• 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 internal cooling of the blades of the turbines in the turbomachines of aircraft is of limited effectiveness because of inhomogeneities of this cooling on each of the walls of the lower and upper surfaces. To remedy this problem, it is proposed a blade comprising a cooling circuit (50) of its blade (34), in which the interconnected series of cavities are such that the flow of air flows radially outwards along the the intrados wall (40) within cavities (52, 56), and radially inwardly along the extrados wall (42) within an extrados cavity (54) separated from the intrados cavities by an inner wall (58) of the blade. Thus, the Coriolis force deflects the flow of air to each of the intrados and extrados walls, thus limiting the inhomogeneities.
    公开号:FR3020402A1
    申请号:FR1453708
    申请日:2014-04-24
    公开日:2015-10-30
    发明作者:Charlotte Marie Dujol；Patrice Eneau；Brou De Cuissart Sebastien Digard；Matthieu Jean-Luc Vollebregt
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present invention relates to the field of aircraft turbomachines and more particularly relates to the cooling of the blades of turbines in such turbomachines. BACKGROUND OF THE INVENTION STATE OF THE PRIOR ART Within a turbomachine used to propel an aircraft, the blades of the turbines are subjected to the high heat of the combustion gases from the combustion chamber. To protect the blades from these high temperatures, it is known to cool the blades by means of cooling circuits formed by cavities formed inside the blades of the blades. These cooling circuits are generally fed with relatively fresh air taken from a compressor stage of the turbomachine. Nevertheless, the constant improvement in the performance of aircraft engines leads to an increase in the temperature of these combustion gases. Advances in the materials and coatings used to form the blades do not on their own compensate for the increase in temperature. Therefore, it is desirable to improve the performance of the blade cooling circuits. In the course of its research work, the Applicant has in particular discovered that a disadvantage of known cooling circuits lies in the inhomogeneity of the cooling on each of the intrados and extrados walls of the blades.
    [0002] The Applicant has identified a cause of such inhomogeneities, as will now be explained with reference to FIG. 1. FIG. 1 represents the blade 10 of a turbine engine turbine blade of a known type, seen in section along a plane transverse blade, ie a plane orthogonal to the direction of the span or length of the blade, which merges with the radial direction relative to the motor axis when the blade is mounted in a turbomachine turbine. The blade 10 comprises an internal cooling circuit 12 formed of three cavities extending in the radial direction, arranged between the intrados wall 14 and the extrados wall 16, and interconnected in series so as to allow the circulation of a flow of cooling air from an inlet section of the first cavity 18 to the second cavity 20 and then to an outlet section of the third cavity 22. The inlet section of the first cavity 18 is connected to air supply means integrated into a root of the blade and is therefore arranged at a radially inner end of the first cavity. The outlet section of the third cavity 22 is generally formed near the radially outer end of the cavity, and generally takes the form of orifices formed in the intrados and / or extrados walls and / or in a bottom wall delimiting the radially outer end of the cavity. Thus, the air flows in the first and third cavities 18, 22 in the radial outward direction, while the air flows in the second cavity 20 in the inward radial direction. Due to the Coriolis force induced by the rotation of the blade around the motor shaft, the Applicant has noticed that the air flowing in the first and third cavities 18, 22 is deflected towards the wall of the engine. intrados 14 to the detriment of the extrados wall 16, while the opposite occurs in the second cavity 20. SUMMARY OF THE INVENTION The invention aims in particular to provide a simple, economical and effective solution to this problem. problem.
    [0003] It proposes for this purpose an aircraft turbine engine turbine blade, comprising a blade root defining a radially inner end of the blade and a blade extending radially outwards from the blade root and having an intrados wall and an extrados wall connected to the intrados wall at a leading edge and a trailing edge of the blade, the blade comprising at least one internal cooling circuit. According to the invention, said internal cooling circuit comprises a plurality of cavities interconnected in series and distributed in: at least one cavity extending radially along the extrados wall, hereinafter referred to as "extrados cavity" and cavities extending radially along the intrados wall, hereinafter referred to as "intrados cavities", in a number equal to the number of extrados cavity (s) increased by one. In addition, the or each extrados cavity is separated from at least one of the intrados cavities by a first inner wall of the blade extending between the intrados and extrados walls. Each intrados cavity has an air inlet section and an air outlet section, said air outlet section of the intrados cavity being arranged radially outwardly with respect to said air inlet section. air inlet of this same intrados cavity. The or each extrados cavity has an air inlet section connected to the air outlet section of one of the intrados cavities and an air outlet section connected to the inlet section of the air inlet section. air of another of the intrados cavities, said air outlet section of the extrados cavity being arranged radially inward with respect to said air inlet section of said same extrados cavity . Finally, said air inlet section of one of the intrados cavities is connected to means for supplying cooling air. Thus, the invention allows the air circulating along the intrados wall to be deflected by the Coriolis force towards this intrados wall and the air flowing along the extrados wall is deflected. by the force of Coriolis in the direction of this wall of extrados. The invention thus makes it possible to considerably improve the homogeneity of the cooling procured by the cooling circuit of the blade.
    [0004] Preferably, each intrados cavity is separated from at least one other adjacent intrados cavity by a second inner wall of the blade connecting the intrados wall to the first inner wall of the blade. Preferably, said at least one extrados cavity is arranged opposite two of said intrados cavities, from which it is separated by said first internal wall of the blade, said at least one extrados cavity comprising at least one first deflector projecting from the upper surface wall towards the first inner wall of the blade, stopping at a distance from the first inner wall, and having a concavity directed radially outwards and towards a wall lateral of the extrados cavity disposed on the side of the intrados cavity to which is connected the air outlet section of said at least one extrados cavity. Such a deflector makes it possible to orient a portion of the air flow towards an area separated from the main path followed by the air within the cooling circuit. In this case, the first deflector advantageously comprises a radially outer end extending in the air inlet section of said at least one extrados cavity and a radially inner end connected to said side wall of the extrados cavity. disposed on the side of the intrados cavity to which is connected the outlet section of the extrados cavity, said first deflector being provided with through-air openings. The deflector thus makes it possible to orient a portion of the airflow towards a radially outer zone of the extrados cavity, this zone being offset with respect to the air inlet of this cavity. Preferably, said at least one extrados cavity comprises at least one second deflector projecting from the upper surface wall towards the first inner wall of the blade, stopping at a distance from the first internal wall, and configured in an inverted V-shape with a vertex radially outward. Such a deflector makes it possible to orient a portion of the airflow towards lateral regions of the cavity.
    [0005] Preferably, the air outlet section of one of the intrados cavities of said cooling circuit communicates with the outside of the blade through air outlet orifices formed in at least one of : - the intrados wall, and - a bottom wall delimiting a radially outer end of the intrados cavity. These outlet orifices are preferably arranged in relatively hot regions of the intrados wall. Preferably, the blade comprises another internal cooling circuit similar to said internal cooling circuit.
    [0006] The invention also relates to an aircraft turbine engine turbine, comprising at least one rotary disc provided with blades of the type described above. The invention also relates to a turbomachine for an aircraft, comprising at least one turbine of the type described above. BRIEF DESCRIPTION OF THE DRAWINGS The invention will be better understood, and other details, advantages and characteristics thereof will appear on reading the following description given by way of non-limiting example and with reference to the appended drawings in which: Figure 1, already described, is a schematic cross-sectional view of an aircraft turbine engine turbine blade of a known type; FIG. 2 is a schematic perspective view of an aircraft turbine engine turbine blade according to a preferred embodiment of the invention; FIGS. 3 to 5 are diagrammatic cross-sectional views of the blade of the blade of FIG. 2, respectively along the planes III-III, IV-IV and V-V of FIG. 2; FIG. 6 is a partial diagrammatic view, developed in plan, of the extrados wall of the blade of the blade of FIG. 2, viewed from the inside of an extrados cavity of an internal cooling circuit of FIG. the blade; Figure 7 is a view similar to Figure 4, illustrating an alternative embodiment of the invention; - Figure 8 is a view similar to Figure 4, illustrating another embodiment of the invention. In all of these figures, identical references may designate identical or similar elements.
    [0007] DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS FIG. 2 illustrates a blade 30 for an aircraft turbine engine turbine according to a preferred embodiment of the invention, generally comprising a blade root 32 to which a blade 34 terminating is connected. by a top 35 of the blade opposite the blade root 32. The blade root has a radially inner portion for allowing the retention of the blade by interlocking in a rotor disk, in a manner well known. In addition, the blade root is connected to the blade via an aerodynamic platform 36 for internally defining a primary flow flow channel within the turbine. In the present description, the direction X is a direction corresponding to the direction of the motor axis when the blade 30 is mounted on a rotor disk within a turbomachine turbine. The Z direction is the radial direction relative to the X direction, which merges with the direction of the length or span of the dawn. The direction Y is such that the three directions X, Y and Z form an orthogonal reference. A plane is said to be transversal if it is parallel to the X and Y directions.
    [0008] As can be seen in FIGS. 3 to 5 illustrating the blade 34 in cross section, respectively along the planes III-III, IV-IV and VV of FIG. 2, the blade generally comprises a lower wall wall 40 and a wall of FIG. extrados 42 connected to each other at a leading edge 44 and at a trailing edge 46 of the blade.
    [0009] The blade 34 comprises an internal cooling circuit 50 formed of three cavities interconnected in series and each extending radially, that is to say in the direction of the span of the blade. These three cavities, visible in FIG. 4, are distributed in a first cavity 52, a second cavity 54 and a third cavity 56. The second cavity 54 extends along the extrados wall 42, and is for convenience denominated "Extrados cavity" in what follows. In contrast, the first and third cavities 52, 56 extend along the intrados wall 40, and are referred to as "intrados cavities" in the following. In the example illustrated, the lower surface cavities 52, 56 of the cooling circuit are thus two in number, while this cooling circuit comprises a single extrados cavity 54. The extrados cavity 54 is separated from the cavities of intrados 52 and 56 by a first inner wall 58 of the blade, which extends between the intrados 40 and extrados 42, at a distance from each of these walls. The two intrados cavities 52 and 56 are separated from each other by a second inner wall 59 of the blade, which connects the intrados wall 40 to the first inner wall 58 of the blade. In addition, each intrados cavity 52, 56 has an air inlet section 60, 62 (Fig. 5) and an air outlet section 64, 66 (Fig. 3), arranged so that the air outlet 64, 66 of each intrados cavity is positioned radially outwardly with respect to the air inlet section 60, 62 of the same intrados cavity, as illustrated by the relative position of III-III and VV of Figure 2 which respectively correspond to Figures 3 and 5. In the example shown, the air inlet section 60, 62 of each intrados cavity 52, 56 forms a region of radially inner end of the cavity, while the air outlet section 64 of the intrados cavity 52 forms a radially outer end region of the cavity. Further, the extrados cavity 54 has an air inlet section 68 connected to the air outlet section 64 of the intrados cavity 52, and the extrados cavity 54 has an outlet section of 70 is connected to the air inlet section 62 of the other intrados cavity 56. The air outlet section 70 of the extrados cavity is arranged radially inwardly with respect to the air inlet section 62. air inlet 68 of this same extrados cavity, as illustrated by the relative position of the planes VV and III-III of FIG. 2 which respectively correspond to FIGS. 5 and 3. In the example illustrated, the section the air outlet 70 of the extrados cavity 54 forms a radially inner end region of the cavity, while the air inlet section 68 of this extrados cavity forms a radially outer end region of the cavity. The air inlet section 60 of the intrados cavity 52 (FIG. 5) is connected to a device for supplying cooling air integrated into the foot 32 of the blade 30. This air supply device of cooling is not visible in the figures and may be of a type known to those skilled in the art.
    [0010] The series interconnection of the three cavities 52, 54, 56 thus allows the circulation of a flow of cooling air from the air inlet 60 of the intrados cavity 52 connected to the air supply device of FIG. cooling down into the outlet section 66 of the other intrados cavity 56. In addition, the intrados cavity 56 communicates with the outside of the vane through air outlets formed in the wall intrados (not visible in the figures). Additional air outlet ports of the intrados cavity 56 may be formed in a bottom wall delimiting a radially outer end of the cavity. In the terminology of the present description, the "air outlet section" 66 of the intrados cavity 56 corresponds to the portion of this cavity extending opposite the aforementioned air outlet orifices. Independently of the cooling circuit 50 described above which is specific to the invention, the blade 34 also incorporates a leading edge cooling cavity 72 extending along the leading edge 44 of the blade and delimited by a third inner wall 74 of the blade connected on one side to the intrados wall 40 and on the other side to the extrados wall 42. The leading edge cooling cavity 72 communicates with the outside of the wall. dawn, for example by means of air outlet orifices formed through the walls of intrados and extrados (these orifices not being visible in the figures). The air supply of the leading edge cooling cavity 72 is preferably provided by a connection of this cavity to a cooling air supply device integrated with the root 32 of the blade 30, in a manner known in itself commonly referred to as "direct feeding". This device is in general distinct from the device supplying the cooling circuit 50. In a similar manner, the blade 34 comprises a trailing edge cooling cavity 76 extending along the trailing edge 46 of the blade and delimited by a fourth internal wall 78 of the blade connected on one side to the intrados wall 40 and on the other side to the extrados wall 42. The trailing edge cooling cavity 76 communicates with the outside of the dawn by means of air outlet orifices formed through the intrados wall 40 and taking for example the form of slits 79 (visible in Figure 2) extending substantially parallel to a transverse plane. The air supply of the trailing edge cooling cavity 76 is for example ensured by a connection of this cavity to a cooling air supply device integrated into the root 32 of the blade 30, in a known manner in itself commonly referred to as "direct feeding". This device is preferably separate from the device supplying the cooling circuit 50. Furthermore, FIG. 6 illustrates preferred characteristics of the cooling circuit 50, making it possible to optimize the efficiency of the latter. More precisely, FIG. 6 shows the extrados wall 42 viewed from inside the extrados cavity 54, in the Y direction, and developed in plan. For a better understanding of the operation, FIG. 6 also shows the outlet section 64 of the intrados cavity 52 and the inlet section 62 of the intrados cavity 56, which for convenience of drawing have been respectively represented. above and below the extrados cavity. It should be understood that these sections are actually not localized in this way, but facing this cavity and outside the plane of Figure 6. As shown in Figure 6, the extrados cavity 54 has a first deflector 80 extending protruding from the upper wall 42 in the direction of the first inner wall 58 of the blade, that is to say in the direction of Y decreasing dimensions. The first deflector 80 has a free end extending away from the first inner wall 58, and is curved, with a concavity oriented radially outwardly and toward the fourth inner wall 78 which forms a sidewall of the cavity extrados 54 delimiting the latter on the side of the trailing edge 46, that is to say more generally on the side of the intrados cavity 56 to which is connected the outlet section 70 of the extrados cavity.
    [0011] In the example shown, the first deflector 80 has a radially outer end portion 82 extending substantially in the Z and Y directions, to a radially outer end of the extrados cavity 54, ie typically to the bottom wall 83 of the blade closing cavities 52, 54, 56, 72, 76 in the radial outward direction. The radially outer end portion 82 preferably extends into the air inlet section 68 of the extrados cavity 54, hence on the side of the third inner wall 74. In addition, the first deflector 80 has a radially inner end portion 84 extending substantially in the X and Y directions, and connected to the fourth inner wall 78. Finally, the first deflector 80 has air passage holes 86.
    [0012] As shown in FIG. 6, the extrados cavity 54 has second baffles 90 projecting from the upper wall 42 in the direction of the first inner wall 58 of the blade. The second baffles 90 each have a free end extending at a distance from the first internal wall 58. These second baffles 90 are configured in inverted V-shape with apex 92 oriented radially outwards, that is to say toward the wall bottom 83 delimiting the cavities 52, 54, 56, 72 and 76 on the side of the apex 35 of the blade. The respective peaks 92 of the second deflectors 90 are advantageously centered substantially on the same line parallel to the radial direction Z. Other types of deflectors or disrupters may be used alternatively or in addition. In addition, an arrangement of deflectors or disrupters similar to that described above with reference to FIG. 6 may be provided for the intrados wall within the intrados cavities 52, 56, and / or which relates to the internal walls 58, 74, 78, within the cavities 52, 54, 56.30 The operation of the cooling circuit 50 will now be described. For this, it is considered an aircraft turbomachine comprising a turbine comprising a rotating rotor disc carrying the blade 30 described above. In practice, the disc carries a plurality of blades similar to the blade 30. In operation, the cooling circuit 50 is supplied with cooling air taken for example at a compressor stage of the turbomachine. The cooling air enters the intrados cavity 52 of the vane 30 via the air inlet section 60 of this cavity and then circulates radially outwards within this cavity, that is to say in the direction from the blade root 32 to the blade apex 35. The cooling air then passes into the outlet section 64 of the intrados cavity 52 and then into the inlet section 68 of the cavity. extrados 54 (arrow 100 in Figure 3), then the air flows radially inwardly within this extrados cavity 54, that is to say in the direction from the blade tip 35 to the foot d blade 32 (arrow 102 in FIG. 6). The cooling air then passes into the outlet section 70 of the extrados cavity 54 and into the inlet section 62 of the intrados cavity 56 (arrow 104 in FIG. 5), and then the air circulates radially. outwardly within this intrados cavity 56. According to a principle of the present invention, the air circulating in the intrados cavities 52 and 56 thus circulates radially outwards while the air flowing in the extrados cavity 54 circulates radially inwards. As a result, the air circulating in the intrados cavities 52 and 56 is deflected towards the intrados wall 40 by the Coriolis force due to the rotation of the rotor, while the air circulating in the extrados cavity 54 is deflected to the upper wall 42 by the Coriolis force. Thus, the intrados and extrados walls are optimally cooled and homogeneous.
    [0013] It should be noted that the successive reversals or connections between the different cavities forming the cooling circuit 50 are oriented generally in the direction of the thickness of the blade. In particular, the air circulating in the extrados cavity 54 is partly deflected by the first deflector 80 (arrow 106 of FIG. 6) in the direction of the fourth internal wall 78 in a radially external portion of the cavity so as to optimizing the cooling of an area 108 of the extrados cavity 54 near the radially outer end of this cavity and offset relative to the air outlet 64 of the intrados cavity 52. The air deflected by the first deflector 80 then passes through the air passage holes 86 and continues its path radially inwardly. In addition, the air flow 102 is partly deflected to the side walls of the extrados cavity 54, that is to say to the third and fourth inner walls 74 and 78 of the blade (arrows 110). This makes it possible to optimize the cooling of an area 112 of the extrados cavity 54 close to the radially inner end of this cavity and offset with respect to the air inlet 62 of the intrados cavity 56. 7 illustrates blade 34a of a blade according to an alternative embodiment of the invention, which is distinguished from the blade 30 described above that the blade 34a has two cooling circuits 50 and 50 '. Each of these cooling circuits is analogous to the cooling circuit 50 of FIGS. 3 to 6. As shown in FIG. 7, the intrados and extrados cavities 54 belonging to the cooling circuit 50 located on the edge side of FIG. attack 44 are respectively separated from the cavities 52 'and extrados suction surface 54', belonging to the cooling circuit 50 'located on the trailing edge 46 side, by a fifth inner wall 113 of the blade connecting the cavity of intrados 40 to the extrados cavity 42. In addition, the air inlet section of the intrados cavity 52, 52 'of each of the two cooling circuits 50 and 50' is connected to the air supply device. integrated cooling device at the foot 32 of the dawn 30.
    [0014] Of course, the or each cooling circuit according to the invention may comprise a higher number of cavities than in the examples described above, since the number of intrados cavities is equal to the number of extrados cavities increased of one.
    [0015] Thus, FIG. 8 illustrates blade 34b of a blade according to another embodiment of the invention, which differs from blade 30 described above in that blade 34b comprises a cooling circuit 50a comprising two extrados cavities and three intrados cavities interconnected in series. More specifically, an intermediate intrados cavity 114 is positioned between the intrados cavity 52, connected to the cooling air supply device, and the intrados cavity 56 opening to the outside of the blade through the outlet ports described above. In addition, an extrados cavity 116 is positioned adjacent to the extrados cavity 54. The intrados cavities 114 and 56 are separated from each other by a fifth internal wall 118 of the blade connecting the wall. of intrados 40 to the first inner wall 58, while the extrados cavities 54 and 116 are separated from each other by a sixth inner wall 120 of the blade, connecting the first inner wall 58 to the wall 42. The outlet section of the intermediate intrados cavity 114 is connected to the inlet section of the extrados cavity 116, and the outlet section of the extrados cavity 116 is connected to the suction section 116. In this way, the cooling air circulates radially outwardly along the pressure wall 40 in each of the intrados cavities 52, 114 and 56, and it flows radially towards the inside wall. the interior along the upper wall 42 in each of the extrados cavities 54 and 116.
    权利要求:
    Claims (9)
    [0001]
    REVENDICATIONS1. A blade (30) for an aircraft turbomachine turbine comprising a blade root (32) defining a radially inner end of the blade and a blade (34) extending radially outwardly from the foot of the blade. vane and having an intrados wall (40) and an extrados wall (42) connected to the intrados wall at a leading edge (44) and a trailing edge (46) of the blade, the blade comprising at least one internal cooling circuit (50; 50 '; 50a), characterized in that said internal cooling circuit comprises a plurality of cavities interconnected in series and distributed in: - at least one cavity ( 54, 54, 54 ', 54, 116) extending radially along the suction wall (42), hereinafter referred to as "extrados cavity", and - cavities (52, 56; 56 ', 52, 114, 56) extending radially along the pressure wall (40), hereinafter referred to as "intrados cavities", in a number equal to the number of cavity (s) of e xtrados increased by one, and in that: - the or each extrados cavity (54; 54, 54 '; 54, 116) is separated from at least one of the lower surface cavities (52, 56; 52 ', 56'; 52, 114, 56) by a first inner wall (58) of the blade extending between the walls of the lower surface (40) and the upper surface (42), each lower cavity (52, 56, 52, 56, 52 ', 56', 52, 114, 56) has an air inlet section (60, 62) and an air outlet section (64, 66), said air outlet section of the intrados cavity being arranged radially outwardly with respect to said air inlet section of the same intrados cavity, the or each extrados cavity (54; 54, 54 '; 54, 116) has an air inlet section (68) connected to the air outlet section ( 64) of one (52; 52; 52 '; 52,114) of the lower surface cavities and an air outlet section (70) connected to the air inlet section of another (56; 56, 56 '; 114, 56) of the intrados cavities, said air outlet section (70) of the extrados cavity being arranged radially inwardly relative to each other; ort to said air inlet section (68) of said same extrados cavity, and said air inlet section (60) of one of the intrados cavities (52; 52, 52 '; 52) is connected to means for supplying cooling air.
    [0002]
    2. A blade according to claim 1, wherein each intrados cavity (52, 56, 52, 56, 52 ', 56', 52, 114, 56) is separated from at least one other adjacent intrados cavity by a second inner wall (59; 59; 59 '; 113; 59,118) of the blade connecting the intrados wall (40) to the first inner wall (58) of the blade.
    [0003]
    The blade according to claim 1 or 2, wherein said at least one extrados cavity (54; 54, 54 '; 54, 116) is arranged opposite two of said intrados cavities (52, 56; 56, 52 ', 56', 52, 114, 56), from which it is separated by said first inner wall (58) of the blade, said at least one extrados cavity having at least one first deflector (80) extending projecting from the upper surface (42) towards the first inner wall (58) of the blade, stopping at a distance from the first inner wall, and having a concavity oriented radially outwardly and in the direction of a side wall (78; 113; 78; 120; 78) of the extrados cavity disposed on the side of the intrados cavity to which is connected the air outlet section (70) of said at least one extrados cavity.
    [0004]
    The blade of claim 3, wherein the first baffle (80) has a radially outer end (82) extending into the air inlet section (68) of said at least one extrados cavity (54). 54, 54 ', 54, 116) and a radially inner end (84) connected to said side wall (78; 113, 78; 120, 78) of the extrados cavity disposed on the side of the intrados cavity ( 56, 56, 56 ', 114, 56) to which is connected the outlet section of the extrados cavity, said first deflector being provided with through-air through-holes (86).
    [0005]
    A blade according to any one of claims 1 to 4, wherein said at least one extrados cavity (54; 54,54 '; 54,116) has at least one second protruding baffle (90) from the upper surface (42) of the first inner wall (58) of the blade, stopping at a distance from the first inner wall, and configured as an inverted V-shaped vertex (92) radially oriented towards the first outside.
    [0006]
    A blade according to any one of claims 1 to 5, wherein the air outlet section (66) of one of the lower surface cavities (56; 56,56 '; 56) of said cooling circuit communicates. with the outside of the blade through air outlet orifices formed in at least one of: - the intrados wall (40), and - a bottom wall (83) delimiting a radially end external of the intrados cavity.
    [0007]
    A blade according to any one of claims 1 to 6, wherein the blade has another internal cooling circuit (50 ') similar to said internal cooling circuit (50).
    [0008]
    8. Turbine for aircraft turbomachine, characterized in that it comprises at least one rotary disk provided with blades (30) according to any one of the preceding claims.
    [0009]
    9. Turbomachine for aircraft, characterized in that it comprises at least one turbine according to the preceding claim.
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    同族专利:
    公开号 | 公开日
    WO2015162389A1|2015-10-29|
    JP2017521590A|2017-08-03|
    RU2674105C2|2018-12-04|
    CN106460525A|2017-02-22|
    CN106460525B|2018-03-02|
    FR3020402B1|2019-06-14|
    US9869187B2|2018-01-16|
    RU2016146011A3|2018-10-22|
    BR112016024618A2|2018-01-23|
    EP3134620A1|2017-03-01|
    EP3134620B1|2018-03-21|
    US20170037733A1|2017-02-09|
    CA2946708C|2021-11-23|
    RU2016146011A|2018-05-24|
    JP6148413B1|2017-06-14|
    CA2946708A1|2015-10-29|
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    US8721285B2|2009-03-04|2014-05-13|Siemens Energy, Inc.|Turbine blade with incremental serpentine cooling channels beneath a thermal skin|
    US20140069108A1|2012-09-07|2014-03-13|General Electric Company|Bucket assembly for turbomachine|FR3021697B1|2014-05-28|2021-09-17|Snecma|OPTIMIZED COOLING TURBINE BLADE|
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    FR3067388B1|2017-04-10|2020-01-17|Safran|BLADE WITH IMPROVED COOLING CIRCUIT|
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    法律状态:
    2015-04-13| PLFP| Fee payment|Year of fee payment: 2 |
    2015-10-30| PLSC| Publication of the preliminary search report|Effective date: 20151030 |
    2016-04-12| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-07| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-03-22| PLFP| Fee payment|Year of fee payment: 5 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1453708|2014-04-24|
    FR1453708A|FR3020402B1|2014-04-24|2014-04-24|DRAWER FOR TURBOMACHINE TURBINE COMPRISING AN IMPROVED HOMOGENEITY COOLING CIRCUIT|FR1453708A| FR3020402B1|2014-04-24|2014-04-24|DRAWER FOR TURBOMACHINE TURBINE COMPRISING AN IMPROVED HOMOGENEITY COOLING CIRCUIT|
    US15/305,605| US9869187B2|2014-04-24|2015-04-23|Turbomachine turbine blade comprising a cooling circuit with improved homogeneity|
    EP15723267.9A| EP3134620B1|2014-04-24|2015-04-23|Turbomachine turbine blade comprising a cooling circuit with improved homogeneity|
    CN201580021256.3A| CN106460525B|2014-04-24|2015-04-23|Turbine wheel blades containing the cooling circuit for improving homogenieity|
    PCT/FR2015/051111| WO2015162389A1|2014-04-24|2015-04-23|Turbomachine turbine blade comprising a cooling circuit with improved homogeneity|
    BR112016024618-7A| BR112016024618A2|2014-04-24|2015-04-23|blade for an aircraft turbomachine turbine, aircraft turbomachine turbine and aircraft turbomachine|
    JP2016563991A| JP6148413B1|2014-04-24|2015-04-23|Turbomachine turbine blade including a cooling circuit with improved uniformity|
    CA2946708A| CA2946708C|2014-04-24|2015-04-23|Turbomachine turbine blade comprising a cooling circuit with improved homogeneity|
    RU2016146011A| RU2674105C2|2014-04-24|2015-04-23|Turbomachine turbine blade comprising cooling circuit with improved homogeneity|
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