Improved surface heat exchanger for an aircraft nacelle

Abstract

The invention relates to a surface heat exchanger (20), in particular for an aircraft nacelle, comprising a first metal sheet (2) and a second metal sheet (3) that are joined together, and a plurality of distribution channels (4) for a fluid which are arranged between the first metal sheet (2) and the second metal sheet (3), the exchanger further comprising fluid inlet (5) and outlet (6) interfaces. The exchanger further comprises fluid distribution means which define, for each distribution channel (4), a fluid flow section, each of the distribution channels (4) being connected to the inlet (5) and outlet (6) interfaces by such a flow section, the distribution channels (4) being distributed over the entire periphery of the inlet interface (5) and / or of the outlet interface (6).

Description

[0001] DESCRIPTION

[0002] TITLE: Improved surface heat exchanger for aircraft nacelle

[0003] Technical field

[0004] The present invention relates to the field of heat exchangers, in particular fairings of an aircraft engine, called "nacelle".

[0005] Previous techniques

[0006] Climate change is a major concern for many legislative and regulatory bodies around the world. Indeed, various restrictions on carbon emissions have been, are being, or will be adopted by various states. In particular, an ambitious standard applies to both new aircraft types and those already in operation, requiring the implementation of technological solutions to make them compliant with current regulations. Civil aviation has been mobilizing for several years now to make a contribution to the fight against climate change.

[0007] Technological research efforts have already made it possible to significantly improve the environmental performance of aircraft. The Applicant takes into consideration the impact factors in all phases of design and development to obtain less energy-intensive, more environmentally friendly aeronautical components and products whose integration and use in civil aviation have moderate environmental consequences with the aim of improving the energy efficiency of aircraft.

[0008] Consequently, the Applicant is constantly working to reduce its negative climate impact by using methods and operating virtuous development and manufacturing processes and minimizing greenhouse gas emissions to the minimum possible in order to reduce the environmental footprint of its activity.

[0009] This sustained research and development work focuses on new generations of aircraft engines, the lightening of aircraft, particularly through the materials used and lighter on-board equipment, the development of the use of electrical technologies to ensure propulsion, and, as an essential complement to technological progress, aeronautical biofuels.

[0010] Generally, an aircraft is powered by one or more propulsion units, each comprising an engine or turbojet housed in a tubular nacelle.

[0011] Generally speaking, the turbojet engine comprises a set of blades driven in rotation by a gas generator through a set of transmission means. The nacelle further comprises a lubricant distribution system to ensure good lubrication of these transmission means and to cool them. The lubricant is advantageously oil.

[0012] In order to cool the lubricant, the nacelle generally includes a cooling system comprising at least one heat exchanger. The cooling system is configured to circulate a fluid, for example the lubricant or a lubricant coolant.

[0013] There are air / lubricant heat exchangers that use air taken from a secondary stream of the compressor, but this results in additional pressure losses.

[0014] There are also finned heat exchangers attached to one of the nacelle walls to cool the fluid by circulating air in the secondary vein along the fins, but such a solution also generates significant aerodynamic losses.

[0015] These aerodynamic losses cause excess fuel consumption.

[0016] Fluid cooling systems are also known comprising a structural surface exchanger, that is to say an exchanger without fins and forming a generally smooth contact surface with the fluid circulating outside the exchanger, so as to avoid pressure losses caused by the presence of fins.

[0017] Such a structural surface exchanger generally comprises a first corrugated sheet and a second smooth sheet, assembled to form distribution channels which allow the flow of the cooling fluid from a distributor to a fluid collector.

[0018] Such an exchanger also comprises one or more stiffeners arranged between the first and second sheets and configured to ensure the structural strength of the exchanger.

[0019] However, the presence of the distributor and the collector increases the difficulty of shaping the exchanger because of the risk of tearing the sheet metal.

[0020] Apart from the manufacturing difficulties mentioned, current exchangers present risks of non-uniform distribution of flows between the different distribution channels, which degrades their thermal efficiency.

[0021] Furthermore, the stiffeners constitute singularities which disturb the flow and generate significant pressure losses.

[0022] Statement of the invention

[0023] The present invention therefore aims to reduce the pressure losses inherent in the inlet / outlet interfaces of a heat exchanger and thus to improve the thermal exchanges between respectively a fluid circulating inside and the air circulating outside said heat exchanger, while optimizing the structural strength of the heat exchanger.

[0024] The subject of the invention is a heat exchanger, in particular for an aircraft nacelle, comprising a first sheet and a second sheet assembled together and a plurality of fluid distribution channels arranged between the first sheet and the second sheet, the exchanger further comprising fluid inlet and outlet interfaces. The exchanger further comprises fluid distribution means defining for each distribution channel a fluid passage section, each of the distribution channels being connected to the inlet and outlet interfaces by such a passage section, said distribution channels being distributed over the entire periphery of the inlet interface and / or the outlet interface.

[0025] Such an exchanger improves the fluid flow between the interfaces and the distribution channels and makes it possible to control the distribution of flows between the distribution channels.

[0026] Advantageously, said passage section defined for each distribution channel has a value which depends on the length of said channel, so as to homogenize the flow rates of the distribution channels between them.

[0027] Such a definition of the passage section makes it possible to control the distribution of flows between the distribution channels.

[0028] For example, said plurality of channels comprises a first channel and a second channel with different cross-sections.

[0029] Advantageously, the exchanger comprises a plate fixed to the second sheet and provided with studs arranged between the second and first sheets, so as to ensure the fixing of the interfaces to the first and second sheets by means of fixing means cooperating with the studs.

[0030] Such fastening means are, for example, screws, bolts, rods or rivets.

[0031] Preferably, the studs comprise threaded holes and the distribution means comprise a sheet provided with holes aligned with said threaded holes of the studs.

[0032] For example, the fluid distribution means comprise vertical walls arranged between the pads and the distribution channels, the walls being of constant thickness and oriented radially relative to a longitudinal axis of the inlet interface and / or the outlet interface.

[0033] Such walls make it possible to improve the flow around the pads, thus reducing pressure losses inside the exchanger. For example, the distribution means comprise vertical walls of variable thickness arranged between the pads and the inlet and outlet ends of the distribution channels, so as to reduce turbulence due to the flow of the fluid.

[0034] Advantageously, the means for distributing said fluid comprise leading edges and trailing edges formed by circular arcs, the convexity of the arcs being directed towards a center of the plate.

[0035] According to another characteristic, the plate is provided with throttling members intended to be placed in the inlet ends and / or in the outlet ends of the distribution channels, so as to create a reduction in the useful section of the channels at the location of the throttling members.

[0036] According to another aspect, the invention relates to a turbomachine nacelle comprising at least one heat exchanger as described above.

[0037] Brief description of the drawings

[0038] Other aims, characteristics and advantages of the invention will appear on reading the following description, given solely by way of non-limiting example, and made with reference to the appended drawings in which:

[0039] [Fig 1] is a schematic view of a surface heat exchanger according to one embodiment of the invention;

[0040] [Fig 2] is a partial sectional detail view of the exchanger of Figure 1;

[0041] [Fig 3] and [Fig 4] are respectively a partial sectional view and a plan view of a connection to an inlet or outlet interface of an exchanger according to an embodiment of the invention;

[0042] [Fig 5] illustrates a plan view of a connection to an inlet or outlet interface of an exchanger according to a second embodiment of the invention; [Fig 6] illustrates a plan view of a connection to an inlet or outlet interface of an exchanger according to a third embodiment of the invention;

[0043] [Fig 7] illustrates a plan view of a connection to an inlet or outlet interface of an exchanger according to a fourth embodiment of the invention;

[0044] [Fig 8] is a perspective view of a plate of an exchanger according to a fifth embodiment of the invention;

[0045] [Fig 9] is a partial sectional view of a throttle member of the plate of [Fig 8];

[0046] [Fig 10] is a plan view of the distribution means illustrating the principle of variation of section Sp for a channel as a function of the length of the channel; and

[0047] [Fig 11] is a schematic view of a nacelle equipped with a heat exchanger according to one of the embodiments of the invention.

[0048] Detailed description of at least one embodiment

[0049] With reference to the example illustrated in Figures 1 and 2, a heat exchanger 1 comprises a first skin or sheet 2 and a second skin or sheet 3.

[0050] The first sheet 2 comprises a plurality of corrugations 4c and the second sheet 3 is here flat.

[0051] The exchanger 1 comprises a plurality of distribution channels 4 each delimited by a corrugation 5 of the first corrugated sheet 2 and the second sheet 3 called smooth.

[0052] The exchanger 1 is a heat exchanger between a first fluid E1 and air E2. The fluid E1 is intended to circulate in the channels 4 and the air E2 is intended to circulate in contact with the second smooth sheet 3.

[0053] Each distribution channel 4 has a semicircular section. Alternatively, it could be provided that the section has any general shape.

[0054] As illustrated, the distribution channels 4 have a section of identical size between them. Alternatively, sections of different sizes could be provided between each of the channels.

[0055] The distribution channels 4 are connected respectively to an input interface 5 and to an output interface 6.

[0056] In other words, there is no collector and distributor located between channels 4 and respectively input 5 and output 6 interfaces.

[0057] In this description, the inlet and outlet are defined relative to the normal flow direction of the cooling fluid in the exchanger.

[0058] As illustrated in Figure 1, the inlet ends 4a of the distribution channels 4 are distributed uniformly, that is to say regularly, over the entire circumference of the inlet interface 5 and the outlet ends 4b of the distribution channels 4 are distributed uniformly over the entire circumference of the outlet interface 6.

[0059] The inlet ends 4a of the channels 4 and the outlet ends 4b of the channels 4 have a curved shape.

[0060] The inlet ends 4a and the outlet ends 4b are connected to each other by a rectilinear portion 4d.

[0061] In the embodiment illustrated in Figure 1, the exchanger 1 comprises an anteroposterior axis of symmetry Sl-Sl passing through the inlet interface 5 and the outlet interface 6 and a transverse axis of symmetry S2-S2 perpendicular to the axis SI -SI. The distribution channels 4 are arranged symmetrically with respect to the axis of symmetry Sl-Sl. The concavity of the inlet ends 4a and the outlet ends 4b of the channels 4 is directed towards the center of the exchanger 1 constituted by the intersection of the two axes of symmetry Sl-Sl and S2-S2.

[0062] Alternatively, it remains possible that the exchanger does not have an axis of symmetry.

[0063] The first and second sheets 2, 3 are assembled by a welding or brazing zone 8, 9 on either side of the corrugation 4c of the corrugated sheet 2. Said welding or brazing zone 8, 9 extends from the first sheet 2 to the second sheet 3 (figure 2).

[0064] Figure 3 is a partial sectional view of the connection of an input 5 or output 6 interface to the first 2 and second 3 sheets, according to the invention.

[0065] With reference to the example illustrated in Figures 3 and 4, the heat exchanger 1 comprises a plate 10 fixed to the second sheet 3, preferably by welding with beads 10a.

[0066] The plate 10 is provided with studs 11 arranged between the second 3 and the first 2 sheets and between the corrugations 4c of the first sheet 2. The studs 11 here have a cylindrical cross-section.

[0067] The connection is made with screws 12 each comprising a head 13 and a threaded rod 14.

[0068] The threaded rods 14 pass through a base 15 of the interface 5, 6 and the first sheet 2 and collaborate with corresponding threads provided on the studs 11, so as to tighten the base 15 and the first sheet 2 between the heads of the screws 12 and the studs 11.

[0069] The exchanger 1 comprises eight distribution channels 4 distributed over the entire perimeter of the inlet 5 or outlet 6 interface (figure 4). Alternatively, the heat exchanger 1 could comprise a different number of distribution channels 4, for example greater than or equal to three.

[0070] The heat exchanger 1 further comprises means 16 for distributing the fluid E1.

[0071] The flow of the fluid E l is schematically represented by the arrows connecting an interface 5, 6 and distribution channels 4. The direction of flow naturally depends on the type of interface. Thus, the direction of flow goes from an inlet interface 5 to distribution channels 4 and from distribution channels 4 to an outlet interface 6.

[0072] The distribution means 16 define for each distribution channel 4 a passage section Sp of the fluid E1, each channel 4 being connected to the inlet 5 and outlet 6 interfaces by such a passage section Sp. Preferably, the surface area of ​​the passage section Sp can be adjusted for each distribution channel 4. It thus becomes possible to be able to control the distribution of fluid flow between the different distribution channels.

[0073] The passage section Sp of a distribution channel 4 is the useful section allowing the flow of fluid F l towards or from this channel.

[0074] Preferably, the passage section Sp is parallel to an inlet or outlet cross-section S of the corresponding distribution channel 4, so as to reduce the pressure losses. Preferably, the section Sp is centered relative to the inlet or outlet cross-section S of the corresponding distribution channel 4, so as to reduce the pressure losses. For example, a section Sp is considered centered relative to a section S of a corresponding channel 4 when a ray which starts from the center C towards this channel 4 and which passes at an equal distance from two neighboring distribution means 16, also passes through the respective centers of the sections Sp and S.

[0075] For example, to homogenize the flow rates between the distribution channels 4, the passage section Sp corresponding to a given distribution channel depends on the length of said channel. The length of a distribution channel 4 is understood as the distance between the centers C corresponding to the inlet interface 5 and the outlet interface 6, measured on the curvilinear axis of the distribution channel. For example, the passage section Sp is proportional to the length of the channel, in particular when the distribution channels have an identical cross-section between them. Thus, in the case of channels C1 and C2 of identical cross-section, an enlarged passage section Spe and a reduced passage section Spr are associated respectively with the channel C1 having a greater length and with the channel C2 having a shorter length (figure 10).

[0076] The distribution means 16 comprise a sheet 16a provided with holes aligned with the threaded holes of the studs 11 of the plate 10. This alignment facilitates the positioning of the distribution means 16 relative to the plate 10 and allows the rods 14 of the screws 12 to pass through the sheet 16a to improve the fixing.

[0077] In the embodiment illustrated in Figures 3 and 4, the distribution means 16 of the fluid F1 comprise vertical walls 17 arranged between the pads 11 and the distribution channels 4. The walls 17 have a constant thickness e and are oriented radially relative to a longitudinal axis X of the interface 5, 6 which perpendicularly intersects the plate 10 at the center C.

[0078] Another embodiment is illustrated in Figure 5, in which the same elements bear the same references.

[0079] The embodiment illustrated in Figure 5 differs from the embodiment illustrated in Figures 3 and 4 only in that the distribution means 16 comprise vertical walls 18 of variable thickness. The walls 18 are arranged between the pads 11 and the inlet 4a and outlet 4b ends of the distribution channels 4, so as to reduce the turbulence due to the flow of fluid F1.

[0080] Figure 6 illustrates another embodiment which differs from the embodiment illustrated in Figure 5 only by the fact that the cross-section of each pad 11 comprises two opposite circular arcs 11a, 11b connected by two straight line segments, the circular arcs 11a, 11b being of different radii. Alternatively, it remains possible to replace the two circular arcs 11a, 11b with other curved shapes, in particular ellipses or parabolas.

[0081] The plots 1 1 can be identical to each other, but alternatively it is still possible that they are different.

[0082] Figure 7 illustrates another embodiment in which the distribution means 16 envelop the pads 11, so that the fluid F1 does not come into contact with the pads 11.

[0083] The distribution means 16 comprise leading edges and trailing edges formed by circular arcs 19, the convexity of the arcs being directed towards the center C of the plate 10.

[0084] Alternatively, it remains possible to replace the circular arcs 19 with other curved shapes, in particular ellipses or parabolas.

[0085] Sheet 16a has not been shown in Figures 5 to 7 in order not to overload the drawings and to facilitate understanding.

[0086] Figure 8 is a perspective view of a plate 10 and fluid distribution means 16 comprising vertical walls 17 of constant thickness. In the example illustrated in Figure 8, the plate 10 comprises throttling members 21 intended to be placed in the inlet ends 4a and / or in the outlet ends 4b, so as to create a reduction in the fluid passage section. The size of the members 21 can vary from one channel 4 to another. In the example illustrated in Figure 8, the plate 10 is provided with throttling members 21 whose size varies between a minimum size 22 corresponding to the longest channel and a maximum size 23 corresponding to the shortest channel. The variable relative size of the throttling members 21 makes it possible to adjust the distribution of the fluid flow rates between the different distribution channels 4.

[0087] Figure 9 is a sectional view of a throttle member 21 arranged in a distribution channel 4. The presence of the throttle member 21 reduces the useful section Su of the channel 4. It should be noted that when the cross-section of the throttle member increases, the useful section Su decreases accordingly. In the example illustrated in Figure 9, the throttle member 21 has a cross-section in the shape of a truncated semicircle. Alternatively, it remains possible for the cross-section of the throttle member 21 to have a different shape, in particular a semicircle or polygon shape.

[0088] The heat exchanger 1 described above is advantageously intended to equip a nacelle of a turbomachine or aircraft engine visible in figure 11.

[0089] In Figure 11 is shown very schematically an axial section of a turbomachine 50, of general longitudinal axis X-X', for example of the double-flow and double-spool turbojet type comprising a fan 51, coupled to a gas turbine engine comprising a low-pressure compressor 52, a high-pressure compressor 53, an annular combustion chamber 54, a high-pressure turbine 55 and a low-pressure turbine 56.

[0090] The rotors of the high-pressure compressor and the high-pressure turbine are connected by a high-pressure (HP) shaft (not shown) and form with it a high-pressure body. The rotors of the low-pressure compressor and the low-pressure turbine are connected by a low-pressure (LP) shaft (not shown) and form with it a low-pressure body. The HP and LP shafts extend along a longitudinal axis X-X' of the turbomachine 50.

[0091] The fan shaft is rotatably connected to the LP shaft directly or indirectly.

[0092] It will be noted that the invention is not limited to such a turbomachine structure and could be applied to a turbomachine of different structure, for example to a turbomachine of the double-flow turbojet type, in which the low-pressure compressor acts as a fan.

[0093] The nacelle 40 of the turbomachine comprises a housing 41 for the turbomachine 50 and has a tubular structure comprising an external fairing 42 defining an external aerodynamic surface and an internal fairing 43 defining an internal aerodynamic flow surface through the turbomachine 50 and in particular the fan 51.

[0094] The external and internal fairings 42, 43 are connected upstream by an air inlet lip wall 44 forming a leading edge of the nacelle 40.

[0095] The external and internal fairings 42, 43 delimit an external structure usually comprising a fixed part and a mobile part (not shown), such as for example thrust reversal means.

[0096] The nacelle 40 further comprises a fixed internal structure 45, called “inner fixed structure”, with the acronym “IFS” in English terms. The fixed internal structure 45 is concentric with the external structure, at a downstream section and surrounds the core of the turbojet engine 50 downstream of the fan 51.

[0097] These external and internal structures define an annular flow vein, called secondary vein VS, aimed at channeling a flow of cold air, called secondary, circulating outside the turbomachine 50.

[0098] Downstream of the blower 51, the main air flow F is separated by the fixed internal structure 45 of the nacelle, here acting as a separation member, into a primary air flow FP and a secondary air flow FS.

[0099] The primary air flow FP travels through an internal passage or primary vein VP when entering the low pressure compressor 52, for example at the level of inlet guide vanes 57 or “inlet guide vanes”, acronym IGV in English terms.

[0100] The secondary air flow FS passes through an external annular passage or secondary vein VS, for example towards outlet guide vanes 58 or "outlet guide vanes", acronym OGV in English terms, then towards the outlet of the turbomachine.

[0101] The nacelle 40 is equipped with a heat exchanger 1, fixed here on the internal surface of the internal fairing 43. The heat exchanger 1 is fixed in the secondary vein VS, so that the air flow circulating in the secondary vein VS is in contact with the second sheet 3 of the heat exchanger 1.

[0102] Alternatively, it could be provided that the heat exchanger 1 is fixed to the external surface of the internal structure 45 of the nacelle 40.

[0103] According to another variant, the heat exchanger 1 can be fixed on the external surface of the external fairing 42 of the nacelle 40. Thus, the heat exchanger 1 can be used to cool a fluid from the secondary flow FS or from the outside air.

[0104] According to yet another variant, the heat exchanger 1 could be fixed on the internal surface of the internal structure 45, that is to say in the fluid flow of the primary vein VP.

[0105] Thus, heat exchanger 1 can be used to heat a fluid from the primary flow FP.

Claims

CLAIMS 1. Heat exchanger (1), in particular for an aircraft nacelle, comprising a first sheet (2) and a second sheet (3) assembled together and a plurality of distribution channels (4) for a fluid (Fl) arranged between the first sheet (2) and the second sheet (3), the exchanger further comprising inlet (5) and outlet (6) interfaces for said fluid, characterized in that said exchanger further comprises means (16) for distributing said fluid (Fl) defining for each distribution channel (4) a passage section (Sp) of said fluid (Fl), each of the distribution channels (4) being connected to the inlet (5) and outlet (6) interfaces by such a passage section (Sp), said distribution channels (4) being distributed over the entire periphery of the inlet interface (5) and / or the outlet interface (6).

2. Exchanger (1) according to claim 1, in which said passage section (Sp) defined for each distribution channel (4) has a value which depends on the length of said channel (4), so as to homogenize the flow rates of the distribution channels (4) between them.

3. Exchanger (1) according to claim 1 or 2, wherein said plurality of channels (4) comprises a first channel and a second channel with different cross-sections (S).

4. Exchanger (1) according to any one of the preceding claims, comprising a plate (10) fixed to the second sheet (3) and provided with studs (11) arranged between the second and first sheets, so as to ensure the fixing of said interfaces (5, 6) to the first (2) and second (3) sheets by means of fixing means (12) cooperating with said studs (11).

5. Exchanger (1) according to claim 4, in which said studs (11) comprise threaded holes and said distribution means (16) comprise a sheet metal (16a) provided with holes aligned with said threaded holes of the studs (11).

6. Exchanger (1) according to claim 4 or 5, in which the means (16) for distributing said fluid comprise vertical walls (17) arranged between the pads and the distribution channels, said walls being of constant thickness and oriented radially by relative to a longitudinal axis (X) of said input interface (5) and / or said output interface (6).

7. Exchanger (1) according to claim 4 or 5, wherein said distribution means (16) comprise vertical walls (18) of variable thickness arranged between said pads (11) and inlet (4a) and outlet (4b) ends of the distribution channels (4), so as to reduce the turbulence due to the flow of the fluid (F1).

8. Exchanger (1) according to claim 7, in which the means (16) for distributing said fluid (F1) comprise leading edges and trailing edges constituted by circular arcs (19), the convexity of said arcs (19) being directed towards a center (C) of the plate (10).

9. Exchanger (1) according to any one of claims 4 to 8, in which said plate (20) is provided with throttling members (21) intended to be placed in inlet ends (4a) and / or in outlet ends (4b) of the distribution channels (4), so as to create a reduction in the useful section of the channels (4) at the location of the throttling members (21).

10. Turbomachine nacelle (40) comprising at least one heat exchanger (1) according to any one of the preceding claims.

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