• 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:
    Ceramic core used for the manufacture of a turbomachine hollow turbine blade according to the lost wax foundry technique and shaped to constitute the cavities of this blade in a single element, comprising, to jointly feed the interior of these cavities in cooling air, core portions (60, 62) for forming first and second lateral cavities connected to a core portion (48) for forming at least one central cavity, on the one hand at the bottom of the core ( 54) by at least two ceramic junctions (70) and on the other hand at different heights of this core by a plurality of other ceramic junctions (64, 66, 68) whose positioning defines the thickness of internal partitions of the vane while providing additional cooling air to predetermined critical areas of the first and second lateral cavities.
    公开号:FR3034128A1
    申请号:FR1552383
    申请日:2015-03-23
    公开日:2016-09-30
    发明作者:Sylvain Paquin；Charlotte Marie Dujol；Patrice Eneau；Hugues Denis Joubert；Adrien Bernard Vincent Rollinger
    申请人:Safran SA；SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present invention relates to the general field of turbomachine turbine blades, and more particularly to turbine blades provided with integrated cooling circuits produced by the lost-wax casting technique. PRIOR ART In a manner known per se, a turbomachine comprises a combustion chamber in which air and fuel are mixed before being burned. The gases from this combustion flow downstream of the combustion chamber and then feed a high pressure turbine and a low pressure turbine. Each turbine has one or more rows of stationary blades (called distributors) alternating with one or more rows of moving blades (called moving wheels), circumferentially spaced around the rotor of the turbine. These turbine blades are subjected to very high temperatures of the combustion gases, which reach values much higher than those which can bear without damage these blades which are in direct contact with these gases, which has the effect of limiting their service life. . In order to solve this problem, it is known to provide these vanes with internal cooling circuits having high levels of thermal efficiency and aimed at reducing the temperature of the latter by creating, within the dawn, an organized circulation. this air (simple cavities direct supply or paperclips for example) and, in the wall of the blade, perforations for generating a protective film for this blade. This technology, however, has several disadvantages.
    [0002] Firstly, the trombone cavity circuits which have the advantage of maximizing the work of air through the circuit, cause a significant heating of this air which results in a decrease in the thermal efficiency of the holes located in end of trombone. Likewise, configurations with leading edge cavities and direct feed trailing edge do not provide an effective response to the high temperature levels typically seen at the top of the blade. Finally, the different cavities are separated from the vein only by a wall of variable thickness depending on the areas of the blade. In view of the constraints on the flow rate for bladed cooling and the current tendency to increase the vein air temperatures, it is not possible to cool the dawn effectively with a circuit of this type without significantly increasing air flow and penalize engine performance. FIG. 5 illustrates a gas turbine engine high pressure turbine blade 10 having an aerodynamic surface or blade 12 which extends radially between a root 14 and a blade tip 16. The foot of the dawn is shaped so that it allows the mounting of the blade on a rotor disc. The top of the blade has a so-called bathtub-shaped portion 18 consisting of a bottom transverse to the blade and a wall forming its edge in the extension of the wall of the blade 12. As shown in the view in FIG. In FIG. 6, the blade 12 comprises, in the example illustrated, a plurality of cavities 20, 22, 24, 26, 28, 30, and 32. First and second central cavities 20, 22 extend. from the foot to the top of the blade and two other cavities 24, 26 are disposed on either side of these central cavities, along the wall of the extrados between these central cavities and the extrados wall of the dawn and along the wall of the intrados between these central cavities and the intrados wall of the dawn. Finally, a cavity 28 is located in the portion of the blade near the leading edge and two cavities 30, 32 follow one another in line in the portion of the blade near the trailing edge.
    [0003] The shape and number of the cavities as well as the position of the external bores 34, 36 and the geometry of the trailing edge slots 38 are given by way of illustration, all these elements being in fact generally optimized to maximize the thermal efficiency in the zones. the most sensitive to the heat of the combustion gases in which these vanes 30 are immersed. Internal cavities are also often equipped with disrupters (not shown) to increase heat exchange. As described in FR 2961552 in the name of the applicant, the blades of high pressure turbines are conventionally made in lost-wax foundry, the geometry of the circuits being realized, according to its complexity, by the positioning in the mold of one or 3034128 3 several ceramic cores whose outer surface forms the inner surface of the finished blade. In particular, the cooling circuits comprising a plurality of cavities, such as those of FIGS. 5 and 6, require the assembly of several separate ceramic cores (intended to produce the central cold cavities isolated from the hot gases and the fine external cavities having energies in separate air) to ensure the metal wall thickness before it can be cast. It is therefore a complex operation whose assembly, which is done manually by the foot and the head of the ceramic cores, prevents the casting of the bath at the head of the blade, which requires an additional finishing operation costly may lead to a limitation of the mechanical strength of the blade in this area (intake of the bath or closure by brazing for example).
    [0004] OBJECT AND SUMMARY OF THE INVENTION The present invention therefore aims at overcoming the disadvantages associated with the manual assembly of several separate cores by proposing a cooling circuit for a turbine blade which can be produced in a single core so as to eliminate these tub assembly and finishing operations of the prior art circuits while ensuring the inter-cavity distance corresponding to the thickness of the metal partition after casting of the molten metal, more reliably than in the current manual assemblies.
    [0005] To this end, there is provided a ceramic core used for the manufacture of a turbomachine hollow turbine blade according to the lost-wax foundry technique, the blade comprising at least one central cavity, a first lateral cavity disposed between said at least one central cavity and an extrados wall of the blade and a second lateral cavity disposed between said at least one central cavity and an intrados wall of the blade. The core is shaped to form said cavities in a single member and comprises, to jointly feed the interior of said cooling air cavities, core portions for forming said first and second lateral cavities connected to a core portion for forming said at least one central cavity, on the one hand at the bottom of the core by at least two ceramic junctions and on the other hand at different heights of said core by a plurality of other ceramic junctions whose positioning defines the thickness of the internal partitions of the blade while providing additional cooling air to predetermined critical areas of said first and second lateral cavities. In addition, a core portion for forming a bath and connected to said core portion for forming said at least one central cavity by ceramic junctions whose positioning defines the thickness of said bath while providing air evacuation 10 cooling at the head of the blade. Through these junctions by the body of the dawn, the need for assembling fireworks at the head of the blade is removed, which makes it possible to obtain a foundry bath having the same mechanical properties as the body of the dawn. In addition, the main feed of the lateral cavities by their foot makes it possible to better control the flow of air and the overall cooling of the external walls on the finished blade and, on the core, the feeds of the different cavities can be joined as soon as possible. injection, which further improves the mechanical strength of the cores. According to the embodiment envisaged, said predetermined critical zones 20 are chosen from the most thermomechanically stressed zones of said first and second lateral cavities and said ceramic junctions have a section dimensioned to ensure the mechanical strength of said internal partitions during the casting of the molten metal. The invention also relates to the method of manufacturing a turbomachine hollow turbine blade made according to the lost-wax casting technique by means of a single-element core as explained above and any turbomachine turbine equipped with a plurality of cooled vanes made from such a method.
    [0006] BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the present invention will be apparent from the description given below, with reference to the accompanying drawings which illustrate an embodiment thereof which is devoid of any limiting character and in which: FIG. 1 Fig. 2 is an extrados view of a turbine vane core according to the invention, - Fig. 3 is a view of the core of the turbines of the invention. FIGS. 1 and 2 intersected on the height of the blade to show its junction areas, FIGS. 4A, 4B and 4C are sectional views at different elevations of the blade, FIG. perspective of a turbine blade of the prior art, and - Figure 6 is a sectional view of the blade of Figure 5.
    [0007] DETAILED DESCRIPTION OF THE EMBODIMENT FIGS. 1 and 2 show a ceramic core 40 intended for the production of a turbomachine turbine blade respectively seen on the extrados side and seen on the intrados side of this blade. The ceramic core, in the illustrated example, has seven parts or columns forming a single element. The first column 42, which is intended to be on the side of the arrival of the combustion gases, corresponds to the leading edge cavity 28 which will be created after casting, while the second column 44 corresponds to the central cavity 20 adjacent to it. The latter receives a flow of cooling air through a pipe (not shown) resulting, after casting, the presence of a first column foot 46 of the core 40. The other three columns 48, 50, 52 making a go- return correspond to the following cavities 22, 30, 32 which receive a second flow of cooling air supplied by another pipe resulting from the presence of a second column foot 54 connected to the first column foot 46 to form the foot of the core. The first and second columns 42 and 44 are connected to each other by a series of bridges 56, to which will correspond, after casting, air supply ports (see reference 80 in Figure 4A) for the 30 cooling the leading edge cavity 28. At least two upper bridges 57, to the connection with the columns and a head 59 of the core 40 allow to obtain the desired wall thickness at the bottom of the bath during casting and are also dimensioned to form air outlets. With respect to the fourth column 50, vertically inclined bridges 58 create core thinned regions to create stiffened blade regions.
    [0008] The size of the various bridges is determined to prevent them from breaking during handling of the core 40, which would render it unusable. The bridges are, in the example considered, distributed spaced substantially regularly over the height of the core 40 in particular to the first column 42 of the core. According to the invention, the core 40 further comprises sixth and seventh lateral columns 60 and 62 separated from each other of the second and third columns 44, 48 by a determined spacing thus leaving room for the creation of a solid inter-cavity wall during casting of the molten metal. For reasons of maintaining these columns and rigidity of the entire core, the lower end of the sixth column 60 is connected to the first column foot 46 and the lower end of the seventh column 62 is connected to the second foot of column 54 and multiple ceramic junctions of small section (see for example the references 64, 66, 68 of Figure 3), dimensioned however to ensure the mechanical strength of the internal partitions formed during the casting of the molten metal in the mold casting, are arranged on the functional part of the blade between these two lateral columns and the second and third central columns.
    [0009] The presence of the two connections at the bottom of the column (however, only the ceramic junction 70 at the bottom of the seventh column 62 is illustrated) will have the consequence, after the foundry, that the lateral cavities 24, 26 will be connected directly to the pipe. supply cooling air central cavities 20 and 22, which further improves the mechanical strength of the core and, on the finished blade, the feed by the foot of the core provides better control of the internal air flow cooling and global cooling of the outer walls. Figures 4A, 4B and 4C show the orifices 72, 74, 76, 78 left by the junctions between the two central cavities 20, 22 and the lateral cavities 24, 26 at different heights of the blade (or core). In FIG. 4A, it is possible to note the two orifices 72, 74 ensuring an air passage between the central cavity 22 and the lateral cavities 24, 26 respectively, the orifice 80 at the resulting leading edge cavity 28. of a bridge 56. In FIG. 4B, the orifice 76 ensures an air passage 35 between the central cavity 20 and the lateral cavity 24 and in FIG. 4C, the orifice 78 ensures an air passage between the central cavity 20 and the side cavity 26. The lost wax manufacturing process of the blade once the nucleus into a single element made is conventional and consists first of all in forming a mold of injection in which is placed the nucleus before injection of the wax. The wax model thus created is then dipped in slips consisting of ceramic suspension to make a casting mold (also called shell mold). Finally, the wax is removed and the shell mold is baked into which the molten metal can then be cast. Due to the ceramic junctions linking the central and lateral columns of the core, their relative spacing is mastered over the entire height of the blade. These junctions are furthermore positioned to drive, on the finished blade, an additional supply of fresh air from the central cavities towards the most thermomechanically stressed zones of the lateral cavities, which also improves the thermal efficiency. local and the life of dawn. These junctions are especially dimensioned and arranged so as to ensure: - their mechanical strength during casting, 20 - the relative positioning of the central and lateral cavities, that is to say the thickness of the internal partitions of the blade, Additional cooling air sufficient in the critical areas, especially in correspondence of the proximity of the leading edge.
    权利要求:
    Claims (8)
    [0001]
    REVENDICATIONS1. Ceramic core used for the manufacture of a turbomachine hollow turbine blade according to the lost-wax foundry technique, the blade comprising at least one central cavity (20, 22), a first lateral cavity (24) disposed between said at least one central cavity and an extrados wall of the blade and a second lateral cavity (26) disposed between said at least one central cavity and an intrados wall of the blade, the core being characterized in that it is shaped for constituting said cavities in a single element and comprising, to jointly feed the interior of said cooling air cavities, core portions (60, 62) for forming said first and second lateral cavities connected to a core portion (44); , 48) for forming said at least one central cavity, on the one hand at the bottom of the core (46, 54) by at least two ceramic junctions (70) and on the other hand at different heights of said core by a a plurality of other ceramic junctions (64, 66, 68) the positioning of which defines the thickness of internal vane partitions while providing additional cooling air to predetermined critical areas of said first and second lateral cavities.
    [0002]
    2. Ceramic core according to claim 1, characterized in that it further comprises a core portion (59) for forming a bath (18) and connected to said core portion for forming said at least one central cavity by ceramic junctions (57) whose positioning defines the thickness of said bath while ensuring a cooling air discharge at the head of the blade.
    [0003]
    Ceramic core according to claim 1 or claim 2, characterized in that said predetermined critical zones are selected from the most thermomechanically stressed zones of said first and second lateral cavities.
    [0004]
    4. Ceramic core according to claim 1 or claim 2, characterized in that said ceramic junctions have a section designed to ensure the mechanical strength of said internal partitions during the casting of the molten metal.
    [0005]
    5. Use of a ceramic core according to any one of claims 1 to 4 for the manufacture of a turbomachine hollow turbine blade according to the technique of lost wax casting.
    [0006]
    6. A method of manufacturing a turbomachine hollow turbine blade made by the lost-wax casting technique, the blade having at least one central cavity (20, 22), a first lateral cavity (24) arranged between said at least one central cavity and an extrados wall of the blade and a second lateral cavity (26) disposed between said at least one central cavity and an intrados wall of the blade, the method being characterized in that it comprises a step of manufacturing a single element ceramic core corresponding to said at least one central cavity and said first and second side cavities, core portions (60, 62) for forming said first and second side cavities being connected a core portion (44, 48) for forming said at least one central cavity, on the one hand at the bottom of the core (46, 54) by at least two ceramic junctions (70) to feed jointly the interior of said cooling air cavities and secondly at different heights of said core by a plurality of other ceramic junctions (64, 66, 68) whose positioning defines the thickness of internal partitions of the dawn while providing additional cooling air to predetermined critical areas of said first and second lateral cavities, the ceramic core thus formed being placed in a casting mold and molten metal cast in said mold. 30
    [0007]
    7. Manufacturing process according to claim 6, characterized in that said ceramic core in a single element further comprises a core portion (59) for forming a bath (18) and connected to said core portion for forming said at least one central cavity by ceramic junctions (57) whose positioning defines the thickness of said bath while ensuring a cooling air discharge at the head of the blade. 3034128 10
    [0008]
    8. A turbomachine comprising a hollow turbine blade manufactured according to the manufacturing method of claims 6 or 7.
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    法律状态:
    2016-02-25| PLFP| Fee payment|Year of fee payment: 2 |
    2016-09-30| PLSC| Publication of the preliminary search report|Effective date: 20160930 |
    2017-01-09| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 Owner name: SAFRAN, FR Effective date: 20170719 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 4 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 7 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1552383A|FR3034128B1|2015-03-23|2015-03-23|CERAMIC CORE FOR MULTI-CAVITY TURBINE BLADE|FR1552383A| FR3034128B1|2015-03-23|2015-03-23|CERAMIC CORE FOR MULTI-CAVITY TURBINE BLADE|
    PCT/FR2016/050628| WO2016151234A1|2015-03-23|2016-03-22|Ceramic core for a multi-cavity turbine blade|
    JP2017549652A| JP2018515343A|2015-03-23|2016-03-22|Ceramic core for multi-cavity turbine blades|
    CA2981994A| CA2981994A1|2015-03-23|2016-03-22|Ceramic core for a multi-cavity turbine blade|
    BR112017020233-6A| BR112017020233A2|2015-03-23|2016-03-22|ceramic core, use of a ceramic core, manufacturing method for fabricating a hollow turbine blade for a turbine engine, and turbine engine|
    EP16714492.2A| EP3274559A1|2015-03-23|2016-03-22|Ceramic core for a multi-cavity turbine blade|
    CN201680018252.4A| CN107407152A|2015-03-23|2016-03-22|Ceramic core for multi-cavity turbo blade|
    RU2017134365A| RU2719410C2|2015-03-23|2016-03-22|Ceramic core and a method for making a hollow turbine blade, using a ceramic core and a gas turbine engine with a hollow turbine blade|
    US15/560,234| US10961856B2|2015-03-23|2016-03-22|Ceramic core for a multi-cavity turbine blade|
    JP2021000819A| JP2021062408A|2015-03-23|2021-01-06|Ceramic core for multi-cavity turbine blade|
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