Assembly comprising annular duct and heat exchanger having inclined front surface and deflector, and turbine engine comprising such assembly

Abstract

The invention relates to an assembly for a turbine engine, in particular for an aircraft, comprising:-an annular duct having a longitudinal axis through which a first fluid is configured to circulate, and-a heat exchanger (3) arranged in the annular duct, the invention relates to a heat exchanger (1) comprising a longitudinal axis (2) and having a front surface (11) inclined in a main direction (A) with respect to the longitudinal axis, the heat exchanger comprising fins (8) extending transversely between two panels (6, 7) arranged facing each other, the thickness of each of the panels being greater than the thickness of each of the fins. According to the invention, the fins are arranged in a plurality of rows transverse to the main direction, and a portion of the fins is elongated so as to form a first deflector (15) configured such that a first fluid entering the heat exchanger via the front surface deflects in a direction substantially parallel to the direction of extension of the fins.

Description

Technical Field

[0001] This invention relates to the general field of aviation. In particular, this invention relates to a plate-fin heat exchanger for a turbine engine, especially a turbine engine for aircraft. Background Technology

[0002] Existing technologies include documents FR-A1-3132542, US-A1-2008 / 017360, and FR-A1-3118151.

[0003] Aircraft turbine engines and aircraft include various components and / or equipment that require lubrication and / or cooling to function properly. These components and / or equipment may be bearings or gears in a turbine engine, or electrical and / or electronic components in an electrical system within a turbine engine of an aircraft, or in a system for regulating the internal space of an aircraft. The heat generated by these components and / or equipment (which can be very high depending on the power of the components and / or equipment) is dissipated through heat exchange with a cold source available in the turbine engine and / or aircraft.

[0004] Heat exchange is achieved using one or more heat exchangers installed in turbine engines or aircraft for various applications. As the need to cool lubricating fluids and electrical and / or electronic systems (motors, generators, batteries, etc.) in turbine engines and / or aircraft increases, heat exchangers are under increased pressure.

[0005] Plate-fin heat exchangers are known for improving and / or supplementing cooling requirements and are typically arranged in the ducts of turbine engines. These heat exchangers generally comprise two panels extending in a main direction and fins extending laterally between the two panels. The heat exchanger also includes a front surface and a distal surface; the flow circulating in the duct enters the heat exchanger through the front surface and exits through the distal surface. It has been proposed that the heat exchanger should be tilted relative to the longitudinal axis of the turbine engine such that the flow circulating in the duct is not oriented perpendicular to the front surface of the heat exchanger. However, tilting the exchanger requires a significant deflection of the flow close to the exchange surface. If the conversion from dynamic to static pressure is only partial due to flow separation downstream of the leading edge of the fins, this deflection is associated with a significant reduction in velocity (significant increase in the cross-sectional area of ​​the passage) and a significant loss of total pressure. This becomes even more important when the density of the airflow under consideration is low (e.g., high-altitude air) and the mass flow rate of the considered flow is high.

[0006] Some or all of the above-mentioned drawbacks need to be addressed. Summary of the Invention

[0007] The purpose of this invention is to provide a heat exchanger that has an improved front surface on the one hand and a small overall radial and axial dimension on the other hand, while reducing pressure drop and avoiding a significant impact on quality.

[0008] According to the invention, this is achieved by a component for a turbine engine, particularly a turbine engine for an aircraft, the component comprising: - An annular pipe with a longitudinal axis, through which the first fluid is configured to flow, and A heat exchanger located between a first fluid and a second fluid, the heat exchanger being arranged in an annular pipe and having a front surface inclined in the main direction relative to the longitudinal axis, the heat exchanger comprising at least two panels arranged facing each other and a plurality of fins extending laterally between the two panels, each panel having a thickness greater than the thickness of each of the fins, the fins being arranged in multiple rows transverse to the main direction, and a portion of the fins being extended to form a first baffle plate, the first baffle plate being configured such that the first fluid entering the heat exchanger via the front surface is deflected in a direction substantially parallel to the extension direction of the fins.

[0009] Therefore, this solution enables the achievement of the aforementioned objectives. Specifically, by extending a portion of the fins to incorporate baffles, the flow of the first fluid is redirected by a significant deflection towards the inclined front surface of the heat exchanger, and significantly slowed before entering the heat exchanger. Arranging the baffles on the fins allows for greater freedom in arranging the fins within the heat exchanger (e.g., in terms of the number of fins), thereby reducing pressure drop. The inclination of the heat exchanger reduces the overall radial and axial dimensions. More precisely, the inclination of the heat exchanger significantly reduces the relative overall radial dimension of the heat exchanger (which is height-limited) and significantly reduces the axial overall dimension of the flow lines upstream of the heat exchanger to prevent flow separation. Furthermore, the baffles restrict flow separation of the first fluid to ensure that dynamic pressure is converted into static pressure.

[0010] The component also includes one or more of the following features, either individually or in combination: - The thickness of each fin is between 50μm and 300μm.

[0011] - The lateral pitch between adjacent fins in the main direction is between 1 mm and 25 mm.

[0012] - The tilt angle is between 5° and 60°, preferably between 15° and 45°.

[0013] - The heat exchanger is annular and centered on the longitudinal axis, or extends in corner sectors around the longitudinal axis.

[0014] Another portion of the fins is extended to form a second deflector, which is configured to deflect the first airflow leaving the heat exchanger in a direction substantially parallel to the longitudinal axis.

[0015] - At least one of the two fins is extended by a first guide vane or a second guide vane.

[0016] - The first deflector and / or the second deflector have different lengths.

[0017] - A row of fins arranged near the front surface includes different profiles arranged along the main direction, the profiles being selected at least from fins, extended fins with a first guide plate having a first length, and extended fins with a second length of the first guide plate.

[0018] - The first and second guide vanes have the same radius of curvature or different radii of curvature.

[0019] - Each first or second deflector has a variable radius of curvature between its first and second edges.

[0020] - The curved portion of the first guide plate and / or the second guide plate is located at least partially within the core (interior) of the heat exchanger.

[0021] - The first guide vane and / or the second guide vane have a thickness that varies between a first edge and a second edge, the first edge of each first guide vane or second guide vane defining a leading edge or a trailing edge, and the second edge connecting to the remainder of the body of the extended fin.

[0022] - The first deflector and / or the second deflector are configured such that the thickness increases with deflection and then gradually decreases after most of the deflection has been achieved.

[0023] --The extension direction of the fins is transverse, preferably perpendicular to the main direction.

[0024] --The heat exchanger extends at least partially around the longitudinal axis.

[0025] --The heat exchanger includes a first end, which is arranged at a predetermined distance from the radial inner wall of the flow channel.

[0026] --Finals without a first or second deflector have the same length.

[0027] --Each first or second deflector includes a maximum thickness that is a function of the lateral pitch between the two fins.

[0028] The present invention also relates to a turbine engine having a longitudinal axis X, the turbine engine comprising the components described above.

[0029] The present invention also relates to an aircraft comprising a turbine engine as described above. Attached Figure Description

[0030] The invention will be better understood by reading the following detailed explanatory description of embodiments of the invention, given by way of purely illustrative and non-limiting example, with reference to the illustrative drawings, in which: Figure 1 This is a perspective axial cross-sectional view of a turbine engine pipe according to the present invention; Figure 2 An example of a heat exchanger according to the invention arranged at an angle in a flow channel is shown schematically and in axial cross-section; Figure 3 A portion of the plate-fin heat exchanger according to the invention is shown schematically and in perspective view; Figure 4 This is a detailed view of the arrangement of the first guide vanes on the secondary exchange surface of the heat exchanger according to the present invention; Figure 5 An embodiment of a heat exchanger according to the present invention is shown, the heat exchanger including baffles at the inlet and outlet of the heat exchanger; Figure 6 An example of the arrangement of the first baffle at the inlet of the heat exchanger according to the invention is shown; Figure 7 This is an axial cross-sectional view of an embodiment of the fin arrangement of a heat exchanger according to the present invention; Figure 8 This is an axial cross-sectional view of another embodiment of the arrangement of fins in a heat exchanger according to the present invention; Figure 9 Is it like this? Figure 8 A perspective view of the fin arrangement shown. Detailed Implementation

[0031] Figure 1 An example of a flow duct 1 of a turbine engine 2 with a longitudinal axis X is shown. The turbine engine 2 can be a turbojet engine, a turboshaft engine, or a turboprop engine.

[0032] Flow duct 1 can be a secondary duct in which a secondary flow from the airflow passing through the fan upstream of the turbine engine circulates. Flow duct can also be a tertiary duct in which an external mainstream flow from the main flow (which also originates from the airflow passing through the fan) circulates. The main and secondary flows are typically separated by a splitter nose located downstream of the fan.

[0033] In this invention, the terms "upstream" and "downstream" are defined relative to the flow of gas in the turbine engine, here along the longitudinal axis X and with reference to... Figure 1 Defined from left to right.

[0034] Figure 1 The components shown include one or more heat exchangers mounted in the turbine engine 2 to exchange heat between a first fluid and a second fluid. Generally, the second fluid is configured to lubricate and / or cool components and / or equipment of the turbine engine and / or the aircraft. These components and / or equipment may be one or more motors, bearings, accessory gearboxes, electronic / electrical systems, cooling systems for cooling the interior space of the aircraft, cryogenic fuel tanks, etc. Heat is dissipated in the first fluid via the heat exchangers.

[0035] like Figure 1 As shown, a heat exchanger 3 is installed in a flow pipe 1 to cool a first fluid (which is a heat transfer fluid) configured to lubricate and / or cool these components and / or equipment. Specifically, the heat exchanger 3 is supported by an annular radial inner wall 4 of the pipe 1. The flow pipe 1 includes a radial outer wall 5 coaxial with the radial inner wall 4. The heat exchanger 3 may be supported by the radial outer wall 5. The first fluid (such as an airflow circulating in the flow pipe 1) flows in an upstream-downstream direction. Alternatively, the first fluid flows from downstream to upstream.

[0036] Advantageously, the heat exchanger 3 includes at least one primary exchange surface and at least one secondary exchange surface. In particular, the heat exchanger 3 is a plate-fin heat exchanger. The heat exchanger 3 includes at least two panels (in this case, a first panel 6 and a second panel 7) extending in mutually parallel planes. These first panels 6 and second panels 7 form the primary exchange surface. The second panel 7 is arranged facing the first panel 6. The heat exchanger 3 includes a plurality of fins 8 arranged laterally between the first panel 6 and the second panel 7. The fins 8 form the secondary exchange surface. Advantageously, but not limited to, the fins 8 extend perpendicular to the first panel 6 and the second panel 7.

[0037] In the installation configuration considered in the remainder of this specification, the heat exchanger 3 has a principal direction A of inclination relative to the longitudinal axis X. The heat exchanger 3 is also inclined relative to the direction of the airflow entering the flow duct 1. This inclination reduces the overall axial dimension of the heat exchanger in the flow duct 1. The inclination angle α of the heat exchanger 3 is between 5° and 60°. Preferably, the inclination angle α is between 15° and 45°.

[0038] Advantageously, the heat exchanger 3 includes a first end 9 and a second end 10 opposite to each other in the main direction A. In this example, the first end 9 is arranged at a distance D1 from the radial inner wall 4, and the second end 10 is connected to the radial inner wall 4. Advantageously, the predetermined distance D1 is between 10 mm and 250 mm. Preferably, the predetermined distance D1 is between 30 mm and 100 mm. In this way, airflow can circulate above the heat exchanger (radially outward). Alternatively, the heat exchanger can occupy the entire height of the duct.

[0039] The second end 10 can be connected to the radial inner wall 4 with a gap, or it can be connected to the radial inner wall 4 without a gap. However, the attachment distance of the second end 10 can be minimal to avoid the boundary layer. The connection distance will be less than the distance D1.

[0040] refer to Figure 2 The first panel 6 and the second panel 7 also extend radially. In this case, the fins 8 advantageously extend from the first or second panel about the longitudinal axis X in a direction parallel or substantially parallel (positive or negative 10°) to the circumferential direction. It should be noted that the fins have an extension direction that depends on the tilt angle. For example, if the tilt angle of the main direction of the heat exchanger is 90°, the extension direction will be parallel to the longitudinal axis.

[0041] Advantageously, the fins 8 are arranged in multiple rows parallel to the main direction A. The fins 8 in each row are spaced apart and arranged parallel to each other along the main direction A.

[0042] exist Figure 2 In the illustrated embodiment, the row of fins 8 is discontinuous and staggered relative to adjacent rows of fins 8 along the lateral direction B. In other words, the fins 8 are discontinuous and staggered by a pitch. Of course, the fins 8 can be arranged differently without obstructing the flow of the first fluid between the fins.

[0043] For example, heat exchanger 3 includes a front surface 11 through which a first fluid enters heat exchanger 3. Due to the inclination of heat exchanger 3, the front surface 11 is transverse to or partially transverse to the longitudinal axis X. For example, the normal of the front surface may have a transverse component and a component parallel to the longitudinal axis X. The front surface 11 is inclined along the principal direction A. Furthermore, the cross-section of the front surface 11 increases with the inclination of heat exchanger 3, which slows down the flow of air entering heat exchanger 3.

[0044] For example, heat exchanger 3 includes a distal surface 12 through which a first fluid is discharged from heat exchanger 3. In particular, the space between the fins 8 (which defines the lateral pitch P) opens to the front surface 11 and also to the distal surface 12.

[0045] On the other hand, the cover (not shown) is arranged at the first end 9 and the second end 10.

[0046] Each fin 8 has a leading edge 8a and a trailing edge 8b that are opposite each other in the transverse direction B relative to the principal direction A. The fin 8 has a length in its elongating direction (parallel to the transverse direction B), which is measured between the leading edge 8a and the trailing edge 8b. Each fin 8 includes a first surface 8c and a second surface 8d connected by the leading edge 8a and the trailing edge 8b. Each fin 8 has a generally rectangular shape. Advantageously, the fin 8 is thin and flat.

[0047] In this application, the thin fin is a fin with a thickness e1 between 50 μm and 300 μm. The thickness e1 of the fin 8 is measured between the first surface 8c and the second surface 8d, which are laterally opposed to each other. For example, the thickness of each fin 8 is constant over the entire height of the fin 8 measured between the two panels 6 and 7.

[0048] The lateral pitch P between adjacent fins 8 in the main direction A is between 1 mm and 25 mm. Preferably, the lateral pitch P is between 1 mm and 5 mm. In this example of the lateral pitch, the fins 8 are considered to be arranged "closely" in the heat exchanger 3. This allows for the arrangement of a large number of fins 8 in the heat exchanger 3, and in particular, increases the heat exchange surface by considering fins equipped with baffles. This type of heat exchanger has a close lateral pitch P, which also makes the heat exchanger easier to manufacture, reduces the manufacturing cost of the heat exchanger 3, and provides great flexibility in the arrangement of fins and baffles. The fins extend to form baffles. The baffles are small in size, making them attractive in terms of weight and overall size.

[0049] refer to Figure 3 Advantageously, the two panels (in this case, the first panel 6 and the second panel 7) each have a thickness e2, which is greater than the thickness e1 of each of the fins (see...). Figure 7 The thickness e2 of each first panel 6 and second panel 7 is measured by (in this case, circumferentially) laterally opposed inner surfaces 13a and outer surfaces 13b. The thickness of each panel 6, 7 can be 1.5 to 4 times the thickness of the fin 8. This thickness e2 of the panels 6, 7 ensures watertightness.

[0050] Advantageously, but not limited to, the distance D2 between the two panels 6 and 7 (i.e., the height of the fin 8) is between 2 mm and 20 mm, preferably between 7 mm and 15 mm or between 2 mm and 5 mm.

[0051] The heat exchanger 3 extends at least partially around the longitudinal axis X. In this embodiment, the heat exchanger 3 is annular (360°) and centered on the longitudinal axis X. Alternatively, the heat exchanger 3 extends in a corner sector around the longitudinal axis X. In this case, the heat exchanger 3 includes a plurality of panels 6, 7 arranged in a radial plane around the longitudinal axis X and fins 8 extending between two panels 6, 7. The extension direction of the fins 8 extends transversely to the main direction A. The distance D2 is measured circumferentially or around the longitudinal axis X.

[0052] As in Figure 2 and Figure 3 As can be seen, a portion of fin 8 is extended to form a first baffle 15, which is configured to deflect the first fluid entering the heat exchanger 3 in a direction parallel to the extension direction of fin 8. In other words, the leading edge of this portion of the fin is altered. Since the first baffle 15 is aligned with fin 8, it also facilitates heat exchange. Because the lateral pitch P of the first baffle 15 is the same as that of fin 8, a very long baffle is not required. In other words, the lateral pitch P is directly proportional to the length of both the baffle and fin 8. For example, by dividing the lateral pitch by ten, the length of the baffle will be divided by ten (keeping the same ratio).

[0053] In the remainder of the instruction manual, the fin 8 equipped with the deflector is referred to as "extended fin 8'".

[0054] Furthermore, for example, the length of these extended fins 8' differs from the length of the other fins 8. Advantageously, but not limited to, the fins 8 without the first guide vane 15 have the same length.

[0055] Advantageously, the first deflector 15 extends through the front surface 11 of the heat exchanger 3. In other words, the first deflector 15 is at least partially arranged on the outside of the heat exchanger 3. Extended fins 8' are arranged in the first row of fins 8, i.e., the row of fins closest to the front surface 11. In this way, the airflow undergoes an initial change of direction at the inlet of the heat exchanger 3. The airflow flows in the heat exchanger 3 in a transverse direction B perpendicular to the main direction A. This deflection at the inlet is associated with significant deceleration. The first deflector 15 is also configured to define a divergent guide path from the first deflector to the front surface 11 leading into the interior of the heat exchanger 3. The deflection caused by the first deflector 15 and the deceleration caused by the tilt are then associated, and the deceleration effect obtained by this combination is greater.

[0056] The first deflector plates 15 are spaced apart to form a channel 16 or airflow path leading to the front surface 11.

[0057] Each first guide vane 15 includes an elongated body between a first edge 15a and a second edge 15b. The first edge 15a forms the leading edge of a fin 8, which is elongated. Each first guide vane 15 has a length L1 (measured between the first edge 15a and the second edge 15b) that is less than the length L2 of a non-elongated fin.

[0058] refer to Figure 4 Each first guide vane 15 has a relatively constant thickness between its body and its second edge 15a and second edge 15b. The thickness e1 at the second edge 15b is the same as the thickness of the rest of the fin 8. The first edge 15a has a tapered (but straight) tip. For example, the thickness of each first edge 15a is less than or equal to 0.5 mm. The shape of the first guide vanes 15 reduces aerodynamic losses due to introducing the guide vanes into the first fluid (in this case, airflow). All first edges 15a (or tapered tips) are oriented in the same direction.

[0059] Advantageously, but not limited to, each first deflector 15 includes a first side 15c and a second side 15d connected by a first surface 15e and a second surface 15f. The first and second surfaces 15e, 15f are connected to a first edge 15a and a second edge 15b. Each first surface 15e is oriented toward the front surface 11 of the heat exchanger. Similarly, each first edge 15a faces upstream. Airflow arriving parallel to the longitudinal axis X is deflected at the first deflector 15 to be directed toward the front surface 11, thereby leading to the core of the heat exchanger 3.

[0060] A first concave curved surface 15e extends between a first end 15e1 and a second end 15e2. A second convex curved surface 15f extends between a first end 15f1 and a second end 15f2. The first ends 15e1 and 15f1 are connected to a first edge 15a, and the second ends 15e2 and 15f2 are connected to a second edge 15b.

[0061] Advantageously, the first surface 15e has a convex curved shape, and the second surface has a concave curved shape. Another advantageous, but non-limiting, feature is that the body of the first guide vane 15 has at least one radius of curvature. The radius of curvature can be equal to 1 to 20 times the lateral pitch P. Preferably, the radius of curvature can be between 1 and 7 times the lateral pitch P. For example, the smaller the lateral pitch P, the smaller the radius of curvature.

[0062] The curvatures of the first surface 15e and the second surface 15f can be the same or different. Advantageously, the curvatures of the first guide vane 15 are different in order to provide converging or diverging paths.

[0063] In another embodiment, the first guide vane 15 has a different radius of curvature. More specifically, a row of fins near the front surface 11 may include extended fins 8' and extended fins, each extended fin 8' having a first guide vane 15 with a first radius of curvature, and each extended fin having a first guide vane 15 with a second radius of curvature. Of course, it is also conceivable to arrange extended fins with two or more first guide vanes 15 having different radii of curvature from each other. First guide vanes 15 with different curvatures can be arranged alternately. This will reduce the pressure drop in the region where the channel cross-section of the front surface 11 is still small and therefore the velocity is still high.

[0064] according to Figure 5 In the illustrated embodiment, the heat exchanger 3 includes a second baffle 17 disposed at the outlet (far end surface 12) of the heat exchanger 3. In this case, another portion of the fin 8 is extended to form the second baffle 17, which is configured to deflect the first fluid (in this case, airflow) leaving the heat exchanger in a direction substantially parallel to the longitudinal axis. Here, the trailing edge of the extended fin 8' is altered. In this way, the airflow undergoes two deflections, once at the heat exchanger inlet and once at the heat exchanger outlet. In addition to deflection, this configuration significantly accelerates the airflow exiting the heat exchanger 3. The second baffle 17 is also configured to define a converging path for guiding the first fluid leaving the heat exchanger 3. When accelerated, the airflow is less prone to flow separation.

[0065] These second deflectors 17 have the same configuration as the first deflector 15, i.e., the same thickness, curved surface, and radius of curvature. However, the first edge 17a' faces downstream. The second surface 15f faces the distal surface of the second panel. The airflow through the heat exchanger 3 is discharged through channels formed between the fins, which lead to the distal surface and to the second deflectors 17, which, by their shape and configuration, guide the airflow in a direction substantially parallel to the longitudinal axis X, while simultaneously slowing the airflow.

[0066] exist Figure 6 In another embodiment shown, the first guide vane 15 and / or the second guide vane 17 can be arranged in different ways. In this case, at least one of the two fins 8 is extended with the first guide vane 15. Alternatively, each third fin is extended with the first guide vane 15. Not all fins 8 (especially those fins 8 near the front surface 11) need to be extended / stretched. This configuration allows for arrangements with more or less narrow lateral pitch P between the fins 8. Alternatively or additionally, at least one of the two fins 8 is extended with the second guide vane 17.

[0067] Figure 6The first guide vane 15 is also shown to have different lengths. The extended fins 8' include at least two different lengths, one longer and one shorter. In this example, there are three fin profiles arranged continuously along the main direction A. Advantageously, these profiles are arranged in the first row of fins near the front surface 11. In particular, there are fins 8 alternating with two extended fins 8' (i.e., an extended fin 8' of the first guide vane 15 with a first length L11 and an extended fin 8' of the first guide vane 15 with a second length L12). The first length L11 is greater than the second length L12. The extended fin 8' of the first guide vane 15 with the first length L11 extends to the outside of the heat exchanger 3 and passes through the front surface 11. The extended fin 8' of the first guide vane 15 with the second length L12 extends inside the heat exchanger 3 and is located downstream of the front surface 11 along the airflow direction. Other configurations of the first guide vane having multiple fin profiles (e.g., two to four different fin profiles) and different lengths are possible. This configuration can also be applied to extended fins 8' with a second deflector 17.

[0068] The arrangement of the first guide vanes 15 and / or the second guide vanes 17 of different lengths allows for control of the velocity of the first fluid and the pressure drop at the front surface 11. The first fluid (in this case, airflow) arrives at the first edge 15a at high speed and decelerates upon contact with the first guide vanes 15. The airflow passes through an "expanding channel 18" formed between the two longer first guide vanes 15, thereby reducing the pressure drop. The first edge 15a of the shorter first guide vane 15 is located downstream of the first edge 15a of the longer first guide vane 15, thus forming the expanding channel. Once the airflow decelerates, the extended fins 8' become more compact to ensure greater deflection over a shorter distance.

[0069] exist Figure 7In another embodiment shown, the heat exchanger 3 includes alternating extended fins 8' along the circumferential direction, the extended fins 8' having first guide vanes 15 with different profiles. Specifically, a row of fins near the front surface 11 includes extended fins (referred to as long extended fins) of the first guide vane 15 having a first length L11 and a first radius of curvature, and extended fins (referred to as long extended fins) of the first guide vane 15 having a second length L12 and at least a second radius of curvature. This arrangement is repeated along the circumferential direction. The second length L12 is greater than the first length L11. The first guide vane 15 having the first length L11 further increases deflection and reduces pressure drop by being arranged downstream of the second guide vane having the second length L12. The ratio between the second length L12 and the first length L11 (L12 / L11) can be between 1.2 and 4. Similarly, the first radius of curvature is greater than the second radius of curvature. Alternatively, the first radius of curvature and the second radius of curvature can be the same. Preferably, the curved portion of the baffle 15 (which has lengths L11 and L12) is at least partially located in the core of the heat exchanger, i.e., downstream of the front surface 11. It should be understood that the second edge 15b may be outside or inside the heat exchanger (downstream of the front surface 11).

[0070] Advantageously, but not limited to, the first guide vane 15 of the extended fin includes a change in the radius of curvature between the first edge 15a and the second edge 15b. Figure 7 In the illustrated embodiment, the first radius of curvature follows a pattern: a large radius of curvature Rc1 at the first edge of the first guide vane 15, a small radius of curvature Rc2 near the first edge of an adjacent first guide vane, and a large radius of curvature Rc3 towards the second edge of the first guide vane. In other words, the radius of curvature decreases, increases, and then decreases again from the longest first edge 15a of the first guide vane 15 to the second edge 15b. For example, the small radius of curvature Rc2 is less than 0.7*Rc1 and / or the small radius of curvature Rc2 is less than 0.7*Rc3. The small radius of curvature Rc2 can even be less than 0.4*Rc2 and / or the small radius of curvature Rc2 is less than 0.4*Rc3. This configuration can also be applied to an extended fin 8' with a second guide vane 17.

[0071] Figure 8 and Figure 9Another embodiment of the first guide vane 15 is shown. Each first guide vane 15 has a thickness e3 that varies between a first edge 15a and a second edge 15b. By varying the thickness, the variation in the channel cross-section at the front surface 11 of the heat exchanger 3 can be better controlled, and the deceleration of the first fluid can be controlled relatively independently of the change in the orientation of the first fluid. Each first guide vane 15 is configured such that the thickness e3 increases with deflection and then gradually decreases after most of the deflection has been achieved. The expression “basic deflection” means that 75% to 99% of the orientation change of the first fluid has been achieved. The term “gradual” means that the change in value is substantially linear and the thickness does not change abruptly. The target channel cross-section (the conventional spacing of the fins in the core of the exchanger downstream of the deflection) is then obtained. For example, the gradual decrease in thickness shows a thickness variation from about 0.5 mm to 2 mm to a fine thickness of about 0.2 mm to 4 mm. The thickness and / or thickness variation depends on the target channel cross-section, for example, having an opening angle between 5° and 20°.

[0072] Due to the small lateral pitch P between the fins 8, before obtaining thinner fins again, the fins extend transversely to the extension direction of the fins and through the thickness e3. 最大 The length L3 measured between the straight line D3 (described below) and the second edge 15b of the guide vane 15 is relatively short (approximately 1 mm to 10 mm). Therefore, the increase in mass and pressure drop associated with a larger thickness is minimal.

[0073] In particular, Figure 8 In this configuration, all first deflectors 15 are identical. Each first deflector 15 includes a maximum thickness e3. 最大 The maximum thickness e3 最大 It is a function of the lateral pitch P between the two fins 8. For example, the maximum thickness e3 最大 The thickness of the first guide vane increases from the first edge 15a to the maximum thickness e3, which is between 0.5 and 0.10 times the lateral pitch P. 最大 The thickness decreases from the maximum thickness to the second edge 15b that engages with the rest of the body of the extended fin 8'. The thickness at the first edge 15a differs from the thickness at the second edge 15b. More specifically, the thickness at the second edge 15b is greater than the thickness at the first edge 15a. This configuration can also be applied to extended fins having a second guide vane 17.

[0074] Figure 8 It is also shown that the curved portion of the baffle 15 is preferably located at least partially at the core of the heat exchanger, i.e., downstream of the front surface 11. Here, the second edge 15b is inside the heat exchanger (downstream of the front surface 11). Of course, the second edge 15b can also be outside the heat exchanger.

[0075] Figure 9 and Figure 8 The difference lies in the different lengths of the first guide vanes 15. Specifically, there is an alternation between first guide vanes with a first length L11 and first guide vanes with a second length L12. This configuration reduces the pressure drop in region 18, where the channel cross-section is smaller and the velocity of the first fluid remains high. This configuration can also be applied to extended fins with second guide vanes 17.

[0076] Advantageously, the heat exchanger 3 is produced using additive manufacturing methods. This allows for the production of complex shapes. The material of the heat exchanger 3 is metallic, advantageously but not limitingly including aluminum. Aluminum has good thermal conductivity.

[0077] The heat exchanger 3 may include one or more passages (not shown) arranged in the thickness of the first panel and / or the second panel, wherein a second fluid flows to achieve heat transfer of the airflow flowing through the heat exchanger 3.

[0078] In this way, the heat exchanger 3 of this type, with baffles 15 and 17, is equipped with certain extended fins, particularly at the front surface 11. This increases the size of the front surface 11, significantly slows the flow, and reduces the overall size because the lateral pitch P between the fins 8 is relatively small (approximately one micrometer) compared to the distance between the panels 6 and 7. Furthermore, a better distribution of the first fluid is achieved within the heat exchanger 3, which improves the overall performance of the heat exchanger.

Claims

1. A component for a turbine engine (2), particularly a turbine engine for an aircraft, the component comprising: - An annular pipe (1) having a longitudinal axis (X), through which a first fluid is configured to flow, and A heat exchanger (3) located between the first fluid and the second fluid is arranged in the annular pipe (1) and has a front surface (11) inclined in the main direction (A) relative to the longitudinal axis. The heat exchanger includes at least two panels (6, 7) arranged facing each other and a plurality of fins (8) extending laterally between the two panels (6, 7). The thickness (e2) of each panel (6, 7) is greater than the thickness (e1) of each fin (8). The fins (8) are characterized in that they are arranged in multiple rows transverse to the main direction (A), and a portion of the fins are extended to form a first guide plate (15), which is configured such that the first fluid entering the heat exchanger (3) via the front surface (11) is deflected in a direction substantially parallel to the extension direction of the fins (8).

2. The component according to claim 1, characterized in that, The thickness (e1) of each fin (8) is between 50 μm and 300 μm.

3. The component according to any one of the preceding claims, characterized in that, The lateral pitch (P) between adjacent fins (8) in the main direction (A) is between 1 mm and 25 mm.

4. The component according to any one of the preceding claims, characterized in that, The tilt angle (α) is between 5° and 60°, preferably between 15° and 45°.

5. The component according to any one of the preceding claims, characterized in that, The heat exchanger (3) is annular and centered on the longitudinal axis (X), or extends in a corner sector around the longitudinal axis (X).

6. The component according to any one of the preceding claims, characterized in that, Another portion of the fin (8) is extended to form a second deflector (17), which is configured to deflect the first airflow leaving the heat exchanger (3) in a direction substantially parallel to the longitudinal axis (X).

7. The component according to any one of the preceding claims, characterized in that, At least one of the two fins (8) is extended by a first guide plate (15) or a second guide plate (17).

8. The component according to any one of the preceding claims, characterized in that, The first guide vane (15) and / or the second guide vane (17) have different lengths.

9. The component according to any one of the preceding claims, characterized in that, A row of fins (8) arranged near the front surface (11) includes different profiles arranged along the main direction (A), the profiles being selected at least from fins (8), extended fins (8') of a first guide plate having a first length (L11), and extended fins (8') of a first guide plate (15) having a second length (L12).

10. The component according to any one of the preceding claims, characterized in that, The first and second guide vanes (15, 17) have the same radius of curvature or different radii of curvature.

11. The component according to any one of the preceding claims, characterized in that, Each of the first guide vanes (15) or the second guide vanes (17) has a variable radius of curvature between the first edge (15a) and the second edge (15b).

12. The component according to claim 10 or 11, characterized in that, The curved portions of the first guide plate and / or the second guide plate are at least partially located in the core of the heat exchanger (3).

13. The component according to any one of the preceding claims, characterized in that, The first guide plate (15) and / or the second guide plate (17) have a thickness (e1, e3) that varies between a first edge (15a) and a second edge (15b), the first edge (15a) of each first guide plate or second guide plate (15, 17) defining a leading edge (8a) or a trailing edge (8b), and the second edge (8b) connecting to the remainder of the body of the extension fin (8').

14. The component according to the preceding claim, characterized in that, The first and / or second deflector (15, 17) are configured such that the thickness (e3) increases with deflection and then gradually decreases after most of the deflection has been achieved.

15. A turbine engine (1) having a longitudinal axis (X), characterized in that, The turbine engine includes the components according to any one of the preceding claims.

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