• 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 main object of the invention is a turbine distributor blade (1) of a gas turbine engine, comprising an outer platform (5) and an inner platform between which an outer wall (7) extends, forming an outer skin, characterized in that it comprises an inner wall (8), forming an inner skin, facing the outer wall (7) so as to define an inter-skin cavity (10) between the outer walls ( 7) and internal (8), the inner wall (8) having a plurality of cooling orifices (3) for the impact cooling of the outer wall (7), the outer (7) and inner (8) walls being additive manufacturing issues.
    公开号:FR3079551A1
    申请号:FR1852764
    申请日:2018-03-29
    公开日:2019-10-04
    发明作者:Baptiste Hallouin；Jean-Luc Breining；Damien Laberny
    申请人:Safran Helicopter Engines SAS；
    IPC主号:
    专利说明:

    TURBINE DISTRIBUTOR BLADE HAVING AN INTERNAL COOLING WALL ARISING FROM ADDITIVE MANUFACTURING
    DESCRIPTION
    TECHNICAL AREA
    The present invention relates to the general field of turbomachinery, and more particularly to the field of turbine distributor blades, in particular high pressure, of a gas turbine engine.
    The invention applies to any type of terrestrial or aeronautical turbomachinery, and in particular to aircraft turbomachinery such as turbojets and turbopropellers.
    Thus, it relates to a turbine distributor blade of a gas turbine engine, comprising an internal cooling wall resulting from additive manufacturing, a turbine comprising a plurality of such blades, a turbomachine comprising such a turbine, as well as a process for manufacturing such a distributor vane.
    STATE OF THE ART
    A high pressure turbine of a gas turbine engine conventionally comprises one or more rows of turbine blades spaced circumferentially all around the rotor of the turbine. It also includes a distributor assembly making it possible to direct the flow of gas from the combustion chamber towards the turbine blades at an appropriate angle and speed in order to rotate the blades and the rotor of the turbine.
    The dispenser assembly generally includes a plurality of guide vanes which extend radially between lower and upper annular platforms and which are circumferentially spaced from one another. These distributor vanes are directly in contact with the hot gases from the combustion chamber. They are subjected to very high temperatures and therefore need to be cooled.
    In order to be able to ensure efficient cooling of a distributor blade, it is desirable to have a cooling device which is thermally efficient in order to dissipate high thermal power by using a moderate air flow.
    In addition, it is desirable to have such a cooling device which is sealed. The tightness ensures that the air mobilized is only dedicated to cooling the blade: the higher the tightness of the device, the greater its overall efficiency, this being an increasing function of the tightness and the thermal efficiency of the device.
    In addition, it is desirable to have a compact cooling device. Indeed, the integration of the cooling device must minimize its impact on the size of the engine.
    It is also desired to have a cooling device which is economically advantageous. The cost of producing it should be as low as possible.
    The prior art already teaches solutions for cooling turbine distributor blades, such as, for example, French patent applications FR 2 893 080 Al and FR 3 039 199 Al.
    Thus, one of the most widespread solutions currently consists in using a multi-drilled sheet metal insert to cool the blade by impacts of cooling air.
    FIG. 1 very schematically illustrates, in section, an example of cooling a distributor blade 1 'by an insert 2 multi-drilled with cooling orifices 3 by impact.
    In this figure 1, the arrows AF represent the flow of the cooling air flow which feeds the insert 2 and then passes through the orifices 3 to effect the impact cooling of the wall of the blade Γ. The arrows PF represent the purging of the rest of the cooling flow.
    The insert 2 thus constitutes a cavity supplied with cold air. Under the action of a pressure gradient, this air is then routed outside the insert 2 through the holes 3, thus forming a set of jets which explode on the wall of the blade Γ.
    This type of air impact cooling is particularly effective. However, the use of an insert, which forms an insert, has several drawbacks.
    First of all, the connection between the insert and the rim of the dispenser is not necessarily sealed. Thus, FIG. 2 illustrates the appearance of leaks, shown diagrammatically by the arrows FU, generated by the presence of an insert 2 added.
    The inserts 2 are generally welded to a distributor rim 4. The welding can be continuous or by spots. In the latter case, the connection between the insert 2 and the distributor is permeable, which then generates a leak at this interface which reduces the cooling efficiency.
    Furthermore, the fitting of the insert may require bulky arrangements.
    In addition, the solution of the insert is expensive. The connection between the insert and the distributor rim is generally carried out by welding or adjusting the shapes in contact. Welding is an expensive operation, especially if the welding is continuous, and depending on the substrate, it may include microcracks. Adjusting the shapes in contact is also expensive. In addition, the inserts must be drilled, which complicates their implementation.
    In addition, control of the distance between the insert and the distributor vane is not necessarily high. FIG. 3 illustrates the impact distance d between the distributor vane 1 ′ and the insert 2. This distance d is generally close to 1 mm and influences the cooling efficiency. The control of this distance d can be degraded by the deformations induced by the weld or by certain geometric deviations such as a too high insert perimeter.
    STATEMENT OF THE INVENTION
    The invention therefore aims to at least partially remedy the needs mentioned above and the drawbacks relating to the embodiments of the prior art.
    According to one of its aspects, the invention thus relates to a turbine distributor blade, in particular a high pressure blade, of a gas turbine engine, comprising an external platform and an internal platform between which a outer wall, forming an outer skin, characterized in that it has an inner wall, forming an inner skin, facing the outer wall so as to define an inter-skin cavity between the outer and inner walls, the inner wall comprising a plurality of cooling orifices for impact cooling of the external wall, the external and internal walls being from additive manufacturing.
    The distributor vane according to the invention may also include one or more of the following characteristics taken in isolation or according to any possible technical combination.
    The distributor blade may have a hook, in particular at the level of the external platform, making it possible to link the blade to a turbine ring, and the internal wall may be superposed radially on the hook, in particular at the front end of the hook. Advantageously, the axial size of the blade can thus be reduced.
    The distributor vane according to the invention can preferably be produced in one piece by additive manufacturing.
    The cooling holes of the internal wall can come from additive manufacturing.
    The external and internal walls can preferably be made of the same material and there can be a continuity of material between them.
    A junction between the external and internal walls can be formed radially at the level of the external platform.
    Furthermore, the subject of the invention is also, according to another of its aspects, a gas turbine engine, in particular a high pressure turbine, characterized in that it comprises a plurality of distributor blades as defined above .
    In addition, the invention also relates, according to another of its aspects, to a turbomachine, characterized in that it comprises a turbine as defined above.
    In addition, the subject of the invention is, according to another of its aspects, a method of manufacturing a distributor blade as defined above, characterized in that the external and internal walls of the blade are produced by a method additive manufacturing, in particular by laser fusion on a metal powder bed.
    The distributor vane, the turbine, the turbomachine and the manufacturing method according to the invention may include any of the characteristics set out in the description, taken in isolation or in any technically possible combination with other characteristics.
    BRIEF DESCRIPTION OF THE DRAWINGS
    The invention will be better understood on reading the detailed description which follows, of an example of non-limiting implementation thereof, as well as on examining the figures, schematic and partial, of the appended drawing , on which :
    FIG. 1 very schematically illustrates, in section, an example of cooling a distributor blade by a multi-drilled insert of impact cooling orifices,
    FIG. 2 illustrates the appearance of leaks generated by the presence of an insert reported on the blade of FIG. 1,
    FIG. 3 illustrates the impact distance between the distributor blade and the insert on the blade of FIG. 1,
    FIG. 4 partially represents, in a perspective view and in section, an example of a distributor vane according to the invention,
    FIG. 5 very schematically illustrates, in section, the operation of the blade of FIG. 4, and
    - Figures 6A to 6C schematically illustrate, in partial section, the cases of distributor vanes according to the prior art (Figure 6A), according to the invention (Figure 6B), and the comparison between the two in terms of size (Figure 6C).
    Throughout these figures, identical references may designate identical or analogous elements.
    In addition, the different parts shown in the figures are not necessarily shown on a uniform scale, to make the figures more readable.
    DETAILED PRESENTATION OF A PARTICULAR EMBODIMENT
    FIGS. 1 to 3 have been described previously in the section relating to the state of the prior art and to the technical context of the invention.
    Figure 4 partially shows, in a perspective view in section, an example of a distributor vane 1 according to the invention, and Figure 5 very schematically illustrates, in section, the operation of the vane of Figure 4 .
    In order to be able to overcome the drawbacks of the solutions of the prior art presented above, essentially based on the use of an insert, the invention advantageously uses the additive manufacturing process, for example laser fusion on a bed of metal powder. , in order to integrate a cooling skin at the vane 1. Thus, the distributor vane 1 becomes an integrated double-skin vane ensuring cooling by impacts of air jets.
    Thus, with reference to FIG. 4, the distributor blade 1 comprises an external platform 5 and an internal platform 6, visible in FIG. 6B, between which extends an external wall 7, which forms an external skin.
    Advantageously, the blade 1 has an internal wall 8, which forms an internal cooling skin integrated by additive manufacturing. In this way, there is a continuity of material between the internal skin and the rim of the dispenser without resorting to welding.
    This internal skin 8 makes it possible to cool the external skin 7 which is in contact with the hot gases from the aerodynamic stream. To do this, the internal skin 8 has cooling orifices 3 which project the cooling air by impact on the external skin 7.
    These cooling orifices 3 are obtained directly by additive manufacturing. They allow the air jets to be directed towards the areas to be cooled.
    The outer 7 and inner 8 skins define between them an inter-skin cavity 10 in which the cooling air from the cooling orifices 3 circulates before cooling the external skin 7 by impact.
    Advantageously, the entire blade is obtained by additive manufacturing. The junction J between the outer 7 and inner 8 skins is located radially near the outer platform 5.
    Note also that in Figure 4, the reference 9 designates a front hook of the distributor which allows to link the part to the turbine ring.
    The advantages of the proposed solution result mainly from the integration of a cooling skin at dawn by additive manufacturing. Thus, the connection between the internal skin and the rim of the dispenser is waterproof, which makes the proposed cooling device waterproof.
    In addition, it is not necessary to provide arrangements which make possible or facilitate the mounting of the internal cooling skin. It is thus possible to design very compact dispensers. By way of examples, FIGS. 6A to 6C schematically illustrate, in partial section, the cases of distributor blades according to the prior art (FIG. 6A), according to the invention (FIG. 6B), and the comparison between the two in terms of size (Figure 6C).
    In FIG. 6A, the conventional embodiment of a blade 1 ′ is visualized with the presence of an insert 2. In FIG. 6B, the blade 1 comprises the double skin 7, 8 according to the invention. In FIG. 6C which compares the vanes 1 ′ according to the prior art and 1 according to the invention, it can be seen that the internal skin 8 is integrated under the hook 9 before the distributor. In particular, the internal skin 8 is superimposed radially at the end of the front hook 9. This makes it possible to reduce the axial size with a gain in size G, and thus to make it possible to reduce the mass of the motor increasing its efficiency.
    In addition, the solution proposed by the invention is economical since the costly operations of welding and drilling an insert are eliminated.
    Furthermore, it is possible to have a high level of control of the distance between the internal cooling skin 8 and the external skin 7 of the blade 1, in other words the axial dimension of the inter-skin cavity 10. Efficiency cooling is therefore optimal.
    Of course, the invention is not limited to the embodiment which has just been described. Various modifications can be made by those skilled in the art.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    1. Turbine distributor vane (1) of a gas turbine engine, comprising an external platform (5) and an internal platform (6) between which extends an external wall (7), forming an external skin, characterized in that it has an internal wall (8), forming an internal skin, facing the external wall (7) so as to define an inter-skin cavity (10) between the external (7) and internal ( 8), the internal wall (8) comprising a plurality of cooling orifices (3) for impact cooling of the external wall (7), the external (7) and internal (8) walls being produced by additive manufacturing.
    [2" id="c-fr-0002]
    2. Dawn according to claim 1, characterized in that it comprises a hook (9), in particular at the level of the external platform (5), making it possible to link the blade (1) to a turbine ring, and in that that the internal wall (8) is superimposed radially on the hook (9), in particular at the front end of the hook (9).
    [3" id="c-fr-0003]
    3. Dawn according to claim 1 or 2, characterized in that it is produced in one piece by additive manufacturing.
    [4" id="c-fr-0004]
    4. Dawn according to one of the preceding claims, characterized in that the cooling orifices (3) of the internal wall (8) come from additive manufacturing.
    [5" id="c-fr-0005]
    5. Dawn according to any one of the preceding claims, characterized in that the external (7) and internal (8) walls are made of the same material and in that there is a continuity of material between them.
    [6" id="c-fr-0006]
    6. Dawn according to any one of the preceding claims, characterized in that a junction (J) between the external (7) and internal (8) walls is formed radially at the level of the external platform (5).
    [7" id="c-fr-0007]
    7. Gas turbine engine turbine, characterized in that it comprises a plurality of distributor vanes (1) according to any one of the preceding claims.
    5
    [8" id="c-fr-0008]
    8. Turbomachine, characterized in that it comprises a turbine according to claim 7.
    [9" id="c-fr-0009]
    9. A method of manufacturing a distributor vane (1) according to any one of claims 1 to 6, characterized in that the external walls (7) and internal (8) of the vane (1) are produced by an additive manufacturing method, in particular by laser fusion on a metal powder bed.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP1775427B1|2008-11-05|Device for regulating the clearance between a rotor blade and a fixed ring in a gas turbine engine.
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    FR2662742A1|1991-12-06|COOLING DEVICE FOR OVERFLOWING NOZZLE.
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    EP3392464B1|2020-03-25|Sealing ring member for a turbine comprising an angled cavity made of an abradable material
    FR2540937A1|1984-08-17|Ring for a turbine machine turbine rotor
    CA2027283C|1999-02-16|Turbomachine comprising thermal deformation means
    FR3072448B1|2019-10-18|TURBOMACHINE COMBUSTION CHAMBER
    WO2012101376A1|2012-08-02|Method for perforating a wall of a combustion chamber
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    FR3035481A1|2016-10-28|TURBOMACHINE COMBUSTION CHAMBER COMPRISING A SPECIFICALLY SHAPED AIR FLOW GUIDING DEVICE
    FR2967453A1|2012-05-18|AUBES RETENTION DISC
    FR3026428B1|2019-10-25|RADIANT TURBOMACHINE TURBOMACHINE ROTOR BEARD
    FR3040735A1|2017-03-10|HIGH-PRESSURE TURBINE HOUSING OF A LOCALIZED COOLING TURBOMACHINE
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    CA3146412A1|2021-02-04|Turbomachine moving blade with cooling circuit having a double row of discharge slots
    同族专利:
    公开号 | 公开日
    WO2019186046A1|2019-10-03|
    US20210003015A1|2021-01-07|
    CN111886087A|2020-11-03|
    EP3746235A1|2020-12-09|
    FR3079551B1|2020-04-24|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2015009448A1|2013-07-19|2015-01-22|United Technologies Corporation|Additively manufactured core|
    EP3051066A1|2015-01-30|2016-08-03|United Technologies Corporation|Staggerd casting core extensions|
    FR3037974A1|2015-06-29|2016-12-30|Snecma|METHOD FOR MANUFACTURING A VANE COMPRISING A BATHTUB INTEGRATING A WALL|
    FR3044038A1|2015-11-19|2017-05-26|Turbomeca|DAWN EQUIPPED WITH AN ASSOCIATED COOLING SYSTEM, DISTRIBUTOR AND TURBOMACHINE|
    WO2017137709A1|2016-02-12|2017-08-17|Safran|Method for forming dust-removal holes for a turbine blade and associated ceramic core|
    US6283708B1|1999-12-03|2001-09-04|United Technologies Corporation|Coolable vane or blade for a turbomachine|
    US6435813B1|2000-05-10|2002-08-20|General Electric Company|Impigement cooled airfoil|
    FR2893080B1|2005-11-07|2012-12-28|Snecma|COOLING ARRANGEMENT OF A DAWN OF A TURBINE, A TURBINE BLADE COMPRISING IT, TURBINE AND AIRCRAFT ENGINE WHICH ARE EQUIPPED|
    US9289826B2|2012-09-17|2016-03-22|Honeywell International Inc.|Turbine stator airfoil assemblies and methods for their manufacture|
    US8864438B1|2013-12-05|2014-10-21|Siemens Energy, Inc.|Flow control insert in cooling passage for turbine vane|
    US10012106B2|2014-04-03|2018-07-03|United Technologies Corporation|Enclosed baffle for a turbine engine component|
    US9896943B2|2014-05-12|2018-02-20|Honeywell International Inc.|Gas path components of gas turbine engines and methods for cooling the same using porous medium cooling systems|
    US10946473B2|2015-05-14|2021-03-16|General Electric Company|Additive manufacturing on 3-D components|
    FR3039199B1|2015-07-20|2019-12-13|Safran Helicopter Engines|BLADE OF HIGH PRESSURE DISTRIBUTOR WITH A VARIABLE GEOMETRY INSERT|
    US10350684B2|2015-11-10|2019-07-16|General Electric Company|Additive manufacturing method for making complex film holes|FR3112367A1|2020-07-07|2022-01-14|Safran Helicopter Engines|BLADE OF A TURBOMACHINE DISTRIBUTOR INCLUDING A COOLING SYSTEM BY IMPACT OF AIR JETS|
    RU201312U1|2020-07-21|2020-12-09|Федеральное государственное бюджетное образовательное учреждение высшего образования "Рыбинский государственный авиационный технический университет имени П.А. Соловьева"|Cooled turbine nozzle blade of a gas turbine engine|
    法律状态:
    2019-02-19| PLFP| Fee payment|Year of fee payment: 2 |
    2019-10-04| PLSC| Publication of the preliminary search report|Effective date: 20191004 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 3 |
    2021-02-18| PLFP| Fee payment|Year of fee payment: 4 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1852764|2018-03-29|
    FR1852764A|FR3079551B1|2018-03-29|2018-03-29|TURBINE DISTRIBUTOR BLADE HAVING AN INTERNAL COOLING WALL ARISING FROM ADDITIVE MANUFACTURING|FR1852764A| FR3079551B1|2018-03-29|2018-03-29|TURBINE DISTRIBUTOR BLADE HAVING AN INTERNAL COOLING WALL ARISING FROM ADDITIVE MANUFACTURING|
    CN201980019318.5A| CN111886087A|2018-03-29|2019-03-26|Turbine stator blade including an internal cooling wall produced by additive manufacturing|
    US16/982,727| US20210003015A1|2018-03-29|2019-03-26|Turbine stator vane comprising an inner cooling wall produced by additive manufacturing|
    PCT/FR2019/050678| WO2019186046A1|2018-03-29|2019-03-26|Turbine stator vane comprising an inner cooling wall produced by additive manufacturing|
    EP19718800.6A| EP3746235A1|2018-03-29|2019-03-26|Turbine stator vane comprising an inner cooling wall produced by additive manufacturing|
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