• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a heat exchanger for an air circulation channel of a turbomachine, the heat exchanger being configured to be traversed by a fluid to be cooled and comprises a plurality of fins projecting from a surface support, each fin extends axially along a length in the direction of air flow and comprises a leading edge and a trailing edge, the heat exchanger being characterized in that each fin further comprises a central body between the leading edge and the trailing edge, the central body having in a plane parallel to the support surface a curved central profile.
    公开号:FR3016956A1
    申请号:FR1400220
    申请日:2014-01-29
    公开日:2015-07-31
    发明作者:Gabriela Philippart；Imane Ghazlane；Julien Szydlowski
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] GENERAL TECHNICAL FIELD The invention relates to a heat exchanger of an air circulation channel of a turbomachine. Such an exchanger is particularly suitable for being installed in a turbomachine of an aircraft and, more specifically, an aircraft turbojet, STATE OF THE ART. A turbomachine comprises many elements such as rolling bearings supporting the shaft (s) of the turbomachine. , which need to be both lubricated and cooled. Also, it is known to supply these elements with "cold" oil. Thus, some turbomachines are equipped with an air-oil surface exchanger type SACOC (in English, "Surface Air-Cooled Oil-cooler") disposed in an air circulation channel of the turbomachine. In this air-oil exchanger SACOC type are formed a multitude of channels in which circulates the oil to be cooled. The exchanger comprises a body surmounted by fins having an isosceles trapezoidal profile. These fins increase the heat exchange surface between the oil to be cooled circulating in the channels of the body and the air circulating in the air circulation channel of the turbomachine. However, these fins also generate undesirable pressure losses.
    [0002] PRESENTATION OF THE INVENTION The invention makes it possible to improve heat exchangers of the known type and for this purpose relates to a heat exchanger for an air circulation channel of a turbomachine, the heat exchanger being configured to be traversed by a fluid to be cooled and comprises a plurality of fins projecting from a support surface, each fin extends axially along a length in the air flow direction and comprises a leading edge and a leading edge. leakage, the heat exchanger being characterized in that each fin further comprises a central body, between the leading edge and the trailing edge, the central body having in a plane parallel to the support surface a curved central profile.
    [0003] The invention is advantageously completed by the following characteristics, taken alone or in any of their technically possible combination. The curved central profile of the fin is defined by a Bézier curve such that n P (u) = ui (1 - i = 0 i = o with u a parameter varying from zero to one to characterize a point of the curve, Pi the coordinates, in the plane parallel to the support surface, of the control points of the Bézier curve and n the number of control points, not being greater than or equal to three, the second point can be placed between 0% and 70% of the central body, the third point is placed according to the position of the second point and can be placed between 20% and 100% of the central body - The leading edge and the trailing edge respectively have an attack profile and a leak profile in the plane parallel to the support surface, the driving profile forming an acute angle with the profile leakage - The acute angle is s between 2 ° and 10 °, typically between 3 ° and 4 °. - The leading edge is between 10% and 20% of the length of the fin. - The central body represents between 70% and 85% of the length of the fin. - The trailing edge is between 5% and 10% of the length (L) of the fin (20). The advantages of the invention are manifold.
    [0004] The curved profile of the fin reduces the length of the latter, while keeping the same exchange surface. Consequently, the length of the exchange device in contact with the fins (oil ducts inside) is also reduced, which makes it possible to optimize its thermal iso-exchange mass. In particular, in the case where the air circulation channel is a secondary vein of a turbomachine, the shape of the fins makes it possible to absorb the residual gyration. In fact, the fan creates a gyratory flow, and although the output straightening vanes, better known as OGV, straighten the flow to align it with the motor axis, residual gyration still remains. There is residual gyration if the flow of the fluid behind the OGVs is at a non-zero angle with respect to the motor axis.
    [0005] PRESENTATION OF THE FIGURES Other features, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and nonlimiting, and which should be read with reference to the accompanying drawings, in which: FIG. turbomachine; FIG. 2 illustrates a schematic view of an air circulation channel of a turbomachine comprising a heat exchanger according to the invention; - Figure 3 illustrates a side view of a heat exchanger according to the invention; FIG. 4 illustrates a schematic view from above of a heat exchanger according to the invention; FIG. 5 illustrates a schematic side view of a heat exchanger according to the invention; FIG. 6 illustrates a schematic side view of a heat exchanger according to the invention; - Figure 7 illustrates a top view of a curved profile of the central body of a fin of an exchanger according to the invention. In all the figures, similar elements bear identical references. DETAILED DESCRIPTION OF THE INVENTION The term "turbomachine" in the following text is understood to mean any machine that makes it possible to convert the thermal energy of a working fluid into mechanical energy by expanding said working fluid in a turbine. More particularly, this working fluid may be a combustion gas resulting from the chemical reaction of a fuel with air in a combustion chamber. Thus, the turbomachines, as described herein, include single or double flow turbojets, turboprops, turboshaft engines or gas turbines, among others. In what follows, the terms "upstream" and "downstream" are defined with respect to the direction of normal circulation of the air in the air circulation channel of the turbomachine. Figure 1 is a schematic view of a turbomachine 100 extending in an axial direction corresponding to the main axis X of rotation of the fan. From upstream to downstream, the turbomachine 100 successively comprises the following outer casings: an air intake casing I, a fan casing II arranged around a fan 102, an intermediate casing III connected to arms radial and supporting the set of rotors and stators of the turbomachine 100 and a thrust reverser casing IV. In this example, the turbomachine 100 is a dual-flow twin-turbojet engine, but can of course be, alternatively, a monoflux turbojet engine and / or a single-engine turbojet engine. The intermediate casing III comprises an intermediate housing shell 14, a flow separator 15 radially separating the primary stream V1 from the gases of the secondary vein V2 of the gases, the shell 14 and the flow separator 15 being connected by portions of vane. straightening 104a. Of course, in the case where the turbomachine is a single-stream turbojet engine, the intermediate casing does not have a flow separator. The fan casing II and the intermediate casing III are covered, on the outside, by an outer cover 17, generally called "fan cowl", extending axially and azimuthally around the fan casing II and the intermediate casing III. This outer cover 17 ensures the geometrical continuity of the outside of the turbomachine 100 between the outside of the air intake casing I and the outside IVa of the thrust reverser casing IV. In what follows it is considered that the air flow channel within the meaning of the invention relates for example to the secondary vein V2 of the turbomachine illustrated in FIG.
    [0006] Figure 2 is a schematic view of the channel 10 of air circulation of a turbomachine. It is an axial half-sectional view with respect to its main axis X. The air circulation channel 10 is symmetrical or quasi-symmetrical about the axis X. The turbomachine comprises a heat exchanger 12 In this example the heat exchanger is an air-oil heat exchanger of the SACOC type. In the example, the heat exchanger 12 is disposed at the inlet of the air circulation channel 10. In the remainder of the description, the invention will be described for any air circulation channel of a turbomachine delimited by a first structure 18 and a second structure 19 which may be respectively ferrule 14 and the flux separator 15. The direction in which the air circulates in the air circulation channel 10 is indicated by the arrow A. The heat exchanger 12 comprises, in this example, a body 21, forming part of the first structure 18. The Heat exchanger 12 is thus integrated in part with the first structure 18 and can be partially annular to correspond to the shell 14. In other embodiments, the heat exchanger 12 can be integrated in part to the second structure 19. The heat exchanger 12 comprises fins 20 connected to the body 21. Each fin 20 is protruding from the first structure and extends in height in the channel 10 of air circulation. The fins 20 are preferably parallel to each other. The first structure is hereinafter called "support surface".
    [0007] FIG. 3 is a side view of the heat exchanger 12 taken along a median surface P of a fin and perpendicular to the support surface 18 of the heat exchanger 12. This median surface extends approximately in a plane axial section comprising the main axis X of the turbojet engine. The body 21 of the heat exchanger 12 comprises a "hot" oil inlet channel 24 to be cooled, a plurality of channels 26 in which the "hot" oil circulates, and an outlet channel 28 allowing to recover the "cold" oil. The body 21 of the heat exchanger 12, however, may include other channels of entry, circulation and output of the "hot" oil. As can be seen in part in FIGS. 2 and 3, the fins 20 ensuring the exchange of heat between the "hot" oil and the "cold" air circulating in the air circulation channel 10, are arranged circumferentially facing the second structure 19. These fins 20 are fixed to the body 21 of the exchanger 12 and protrude from the surface 18S of the body 21, that is to say with respect to the surface 14S of the external fixed structure 14 which is the support surface. The fins 20 thus project into the air circulation channel 10. The fins 20 are disposed at the channels 26 for circulation of the "hot" oil. The "hot" oil which arrives in the body 21 of the exchanger 12 and which needs to be cooled, passes through the plurality of channels 26 of circulation. The heat generated by the "hot" oil is transferred to each fin 20 projecting into the air circulation channel 10 in which cold air circulates. Thus, the thermal energy "stored" in each fin 20 is transferred via a heat exchange surface of each fin 20 to the "cold" air. As illustrated in FIG. 3, each fin 20 extends axially in the medial surface P along the main axis X of the turbojet engine over a length L and comprises a leading edge 30 facing the air flow and a trailing edge 32. Between the leading edge 30 and the trailing edge 32, each fin further comprises a central body 37. The leading edge 30 defines an upstream end of the fin while the trailing edge 32 defines a downstream end of the fin 20. The central body 37 rises above the support surface at a height h. This height h may be constant or variable in the direction of the length L of the fin 20. Moreover, as illustrated more specifically in FIG. 3, each fin 20 comprises two lateral faces 33 connecting the leading edge 30 to the edge leakage 32 (only one side face 33 is visible in Figure 2). Thus, the surface formed by the side faces 33 and delimited by the leading edge 30, the trailing edge 32 the central body 37 of the fin 20 defines a heat exchange surface. The heat exchange surface of each fin 20 is in contact with the "fresh" air circulating in the air circulation channel 10, which allows the "hot" oil to be cooled. As illustrated in Figure 4 and Figure 5, the central body 37 of each fin 20 has in a plane P 'parallel to the support surface a central profile PR2 curved with respect to the main axis of the turbojet engine. Each fin 20 has a thickness e of between 1 mm and 3 mms. In addition, as shown in FIG. 6 (and as already mentioned in connection with FIG. 3), the fin 20 has a trapezoidal side view.
    [0008] Each fin 30 thus comprises a leading edge 30 having an attack profile PR1, a central body 37 having a central profile PR2 and a trailing edge 32 having a leakage profile PR3. Advantageously, the leading edge 30 has a profile PRI, driving in S the plane P 'parallel to the support surface forming an acute angle α with an axis parallel to the main axis X of the turbomachine. This angle a is between 2 ° and 10 °, typically between 3 ° and 4 °. Such a leading edge 30 which is not oriented parallel to an axis parallel to the main axis X of the turbomachine but which is offset relative thereto makes it possible to absorb a residual gyration of the OGVs in the case where the air circulation channel 10 corresponds to a secondary vein V2 of a turbojet engine. . In fact, the fan creates a gyratory flow, and although the output straightening vanes, better known as OGV, straighten the flow to align it with the motor axis, residual gyration still remains. Residual gyration occurs if the flow of fluid behind the OGVs is at a non-zero angle to the motor axis. Thus, in order to gradually straighten the flow coming from the leading edge, the curved central profile PR2 of the central body 37 of the fin 20 is preferably defined by a Bézier curve such that P (u) 1 = 0 i, nI Pi = (nt ui (1- u) n-1Pi i = o with u parameter varying from zero to one to characterize a point of the curve, Pi the coordinates 20 in the plane P 'parallel to the support surface 14 of the control points of the Bézier curve and n the number of control points The junction of the profiles PR2 and of the profile PRi advantageously has a continuity in order to participate in limiting the pressure losses and gradually straighten the flow coming from the leading edge. in order to guide the flow coming from the central body 37 parallel to the main axis X of the turbomachine, the trailing edge has a leakage profile PR3 parallel to the direction of air flow, otherwise known as the profiles PRI and PR3. do not have the same orientation and form an acute angle s between 2 ° and 10 °, typically between 3 ° and 4 °. Preferably, the leading edge 30 represents between 10% and 20% of the length L 30 of the fin 20, and / or the central body represents between 70% and 85% of the length L of the fin 20 and / or the trailing edge represents between 5% and 10% of the length L of the fin 20.
    [0009] An example of a curved profile PR2 of the central body 37 of the fin 20 is described in relation to FIG. 7. In this figure, the Bezier curve comprises four control points P0, P1, P2, P3. In particular, the first point PO is placed at 0% of the central body 37 (ie at the very beginning of the central body 37) the fourth point P3 is placed at 100% of the central body 37 (that is, at the beginning of the central body 37). ie at the end of the central body 37). The second point P1 can be placed between 0% and 70% of the central body 37, the third point P2 is placed according to the position of the second point P1 and can be placed between 20% and 100% of the central body. It is therefore possible for the third point P2 to coincide with the second point P1, the curve then being defined by three points. The location of these points is adapted so that the bending distribution minimizes the pressure drops and adapts to the chosen fin length. If the fins must be shorter, the curvature is increased to ensure the same exchange surface. The control points are located on the same side of the curve in FIG. 7 and constitutes a preferred embodiment of the invention. However it is also possible to position the second point P1 and third point P2 on either side of the curve to obtain a point of inflection. This embodiment increases the curvature and therefore the necessary length, always minimizing as far as possible the pressure drops.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Heat exchanger (12) for an air circulation duct (10) of a turbomachine, the heat exchanger being configured to be traversed by a fluid to be cooled and comprises a plurality of fins (20) projecting from relative to a support surface (18, 19), each fin (20) extends axially along a length (L) in the air flow direction and comprises a leading edge (30) and a trailing edge ( 32), the heat exchanger (12) being characterized in that each fin (20) further comprises a central body (37), between the leading edge (30) and the trailing edge (32), the central body (37) having in a plane (P ') parallel to the support surface a curved central profile (PR2).
    [0002]
    2. Heat exchanger (12) according to claim 1, wherein the curved central profile (PR2) of the fin is defined by a Bézier curve such that nn P (u) = Bi, n! Pi = (n: (1 - i = 0 i with u a parameter varying from zero to one to characterize a point of the curve, Pi the coordinates, in the plane (P ') parallel to the support surface, of the control points of the Bézier curve and n the number of control points, not being greater than or equal to three, the second point (P1) can be placed between 0% and 70% of the central body (37), the third point (P2) is placed in function the position of the second point (P1) and can be placed between 20% and 100% of the central body.
    [0003]
    3. heat exchanger (12) according to one of the preceding claims, wherein the leading edge (30) and the trailing edge (32) respectively have a profile (PRI) and attack profile (PR3). ) leakage in the plane (P ') parallel to the support surface, the profile (PRI.) attack forming an acute angle (a) with the profile (PR3) leak.
    [0004]
    4. Heat exchanger (12) according to the preceding claim, wherein the acute angle (a) is between 2 ° and 10 °, typically between 3 ° and 4 °.
    [0005]
    5. Heat exchanger (12) according to one of the preceding claims, wherein the leading edge is between 10% and 20% of the length (L) of the fin (20).
    [0006]
    6. Heat exchanger (12) according to one of the preceding claims, wherein the central body is between 70% and 85% of the length (L) of the fin (20).
    [0007]
    7. Heat exchanger (12) according to one of the preceding claims, wherein the trailing edge is between 5% and 10% of the length (L) of the fin (20).
    [0008]
    8. Turbomachine comprising a heat exchanger according to one of the preceding claims.
    [0009]
    9. A turbomachine according to the preceding claim, comprising an air circulation channel (10) delimited between a first structure (18) and a second structure (19), the support surface of the exchanger being a surface of one of the structures. fixed, the circulation channel (10) being in particular a secondary vein of the gases of an intermediate casing of the turbojet of said turbomachine.
    [0010]
    10. A turbomachine according to the preceding claim and claims 3 and 4, wherein the heat exchanger is positioned with the profile (PR1) of driving forming the angle (a) acute relative to an axis parallel to the direction of circulation. of air and the profile (PR3) leak parallel to the direction of air flow.
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    法律状态:
    2016-01-15| PLFP| Fee payment|Year of fee payment: 3 |
    2017-01-06| PLFP| Fee payment|Year of fee payment: 4 |
    2017-11-10| CD| Change of name or company name|Owner name: SNECMA, FR Effective date: 20170713 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 5 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 7 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 8 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1400220A|FR3016956B1|2014-01-29|2014-01-29|HEAT EXCHANGER OF A TURBOMACHINE|
    FR1400220|2014-01-29|FR1400220A| FR3016956B1|2014-01-29|2014-01-29|HEAT EXCHANGER OF A TURBOMACHINE|
    GB1501092.9A| GB2524623B|2014-01-29|2015-01-22|Heat exchanger of a turbomachine|
    US14/605,223| US10066875B2|2014-01-29|2015-01-26|Heat exchanger of a turbomachine|
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