile à l’intérieur du corps de charnière, l’axe de charnière étant solidaire du panneau, et le corps de charnière étant solidaire du mât réacteur,
• une vanne est montée entre le système fluidique et la liaison fluidique tournante,
• le circuit fluidique est raccordé au système fluidique par deux liaisons tournantes, une première de ces liaisons tournantes étant reliée à une entrée dudit circuit fluidique, et une seconde de ces liaisons tournantes étant reliée à une sortie fluidique dudit circuit,
• les première et seconde liaisons tournantes sont formées par deux charnières distinctes et sont à distance l’une de l’autre,
• les première et seconde liaisons tournantes sont formées par une même charnière et sont jumelées,
• l’axe de charnière est relié au circuit fluidique par au moins une conduite rigide,
• le corps de charnière est relié au système fluidique par au moins une conduite rigide,

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:

• the hinge pin is mounted movably inside the hinge body, the hinge pin being secured to the panel, and the hinge body being secured to the reactor mast,
• a valve is mounted between the fluidic system and the rotating fluidic connection,
• the fluidic circuit is connected to the fluidic system by two rotating connections, a first of these rotating connections being connected to an input of said fluidic circuit, and a second of these rotating connections being connected to a fluidic outlet of said circuit,
• the first and second rotating connections are formed by two distinct hinges and are spaced apart from each other,
• the first and second rotating connections are formed by the same hinge and are paired,
• the hinge pin is connected to the fluid circuit by at least one rigid pipe,
• the hinge body is connected to the fluid system by at least one rigid pipe,

-- said plane in which the first and second axes extend is vertical or inclined relative to the vertical;

-- said fluid circuit is a lubrication circuit or a coolant circuit;

-- 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 upper longitudinal edge of the or each panel is fixed by the hinges;

-- 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-cylindrical shape.

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:

there is a partial schematic perspective view of a propulsion assembly for an aircraft,

there 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,

there is a half schematic view in axial section of a propulsion assembly for an aircraft, and illustrates a first embodiment of the invention,

Figures 4a and 4b are partial schematic views in cross section of the propulsion assembly of the , and show two distinct positions of a cowling panel of this propulsion assembly,

Figures 5a and 5b are respectively a schematic perspective view with partial tearing of the rotating fluid connection of the propulsion assembly of the , and a schematic cross-sectional view of this connection, and illustrate this fluid connection in the open state,

Figures 6a and 6b are respectively a schematic perspective view with partial tearing of the rotating fluid connection of the propulsion assembly of the , and a schematic cross-sectional view of this connection, and illustrate this fluid connection in the closed state,

there is a half schematic view in axial section of a propulsion assembly for an aircraft, and illustrates a second embodiment of the invention, and

there is a half schematic view in axial section of a propulsion assembly for an aircraft, and illustrates a third embodiment of the invention.

Figures 9a and 9b are respectively a schematic perspective view with partial tearing of the rotating fluid connection of the propulsion assembly of the , and a schematic cross-sectional view of this connection, and illustrate this fluid connection in the open state, and

Figures 10a and 10b are respectively a schematic perspective view with partial tearing of the rotating fluid connection of the propulsion assembly of the , and a schematic cross-sectional view of this connection, and illustrate this fluid connection in the closed state.

Detailed description of the invention

Figures 1 and 2 have already been described in the above.

There illustrates a first embodiment of a propulsion assembly 10 according to the invention. This propulsion assembly 10 includes:

- a reactor mast 12,

- a turbomachine 14 comprising a fluid system 18 in particular its bearings and rotating elements, and

- a cowling 16 which can surround the turbomachine 14, as in the example shown.

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.

The fluidic system 18 is for example a fluidic system but could alternatively be a cooling system.

The cowling 16 comprises two panels 20 of generally semi-circular shape which extend on either side of the plane P passing through the respective axes A, B of the reactor mast 12 and the turbomachine 14.

In the example shown, the panels 20 comprise upper longitudinal edges 22 which are fixed to the reactor mast 12 by 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.

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 25a, an intermediate hinge 25b and a downstream hinge 25c. 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 which can be parallel to the axis B for example, from a closed position in which its lower edge (not visible) is substantially at the 6 o'clock position, up to a position open in which its lower edge is away from the 6 o'clock position. One of the panels 20 in its closed position is illustrated in Figure 4a, and this same panel 20 in its open position is illustrated in Figure 4b. The angular movement (arrow F) between the two positions is for example greater than 30° around axis C (figures 4a-4b).

Each of the panels 20 carries at least one surface heat exchanger 26 which comprises a fluidic or fluid circuit 26' connected to the fluidic system 18, and an exchange surface which is exposed to a flow of cooling gas.

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.

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 a 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 circuit 26' is for example a fluid circuit but could alternatively be a coolant circuit.

The means of fluidic connection of the fluidic circuit 26' of each exchanger 26 to the fluidic system 18 comprise at least one rotating fluidic connection 30 which is formed by at least one of the hinges 25 and which can therefore be considered as integrated into at least one of these hinges 25.

In the example shown, the fluid circuit 26' comprises a fluid inlet 26a and a fluid outlet 26b. The fluidic system 18 includes a fluidic inlet 18a and a fluidic outlet 18b.

The fluid inlet 26a of the circuit 26' is connected to the fluid outlet 18b of the system 18 by a first rotating connection 30 which is centered on the pivot axis C of the panel 20 which carries the exchanger 26 with this circuit 26'. This rotating connection 30 is integrated into the hinge 25b.

The fluidic outlet 26b of the circuit 26' is connected to the fluidic inlet 18b of the system 18 by a second rotating connection 30' which is also centered on the pivoting axis C of the panel 20. This rotating connection 30' is integrated into the hinge 25c.

In the example shown, each of the hinges 25b and 25c therefore forms a rotating connection 30 within the meaning of the invention.

Each of these hinges 25b, 25c includes a hinge pin 32 mounted inside a hinge body 34, as illustrated in the upper part of the hinge. .

The axis and the hinge body 32, 34 are movable relative to each other with respect to the axis C. In the example shown, the hinge axis 32 is mounted movable at the inside the hinge body 34, the hinge pin being secured to the panel 20, and the hinge body 34 being secured to the reactor mast 12.

The hinge pin 32 comprises at least one internal fluid passage 36 and an external cylindrical surface 38 onto which opens at least one orifice 40 in fluid communication with this internal passage 36.

In the example shown, we see that the hinge pin 32 comprises a threaded end crossed by the internal passage 36. This threaded end facilitates the connection of this passage.

The hinge body 34 extends around the cylindrical surface 38 and has an internal passage 42 which is configured to be placed in fluid communication with the orifice 40 when the panel 20 is in the closed position (Figures 4a and 5a-5b) and to be fluidly isolated from this orifice 40 when the panel is in the open position (Figures 4b and 6a-6b).

The passage 42 may include an outlet at the external periphery of the hinge body 34, for connection of this passage.

The first rotating connection 30 can be connected by rigid pipes respectively to the inlet 26a and the outlet 18b. A valve 33 is advantageously inserted between the connection 30 and the outlet 18b, therefore just upstream of the connection 30. This valve 33 can also be centered on the axis C.

The second rotating connection 30' can be connected by rigid pipes, respectively to the outlet 26b and the inlet 18a. A valve 33 is advantageously inserted between the connection 30' and the inlet 18a, therefore just downstream of the connection 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 connection 30'.

In the present application, a rigid pipe means a pipe which is not deformable or which is not flexible. The pipe can have any shape and for example straight or bent. The drawings show schematic examples of shapes of this type of pipe.

The links 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 26' for example with a view to dismantling the exchanger 26 or the panel 20 during a maintenance operation.

The alternative embodiment of the differs from the previous embodiment in particular in that the two rotating connections 30, 30' are here next to each other and no longer at a distance from each other.

For this, the two connections 30, 30' have a hinge pin 32 in common and a hinge body 34 in common.

The hinge pin 32 comprises two internal fluid passages 36a, 36b and an external cylindrical surface 38 onto which opens at least two orifices 40, 40' in fluid communication respectively with these internal passages 36a, 36b.

A first of the passages 36a extends over approximately half of the hinge pin 36 and opens at a first end of this hinge pin. This first passage 36a is in fluid communication with the orifice 40.

The hinge pin 32 comprises a first threaded end crossed by the internal passage 36a.

A second of the passages 36b extends over approximately the other half of the hinge pin 36 and opens at a second opposite end of this hinge pin. This second passage 36b is in fluid communication with the orifice 40’.

The hinge pin 32 comprises a second threaded end crossed by the internal passage 36b.

The orifices 40, 40' are spaced axially from each other and are here aligned axially along the axis C.

The hinge body 34 extends around the cylindrical surface 38 and has two independent internal passages 42, 42' which are configured to be placed in fluid communication respectively with the orifices 40, 40' when the panel 20 is in the closed position and to be fluidly isolated from these orifices 40, 40' when the panel 20 is in the open position.

The passages 42, 42' can each include an outlet 42a at the external periphery of the hinge body 34, with a view to connecting this passage.

The rotating connections 30, 30' are here integrated into the hinge 25b.

A valve 33 is inserted between the connection 30, and in particular its passage 36a (via its threaded end), and the outlet 18b therefore just upstream of the connection 30. This valve 33 can also be centered on the axis vs.

Another valve 33 is inserted between the connection 30', and in particular the end of) its passage 36b (via its threaded end), and the inlet 18a therefore just downstream of the connection 30'. This valve 33 can also be centered on axis C.

The valves 33 can be connected by rigid pipes, respectively to the outlet 18b and the inlet 18a. Passages 42, 42' are connected by other rigid pipes to inlet 26a and outlet 26b of conduit 26'.

The alternative embodiment of Figures 8, 9a-9b and 10a-10b is close to the previous embodiment insofar as the two rotating connections 30, 30' are joined to each other. The two connections 30, 30' have a hinge pin 32 in common and a hinge body 34 in common.

The hinge pin 32 comprises two internal fluid passages 36a, 36b and an external cylindrical surface 38 onto which opens at least two orifices 40, 40' in fluid communication respectively with these internal passages 36a, 36b.

A first of the passages 36a extends along the hinge axis 36 and opens at a first end of this hinge axis. This first passage 36a is in fluid communication with the orifice 40.

A second of the passages 36b also extends along the hinge axis 36 and opens at the same first end of the hinge axis 36. This second passage 36b is in fluid communication with the orifice 40'.

The orifices 40, 40' are spaced axially from one another and are here aligned axially along the axis C. These orifices 40, 40' have elongated shapes in the circumferential direction in the example shown.

The hinge body 34 extends around the cylindrical surface 38 and has two independent internal passages 42, 42' which are configured to be placed in fluid communication respectively with the orifices 40, 40' when the panel 20 is in the closed position and to be fluidly isolated from these orifices 40, 40' when the panel 20 is in the open position.

The rotating connections 30, 30' are here integrated into the hinge 25b.

The internal passages 42 are configured to be placed in fluid communication with the orifices 40, 40' when the panel 20 is in the closed position (Figures 9a-9b) and to be fluidically isolated from these orifices 40, 40' when the panel 20 is in the open position (figures 10a-10b).

A double valve 33 is inserted between the two passages 42, 42' of the connections 30, 30', on the one hand, and the outlet 18b and the inlet 18a, on the other hand. This valve 33 can also be centered on axis C.

Rigid pipes connect the valve 33 to the fluid system 18, and the connections 30, 30' to the circuit 26'.

Claims (9)

Propulsion assembly (10) for an aircraft, this propulsion assembly (10) comprising:
- a reactor mast (12) extending along a first axis (A),
- 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),
- 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 (B), 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 of the turbomachine (14) to an open position in which it is spaced from the turbomachine (14), said at least one panel (20) carrying at least one surface heat exchanger (26) which comprises a fluidic circuit (26 ') connected to said fluidic system (18),
characterized in that the fluidic circuit (26') is connected to the fluidic system (18) by at least one of said hinges (25) which forms a rotating fluidic connection (30, 30'), this hinge (25) comprising an axis of hinge (32) mounted inside a hinge body (34), the pin and the hinge body (32, 34) being movable relative to each other with respect to the third axis (C),
said hinge pin (32) comprising at least one internal fluid passage (36, 36a, 36b) and an external cylindrical surface (38) onto which opens at least one orifice (40, 40') in fluid communication with this internal passage ( 36, 36a, 36b),
said hinge body (34) extending around said outer cylindrical surface (38) and having an internal passage (42, 42') which is configured to be placed in fluid communication with said port (40, 40') when the panel (20) is in the closed position and to be fluidly isolated from this orifice (40, 40') when the panel (20) is in the open position. Propulsion assembly (10) according to claim 1, wherein said internal passage (42, 42') of the hinge body (34) is configured to be fluidly isolated from said orifice (40, 40') when the panel (20) is in position. open position. Propulsion assembly (10) according to claim 1 or 2, in which the hinge pin (32) is movably mounted inside the hinge body (34), the hinge pin (32) being integral with the panel ( 20), and the hinge body (34) being integral with the reactor mast (36). Propulsion assembly (10) according to one of the preceding claims, in which a valve (33) is mounted between the fluidic system (18) and the rotating fluidic connection (30, 30'). Propulsion assembly (10) according to one of the preceding claims, in which the fluidic circuit (26') is connected to the fluidic system (18) by two rotating connections (30, 30'), a first of these rotating connections (30) being connected to an inlet (26a) of said fluidic circuit (26), and a second of these rotating connections (30') being connected to a fluidic outlet (26b) of said circuit (26'). Propulsion assembly (10) according to claim 5, in which the first and second rotating connections (30, 30') are formed by two distinct hinges (25) and are spaced apart from each other. Propulsion assembly (10) according to claim 5, in which the first and second rotating connections (30, 30') are formed by the same hinge (25) and are twinned. Propulsion assembly (10) according to one of the preceding claims, in which the hinge pin (32) is connected to the fluid circuit (26') by at least one rigid pipe. Propulsion assembly (10) according to one of the preceding claims, in which the hinge body (34) is connected to the fluid system (18) by at least one rigid conduit.