• 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 proposes an air flow rectification assembly, comprising: at least one stator blade (21), - a structural arm (30), the blade and the arm extending radially about an axis ( XX), the arm having: - an upstream end portion (31), having a stator blade profile, and comprising a leading edge (310) aligned with that of the blade, a downstream portion (33) ), and an intermediate portion (34) comprising an extrados wall (44) extending between an upstream end point (A) and a downstream end point (B), characterized in that the upstream end point is distant from the d attacking the arm by an axial distance (xA) between 0.2c and 0.5c, c being the length of the axial cord of the blade, and the angle (αA) of the tangent to the wall extrados extreme point upstream is equal to that at the extreme point down to a degree.
    公开号:FR3032480A1
    申请号:FR1551011
    申请日:2015-02-09
    公开日:2016-08-12
    发明作者:Henri-Marie Damevin；Philippe Jacques Pierre Fessou；Vianney Christophe Marie Maniere；Michael Franck Antoine Schvallinger
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The invention relates to a turbomachine air flow rectification assembly comprising stator vanes and one or more structural arms. The invention applies in particular to double-flow turbomachines.
    [0002] STATE OF THE ART A turbofan engine for aerospace propulsion is shown in FIG. It comprises a fan 10 delivering a flow of air, a central portion, called primary flow Fp, is injected into a compressor 12 which feeds a turbine 14 driving the fan. The peripheral part, called secondary flow Fs, of the air flow is in turn ejected to the atmosphere to provide the bulk of the thrust of the turbomachine 1, after having crossed a ring 20 of blades 21 fixed downstream of the blower. This ring, called the rectifier 20 (also known by the acronym OGV for "Outlet Guide Vane"), straighten the secondary air flow at the output of the fan, while limiting losses to the maximum. In the same figure is shown a structural arm 30, which connects the ferrule 16 of the intermediate casing to the hub 17 of the intermediate casing, thereby contributing to support and maintain in position the (s) shaft (s) motor 18 and ensure the holding structural of the whole. The structural arm also has the function of allowing the transmission of movement or fluids between the turbomachine and the rest of the aircraft on which it is mounted. To do this, the structural arm is hollow, and can accommodate pipes, shafts, etc..
    [0003] Several types of structural arms exist, depending on their role and their position in the turbomachine. For example so-called "main arms" whose main function is to support the turbomachine under the wing of the aircraft, are arranged at "6h" and "12h", that is to say vertically relative to the airplane placed on a horizontal ground (terminology compared with the position of the needles of a watch). Structural arms called "auxiliary" do not have the main function of supporting the turbomachine but to achieve a power transmission, being hollow to contain a transmission shaft. These arms are positioned for example at "8h", that is to say oblique to the vertical.
    [0004] 3032480 2 All types of structural arms are also used to move servitudes of the turbomachine to the rest of the aircraft, that is to say for example oil pipes, fuel, etc.. In order to reduce the mass of a turbomachine and improve its performance, it has been proposed to combine secondary and structural arm functions in one and the same room, and this for all types of structural arms. . As represented in FIG. 1b, so-called "integrated" stator vanes have been proposed, formed by a structural arm 30, in this case of the main type described above, of which an upstream portion is careened to present a profile. aerodynamic stator vane. Such a structural arm therefore has geometrically constrained parts which are: an upstream end portion 31, whose geometry must be that of a stator blade, a hollow zone 32 for transmitting servitudes, in which are arranged pipes, connections, if necessary transmission shafts, etc. This zone takes into account a large number of constraints of the congestion type of easements, operating and assembly games, thickness of material, etc., it is said to be prohibited from drawing (or in the English terminology: "keep-out zone" ), that is to say, it must be kept unchanged in case of change of geometry of the structural arm, and - A downstream portion 33 forming the actual structural arm, that is to say, 25 supporting the turbomachine in position under the wing of the aircraft while supporting the forces induced by the weight of the turbomachine. A structural arm respecting these stresses therefore has an extrados wall 40 successively formed by: the extrados wall of the upstream end portion, corresponding to an extrados wall of the straightener blade; a transition wall bordering the forbidden zone; drawing 32, this wall can be made of sheet metal to lighten the turbomachine, and - the upper surface of the downstream part.
    [0005] 3032480 3 The extrados wall must in particular respect a continuity of surfaces and tangents at the transitions between its different parts. Due to differences in size, in a direction transverse to the axis of the turbomachine, the upstream end portion 31 and the downstream portion 33, the extrados wall 5 of the resulting structural arm may have a relatively marked concavity. However, from an aerodynamic point of view, this solution is not favorable because it causes a slowing down of the flow in the concave zone of the wall formed at the level of the transition zone.
    [0006] As shown in FIG. 1c, on which a structural arm is seen on its extrados side while looking towards the upstream side of the air flow, in this zone of low speed, the secondary flows of Ec corners coming from the foot and the head of the upstream end portion in the form of a straightener blade become stronger and can degenerate into detachment and / or recirculation.
    [0007] This can result in significant pressure losses in the flow, as well as static pressure distortions upstream of the rectifier which can adversely affect the aerodynamic and aeroacoustic performance of the blower. Existing solutions such as, for example The blades of the stator, the arrangement of the blades, etc., each have limitations related to the mechanical strength in statics and dynamics of the vanes, the manufacturability of the vanes, etc. In addition, these solutions, if they prepare the flow upstream of the arms, at the upstream end portion, do not prevent the appearance of certain secondary flows that can develop at the level of the wall of the transition bordering the forbidden zone of drawing. There is therefore a need to remedy the problems raised by this geometry. PRESENTATION OF THE INVENTION The aim of the invention is to overcome the drawbacks of the prior art by proposing an air flow rectification assembly having improved aerodynamic performance compared to the prior art. An object of the invention is to provide a set of air flow rectification whose geometry removes the risk of recirculation of the air flow on the wall 3032480 4 extrados of a structural arm comprising an upstream blade end of rectifier. In this regard, the invention relates to a turbomachine air flow rectification assembly, comprising: - at least one stator blade, comprising a leading edge and a trailing edge, and - a structural arm wherein the blade and the arm extend radially about an axis of the turbomachine, and the structural arm has: an upstream end portion with respect to the direction of flow of air in the turbomachine, having a stator blade profile, and comprising a leading edge aligned with the leading edge of the blade, - a downstream portion, and 15 - an intermediate portion connecting the upstream end portion to the downstream portion, comprising an extrados wall extending between an upstream end point and a downstream end point of determined axial position, characterized in that the upstream end point is located at a distance, in the axial direction, from the leading edge of the arm between 0.2c and 0.5c, where c is the length of the axial cord of the straightener blade; and in that the angle of the tangent to the extrados wall at the upstream end point is equal to that of the tangent to the wall at the extreme downstream point to a degree.
    [0008] Advantageously, but optionally, the straightening assembly according to the invention further comprises at least one of the following features: the upstream end point is situated at a distance, in the axial direction, from the leading edge of the arm , between 0.2 and 0.3c, preferably equal to 0.3c. The downstream end point is located at a distance, in the axial direction, from the leading edge of the arm, greater than the length c of the axial cord of the stator vane.
    [0009] The invention also relates to a turbofan engine, comprising a secondary flow rectifier comprising a plurality of blades arranged radially around an axis of the turbomachine, and at least one structural arm, characterized in that at least one structural arm and a straightener blade form a straightening assembly according to the foregoing description. The proposed airflow rectification assembly has improved aerodynamic performance. The axial position of the upstream end point of the transition zone and the angle of the tangent at this point make it possible to reduce the concavity of the extrados wall of the structural arm at this transition zone. As a result, the airflow is little or not slowed, which hampers the development of the corner flows from the upstream end portion of the rectifier blade profile arm.
    [0010] Thus, the recirculation zones are attenuated or even annihilated, which makes it possible to reduce the total pressure losses in the rectifier by about 0.1%, as well as the level of static pressure distortion in the rectifier. the order of 0.2%.
    [0011] DESCRIPTION OF THE DRAWINGS 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. , schematically represents a double-flow turbomachine. FIG. 1b, already described, shows a schematic developed view of an assembly comprising a structural arm between two secondary flow straightener vanes; FIG. 1c, already described, represents the aerodynamic effects of a structural arm including a zone transition between the upstream portion of the stator vane and the downstream portion of the actual structural arm has a marked concavity, - Figure 2a shows an air flow rectification assembly according to an embodiment of the - Figure 2b schematically illustrates a turbomachine according to one embodiment of the invention. FIG. 3 diagrammatically represents the flow of air between a structural arm and a stator blade represented on the upper surface of the latter. DETAILED DESCRIPTION OF AT LEAST ONE EMBODIMENT OF THE INVENTION With reference to FIG. 2b, there is shown a turbomachine 1 with a double flow comprising, as previously described, a blower 10 and an OGV-type rectifier 20, for rectifying a secondary flow FR from the blower 10. The rectifier comprises a plurality of vanes 21 regularly distributed around a ring (not shown) centered on an axis XX of the turbomachine, corresponding to the axis of the motor shaft . In addition, the turbomachine 1 comprises at least one structural arm 30 described in more detail below. FIG. 2a shows a developed view of a corner sector 20 around the axis XX covered by two blades 21 of the straightener, between which there is a structural arm 30. Another of the arms 30 defines with it a flow vein the air in which the air moves from upstream to downstream, shown in the figure from left to right. In the following, the terms upstream and downstream are always used with respect to the direction of the air flow in the turbomachine, and in particular with respect to the direction of the flow of air in the veins, from left to right on the Fig. Air flow rectification assembly is also called an assembly comprising a structural arm 30 and a stator blade 21, for example a blade 21 adjacent to the arm, advantageously on its extrados side. Indeed the geometry of the arm described below improves the flow of air between the arm and the blade located on the upper arm. Each blade 21 conventionally comprises a leading edge 22 and a trailing edge 23. The axial cord of a blade 21 is the segment extending parallel to the axis XX, 3032480 7, of the axial position of the leading edge. 22 at the axial position of the trailing edge 23. The length of the axial string of the blades 21 is denoted c. The structural arm 30 is of the "integrated stator vane" type, that is to say that it comprises a upstream end portion 31 having the profile of a stator blade 5. Thus, the upstream end portion 31 of the structural arm 30 is identical to the upstream end of each stator vane 21. In particular, the upstream end portion 31 has an aligned leading edge 310. with that of the blades 21 of the rectifier 20, that is to say at the same level with respect to the axis XX, and has, at least at the level of its leading edge, the same thickness and the same angle of camber a blade 21 of the straightener 20, the camber angle being the angle between the camber line, midway between the intrados surface and the extrados surface of a blade 21, with the axis XX. The upstream end portion 31 of the structural arm 30 is defined axially downstream by a point A and upstream by the leading edge 310. All the portion of the arm 15 extending axially from the leading edge 310 at the point A is geometrically constrained to be identical to the portion of the blades 21 of the rectifier extending from the leading edge of each blade to a section at the same axial position as the point A.
    [0012] The structural arm 30 also comprises a downstream portion 33, and an intermediate portion 34 connecting the upstream end portion with the downstream portion 33. The structural arm 30 is preferably of the "main" arm type indicated above, whose function main is to support the turbomachine under the wing of the aircraft while supporting the efforts generated by the weight of the turbomachine.
    [0013] This function is fulfilled by the downstream part 33, whose walls are advantageously made in the foundry to withstand these important efforts. The walls of the intermediate portion 34 have the function of connecting the upstream portion 31 with the downstream portion 33 avoiding any discontinuity surface or tangency. On the other hand, they do not need to bear the weight of the turbomachine as those of the downstream part 33. Consequently, they are advantageously made of sheet metal in order to lighten the weight of the turbomachine. In addition, the intermediate portion 34 includes a so-called forbidden zone 32 for drawing, which is a housing dedicated to the implantation of the servitudes, and in particular to the 3032480 8 housing of pipes, for example of oil or fuel, of electrical connections, the transmission shafts, etc. The structural arm 30 has an extrados wall 40 formed by: - an extrados wall 41 of the upstream end portion, 5 - an extrados wall 44 of the intermediate portion 34, and - an extrados wall 43 of the downstream portion 33. The extrados wall 44 of the intermediate portion is delimited by two end points respectively upstream by the point A and downstream by a point B. The upstream end point A is connected to the extrados walls of the part d upstream end 41 and the intermediate portion 44. As indicated above, the upstream end portion 31 of the arm is constrained to be identical to a corresponding upstream portion of a blade 21. Therefore, axial position (relative to at the axis XX) fixed one point on the extrados wall 41 of the upstream part, the position of this point in azimuth (y-axis in the figure) is also fixed.
    [0014] The downstream end point B is at the connection between the extrados walls of the intermediate portion 44 and the downstream portion 43. The geometry described hereinafter for the structural arm allows the extrados wall of the intermediate portion 34 to be the least concave possible to reduce air recirculation.
    [0015] In the first place, the axial position xB of the extreme point B must be at a distance from the axial position of the leading edge of the arm greater than or equal to the length of the rope of a blade 21, and preferably greater than . Note: xB> C Taking as origin of the X-X axis the axial position of the leading edge of the arm and vanes. Indeed, the greater the axial distance between the point B and the point A, the greater the transition made by the wall of the intermediate portion 44 is soft and limits the concavities. In addition, the axial position xA of the upstream end point A is preferably at a distance, measured in the direction of the axis XX, from the axial position of the leading edge 310 of the arm, between 0.2c and 0 , 5c. Note: 0.2c xA 0.5c 3032480 9 The fact that the point A is at an axial distance from the leading edge 310 of at least 20% of the rope allows the upstream end portion 31 of the arm be long enough to present on the incoming air flow an effect similar to that of a stator blade 21. In particular, this limits the static pressure distortion on the entire rectifier 20, and the upward pressure distortion of the fan upstream of the rectifier. The acoustic and aerodynamic performance of the blower are thus improved. In addition, the fact that the point A is at an axial distance from the leading edge of less than 50% of the length of the rope of a blade allows it to be sufficiently far away from the point B, which lengthens the length of the intermediate portion and reduces the concavity. On the other hand, positioning the point A beyond this axial distance would bring it closer to the forbidden zone of drawing 35. Consequently, the upper wall 44 of the intermediate portion should have an increased concavity to circumvent this zone and connect the point B, which would increase the recirculation of air at this wall. Preferably, the axial position xA of the upstream end point A is even at a distance from the leading edge 310 less than 0.3c, and very advantageously equal to 0.3c, to optimize the effects described above.
    [0016] In addition, the angle A of the tangent to the extrados wall 40 of the arm 30 with respect to the axis XX at the point A is advantageously close to that ag of the tangent to the wall 40 at the point B Preferably, the angle α A is equal to the angle λ to the nearest degree - aA can therefore take all the values between λ-1 and λ + 1: aA = a B 1 Thus the concavity of the upper wall 44 of the intermediate part is minimized. Where appropriate, the angle de of the tangent to the point B, and / or the position, on an axis orthogonal to the axis XX, of the point B, which are normally imposed as a function of the geometry of the downstream portion 33 of the structural arm, and the azimuth position of the arm 30 relative to the rectifier, may be slightly adapted to respect the above relationship, since this relation corresponds to: tan aA = tan (ΔB ± 1 °) YAB XAB Where yAB is the distance, measured on an axis orthogonal to the axis XX, between the point A and the point B, and xAB is the distance, measured axially that is to say parallel to the axis XX, between these same points. With reference to FIG. 3, the flow of air is represented in a straightening assembly comprising a blade 21 and a structural arm 30 conforming to the geometry described above, the structural arm being seen on its extrados side while looking at upstream. It is found that, rather than trying to refine the arm to reduce aerodynamic obstruction, it is preferable to thicken the extrados side by reducing the concavity of the wall 44 at the intermediate portion 34 to limit the airflow. appearance of recirculations.
    权利要求:
    Claims (4)
    [0001]
    REVENDICATIONS1. A turbomachine airflow rectifying assembly, comprising: - at least one stator blade (21), comprising a leading edge (22) and a trailing edge (23), and - a structural arm (30) , wherein the blade (21) and the arm (30) extend radially about an axis (XX) of the turbomachine, and the structural arm has: - an upstream end portion (31) with respect to the flow direction of air in the turbomachine, having a stator blade profile, and comprising a leading edge (310) aligned with the leading edge (22) of the blade, - a part downstream (33), and - an intermediate portion (34) connecting the upstream end portion (31) to the downstream portion (33), comprising an extrados wall (44) extending between an upstream end point (A) and a downstream end point (B) of determined axial position, characterized in that the upstream end point (A) is located at a distance (xA), in the axial direction, from the leading edge (310) of the arm e between 0.2c and 0.5c, where c is the length of the axial cord of the stator blade (21), and in that the angle (aA) of the tangent to the extrados wall (44) at extreme point upstream (A) is equal to that of the tangent (aB) to the wall (44) at the extreme downstream point (B) to a degree.
    [0002]
    The airflow rectifying assembly of claim 1, wherein the upstream end point (A) is located at a distance (xA), in the axial direction, from the leading edge (310) of the arm, between 0.2 and 0.3c, preferably equal to 0.3c.
    [0003]
    The airflow rectifying assembly according to one of claims 1 or 2, wherein the downstream end point (B) is located at a distance (xB), in the axial direction, from the leading edge (310). ) of the arm, greater than the length c of the axial cord of the stator blade (21). 3032480 12
    [0004]
    4. A turbofan engine (A) comprising a secondary flow rectifier (20) comprising a plurality of blades (21) arranged radially about an axis (XX) of the turbomachine, and at least one structural arm ( 30), characterized in that at least one structural arm and a stator blade form a straightening assembly according to one of the preceding claims.
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    法律状态:
    2016-02-08| PLFP| Fee payment|Year of fee payment: 2 |
    2016-08-12| PLSC| Publication of the preliminary search report|Effective date: 20160812 |
    2017-02-01| PLFP| Fee payment|Year of fee payment: 3 |
    2018-01-23| PLFP| Fee payment|Year of fee payment: 4 |
    2018-06-29| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 6 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 7 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
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    FR1551011|2015-02-09|FR1551011A| FR3032480B1|2015-02-09|2015-02-09|AIR RECOVERY ASSEMBLY WITH IMPROVED AERODYNAMIC PERFORMANCE|
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    EP16705981.5A| EP3256697A1|2015-02-09|2016-02-09|Turbine engine air guide assembly with improved aerodynamic performance|
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