THERMAL ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM

Abstract

THERMAL ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM The invention relates to a thermal assembly comprising: - a heat exchanger (11) comprising a central matrix (400) comprising first assembly means (710), an inlet module (200) for a first fluid in the central matrix (400) and an outlet module (300) for the first fluid outside the central matrix (400), and - a support (100) comprising a base (102) fixed to a propulsion system and rails (120) secured to the base (102) and comprising second assembly means (720) cooperating with said first assembly means (710) to form a sliding connection. With such an assembly, it is possible to simply and quickly assemble the central matrix to the support by simply sliding the central matrix into the support. This makes the assembly and disassembly operations of the central matrix, and more generally of the heat exchanger, easier. Fig. 3

Description

Title of the invention: THERMAL ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM Technical field

[0001] The present invention relates to a thermal assembly for a propulsion system of an aircraft, as well as to an aircraft comprising a propulsion system and such a thermal assembly coupled to the propulsion system. STATE OF THE PRIOR ART

[0002] Typically, for an aircraft, a heat exchanger, for example of the air-oil type, is implemented to cool the oil of a propulsion system of the aircraft with incoming fresh air. For example, according to a particular configuration, the incoming fresh air may be taken from the secondary flow of the turbine of the propulsion system.

[0003] As illustrated in [Fig.2], an air-oil thermal assembly 9 according to the prior art comprises a heat exchanger 90 comprising a matrix 92 allowing heat exchange mainly by conduction and convection between the oil of the propulsion system which circulates in the matrix 92 and fresh air, an air inlet 91 allowing efficient entry of fresh air into the matrix 92 and an air outlet 93 which allows air to be evacuated from the matrix 92.

[0004] Such a thermal assembly 9 is assembled using hooks 94 and bolts on the casing of the propulsion system (not shown). The hooks 94 directly connect the inlet 91, the die 92 and the outlet 93 to the casing of the propulsion system. Between the inlet 91, the die 92 and the outlet 93, bolted flanges ensure the clamping and sealing of the elements together. Although the present solution is effective for cooling the oil of the propulsion system, a disadvantage of such an assembly of the thermal assembly lies in the fact that when the replacement of an element 91, 92, 93, in particular of the die 92, is necessary, the hooks 94 must be disassembled and these disassembly and reassembly operations are time-consuming and therefore expensive.

[0005] There is therefore a need to provide a new solution making it possible to facilitate the assembly of the elements of the thermal assembly while ensuring good sealing between these elements. Statement of the invention

[0006] An object of the present invention is to provide a thermal assembly for a propulsion system of an aircraft which allows easy mounting and dismounting of a heat exchanger to be fixed to the propulsion system of the aircraft.

[0007] For this purpose, a thermal assembly is proposed for a propulsion system of an aircraft, said thermal assembly comprising:

[0008] - a heat exchanger comprising a central matrix comprising first assembly means, an inlet module configured to bring a first fluid into the central matrix and an outlet module configured to discharge the first fluid from the central matrix, wherein said central matrix is in fluid connection respectively with said inlet module and said outlet module, and

[0009] - a support comprising a base intended to be fixed to the propulsion system and rails secured to the base and comprising second assembly means cooperating with said first assembly means to form a sliding connection.

[0010] With such an assembly, it is possible to simply and quickly assemble the central die to the support by simply sliding the central die into the support.

[0011] Thus, the operations of assembly and disassembly of the central matrix, and more generally of the heat exchanger, are facilitated.

[0012] According to a particular aspect, said rails comprise third assembly means and said input module comprises fourth assembly means and / or said output module comprises fifth assembly means. Said third assembly means of said rails cooperate with the fourth assembly means and / or with the fifth assembly means to form sliding connections.

[0013] According to another particular aspect, said second assembly means and, when they exist, said third assembly means of said rails comprise a groove or a rib. Said first assembly means, and, when they exist, the fourth assembly means and the fifth assembly means comprise respectively, a rib received in said groove or a groove receiving said rib.

[0014] According to yet another particular aspect, the thermal assembly comprises first sealing means arranged between said first means of assembly of said central matrix and said second means of assembly of the rails, and when they exist, between said third means of assembly, and the fourth means of assembly or the fifth means of assembly.

[0015] According to a particular aspect, said central matrix comprises first stops and second stops. For each first stop, said input module comprises a first counter-stop which abuts against said first stop, and, for each second stop, said output module comprises a second counter-stop which abuts against said second stop.

[0016] According to another particular aspect, the thermal assembly comprises second sealing means arranged between each stop and the associated counter-stop.

[0017] According to yet another particular aspect, the thermal assembly comprises first fixing means which ensure the fixing of said input module to rails of said support and second fixing means which ensure the fixing of said output module to rails of said support.

[0018] According to a particular aspect, said rails extend generally perpendicular to said base.

[0019] According to another particular aspect, said rails extend generally parallel to said base.

[0020] The invention also provides an aircraft comprising a propulsion system and a thermal assembly as described previously, where the base is fixed to the propulsion system. Brief description of the drawings

[0021] The above-mentioned features of the invention, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made in relation to the attached drawings, among which:

[0022] [Fig-1] is a side view of an aircraft according to the invention;

[0023] [Fig.2] is a perspective view of a thermal assembly according to the state of the technique;

[0024] [Fig.3] is an exploded and perspective view illustrating a thermal assembly according to one embodiment of the invention;

[0025] [Fig.4] is a perspective view illustrating a thermal assembly in phase assembly with a main support according to the embodiment of [Fig.3];

[0026] [Fig.5] is a top view schematically illustrating means of assembly of the thermal assembly of [Fig.3];

[0027] [Fig.6] is a side view schematically illustrating sealing means implemented between the modules of the heat exchanger of the assembly of [Fig.3]; and

[0028] [Fig.7] is an exploded and perspective view illustrating a thermal assembly according to a variant of the embodiment of the invention of [Fig.3].

[0029] DETAILED DESCRIPTION OF AN EMBODIMENT

[0030] [Fig.l] shows an aircraft 1 which comprises a propulsion system 12, for example of the turbojet or turboprop type. The propulsion system 12 is linked to a wing 14 of the aircraft 1 via a reactor mast 16.

[0031] The aircraft 1 also comprises a thermal assembly 10 according to the invention which is coupled to the propulsion system 12. Figs. 3 and 4 show the thermal assembly 10 according to one embodiment of the invention and [Fig.7] shows a variant of the rea- lization of the invention.

[0032] The thermal assembly 10 comprises a heat exchanger 11 secured to a support 100 fixed to the propulsion system 12.

[0033] In the following description, the terms relating to a position are taken with reference to an aircraft in normal flight position, that is to say as it is shown in [Fig.l] and the "front" and "rear" positions are taken with respect to the front and rear of the propulsion system 12 and with respect to the direction of advance F of the aircraft 1 when the propulsion system 12 is operating.

[0034] In the following description, and by convention, we call X the longitudinal direction of the propulsion system which is horizontal when the aircraft is on the ground, we call Y the transverse direction which is horizontal when the aircraft is on the ground, and Z the vertical direction which is vertical when the aircraft is on the ground, these three directions X, Y and Z being orthogonal to each other.

[0035] The heat exchanger 11 and the support 100 here have a vertical median plane XZ.

[0036] The thermal assembly 10 comprises a heat exchanger 11 crossed by a first fluid which has the function of cooling or heating a second fluid circulating in the heat exchanger 11. In this example, the second fluid consists of a fluid circulating in the propulsion system 12, and in particular oil. It is understood, however, that other fluids may, in addition to or as a substitute for the fluid circulating in the propulsion system 12, circulate in the heat exchanger 11 to be cooled or heated.

[0037] The heat exchanger 11 comprises a central matrix 400 comprising first assembly means 710, an inlet module 200 configured to cause the first fluid, called the exchange fluid, to enter the central matrix 400 and an outlet module 300 configured to evacuate the first fluid from the central matrix 400.

[0038] The central matrix 400 allows thermal exchanges, in other words heat exchanges, between the second fluid and the first fluid (for example air, and in particular fresh air generally taken from the secondary flow of the turbine of the propulsion system 12). The thermal exchanges within the central matrix 400 are carried out mainly by conduction and convection.

[0039] The central matrix 400 is in fluid connection respectively with the inlet module 200 and the outlet module 300 to ensure the circulation, without leakage, of the first fluid successively through the inlet module 200, the central matrix 400 and the outlet module 300 of the heat exchanger 11. The heat exchanger 11, and more precisely the central matrix 400, is further in fluid communication with the circuit of the second fluid. In this example, the matrix 400 is in fluid communication with the fluid circuit of the propulsion system 12 by means of a first connector 411 through which the second fluid enters the heat exchanger 11 and a second connector 412 through which the second fluid leaves the heat exchanger 11 after the heat exchanges have taken place in the central matrix 400. For example, the first 411 and second 412 connectors are quick connect / disconnect type connectors.

[0040] In particular in order to limit the length of the conduits for transporting the second fluid, such a heat exchanger 11 is preferably fixed to a casing of the propulsion system 12. To do this, the thermal assembly 11 comprises a support 100 comprising a base 102 intended to be fixed to the propulsion system 12 and rails 120 secured to the base 102. The rails 120 comprise second assembly means 720 cooperating with the first assembly means 710 to form a sliding connection in an assembly direction which is here parallel to the vertical direction Z.

[0041] The thermal assembly 10 according to the invention therefore allows simple and rapid assembly of the central matrix 400 to the support 100 fixed to the propulsion system 12. More particularly, the central matrix 400 can be fixed to the support 100 by simply sliding the central matrix 400 into the support 100, thanks to the first 710 and second 720 assembly means forming a sliding connection.

[0042] Thus, the operations of mounting and, where appropriate, replacing the central matrix 400 of the heat exchanger 11 are facilitated. The present solution therefore makes it possible to refrain from dismantling / removing the entire heat exchanger 11 from the propulsion system 12 since the support 100 can remain fixed to the propulsion system 12, which ensures ease of use and a significant saving of time.

[0043] In the illustrated example, the support 100 comprises coupling means 122 of the support 100 to the propulsion system 12. The coupling means 122 are here in the form of protrusions projecting from the base 102 towards the propulsion system 12. More precisely, the base 102 extends here in a plane generally parallel to the horizontal plane XY. The protrusions 122 extend here in a direction generally perpendicular to the plane of the base 102, that is to say in a direction generally parallel to the vertical direction Z. Each protrusion 122 has a hole allowing the passage of a fixing rod, such as a screw or a rivet, cooperating with the casing of the propulsion system 12, for example. Thus, the support 100 is fixed to the propulsion system 12 by its base 102.In this example, the base 102 has a quadrilateral shape and protrusions 122 are arranged at each corner of the base 102 to ensure optimal coupling of the support 100 to the propulsion system 12 of the aircraft 1. The coupling means 122 are preferably located on the edges of the base 102 in order to optimize their accessibility.

[0044] According to a particular aspect, the rails 120 comprise third means assembly means 730. In addition, the input module 200 comprises fourth assembly means 740. In addition, or as a substitute, the output module 300 may also comprise fifth assembly means 750. Thus, when they exist, the third assembly means 730 of the rails 120 cooperate with the fourth assembly means 740 and / or the fifth assembly means 750, to form sliding connections according to the assembly direction.

[0045] In this way, the thermal assembly 10 according to the invention allows simple and rapid assembly of the input 200 and output 300 modules on the support 100. Indirectly, the assembly means 710, 720, 730, 740 and 750 together allow the modules 200 and 300 to be assembled to the central matrix 400 via the support 100. These assembly means 710, 720, 730, 740 and 750 therefore make it possible to facilitate the operations of assembling the thermal assembly 10 and, where appropriate, to facilitate the operations of replacing one or more of the modules of the heat exchanger 11.

[0046] Such a thermal assembly 10 is furthermore modular and allows, if necessary, the input 200 and output 300 modules to be interchanged depending on the configuration and positioning of the propulsion system 12, in particular. This also allows, if necessary, the input 200 and output 300 modules to be replaced by modules of different shapes, adapted to the constraints and configuration of the propulsion system 12, in particular.

[0047] In this example, the input module 200 and the output module 300 both comprise assembly means, respectively fourth assembly means 740 and fifth assembly means 750. It is understood, however, that one or other of the input modules 200 or output modules 300 could not implement such assembly means.

[0048] According to a particular aspect, the second assembly means 720 and, when they exist, the third assembly means 730 of the rails 120 comprise a groove or a rib. Correspondingly, the first assembly means 710 of the central matrix 400, and, when they exist, the fourth assembly means 740 and the fifth assembly means 750 of the input 200 and output 300 modules comprise, respectively, a rib received in the groove or a groove receiving the rib.

[0049] In the example of [Fig. 5] illustrating from above a rail 120 before the central die 400 and the input module 200 are mounted, the second assembly means 720 and the third assembly means 730 carried by the rails 120 comprise a groove. The first assembly means 710 of the central die 400 and the fourth assembly means 740 of the input module 200 each comprise a rib received in the groove of the second 720 and third 730 corresponding assembly means. Although the output module 300 is not illustrated in this figure, it is understood that the fifth assembly means 750 of the output module 300, when they exist, may also comprise a rib received in the groove of the corresponding third assembly means 730 carried by the rail 120 of the support 100.

[0050] Such assembly means allow simple, rapid and reliable assembly of the input 200 and output 300 modules as well as the central matrix 400 with the support 100. Indeed, it is sufficient to slide, that is to say to move in translation in the assembly direction, the modules 200 and 300 as well as the central matrix 400 in the rails 120 of the support 100 to fix them to the latter.

[0051] Such a thermal assembly 11 is also easily modular since it allows, if necessary, the addition of intermediate modules or input 200 and output 300 modules of different shapes, for example on the rails of the support 100.

[0052] In the example illustrated here, the grooves and the ribs have a dovetail shape so as to ensure optimal guidance of the modules 200, 300 and the central matrix 400 in the rails 120. In addition, such a groove and rib shape makes it possible to hold the modules 200, 300 and the central matrix 400 in the rails 120. It is understood, however, that other shapes, such as a T shape for example, are conceivable without departing from the general principle of the invention.

[0053] Referring to the orientation of [Fig.5], the central die 400 is slid into the support 100 in the assembly direction parallel to the vertical direction Z, towards the base 102 of the support. The same applies to the input module 200 (illustrated) and the output module 300 (not illustrated). As indicated previously, the dovetail shape implemented here also makes it possible to hold the modules 200, 300 and the central die 400 in the rails 120. Indeed, the shape of the grooves and ribs prevents movement of the central die 400 and the input 200 and output 300 modules in the longitudinal direction X.

[0054] According to a particular aspect, the thermal assembly 11 optionally comprises first sealing means 810, 820 arranged between the first assembly means 710 of the central matrix 400 and the second assembly means 720 of the rails 120, and when they exist, between the third assembly means 730 and the fourth assembly means 740 or the fifth assembly means 750.

[0055] In this way, the first sealing means 810, 820 make it possible to ensure sealing between the central matrix 400 and the support 100. The first sealing means also make it possible to ensure sealing between the support 100 and the input module 200 and / or the output module 300. Thus, the risks of leakage of the first fluid are avoided so as to optimize the performance of the assembly. thermal 11.

[0056] As illustrated in the example of [Fig. 5], the first sealing means 810, 820 are in the form of sealing teeth, for example made of rubber, which extend generally perpendicular to the longitudinal axis of the grooves and ribs. The sealing teeth of the rails 120 extend towards the central die 400 and the input 200 and output 300 modules while the sealing teeth of the central die 400 and the input 200 and output 300 modules extend towards the rails 120.

[0057] Preferably, each groove has a sealing tooth and each groove has two sealing teeth (or vice versa) spaced apart from each other and between which the sealing tooth of the groove is received. In this way, the sealing teeth form a labyrinth preventing the fluid from passing through the junction between the rails 120 and the modules of the heat exchanger 11 to ensure optimal sealing.

[0058] The sealing teeth therefore make it possible to ensure the sealing of the junction between the rails 120 and the central matrix 400 and between the rails 120 and the input 200 and output 300 modules.

[0059] The implementation of rubber sealing teeth also makes it possible to reduce vibrations between the heat exchanger 11 and the support 100 and between the modules 200, 300 and 400 of the heat exchanger 11.

[0060] According to a particular aspect, the central die 400 comprises first stops 760a and second stops 760b. For each first stop 760a, the input module 200 comprises a first counter-stop 770s, 770i which abuts against the first stop 760a of the central die 400. In the same way, for each second stop 760b, the output module 300 comprises a second counter-stop 780s, 780i which abuts against the second stop 760b of the central die 400.

[0061] Thus, the positioning of the input 200 and output 300 modules against the central matrix 400 is simple and rapid. In addition, the input 200 and output 300 modules are thus held in position relative to the central matrix 400.

[0062] More specifically, and as illustrated in [Fig. 6], the first stops 760a and the second stops 760b of said central die 400 comprise a rim or a recess. In this example, the central die 400 comprises a rim for the stops 760a and 760b located in the upper part of the central die 400 and a recess for the stops 760a and 760b located in the lower part of the central die 400.

[0063] Correspondingly, the input module 200 comprises a first counter-stop 770s in the form of a recess located in the upper part of the input module 200 and which abuts against the first stop 760a in the form of a rim. The module input module 200 further comprises a first counter-stop 770i in the form of a rim located in the lower part of the input module 200 and which abuts against the first stop 760a in the form of a recess.

[0064] Similarly, the output module 300 comprises a second counter-stop 780s in the form of a recess located in the upper part of the output module 300 and which abuts against the first stop 760a in the form of a rim. The output module 300 further comprises a second counter-stop 780i in the form of a rim located in the lower part of the output module 300 and which abuts against the first stop 760a in the form of a recess.

[0065] Thus, and as illustrated, the first 760a and second 760b stops come into abutment against the first counter-stops 770i and 770s and the second counter-stops 780i and 780s to prevent movement of the input 200 and output 300 modules here in the vertical direction Z.

[0066] To assemble the heat exchanger 11 to the support 100, it is possible to first assemble the inlet 200 and outlet 300 modules to the support 100 by moving the latter towards the base 102 of the support 100. The movement of the inlet 200 and outlet 300 modules is carried out parallel to the assembly direction, here parallel to a direction opposite to the vertical direction Z, so that the third assembly means 730 cooperate with the fourth 740 and fifth 750 assembly means. The central die 400 can then be assembled to the support 100 by moving the central die 400 towards the base 102 of the support 100 parallel to the assembly direction, here parallel to a direction opposite to the vertical direction Z, so that the first assembly means 710 cooperate with the second assembly means 720.

[0067] According to a particular aspect, the thermal assembly 10 optionally comprises second sealing means 830 arranged between each stop 760a, 760b and the associated counter-stop 770s, 770i and 780s, 780i.

[0068] More specifically, the second sealing means 830 are in the form of a seal disposed against the first stops 760a and 760b. The seal extends generally over the entire length L of the first stops 760a, 760b of the central die 400. The seal is therefore disposed respectively between the central die 400 and the input module 200 and between the central die 400 and the output module 300.

[0069] Such second sealing means 830 therefore make it possible to ensure the sealing of the junction between the central matrix 400 and the input 200 and output 300 modules.

[0070] The implementation of this sealing joint, for example made of rubber, also makes it possible to reduce vibrations between the modules 200, 300 and 400 of the heat exchanger 11.

[0071] According to another aspect, the thermal assembly 11 comprises first fixing means 800a which ensure the fixing of the input module 200 to rails 120 of the support 100 and second fixing means 800b which ensure the fixing of the output module 300 to rails of the main support 100.

[0072] Such fixing means make it possible to immobilize the input 200 and output 300 modules relative to the rails 120 of the support 100. More particularly, these fixing means 800a, 800b prevent any movement of the modules 200 and 300 in the X, Y and Z directions.

[0073] For example, the first 800a and second 800b fastening means are of the mechanical latch type (known as “aircraft latch” in English), notably used for locking hoods.

[0074] According to a particular aspect, the rails 120 extend generally perpendicular to the base 102.

[0075] Thus, the heat exchanger 11 is secured to the support 100 by translational movement of the heat exchanger 11 in the rails 120. This translational movement is carried out in the example illustrated in Figs. 3 and 4, in a direction parallel and opposite to the vertical direction Z. In other words, the insertion and removal of the heat exchanger 11 in the support 100 are carried out transversely to the base 102, which means that the insertion and removal of the heat exchanger 11 in the support 100 are carried out in a direction transverse to the longitudinal direction X of the propulsion system 12, and more generally in a radial direction relative to the propulsion system 12.

[0076] In an alternative embodiment shown in [Fig.7], the rails 120 extend generally parallel to the base 102. In this case, the rails 120 are in the form of a “C” whose lower base of the “C” is fixed to the base 102 of the support 100. In addition, the base of the “C” extends generally parallel to the base 102.

[0077] In this example, the first 800a and second 800b fixing means are arranged on the upright of the “C” extending parallel to the vertical axis Z. However, it is easily understood that it is possible to arrange the first 800a and second 800b fixing means differently, in particular depending on the positioning of the thermal assembly 10 on the propulsion system 12 and / or the configuration of the thermal assembly 10. For example, the first 800a and second 800b fixing means can be arranged on the upright of the “C” carrying the rails 120.

[0078] As previously, the heat exchanger 11 is secured to the support 100 by translational movement of the heat exchanger 11 in the rails 120. As illustrated in [Fig.7], the translational movement of the heat exchanger 11 is carried out in this example in a direction parallel to the transverse direction ho Y-direction, and more generally in an ortho-radial direction relative to the propulsion system 12.

[0079] Thus, the thermal assembly 10 according to the invention can be adapted to all configurations of the propulsion system 12 so as to meet all the constraints which could be encountered during the installation of the thermal assembly 10.

Claims

Claims

1. Thermal assembly (10) for a propulsion system (12) of an aircraft (1), said thermal assembly (10) comprising: - a heat exchanger (11) comprising a central matrix (400) comprising first assembly means (710), an inlet module (200) configured to bring a first fluid into the central matrix (400) and an outlet module (300) configured to evacuate the first fluid out of the central matrix (400), where said central matrix (400) is in fluidic connection respectively with said inlet module (200) and said outlet module (300), and - a support (100) comprising a base (102) intended to be fixed to the propulsion system (12) and rails (120) integral with the base (102) and comprising second assembly means (720) cooperating with said first assembly means (710) to form a connection slide.

2. Thermal assembly (10) according to claim 1, characterized in that said rails (120) comprise third assembly means (730), and in that said input module (200) comprises fourth assembly means (740) and / or said output module (300) comprises fifth assembly means (750), where said third assembly means (730) of said rails (120) cooperate with the fourth assembly means (740) and / or with the fifth assembly means (750) to form sliding connections.

3. Thermal assembly (10) according to one of claims 1 or 2, characterized in that said second assembly means (720) and, when they exist, said third assembly means (730) of said rails (120) comprise a groove or a rib, and in that said first assembly means (710), and, when they exist, the fourth assembly means (740) and the fifth assembly means (750) comprise respectively, a rib received in said groove or a groove receiving said rib.

4. Thermal assembly (10) according to one of claims 1 to 3, characterized in that it comprises first sealing means (810, 820) arranged between said first assembly means (710) of said central matrix (400) and said second assembly means (720) of the rails (120), and when they exist, between said third assembly means (730), and the fourth assembly means (740) or the fifth assembly means (750).

5. Thermal assembly (10) according to any one of claims 1 to 4, characterized in that said central matrix (400) comprises first stops (760a) and second stops (760b), in that, for each first stop (760a), said input module (200) comprises a first counter-stop (770s, 770i) which abuts against said first stop (760a), and in that, for each second stop (760b), said output module (300) comprises a second counter-stop (780s, 780i) which abuts against said second stop (760b).

6. Thermal assembly (10) according to claim 5, characterized in that it comprises second sealing means (830) arranged between each stop (760a, 760b) and the associated counter-stop (770s, 770i, 780s, 780i).

7. Thermal assembly (10) according to any one of claims 1 to 6, characterized in that it comprises first fixing means (800a) which ensure the fixing of said input module (200) to rails (120) of said support (100) and second fixing means (800b) which ensure the fixing of said output module (300) to rails (120) of said support (100).

8. Thermal assembly (10) according to any one of claims 1 to 7, characterized in that said rails (120) extend generally perpendicular to said base (102).

9. Thermal assembly (10) according to any one of claims 1 to 7, characterized in that said rails (120) extend generally parallel to said base (102).

10. An aircraft (1) comprising a propulsion system (12) and a thermal assembly (10) according to any one of claims 1 to 9, wherein the base (102) is fixed to the propulsion system (12).

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