Surface heat exchanger comprising pressure drop reducing means and aircraft nacelle provided with such a heat exchanger

Abstract

The present invention relates to a heat exchanger (20), particularly for a heat exchanger for an aircraft nacelle, the heat exchanger comprising a first skin (21) and a second skin (22) joined together, and a plurality of channels (23) disposed between the first skin (21) and the second skin (22) for distributing hydraulic fluid (F1), wherein the heat exchanger further comprises a first hydraulic interface (24) and a second hydraulic interface (25) for the hydraulic fluid. The heat exchanger (20) further comprises at least one pressure drop reduction member (40) extending axially toward the first hydraulic interface (24) or the second hydraulic interface (25), wherein the pressure drop reduction member (40) has a generally conical cross-section.

Description

Technical Field

[0001] This invention relates to the field of heat exchangers, and more particularly to the field of heat exchangers for the fairing of an aircraft engine, also known as a "nacelle". Background Technology

[0002] Climate change is a major concern for many legislative and regulatory bodies around the world. Indeed, countries have already taken, are taking, or will take various measures to limit carbon emissions. In particular, an ambitious standard applies to both new and existing aircraft, requiring the implementation of technological solutions to bring them into compliance with current regulations. For many years, the civil aviation industry has been committed to contributing to addressing climate change.

[0003] The technological research has enabled significant improvements in the environmental performance of aircraft. The applicant has considered the influencing factors at all design and development stages to obtain more energy-efficient and environmentally friendly aerospace components and products, and the introduction and use of these components and products in civil aviation will have a moderate environmental impact to improve aircraft energy efficiency.

[0004] Therefore, the applicant has been committed to reducing its negative impact on the climate and thus reducing the environmental footprint of its activities by utilizing benign development and manufacturing methods and processes that minimize greenhouse gas emissions.

[0005] This ongoing research and development effort encompasses next-generation aircraft engines, aircraft lightweighting (particularly through the use of materials and lighter avionics), the development and utilization of electrical technologies to ensure propulsion, and aviation biofuels as an indispensable complement to technological advancements.

[0006] Typically, an aircraft is propelled by one or more propulsion units, each of which includes an engine or turbojet engine housed in a tubular nacelle.

[0007] A nacelle typically comprises a tubular body including an upstream section, a mid-section, and a downstream section. The upstream section includes an air inlet located upstream of the turbojet engine. The mid-section is configured to surround the turbojet engine's fan. The downstream section is configured to house a thrust reverser and surround the turbojet engine's combustion chamber. Typically, the nacelle includes an injection nozzle located downstream of the downstream section, with the nozzle's outlet located downstream of the turbojet engine.

[0008] In addition, the nacelle typically consists of an external structure and an inner fixed structure (IFS). The inner fixed structure is concentric with the external structure in the downstream section and surrounds the core of the turbojet engine downstream of the fan.

[0009] These external and internal structures define an annular flow channel, known as a secondary duct, designed to guide the flow of cold air circulating outside the turbojet engine, known as a secondary flow.

[0010] The external structure includes an external fairing that defines the external aerodynamic surface and an internal fairing that defines the internal aerodynamic surface. The internal and external fairings are connected upstream by a leading edge wall that forms the air inlet lip.

[0011] Typically, a turbojet engine comprises a set of blades that are rotated by a gas generator via a set of transmission mechanisms. The nacelle also includes a system for distributing lubricant to ensure proper lubrication and cooling of these transmission mechanisms. Advantageously, the lubricant is oil.

[0012] To cool the lubricant, the nacelle typically includes a cooling system, which comprises at least one heat exchanger. The cooling system is configured to circulate a fluid, such as a lubricant or a coolant that will cool the lubricant.

[0013] There are air / lubricant heat exchangers that use air drawn from the nacelle's auxiliary duct (referred to as cold flow) or from one of the compressor's first stages. The intake and recirculation of air through these heat exchangers disrupts airflow and results in undesirable additional load losses (referred to as drag).

[0014] Finned heat exchangers attached to one wall of a defining secondary duct of a nacelle are also known. Fluids are cooled by an airflow flowing along the fins on the surface of the exchanger within the secondary duct.

[0015] This solution also results in significant aerodynamic losses, leading to a significant loss in fuel consumption.

[0016] Fluid cooling systems including structured surface exchangers are also known, which are finless exchangers that form a smooth, integral contact surface with the fluid circulating outside the exchanger, thereby avoiding pressure drop due to the presence of fins.

[0017] exist Figure 1 In the example shown, the finless surface exchanger 10 includes a corrugated first skin 11 and a nominally smooth second skin 12, which are joined to form a distribution channel 13 that allows fluid F (e.g., a heat transfer fluid or a lubricant) to flow from an inlet port 14 to a fluid outlet port 15.

[0018] The inlet hydraulic port 14 and the outlet hydraulic port 15 are calibrated to distribute the same flow rate in each distribution channel 13 as well as possible.

[0019] However, these hydraulic interfaces cause significant pressure drops, which need to be reduced.

[0020] Current heat exchangers are at risk of uneven flow distribution between different distribution channels, which degrades the thermal efficiency of the heat exchanger.

[0021] In fact, such as Figure 1 It can be seen that when the fluid arrives at the supply distribution channel 13 perpendicular to the smooth skin 12 or the aerodynamic skin, the fluid F undergoes a 90° change of direction, resulting in a significant pressure drop.

[0022] To maximize the thermal-hydraulic performance of a surface heat exchanger, the pressure drop must be as low as possible and the flow distribution between channels must be nearly identical.

[0023] These pressure drops must also be minimized in order to limit the size, weight, and cost of the onboard circulating pump required to overcome them.

[0024] Regarding surface heat exchangers with rectangular cross-section channels, it is known that pressure drop can be balanced by increasing or decreasing the width of these channels, thereby reducing flow dispersion.

[0025] However, in the case of surface exchangers with channels having a semi-circular cross-section, the channel design does not allow for easy modification of the channel's cross-section.

[0026] The cooling system for the fluid needs to be improved, especially the surface heat exchanger. Summary of the Invention

[0027] Therefore, the purpose of this invention is to overcome the above-mentioned disadvantages.

[0028] The purpose of this invention is to reduce the inherent pressure drop at the inlet and / or outlet ports of a heat exchanger to promote uniform distribution of fluid flow in the distribution channels and thus improve heat exchange between the fluid circulating inside the heat exchanger and the air circulating outside the heat exchanger.

[0029] The object of the present invention is a heat exchanger, preferably a surface heat exchanger, particularly a heat exchanger for an aircraft nacelle, the heat exchanger comprising a first skin or wall and a second skin or wall assembled together, and a plurality of channels disposed between the first skin and the second skin for distributing hydraulic fluid.

[0030] The exchanger also includes a first hydraulic interface (e.g., an inlet hydraulic interface) and a second hydraulic interface (e.g., an outlet hydraulic interface).

[0031] The exchanger also includes at least one pressure drop reduction member extending axially toward the first hydraulic interface or the second hydraulic interface, the pressure drop reduction member having a generally conical cross section.

[0032] The pressure drop reduction component is an intermediate component that separates the hydraulic flow entering the inlet hydraulic interface and distributes it to each distribution channel of the exchanger.

[0033] In the outlet hydraulic interface, the pressure drop reduction component allows for the uniform collection of different hydraulic flows from the distribution channel.

[0034] The specific conical shape of the pressure drop reduction component allows for a reduction in pressure drop without reducing the flow of hydraulic fluid through the associated hydraulic interface.

[0035] As a result of the present invention, the planar transition between the associated hydraulic interface of the surface exchanger and the smooth second skin is softened by the extension of the pressure drop reduction member toward the associated hydraulic interface.

[0036] Furthermore, the heat exchange between the fluid circulating in the heat exchanger and the air circulating outside the heat exchanger is optimized, while improving the structural strength of the heat exchanger and reducing aerodynamic load losses.

[0037] Advantageously, the pressure drop reduction component extends axially at least partially in the first or second hydraulic interface, which improves the smoothness of the transition and thus better reduces the pressure drop.

[0038] Preferably, at least one of the first hydraulic interface and the second hydraulic interface forms an angle with the second skin, the angle being preferably greater than or equal to 60°, for example, equal to 90°.

[0039] Preferably, each of these distribution channels is directly connected to the inlet hydraulic port and the outlet hydraulic port.

[0040] These distribution channels extend within a single plane. In other words, no part of the distribution channel protrudes from either skin. This makes it possible to have a substantially flat exchanger.

[0041] For example, each of these distribution channels is directly connected to the first hydraulic interface and the second hydraulic interface, and these distribution channels are evenly distributed over the entire circumference of the associated hydraulic interfaces.

[0042] This allows for a larger number of channels, evenly distributed at the inlet or outlet, regardless of the number of channels. It also allows for limiting voltage drop by supplying each channel directly from the inlet interface.

[0043] "Surface heat exchanger" refers to a finless heat exchanger or a smooth heat exchanger, wherein the wall or skin of the defined pipe of the finless heat exchanger or smooth heat exchanger forms a heat exchange surface.

[0044] The fact that it does not have fins or other shapes designed to increase the contact surface between the flow and the exchanger allows for unobstructed airflow in the duct, and thus reduces aerodynamic load losses.

[0045] The first and second skins can be, for example, metal sheets.

[0046] "Metal sheet" refers to hot-rolled or cold-rolled flat steel products, which typically have a smooth surface or sometimes have protrusions. Therefore, metal sheet is made of metallic materials.

[0047] The distribution channel is configured to extend in a single plane between the first hydraulic interface and the second hydraulic interface.

[0048] "Distributed across the entire circumference of the hydraulic interfaces" means that some channels are connected to one of these hydraulic interfaces as follows: the first end extends in the opposite direction to the other of these hydraulic interfaces.

[0049] These ends extend from a main section, which is, for example, straight, extending to another hydraulic port among these hydraulic ports until the second end.

[0050] The second end can also extend in the opposite direction to one of these hydraulic interfaces.

[0051] For example, these channels are connected to the inlet hydraulic port via the inlet end and to the outlet hydraulic port via the outlet end.

[0052] For example, the inlet is connected to the outlet via a main section.

[0053] The inlet end of at least one channel extends in the opposite direction to the outlet hydraulic interface, and the outlet end of at least one channel extends in the opposite direction to the inlet hydraulic interface.

[0054] For example, the inlet hydraulic interface and the outlet hydraulic interface have circular cross-sections.

[0055] For example, the inlet hydraulic port and the outlet hydraulic port each include an outlet orifice extending in a plane perpendicular to the extension plane of the skin.

[0056] Advantageously, the thickness of each distribution channel is constant over the entire length of the corresponding channel.

[0057] For example, the distribution channels have the same cross-section as each other.

[0058] Alternatively, different cross-sections can be provided between the channels. For example, the longer distribution channels can be configured to have a larger cross-section in order to balance the flow rates between the distribution channels.

[0059] Advantageously, the pressure drop reduction component is an axisymmetric solid.

[0060] "Axisymmetric entity" means that the hydraulic flow of the pressure drop reduction component is repeatedly arranged in each specific area of ​​each distribution channel according to the number of distribution channels.

[0061] Preferably, the pressure drop reduction member includes: a base pointing towards a second skin on a side opposite to the associated hydraulic interface; and a conical hydraulic flow deflection portion extending from the base to a apex pointing towards the associated hydraulic interface on a side opposite to the second skin.

[0062] In a non-restrictive manner, the vertex is located at the center of the associated hydraulic interface.

[0063] The hydraulic flow deflection portion extends, for example, at least partially into the associated hydraulic interface.

[0064] Advantageously, the base of the pressure drop reduction component has a shape that is homogeneous or similar to that of the associated hydraulic interface, such as circular, elliptical, etc.

[0065] In all cases, it is important not to restrict the cross-section of the hydraulic flow path between the cylindrical inlet of the associated interface and the passage to the right of the hydraulic flow deflection section.

[0066] The circular shape of the base of the pressure-reducing component allows for stress-free attachment in the associated hydraulic interface.

[0067] According to one embodiment, the hydraulic flow deflection portion of the pressure drop reduction component includes a smooth outer surface.

[0068] According to another embodiment, the hydraulic flow deflection portion of the pressure drop reduction component includes an outer surface comprising a plurality of concave facets, which may or may not have curved surfaces, the concave facets extending from a base to a vertex and connecting to the vertex.

[0069] Each concave facet is preferably positioned opposite the associated distribution channel.

[0070] Therefore, the concave facets allow for the guidance of flow in each distribution channel, or help each incident hydraulic flow leave with minimal pressure drop.

[0071] According to another embodiment, the hydraulic flow deflection portion of the pressure drop reduction component includes an outer surface comprising a plurality of protrusions uniformly distributed on the circumference of a cone and a plurality of grooves or recesses evenly distributed alternately on the circumference of the cone, each protrusion extending from a base to a apex and connecting to the apex. Each groove preferably forms a flow path opposite to an associated distribution channel.

[0072] The grooves allow flow to be guided in each distribution channel, or help each incident hydraulic flow leave with minimal pressure drop.

[0073] "Protrusion" refers to the elongated, thin surface that has been extruded.

[0074] The protrusion has, for example, a curved surface.

[0075] Alternatively, the protrusion can be configured to have a non-curved surface.

[0076] Alternatively, the pressure drop reduction component can be configured as an axisymmetric entity with a conical overall shape formed by vertical triangular plates to separate the incident flow or guide the incoming flow.

[0077] According to one embodiment, the pressure drop reduction component is directly integrated into the second skin or the associated hydraulic interface.

[0078] "Direct integration" means that the pressure drop reduction component is attached to the second skin or associated intermediate hydraulic interface by any non-removable attachment method (such as welding, gluing, brazing, riveting) or any removable attachment method (such as threaded connection) without intermediate components, or that the pressure drop reduction component is integrally formed with the second skin or associated intermediate hydraulic interface.

[0079] According to one embodiment, the exchanger includes a plate attached to a second skin and provided with studs disposed between the second skin and a first skin, thereby ensuring that the interface is attached to the first and second skins via attachment means cooperating with the studs. The voltage drop reduction component is preferably integrated directly into the plate.

[0080] "Direct integration" means that the pressure drop reduction component is attached to the board by any non-removable attachment method (such as welding, gluing, brazing, riveting) or any removable attachment method (such as threaded connection) without any intermediate components, or the pressure drop reduction component is integrally formed with the board.

[0081] Therefore, force paths can be optimized to reduce total mass and mechanical load margins depending on the type of mechanical load, such as hydraulic, aerodynamic, and mechanical loads.

[0082] According to one embodiment, each of the first and second epidermis is flat.

[0083] Alternatively, each of the first and second skins is curved to ensure aerodynamic continuity with the rest of the nacelle.

[0084] Advantageously, the switch includes a plurality of spacers or spacer members disposed between the first skin and the second skin, with two adjacent spacers defining the distribution channel.

[0085] For example, the first skin and the second skin are joined together at the spacer by an assembly area (e.g., fusion welding or brazing) that extends from the first skin to the second skin.

[0086] According to one embodiment, the first epidermis includes a plurality of corrugations, each of which distributes channels free from the corrugations of the first epidermis and defined by the second epidermis.

[0087] For example, each distribution channel has a semi-circular cross-section.

[0088] Typically, the thickness of the first epidermis is between 0.6 mm and 3 mm, and the thickness of the second epidermis is between 0.6 mm and 4 mm.

[0089] The first and / or second skins are made of aluminum or an aluminum-containing alloy. This improves the lightness, formability, and heat exchange properties of these skins.

[0090] According to a second aspect, the present invention relates to a turbine engine nacelle comprising an external structure and an internal structure defining an annular secondary flow duct. The nacelle includes a housing for the turbine engine, the housing, together with the internal structure, defining an annular primary flow duct. The nacelle includes at least one heat exchanger as described above, which is either attached to the external structure and on the side of the secondary flow duct or on the outside of the external structure, or attached to the internal structure or an internal fairing and on the side of the secondary flow duct.

[0091] When the heat exchanger is attached to the internal shroud, the second skin of the heat exchanger comes into contact with the airflow circulating in the secondary duct.

[0092] When the heat exchanger is attached to the internal structure of the nacelle, the second skin of the heat exchanger comes into contact with the airflow circulating in the secondary duct.

[0093] Alternatively, when the heat exchanger is attached to the external structure of the nacelle, the second skin of the heat exchanger can be in contact with the external airflow.

[0094] Therefore, heat exchangers can be used to cool fluids from the side stream or outside air. Attached Figure Description

[0095] Referring to the accompanying drawings, further objects, features, and advantages of the invention will become apparent from the following description, provided only as non-limiting examples, in which: [ Figure 1 ] This is a schematic diagram of a cross-sectional view of a surface exchanger based on existing technology; [ Figure 2 ] This is a schematic diagram of a surface heat exchanger according to an embodiment of the present invention; [ Figure 3 ] The exchanger according to the invention is along Figure 2 Detailed partial section view of section III-III; [ Figure 4 ] The exchanger according to the invention is along Figure 2 Detailed partial section view of section IV-IV; [ Figure 5 ] yes Figure 4 A 3D diagram of the components that reduce the voltage drop of the exchanger; [ Figure 6 ] This is a perspective view of a pressure drop reduction component according to a second embodiment of the present invention; [ Figure 7 ] This is a perspective view of a pressure drop reduction component according to a third embodiment of the present invention; [ Figure 8 ] This is a partial cross-sectional view of a surface heat exchanger according to another embodiment of the present invention; [ Figure 9A ]、[ Figure 9B ] This is a view of a surface heat exchanger according to another embodiment of the present invention; [ Figure 10 ] This is a partial cross-sectional view of a surface heat exchanger according to another embodiment of the present invention; and [ Figure 11 ] This is a schematic diagram of a nacelle equipped with a heat exchanger according to an embodiment of the present invention. Detailed Implementation

[0096] In the following description, the terms "upstream" and "downstream" are defined relative to the direction of airflow in the turbine engine. The terms "inner" and "outer" are defined relative to the longitudinal axis of the turbine engine, with the term "inner" defining an element that is closer to said axis than an outer element.

[0097] refer to Figures 2 to 4 In the example shown, heat exchanger 20 includes a first skin 21 (e.g., a metal sheet) and a second skin 22 (e.g., a metal sheet).

[0098] The first skin 21 includes a plurality of corrugations 21a, which are formed, for example, by forming the first skin 21, and the second skin 22 is planar herein.

[0099] The exchanger 20 includes a plurality of distribution channels 23, each distribution channel being defined by a corrugation 21a of a corrugated first skin 21 and a nominally smooth second skin 22.

[0100] Each distribution channel 23 has a semi-circular cross-section. Alternatively, the cross-section can be configured to have any general shape.

[0101] As shown in the figure, the distribution channels 23 have the same cross-sectional size as each other.

[0102] Alternatively, different cross-sectional sizes can be provided between the channels.

[0103] For example, it can be configured that longer distribution channels have larger cross-sections in order to balance the flow rates between the distribution channels.

[0104] The distribution channel 23 is directly connected to the first hydraulic port 24 (e.g., the inlet hydraulic port) and the second hydraulic port 25 (e.g., the outlet hydraulic port), respectively.

[0105] In this specification, inlet and outlet are defined relative to the normal flow direction of the coolant in the exchanger.

[0106] like Figure 2 As shown, the inlet end 23a of the distribution channel 23 is evenly (that is, on average) distributed on the entire circumference of the inlet hydraulic interface 24, and the outlet end 23b of the distribution channel 23 is evenly distributed on the entire circumference of the outlet hydraulic interface 25.

[0107] "Distributed throughout the circumference" means that the inlet end 23a of at least one channel 23 extends in the opposite direction to the outlet hydraulic interface 25, and the outlet end 23b of at least one channel 23 extends in the opposite direction to the inlet hydraulic interface 24.

[0108] The inlet end 23a and the outlet end 23b of the channel 23 have curved shapes.

[0109] The inlet end 23a and the outlet end 23b of channel 23 are connected to each other through the main part 23c, which is straight.

[0110] exist Figure 2In the illustrated embodiment, the switch 20 includes a first front-to-back axis of symmetry S1-S1 passing through the inlet interface 24 and the outlet interface 25, and a lateral axis of symmetry S2-S2 perpendicular to the axis S1-S1. The distribution channel 23 is symmetrically arranged with respect to the axis of symmetry S1-S1.

[0111] The concave surfaces of the inlet end 23a and the outlet end 23b of channel 23 point toward the center of exchanger 20, which is formed by the intersection of two symmetrical axes S1-S1 and S2-S2.

[0112] Alternatively, the switch may also not have an axis of symmetry.

[0113] The distribution channel 23 is disposed in the same plane and does not protrude relative to the skins 21 and 22. Therefore, the channel does not occupy additional area in the total thickness of the switch.

[0114] "Thickness" refers to the dimension along the ZZ axis, which is perpendicular to the longitudinal axis of the switch's extension and the transverse axis of the switch.

[0115] The longitudinal axis is parallel to the S1-S1 axis, and the transverse axis is parallel to the S2-S2 axis.

[0116] exist Figure 2 In the example shown, hydraulic ports 24 and 25 are aligned with the first axis of symmetry S1-S1 in a non-restrictive manner.

[0117] Alternatively, the hydraulic ports 24 and 25 can be configured to align with another axis (e.g., a transverse axis).

[0118] Generally, the present invention is not limited to the shape of the distribution channel, which is configured to extend between the inlet hydraulic port 24 and the outlet hydraulic port 25 in a longitudinal direction.

[0119] The first skin 21 and the second skin 22 pass through the fusion welding area or brazing area 26, 27 on both sides of the corrugation 21a of the corrugated first skin 21. Figure 3 (See in the image) The welded or brazed areas 26 and 27 extend from the corrugated first skin 21 to the second skin 22.

[0120] Exchanger 20 is a heat exchanger between a first hydraulic fluid F1 and air F2. The hydraulic fluid F1 is designed to circulate in channel 23, and the air is designed to circulate in contact with a smooth second skin 22.

[0121] Typically, the thickness of the first skin 21 is between 0.6 mm and 3 mm, and the thickness of the second skin 22 is between 0.6 mm and 4 mm.

[0122] The first skin 21 and / or the second skin 22 are made of aluminum or an aluminum-containing alloy. This improves the brightness, heat exchange, and formability of these skins.

[0123] The exchanger 20 is, for example, sealed to withstand pressures up to 10 bar.

[0124] like Figure 2 As shown, in a non-limiting manner, switch 20 includes eight distribution channels 23.

[0125] Alternatively, the heat exchanger 20 may include a different number of distribution channels 23, such as three or more, or four or more.

[0126] like Figure 4 As shown, the hydraulic interface (here, the inlet hydraulic interface 24) is orthogonal to the nominally smooth second skin 22.

[0127] In general, the invention is particularly advantageous when at least one of these hydraulic interfaces forms an angle with the nominally smooth second skin 22, the angle being preferably greater than 60°, for example equal to 90°.

[0128] In the example shown, each hydraulic port 24, 25 forms an angle of 90° with the nominally smooth second skin 22 of the exchanger.

[0129] Figure 4 This is a partial cross-sectional view of the connection between the inlet interface 24 or outlet interface 25 and the first skin 21 and the second skin 22 according to the present invention.

[0130] like Figure 4 As shown, the inlet interface 24 and the outlet interface 25 have an extension axis Y, which here coincides with the vertical axis ZZ.

[0131] However, it can be configured such that the inlet interface 24 and / or the outlet interface 25 are along an extended axis Y that forms a non-zero angle with the vertical axis ZZ (i.e., intersects with the vertical axis ZZ).

[0132] refer to Figure 4 and Figure 5 In the example shown, the heat exchanger 20 includes a plate 30 attached to a second skin 22, preferably welded to the second skin by solder beads 30a.

[0133] Plate 30 includes a plurality of studs 31 protruding along an axis ZZ perpendicular to the extension plane of exchanger 20.

[0134] The anchor 31 is disposed between the second skin 22 and the first skin 21 and between the corrugations 21a of the first skin 21. The anchor 31 here has a cylindrical cross-section.

[0135] The connection between plate 30, first skin 21 and corresponding hydraulic interfaces 24, 25 is achieved by screws 32, each screw including head 33 and screw 34.

[0136] The screw 34 passes through the base 24a and the first skin 21 of the corresponding hydraulic ports 24 and 25, and engages with the corresponding thread (not shown) on the stud 31, thereby fastening the base 24a, 25a and the first skin 21 between the head of the screw 32 and the stud 31.

[0137] The flow of hydraulic fluid F is schematically shown by the arrow connecting hydraulic port 24 and distribution channel 23. Of course, the flow direction depends on the type of port. Therefore, the flow direction is from inlet port 24 to distribution channel 23, and from distribution channel 23 to outlet port 25.

[0138] like Figure 4 As shown, the heat exchanger 20 also includes a pressure drop reduction member 40, which extends axially in the inlet hydraulic interface 24 in part.

[0139] It can be configured that the heat exchanger 20 also includes a second pressure drop reduction member 40, which extends axially in part in the outlet hydraulic interface 25.

[0140] Typically, the heat exchanger 20 includes at least one pressure drop reduction member 40 extending axially toward the associated hydraulic ports 24, 25.

[0141] The pressure drop reduction component 40 is an intermediate component that separates the hydraulic flow entering the inlet hydraulic interface 24 and distributes it to each distribution channel 23 of the exchanger 20. In the outlet hydraulic interface 25, the pressure drop reduction component 40 allows for the uniform collection of the different hydraulic flows from the distribution channels 23.

[0142] As shown in the figure, the pressure drop reduction component 40 is axisymmetric, that is, the hydraulic flow is introduced into each specific area of ​​each distribution channel 23 and the arrangement is repeated according to the number of channels 23.

[0143] The pressure drop reduction component 40 has a shape adapted to the number of channels 23 to be supplied.

[0144] The pressure drop reduction member 40 includes: a base 41, which is circular in this case, pointing toward the second skin 22 on the side opposite to the associated hydraulic interfaces 24, 25; and a conical hydraulic flow deflection portion 42, which extends from the base 41 to the apex S and points toward the associated hydraulic interfaces 24, 25 on the side opposite to the second skin 22.

[0145] As shown in the figure, and in a non-restrictive manner, vertex S is located at the center of the associated hydraulic interfaces 24 and 25.

[0146] The hydraulic flow deflection section 42 extends at least partially into the associated hydraulic interfaces 24, 25.

[0147] Typically, the base 41 of the pressure drop reduction member 40 has a shape that is homogeneous or similar to that of the associated hydraulic interface, and may be circular, elliptical, etc.

[0148] The circular shape of the base 41 of the pressure drop reduction member 40 allows for stress-free attachment in the associated hydraulic interfaces 24, 25.

[0149] In geometry, an "axisymmetric solid" is generated by rotating a closed plane surface about an axis that lies in the same plane. This closed plane either has no points in common with the axis or only has points in common with the axis at the boundary of the closed plane.

[0150] A cone is a ruled surface defined by a line called the generatrix, which passes through a fixed point S called the vertex and a variable point moving along a curve called the guide curve. In an axisymmetric cone, the guide curve is centered at O ​​(…). Figure 4 A circle (visible in the image) lies in a plane perpendicular to SO. This cone is called a solid of revolution because it can be simply produced by rotating the generatrix about a vertical axis of rotation SZ passing through the vertex S.

[0151] The specific conical shape of the pressure drop reduction component 40 allows for the reduction of pressure drop without reducing the flow path of hydraulic fluid F into or out of the system.

[0152] exist Figure 4 and Figure 5 In the embodiment shown, the pressure drop reduction component 40 is directly integrated into the plate 30.

[0153] "Direct integration" means that the pressure reduction component 40 is fixed to the plate 30 by any non-removable attachment method (e.g., welding, gluing, brazing, riveting) or any removable attachment method (e.g., threaded connection) without any intermediate components, or the pressure reduction component 40 is integrally formed with the plate 30.

[0154] Therefore, force paths can be optimized to reduce total mass and mechanical load margins depending on the type of mechanical load, such as hydraulic, aerodynamic, and mechanical loads.

[0155] In this embodiment, the outer surface 42a of the conical hydraulic flow deflection portion 42 is smooth.

[0156] exist Figure 6In the illustrated embodiment (where the same elements have the same reference numerals), the outer surface 42a of the conical hydraulic flow deflection portion 42 includes a plurality of concave facets 42b, wherein these concave facets have curved surfaces.

[0157] Alternatively, the outer surface 42a of the conical hydraulic flow deflection portion 42 may include a plurality of non-curved concave surfaces 42b. The concave surfaces 42b extend from the base 41 to the vertex S and connect to the vertex S.

[0158] The concave facet 42b is designed to be positioned opposite the associated dispensing channel 23, and to allow flow in each dispensing channel 23 to be guided, or to help each incident hydraulic flow leave with minimal pressure drop.

[0159] exist Figure 7 In the illustrated embodiment (where the same elements have the same reference numerals), the outer surface 42a of the conical hydraulic flow deflection portion 42 includes a plurality of protrusions 42c regularly distributed on the circumference of the cone and a plurality of grooves 42d or recesses that are regularly distributed on the circumference of the cone in alternation with the protrusions 42c.

[0160] "Protrusion" refers to the elongated, thin surface that has been extruded.

[0161] Each protrusion 42c extends from the base 41 to the vertex S and connects to the vertex S.

[0162] Protrusion 42c has a curved surface here.

[0163] Alternatively, protrusion 42c can be configured to have a non-curved surface.

[0164] The grooves 42d form flow paths that are designed to be positioned opposite the associated distribution channels 23, and to allow flow in each distribution channel 23 to be guided, or to help each incident hydraulic flow leave with minimal pressure drop.

[0165] Alternatively, the pressure drop reduction member 40 may be configured as an axisymmetric entity having a generally conical shape formed by vertical triangular plates to separate the incident flow or guide the incoming flow.

[0166] exist Figure 8 In the illustrated embodiment (where the same elements have the same reference numerals), the pressure drop reduction member 40 is directly integrated into the smooth second skin 22.

[0167] "Direct integration" means that the pressure reduction component 40 is fixed to the second skin 22 by any non-removable attachment method (e.g., welding, gluing, brazing, riveting) or any removable attachment method (e.g., threaded connection) without any intermediate components, or the pressure reduction component 40 is integrally formed with the second skin 22.

[0168] exist Figure 8 In the example shown, the pressure drop reduction member 40 has a conical shape with a smooth outer surface 42a.

[0169] Alternatively, any form of pressure drop reduction component 40 may be provided, as referenced. Figure 6 and Figure 7 As stated above.

[0170] exist Figure 9A , Figure 9B and Figure 10 In the illustrated embodiment (where the same elements have the same reference numerals), the pressure drop reduction component 40 is directly integrated into the associated hydraulic interfaces 24, 25.

[0171] "Direct integration" means that the pressure drop reduction component 40 is secured to the associated hydraulic interfaces 24, 25 (in) without any intermediate components by any non-removable attachment method (e.g., welding, gluing, brazing, riveting) or any removable attachment method (e.g., threaded connection). Figure 10 In the example), or the pressure drop reduction component 40 is integrally formed with the hydraulic interfaces 24 and 25 (in Figure 9A and Figure 9B (See examples visible in the text).

[0172] exist Figure 9A and Figure 9B In the example shown, the pressure drop reduction member 40, which includes a conical hydraulic flow deflection portion 42, has a generally conical outer surface 42a. The conical hydraulic flow deflection portion 42 includes a plurality of protrusions 42c regularly distributed on the circumference of the cone and a plurality of grooves 42d or recesses that are regularly distributed on the circumference of the cone, alternating with the protrusions 42c.

[0173] Each protrusion 42c extends from the base 41 to the vertex S and connects to the vertex S.

[0174] Protrusion 42c has a curved surface here.

[0175] Alternatively, protrusion 42c can be configured to have a non-curved surface.

[0176] Alternatively, any form of pressure drop reduction component 40 may be provided, as referenced. Figure 5 and Figure 6 As stated above.

[0177] Advantageously, the aforementioned heat exchanger 20 is intended to be equipped with Figure 11 The visible turbine engine 50 or aircraft engine nacelle 60.

[0178] Figure 11An axial section of a turbine engine 50 is shown schematically, having an overall longitudinal axis X-X', for example, a dual-rotor turbofan engine type including a fan 51 coupled to a gas turbine engine. The gas turbine engine includes 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.

[0179] The rotors of the high-pressure compressor and the high-pressure turbine are connected by a high-pressure (HP) shaft (not shown) and together form 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 together form a low-pressure body. The HP shaft and the LP shaft extend along the longitudinal axis X-X' of the turbine engine 50.

[0180] The fan shaft is rotatably connected to the LP shaft, either directly or indirectly.

[0181] It should be noted that the present invention is not limited to this turbine engine structure, but can be applied to turbine engines with different structures, such as turbofan engine type turbine engines, in which the low-pressure compressor acts as the fan.

[0182] The nacelle 60 of the turbine engine includes a housing 61 for the turbine engine 50 and has a tubular structure including an outer cowl 62 defining an outer aerodynamic surface and an inner cowl 63 defining an inner aerodynamic surface for allowing airflow through the turbine engine 50, particularly the fan 51.

[0183] The outer fairing 62 and the inner fairing 63 are connected upstream via an air inlet lip 64 forming the leading edge of the nacelle 60.

[0184] The outer fairing 62 and the inner fairing 63 define an external structure that typically includes fixed and movable portions (not shown), the movable portions being, for example, thrust reversing devices.

[0185] The nacelle 60 also includes an inner fixed structure (IFS) 65. The IFS 65 is concentric with the external structure in the downstream section and surrounds the core of the jet turbine engine 50 downstream of the fan 51.

[0186] These external and internal structures define an annular flow duct (referred to as the secondary duct VS) designed to guide the flow of cold air circulating outside the turbine engine 50 (referred to as the secondary flow).

[0187] Downstream of fan 51, the main airflow FPP is divided into a main airflow FP and a secondary airflow FS by the internal fixed structure 65 of the nacelle, which serves as a separation component.

[0188] The main airflow FP enters the low-pressure compressor 52, for example, through the internal passage or main duct VP at the inlet guide vane (IGV) 57.

[0189] The secondary airflow FS passes through the external annular passage or secondary duct VS, for example, along the direction of the outlet guide vane (OGV) 58, and then reaches the turbine engine outlet.

[0190] The nacelle 60 is equipped with a heat exchanger 20, which is attached herein to the internal structure 63 of the nacelle 60. Therefore, the second skin 22 of the heat exchanger 20, configured to perform heat exchange, comes into contact with the airflow circulating in the secondary duct VS.

[0191] Alternatively, the heat exchanger 20 may be attached to the internal structure 65 of the nacelle 60.

[0192] According to another variant, the heat exchanger 20 may be attached to the external fairing 62 of the nacelle 60, wherein the second skin 22 of the heat exchanger 20 is in contact with the outside air.

[0193] According to another variation, the heat exchanger 20 can be attached to the internal structure 65, wherein the second skin 22 of the heat exchanger 20 is in contact with the airflow circulating in the secondary duct VS.

[0194] Cooling air circulates through an exchanger, specifically a nominally smooth second skin 22, where the cooling air recovers a portion of the heat energy from the heat transfer fluid.

[0195] As a result of the present invention, the planar transition between the hydraulic interface of the surface exchanger 20 and the smooth second skin 22 is softened by the pressure drop reduction member 40 extending into the associated hydraulic interfaces 24, 25.

[0196] Furthermore, the heat exchange between the fluid circulating in the heat exchanger 20 and the air circulating outside the heat exchanger is optimized, while improving the structural strength of the heat exchanger and reducing aerodynamic load losses.

Claims

1. A heat exchanger (20), particularly for a heat exchanger for an aircraft nacelle, the heat exchanger comprising a first skin (21) and a second skin (22) joined together, and a plurality of channels (23) disposed between the first skin (21) and the second skin (22) for distributing fluid (F1), the heat exchanger further comprising a first hydraulic inlet (24) and a second hydraulic inlet (25) for the fluid, characterized in that, The exchanger (20) further includes at least one pressure drop reduction member (40) extending axially toward the first hydraulic interface (24) or the second hydraulic interface (25), the pressure drop reduction member (40) having a generally conical cross section, and the pressure drop reduction member (40) comprising: a base (41) pointing toward the second skin (22) on the side opposite to the associated hydraulic interface (24, 25); and a conical hydraulic flow deflection portion (42) extending from the base (41) to a apex (S) and pointing toward the associated hydraulic interface (24, 25) on the side opposite to the second skin (22).

2. The switch (20) according to claim 1, wherein, The pressure drop reduction member (40) extends axially at least partially in the first hydraulic interface (24) or the second hydraulic interface (25).

3. The switch (20) according to claim 1 or 2, wherein, At least one of the first interface (24) and the second interface (25) forms an angle with the second epidermis (22), the angle preferably being greater than or equal to 60°.

4. The switch (20) according to any one of the preceding claims, wherein, The base (41) of the pressure reduction member (40) has the same shape as the associated hydraulic interface (24, 25).

5. The switch (20) according to any one of the preceding claims, wherein, The hydraulic flow deflection portion (42) of the pressure drop reduction member (40) includes a smooth outer surface (42a).

6. The switch (20) according to any one of the preceding claims, wherein, The hydraulic flow deflection portion (42) of the pressure drop reduction member (40) includes an outer surface (42a) that includes a plurality of recessed facets (42b) that extend from the base (41) to the apex (S) and are connected to the apex (S), wherein each recessed facet (42b) is positioned opposite to an associated distribution channel (23).

7. The switch (20) according to any one of the preceding claims, wherein, The pressure drop reduction component (40) is directly integrated into the second skin (22) or into the associated hydraulic interface (24, 25).

8. The exchanger (20) according to any one of claims 1 to 6, the exchanger comprising a plate (30) attached to the second skin (22) and having a stud (31) disposed between the second skin (21) and the first skin (22), thereby ensuring that the hydraulic ports (24, 25) are attached to the first skin (21) and the second skin (22) by means of an attachment device (32) cooperating with the stud (31), and wherein, The pressure drop reduction component (40) is directly integrated into the plate (30).

9. A turbine engine nacelle (60) comprising an outer structure (62, 63) and an inner structure (65) defining an annular secondary duct (VS), the nacelle (60) including a housing for a turbine engine (50), the housing, together with the inner structure (65), defining an annular main flow duct (VP), the nacelle (60) including at least one heat exchanger (20) according to any one of the preceding claims, the heat exchanger being either attached to the outer structure (62, 63) and on the side of the secondary duct (VS) or on the outside of the outer structure (62, 63), or attached to the inner structure (65) and on the side of the secondary duct (VS).

Images