• 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 blade (11) for a turbomachine turbine such as a turboprop or a turbojet engine, this blade (11) comprising a foot (12) carrying a blade, this blade (11) comprising at least one circulation duct. air to cool it in operation, this duct comprising at the level of the blade root (12) an intake portion (26a-26e) for collecting the cooling air, this intake portion (26a-26e) s extending from a lower face (21) of the blade root (12) opposite to the blade. At least one intake portion (26a-26e) is provided with a helical member (33) for rotating the cooling air to improve cooling efficiency.
    公开号:FR3052183A1
    申请号:FR1655014
    申请日:2016-06-02
    公开日:2017-12-08
    发明作者:Erwan Daniel Botrel；Sebastien Serge Francis Congratel；Simon Parinet
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    TURBINE DAWN COMPRISING A PORTION OF COOLING AIR INTAKE INCLUDING A HELICAL ELEMENT FOR ROTATING
    COOLING AIR
    DESCRIPTION
    TECHNICAL FIELD The invention relates to a turbine blade intended to equip, for example, an aircraft engine of the turbofan or turbojet type, or an industrial gas turbine.
    STATE OF THE PRIOR ART
    In such a motor 1 shown in Figure 1, the outside air is admitted into an inlet sleeve 2 to pass through a fan 3 comprising a series of rotating blades before splitting into a central primary flow and a secondary flow surrounding the flow primary.
    The primary flow is then compressed in a first and a second compression stage 4 and 6 before arriving in a combustion chamber 7, after which it relaxes by passing through a set of turbines 8 before being evacuated backwards. generating thrust. The secondary flow is propelled directly backwards by the fan into a vein delimited by the housing 9 to generate a complementary thrust.
    The expansion in the turbines, which drives the compressor and the blower, takes place at high temperature because it occurs immediately after combustion. This turbine is thus designed and dimensioned to operate under severe conditions of temperature, pressure and fluid flow.
    It comprises series of blades oriented radially and regularly spaced around a rotation shaft of the engine, and which are subjected to the most severe conditions with respect to the blades of the first stages of expansion of this turbine, namely the stages the closest to the combustion chamber 7 commonly called high pressure stages.
    The increased performance requirements lead to the design of smaller engines operating in harsher environments, which implies improving the cooling efficiency of these blades.
    This cooling is ensured by circulating in these blades of the colder air taken from the compressor and admitted at the bottom of the blade to walk along internal circuits. This air is evacuated by through holes distributed on the wall of the blade and which also allow to create on its external surface a film of air colder than the surrounding air. The use of this cooling air is unfavorable in terms of performance since it is reinjected into the primary flow only at the blades, so that the energy invested in compressing it is not fully restored in terms of thrust. This is the reason why it is necessary to cool the blades as efficiently as possible using as little air as possible. In other words, the cooling air saving reduces the specific consumption of the engine. For this purpose, the inner regions of the dawn include artifices, that is to say, internal reliefs that disrupt the flow of air to increase the efficiency of heat transfer. In addition, the flow distribution is optimized to ensure a minimum overpressure rate at the holes to avoid reintroduction of hot air from the primary flow in the dawn.
    The object of the invention is to provide a solution to improve the transfer of heat from the blade to the cooling air.
    SUMMARY OF THE INVENTION For this purpose, the subject of the invention is a turbine engine turbine blade such as a turboprop engine or a turbojet engine, this blade comprising a foot carrying a blade, this blade comprising at least one circulation duct. air to cool it in operation, this duct comprising at the level of the blade root an intake portion for collecting the cooling air, this intake portion extending from a lower face of the blade root which is opposite characterized in that at least one intake portion is equipped with a helical element for swirling the cooling air to improve the cooling efficiency thereof.
    With this arrangement the admitted air for the cooling of the blade is immediately rotated as soon as it enters the blade root to promote an increased heat exchange with the dawn from the beginning of its course therein. The invention also relates to a blade thus defined, obtained by molding and in which each helical element is molded with the blade. The invention also relates to a dawn thus defined, obtained by additive manufacturing. The invention also relates to a blade thus defined, comprising a calibrated plate having holes for adjusting the flow rate of air admitted into each conduit, this plate being attached to the underside of the blade, and wherein each helical element is carried by this calibrated plate being rigidly secured to this plate. The invention also relates to a blade thus defined, wherein the calibrated plate is secured to the underside of the blade root by welding or brazing. The invention also relates to a dawn thus defined, comprising a helical element having a height of between twenty percent and one hundred percent of the height of the intake portion it equips. The invention also relates to a blade thus defined, comprising a helical element having a total torsion angle of between thirty degrees and one thousand eighty degrees. The invention also relates to a blade thus defined, comprising a helical element having a non-constant pitch which decreases from the base of this element to the top of this element. The invention also relates to a turbomachine turbine comprising a blade thus defined. The invention also relates to a turbomachine comprising a turbine thus defined.
    BRIEF DESCRIPTION OF THE DRAWINGS
    Figure 1 already described is a sectional side view of a turbofan engine of the prior art;
    FIG. 2 is an overall perspective view of a high-pressure turbojet turbine blade;
    Figure 3 is a schematic perspective view of a regular helical shape;
    Figure 4 is a perspective view of a helical element of the blade according to the invention;
    Figure 5 is a perspective view schematically showing a helical element implanted in an intake portion of the blade root according to the invention;
    Figure 6 is a perspective view of a wafer carrying a helical element according to the invention;
    Figure 7 is a perspective view illustrating the mounting of a wafer carrying a helical element for the blade according to the invention;
    Figure 8 is a perspective view showing a plate carrying a helical element fitted to the blade according to the invention;
    Figure 9 is a perspective view showing a lower face of the blade root to which is welded a wafer carrying a helical element according to the invention.
    DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS The idea underlying the invention is to rotate the air during its admission to the blade root, by means of a helical shape, to feed the circuit with a air that is swirling to improve heat exchange.
    Such a blade, which is indicated by 11 in FIG. 2, comprises a foot 12 by which it is fixed to a turbine disk (not shown), and a blade 13 carried by this foot 12, with an intermediate region 14 called a platform. extending approximately parallel to the axis of rotation AX of the motor.
    The blade 13 extends in a direction of wingspan EV close to a radial direction relative to the axis AX, from a base 15 through which it is connected to the platform 14, to a vertex 16. extends longitudinally from a leading edge 18 to a trailing edge 19 which are parallel to the span direction EV, the leading edge 18 corresponding to the region upstream AM of the blade 13, the trailing edge 19 corresponding to its downstream region AV, relative to the direction of flow of the fluid. The blade 11, that is to say the assembly that constitutes the foot 12 and the blade 13 with the platform 14 is a monoblock piece from the foundry here comprising five internal ducts in which circulates cooling air. Each duct has an intake portion in the form of a smooth cylindrical hole extending into the foot 12, which opens into a lower face 21 of the foot 12 to collect the air, and which on the other hand extends in the dawn to form a duct for air circulation.
    The walls of the blade 13 comprise a series of through-holes, 22, 23 and slots 24 ensuring the evacuation of the cooling air which circulates in the internal pipes of this blade 13.
    The five cylindrical inlet portions extending in the foot 12 are marked 26a-26e in the figures, the corresponding pipes that snake in the blade 13 not being shown to simplify the views.
    These five intake portions 26a-26e extend into the foot 12, which in turn has a general box-like shape delimited by its flat bottom face 21 parallel to the axis AX, by an upstream face and a downstream face 27, 28 substantially flat and oriented normal to the axis AX, and two side faces 29, 31. In practice, the lateral faces of the foot have crenellated forms with which this foot 12 is the fastener by which the dawn is secured to the disk, the lower face 21 being the one opposite to the blade 12.
    According to the invention, provision is made to place in one or more of the smooth cylindrical inlet portions a helical element, that is to say of the type of the helicoid 32 shown in FIG. 3 for swirling the air of cooling at its admission in the blade root 12. The helicoid 32 of Figure 3 has a regular shape similar to that of a worm, that is to say having a pitch that is constant while along its height.
    But the shape chosen for the helical element of the blade is advantageously optimized to advantageously have a step which decreases along its height, so as to rotate the air admitted at the foot of the blade in a progressive manner to limit the loss of charge that it induces. In this context, the variation of the pitch is not necessarily linear.
    The pitch, which is defined as the height on which the edge of the helical element 33 describes a complete revolution about its axis, decreases from the base 34 of the element, situated at the level of the face 21, to its top 36 located inside the intake portion.
    In other words, this helicoidal element 33 has at its base 34 an almost flat shape, corresponding to a small twist or a very large pitch, and instead has at its summit 36 a large twist corresponding to a much smaller pitch .
    In the example of Figure 4, the helical element 33 has a total torsion angle of one thousand eighty degrees, which is formed over its entire height. In general, this total torsion angle is advantageously between thirty degrees and one thousand eighty degrees, ie between one twelfth of a turn and three turns.
    In the example of the figures, the height of the helical element 33 corresponds to that of the cylindrical inlet portion 26a which is of the order of half the height of the blade root 12 measured radially with respect to the axis AX rotation of the motor.
    But the height of the helical element does not necessarily correspond to that of the intake portion: it is also determined with other parameters defining this helical element, such as in particular the step and its evolution law, starting from numerical simulations of operation. This height is advantageously between twenty and one hundred percent of the height of the intake portion. In general, this helicoidal element 33 has a shape corresponding to that of a rectangular plate which is twisted by a half-turn around a radial axis AR with respect to the axis AX, whose orientation is close to that of the axis of span EV of the dawn. As will be understood, the rectangular base plate has a length corresponding to that of the cylindrical intake portion and a width corresponding to the diameter of this portion.
    As shown in FIG. 5, this helical element 33 is integrated with the intake portion 26b of the blade 12 so that its base is located at the face 21 of the blade root 12 and that its vertex is located in the body of the blade root 12 at the region in which this intake portion opens into a cooling portion of the blade. The helicoidal element 33 is manufactured with the blade by molding, as is the case in FIG. 5, so that the molded blade immediately integrates into its intake portion or portions 26a-26e one or more helical elements rotating the cooling air to promote the effectiveness of this cooling.
    To simplify the manufacture, and also to integrate the element to a blade which is devoid of it, this helicoidal element 33 is advantageously carried by a calibrated plate 37, as illustrated in FIG. 6, which is attached and welded against the face 21 of the blade root 12 after molding the body of this blade 12 as shown schematically in FIG. 9.
    As can be seen in FIG. 6, such a calibrated plate 37 has a planar rectangular shape comprising, for each intake portion 26a-26e, a corresponding hole 38a-38e having a section whose area is calibrated, to adjust the air flow rate. entering each intake portion 26a-26e vis-à-vis the operating constraints. The helical element 33 has its base 34 which extends into the hole 38a of the plate 37 to divide it into two parts of the same sections, and it extends with respect to this plate 37 so that its torsion axis is oriented substantially perpendicular thereto in the example of the figures. The helical element 33 and the plate 37 may be separate elements joined to each other by welding, before mounting the assembly and fixing the plate 37 to the face 21 of the foot 12 by means for example points 39-48 of the edges of this plate 37 to the face 21, as in Figure 9. In this case, the ends of the base 34 of the helical element are welded to the inner edge of the corresponding calibrated hole for fixing from this element to the plate.
    As illustrated in FIG. 7, the mounting of the plate 37 with its helicoidal element (s) 33 mainly consists in presenting it facing the face 21, to engage each helical element in the corresponding intake portion until at the arrival of the plate 37 in contact with the face 21. The plate can then be welded to the face 21.
    In the example of the figures, the blade is equipped with a single helical element 33 fitted to the intake portion 26b, but the blade can also be equipped with several helical elements equipping all or part of the different intake portions. that includes his foot. These helical elements can be molded with the blade body or reported a posteriori.
    In the case of several helical elements, they may have different characteristics in particular as regards their torsion angles, the evolution of their torsion from their bases to their respective vertices, and their heights. These characteristics are determined by calculation or simulation so as to optimize the cooling for each intake portion. The blade may thus comprise a helical element in each intake portion and each helix may be different from the others.
    The helical elements can be manufactured separately, for example by twisting rectangular sheet elements, and reported to the calibration plate by welding. They can also be obtained directly by additive manufacturing of the blade, or be manufactured in one piece with the calibration plate by foundry or by additive manufacturing.
    The choice of helical elements carried by the calibration plate to be reported at the blade root allows in particular to equip existing blades of helical elements, without having to change the design of the blade body.
    As will be understood, the helical elements rotate the air as soon as it enters the blade root to swirl it so as to increase the heat exchange in the ducts by establishing turbulence. These exchanges are thus improved including in the intake portions passing through the blade root which brings among others a greater uniformity in the cooling of this blade contributing to increase its mechanical strength.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. A blade (11) of a turbomachine turbine such as a turboprop or a turbojet engine, this blade (11) comprising a foot (12) carrying a blade (13), this blade (11) comprising at least one circulation duct air to cool it in operation, this duct comprising at the level of the blade root (12) an intake portion (26a-26e) for collecting the cooling air, this intake portion (26a-26e) s extending from a lower face (21) of the blade root (12) which is opposite to the blade (13), characterized in that at least one intake portion (26a-26e) is equipped with a helical element (33) to swirl the cooling air to improve cooling efficiency.
    [2" id="c-fr-0002]
    2. blade according to claim 1, obtained by molding and wherein each helical element (33) is molded with the blade (11).
    [3" id="c-fr-0003]
    3. blade according to claim 1, obtained by additive manufacturing.
    [4" id="c-fr-0004]
    4. blade according to one of claims 1 to 3, comprising a calibrated plate (37) having holes (38a-38e) for adjusting the flow of air admitted into each conduit, this plate being attached to the underside (21 ) of the blade (12), and wherein each helical element (33) is carried by this calibrated plate (37) being rigidly secured to this plate (37).
    [5" id="c-fr-0005]
    5. blade according to claim 4, wherein the calibrated plate (37) is secured to the underside of the blade root (12) by welding or brazing.
    [6" id="c-fr-0006]
    6. blade according to one of claims 1 to 5, comprising a helical element (33) having a height of between twenty percent and one hundred percent of the height of the intake portion (26a-26e) that team.
    [7" id="c-fr-0007]
    7. blade according to one of the preceding claims, comprising a helical element (33) having a total torsion angle of between thirty degrees and one thousand eighty degrees.
    [8" id="c-fr-0008]
    8. blade according to one of the preceding claims, comprising a helical element (33) having a non-constant pitch which decreases from the base (34) of this element to the top (36) of this element (33).
    [9" id="c-fr-0009]
    9. Turbine turbine engine comprising a blade according to one of the preceding claims.
    [10" id="c-fr-0010]
    10. Turbomachine comprising a turbine according to the preceding claim.
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    同族专利:
    公开号 | 公开日
    FR3052183B1|2020-03-06|
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    WO2017207924A1|2017-12-07|
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    法律状态:
    2017-04-27| PLFP| Fee payment|Year of fee payment: 2 |
    2017-12-08| PLSC| Search report ready|Effective date: 20171208 |
    2018-06-05| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-05-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 5 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1655014A|FR3052183B1|2016-06-02|2016-06-02|TURBINE BLADE COMPRISING A COOLING AIR INTAKE PORTION INCLUDING A HELICOIDAL ELEMENT FOR SWIRLING THE COOLING AIR|
    FR1655014|2016-06-02|FR1655014A| FR3052183B1|2016-06-02|2016-06-02|TURBINE BLADE COMPRISING A COOLING AIR INTAKE PORTION INCLUDING A HELICOIDAL ELEMENT FOR SWIRLING THE COOLING AIR|
    EP17730882.2A| EP3464824B1|2016-06-02|2017-05-31|Turbine vane including a cooling-air intake portion including a helical element for swirling the cooling air|
    CN201780034159.7A| CN109219687A|2016-06-02|2017-05-31|Including the turbine vane comprising the cooling air air inlet parts for making the screw element of cooling air eddy flow|
    US16/306,205| US20190292918A1|2016-06-02|2017-05-31|Turbine vane including a cooling-air intake portion including a helical element for swirling the cooling air|
    PCT/FR2017/051359| WO2017207924A1|2016-06-02|2017-05-31|Turbine vane including a cooling-air intake portion including a helical element for swirling the cooling air|
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