• 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:
    A turbomachine hollow turbine blade having a plurality of upstanding cavities (23, 25, 29, 31) communicating with a dawn tub (18) on the one hand by a plurality of deblocked holes rabies (21A, 21B, 21C) for the removal of dust and secondly by a plurality of inclined cooling bores (20A, 20B, 20C, 20D) intended for e cooling a wall (18B) of the bathtub by opening on a face intrados (12C) of the blade, at least one rising cavity (25) comprising a top without a hole of dehiscence And a tilted cooling bore formed in its side wall and intended to cool the bath wall is enlarged to have a diameter at least equal to the diameter of a hole in the wall. standard dust and thus also act as a deblocking hole (51), so that the air flow rate taken for the cooling of dawn is reduced.
    公开号:FR3072415A1
    申请号:FR1759722
    申请日:2017-10-17
    公开日:2019-04-19
    发明作者:Leandre Ostino；Matthieu Simon
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Field of the invention
    The present invention relates to the general field of turbine engine blades, and more particularly to hollow 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 there. The gases from this combustion flow downstream of the combustion chamber and then supply a high pressure turbine and a low pressure turbine. Each turbine has one or more rows of fixed blades (called distributors) alternating with one or more rows of movable blades (called wheels), circumferentially spaced around the rotor of the turbine. These turbine blades, whether fixed or mobile, are subjected to the very high temperatures of the combustion gases, which reach values much higher than those which the blades in direct contact with these gases can withstand.
    In order to solve this problem, it is therefore known to provide these blades with internal cooling circuits having high levels of thermal efficiency and aiming to reduce the temperature of the latter by creating, inside the blade, a circulation organized by this air (for example by means of simple direct supply cavities or paper clips provided with rising and falling cavities) and, in the wall of the blade, perforations intended to generate a protective film for this blade. The air flow used in these cooling circuits is taken from the high pressure compressor of the engine, so that this air intake degrades the specific consumption of the engine. It is therefore particularly advantageous to minimize this air flow taken to improve the specific consumption of the engine.
    FIG. 4 schematically illustrates a part of the core 10 of a high pressure turbine blade of a gas turbine engine comprising an aerodynamic surface or blade 12 (in phantom line) which extends in the radial direction between a blade root ( not shown) and a blade tip having a so-called bathtub-shaped part 18 consisting of a bottom 18A transverse to the blade and of a wall (or low wall 18B) forming its edge in the extension of the wall of the blade . The blade includes a plurality of cavities of which, however, for the purposes of the description, only four lateral cavities along the lower surface of the blade and a so-called “under-bath” cavity largely placed under the bottom of the bath. 18A are illustrated by their respective core part 22, 24, 26, 28, 30. The core also includes first ceramic rods 32 - 40 extending from the side walls (for example the side wall 24A of the core part 24 ) core parts and intended to form inclined bores ensuring the cooling of the bath wall 18B on the underside of the blade
    Taking into account the environment in which gas turbine engines operate, it is also necessary to provide the aforementioned cooling circuits with dusting holes allowing the evacuation from the dawn of particles or dust ingested by the engine and transported. in the cooling air until the entry of the different cavities. As a result of this function, the dusting holes have a much larger diameter (in a ratio of about 2 to 5) than that of the inclined cooling holes. FIG. 3 shows four of these dusting holes opening into the bottom of the bathtub 18A and illustrated by respective second ceramic rods 42 - 48 extending vertically from the top (for example the top 24B of the core part 24) alone core parts 22, 24, 28, 30 forming rising cavities. The downward cavity 26 does not in fact have a dusting hole.
    The presence of these dusting holes is not without consequence on the specific consumption because the cooling air flow evacuated by these holes is not used in the most efficient way possible for the cooling of the blade. However, it is impossible to remove them because then the risk of creating dust accumulation zones at the level of the rising cavities becomes too great. And the presence of such dust accumulation zones is at the origin of hot spots on the dawn, such as to cause burns or accelerated local oxidation of the dawn.
    Subject and summary of the invention
    The present invention therefore aims to overcome the aforementioned drawbacks by proposing a hollow turbine blade whose cooling air intake is reduced to improve the specific consumption of the engine.
    For this purpose, there is provided a hollow turbine engine turbine blade comprising a plurality of rising cavities communicating on the one hand with a bathtub of the blade by a plurality of dusting holes intended for the evacuation of dust and other part by a plurality of inclined cooling holes intended to cool a wall of said bath by opening onto a lower surface of the blade, characterized in that at least one rising cavity is devoid at its top of a dusting hole and a inclined cooling hole made in its side wall and intended to cool said bath wall is enlarged to have a diameter at least equal to the diameter of a standard dusting hole and thus also act as a dusting hole, so that the flow the air taken for cooling the blade is reduced.
    By this configuration which optimizes the shape and positioning of a particular dusting hole, it is possible to cool a moving blade of a high pressure turbine with a lower cooling rate but with the same thermal efficiency as a conventional moving blade. The air flow evacuated by the dusting holes is thus used to cool by film and pumping effect the low wall of the dawn bathtub, which is an area subjected to the high temperatures of the air from the motor stream and therefore at high thermal stresses.
    According to the embodiment envisaged, the inclined cooling hole thus enlarged also serving as a dusting hole has an inclination oriented towards the bathtub between 45 and 75 °.
    Preferably, said apex of said at least one rising cavity is inclined at an angle substantially equal to that of said inclined cooling hole.
    Advantageously, at least one of the cavities of the blade opposite said inclined apex has an increased volume corresponding to at least the volume subtracted from said at least one rising cavity following the addition of said inclined plane.
    Preferably, said inclined cooling hole thus enlarged is disposed as close as possible to said top of said at least one rising cavity.
    The invention also relates to a ceramic core used for the manufacture of a hollow turbine engine turbine blade according to the lost wax casting technique, the blade comprising a plurality of rising cavities communicating on the one hand with a bathtub of the blade by a plurality of dusting holes intended for the evacuation of dust and on the other hand by a plurality of inclined cooling holes intended to cool a wall of said bathtub by opening onto a lower surface of the blade, the core comprising:
    a plurality of core parts intended to form said plurality of rising cavities,
    a plurality of first ceramic rods of a first determined diameter extending from a side wall of said plurality of core parts and intended to form said plurality of cooling bores, and
    - a plurality of second ceramic rods of a second determined diameter extending vertically from a top of said plurality of core parts and intended to form said plurality of dusting holes, said second determined diameter being greater than said first determined diameter, characterized in that a core part intended to form a rising cavity of the blade is devoid at its top of a second ceramic rod intended to form a dusting hole and a first ceramic rod intended to form a bore in its side wall inclined cooling system also serving as a dusting hole to cool said bathtub wall, has a first diameter at least equal to said second predetermined diameter, and in that said core portion has at its top an inclined plane and l at least one of the other core parts of said plurality of parts of n core has an increase in volume opposite said apex of said core portion.
    Preferably, said increase in volume is substantially equal to the volume resulting from the introduction of said inclined plane at the top of said core part.
    Advantageously, said increase in volume is a projecting part centered on said core part with a width and a height substantially equal to that of said inclined plane without however exceeding the top of said core part.
    The invention also relates to the use of such a ceramic core for the manufacture of a hollow turbine engine turbine blade according to the lost wax casting technique and any turbomachine turbine fitted with several hollow turbine blades.
    Brief description of the drawings
    Other characteristics and advantages of the present invention will emerge from the description given below, with reference to the appended drawings which illustrate an embodiment thereof devoid of any limiting nature and in which:
    FIG. 1 is an external perspective view of a moving blade of a high pressure turbine according to the invention,
    FIG. 2 is a schematic view of a first embodiment of a part of the core of the turbine blade of FIG. 1,
    FIG. 2A is a sectional view at the level of an inclined cooling and dusting hole,
    FIG. 3 is a schematic view of a second embodiment of a part of the core of the turbine blade of FIG. 1, and
    - Figure 4 is a schematic view of a core part of a turbine blade of the prior art.
    Detailed description of an embodiment
    FIG. 1 illustrates a hollow blade of a high pressure turbine of a turbomachine conventionally extending radially with respect to an axis of rotation of a moving wheel on which this hollow turbine blade is intended to be embedded with a plurality of others.
    The blade comprises a blade 12 forming the aerodynamic surface of the blade, a platform 14 supporting this blade and a blade root 16 carrying the assembly and ensuring its embedding in the rotor of the turbine wheel (not shown). The blade 12 comprises, as is known, a leading edge 12A, a trailing edge 12B, a lower face 12C and a lower face (face hidden in the figure). At the top of the blade (corresponding to the head end opposite the blade root) is arranged the bathtub 18 consisting of the bottom 18A transverse to the blade and the wall 18B forming its edge in the extension of the wall of the blade . The blade also has perforations (holes on both sides or slots on the trailing edge) intended to generate a protective cooling air film for this blade. The number and the position of the perforations are optimized to maximize cooling in the areas most sensitive to the heat of the combustion gases in which these blades are immersed and in particular for its lower surface 12C which is subjected to the greatest thermal stresses.
    In order not to overload the figure and ensure a better understanding of the invention, only the perforations related to the invention have been shown, namely the inclined holes 20A to 20D ensuring the cooling of the bath wall 18B by opening onto the face lower surface 12C of the blade and the dusting holes 21A to 21C allowing the evacuation of dust.
    FIG. 2 represents a part of a ceramic core 10 intended for the realization of the movable vane of FIG. 1. This core indeed shows, in the example illustrated, only five parts of core or columns which can be rising or down. The first riser 22 is for example intended to form, once the blade is completed, a lateral cavity of the blade (referenced 23 in FIG. 1) receiving a first flow of cooling air brought in by a first pipe while the three other adjacent columns making a round trip on the lower surface (with two rising columns 24, 28 and one, in the center, falling 26) are intended to form lateral cavities of the blade (referenced respectively 25, 29 and 27 in FIG. 1) which can receive a second flow of cooling air supplied by another pipe for example. The last part of the core 30 is intended to form a so-called “under-bath” cavity (referenced 31 in the figure
    1) largely arranged under the bottom of the bath 18A.
    The core also includes the first ceramic rods 32, 36, 38, 40 extending from a side wall (for example 24A) of the risers and intended to form the inclined bores ensuring the cooling of the bath wall 18B on the underside of the blade and the second ceramic rods 42, 46, 48 extending vertically from the top (for example 24B) of these risers and intended to form the dusting holes allowing the evacuation in the bathtub of the dust passing through with the air cooling the rising cavities 23, 29, 31 formed from these columns.
    Such a multi-cavity ceramic core naturally includes other core parts intended to form other cavities not shown as a cavity located in the part of the blade near the leading edge 12A and one or more successive cavities in line in the part of the blade near the trailing edge 12B, all allowing the routing of the cooling air from the blade root 16 to blade parts associated with cooling. The ceramic rods make it possible to create the inclined holes through which this air passes to reach the wall of the blade or evacuate the dust for those intended to form the dusting holes. The columns are separated from each other by predetermined spacings, thus leaving room for the creation of a solid inter-cavity wall during the casting of the molten metal.
    In accordance with the invention, at least one of the rising cavities is devoid of a dusting hole at its top and the cooling cooling hole inclined (with an inclination oriented towards the bathtub of the order of 45 to 75 °), practiced in its side wall near the top of this cavity and normally intended to cool the bath wall by opening on the lower surface of the blade, is enlarged in a ratio of 2 to 5 to also act as a dusting hole, so that the air flow taken for cooling is reduced.
    In a preferred embodiment of the invention illustrated in FIG. 2, the cavity without a dusting hole is the rising cavity 25. However, the other rising cavities 23 and 29 can also be devoid of dusting hole as far as where these rising cavities are positioned next to the sub-bath cavity 31 (for example FIG. 3 with the cavities 23 and 25).
    Indeed, the diameter of this cooling and dusting hole 51 (corresponding to a ceramic rod 50) must be much greater than the diameter of a standard cooling hole which, as indicated above, is conventionally significantly smaller, in order to '' ensure, in addition to cooling, the proper evacuation of dust circulating in the internal cooling air. As illustrated and to ensure effective dusting, this bore is arranged as close as possible to the closed top of the rising cavity, until it almost comes to tangent to this top, and may possibly be brought closer to the bath wall 18B. Preferably, the diameter of the inclined cooling and dusting hole is chosen at least equal to the diameter of a standard dusting hole.
    However, to correctly ensure the dedusting of the cavity using this inclined bore, it is necessary to incline the top of the rising cavity at an angle substantially identical to that of this inclined bore (i.e. more or less 5 °). The inclination of the top of the rising cavity thus makes it possible to guide the residual dust towards the inclined bore and to avoid the formation of zones of accumulation of particles at the top of this cavity. However, the creation of an inclined plane at the top of the cavity by subtracting a core volume results in a local increase in the quantity of corresponding material at the top of the blade compared to a standard configuration as illustrated in FIG. 4, which is unfavorable. for the mechanical strength of the blade because it is likely to generate a creep phenomenon.
    Also, in order not to degrade the mechanical life of the blade, it is necessary to correct this local increase in the quantity of material due to the reduction of the upper part of the column 24 by the addition of an extension of core 52 arranged as close as possible to the rising cavity with the inclined plane and generating an increase in the volume of the part of the under-bath core 30 situated opposite the inclined plane produced at the top 24A of the rising column 24.
    As shown in FIGS. 2 and 2A, this increase in volume of the part of the bathtub core 30 is substantially equal (that is to say more or less 10%) to the volume resulting from the introduction of the plan inclined at the top of the riser 24 and is preferably a projecting part centered on the riser with a width and a height substantially equal to those of the inclined plane (that is to say more or less 10%), the high level of this core extension 52 does not exceed that of this inclined plane, to ensure mechanical behavior similar to the initial configuration.
    FIG. 3 illustrates another embodiment of the invention in which, not one but two rising cavities 23 and 25, are provided with cooling and dedusting bores corresponding to ceramic rods 50 and 54 of columns 22 and 24. As in the preferred embodiment, these two bores are arranged as close as possible to the top of the two rising cavities. The diameter of these inclined cooling and dusting holes is chosen at least equal to the diameter of a standard dusting hole for which they replace. Similarly, the apex of each of the two rising cavities 23, 25 has an angle substantially identical to that of the inclined holes, that is to say of the order of 45 to 75 °. As before, it is necessary to correct the local increase in the quantity of material due to the reduction in the upper part of the columns 22 and 24 by the addition of a core extension 52 arranged as close as possible to these rising cavities at inclined planes and whose volume is substantially equal to the volume resulting from the introduction of the two inclined planes at the top of the risers 22 and 24. This core extension is preferably a projecting part extending over the two risers with a height substantially equal to that of the inclined planes, the high level of this core extension not exceeding that of these inclined planes.
    With the invention, the conductive-convective heat transfer which takes place in the bore between the cooling air and the surrounding metal walls provides cooling by pumping effect of the area at the top of the blade in general and of the low wall. intrados bathtub in particular. The local lowering of the air temperature in the vein and the increase of the heat exchange coefficient, close to the wall in the areas located just downstream of the holes, under the effect of the air emission cooling by the holes, provides cooling by film effect, unlike a conventional dusting hole where, given the angle of emission of the cooling air relative to the wall of the blade, only the pumping effect contributes to the cooling of the area at the top of the blade.
    It will be noted that the inclination of the cooling and dusting holes must be sufficient (preferably greater than 45 °) to benefit from the cooling by film effect without however being too much (preferably less than 75 °) for reasons of manufacturing using the 5 lost wax casting technique.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. Hollow turbine blade of a turbomachine comprising a plurality of rising cavities (23, 25, 29, 31) communicating on the one hand with a bathtub (18) of the blade by a plurality of dusting holes (21A, 21B, 21C) intended for the evacuation of dust and on the other hand by a plurality of inclined cooling bores (20A, 20B, 20C, 20D) intended to cool a wall (18B) of said bath by opening onto a lower surface (12C ) of the blade, characterized in that at least one rising cavity (25) comprises a top (22B, 24B) devoid of a dusting hole and an inclined cooling hole made in its side wall and intended to cool said wall bathtub is enlarged to have a diameter at least equal to the diameter of a standard dusting hole and thus also act as a dusting hole (51), so that the air flow taken for cooling the blade is reduced.
    [2" id="c-fr-0002]
    2. Hollow turbine blade according to claim 1, characterized in that the inclined cooling hole thus enlarged also acting as a dusting hole has an inclination oriented towards the bath (18) between 45 and 75 °.
    [3" id="c-fr-0003]
    3. hollow turbine blade according to claim 1, characterized in that said apex of said at least one rising cavity is inclined at an angle substantially equal to that of said inclined cooling bore.
    [4" id="c-fr-0004]
    4. Hollow turbine blade according to claim 3, characterized in that at least one of the cavities of the blade opposite said inclined apex has an increased volume corresponding at least to the volume subtracted from said at least one rising cavity the addition of said inclined plane.
    [5" id="c-fr-0005]
    5. Hollow turbine blade according to any one of claims 1 to 4, characterized in that said inclined cooling hole thus enlarged is disposed as close as possible to said top of said at least one rising cavity.
    [6" id="c-fr-0006]
    6. Turbomachine comprising a plurality of hollow turbine blades according to any one of claims 1 to 5.
    [7" id="c-fr-0007]
    7. Ceramic core used for the manufacture of a hollow turbine engine turbine blade according to the lost wax casting technique, the blade comprising a plurality of rising cavities (23, 29, 31) communicating on the one hand with a bathtub (18) of the blade by a plurality of dusting holes (21A, 21B, 21C) intended for the evacuation of dust and on the other hand by a plurality of inclined cooling holes (20A, 20B, 20C, 20D) intended to cool a low wall (18B) of said bath by opening onto a lower surface (12C) of the blade, the core comprising:
    - a plurality of core parts (22, 24, 28, 30) intended to form said plurality of rising cavities,
    - a plurality of first ceramic rods (32, 36, 38, 40) of a first determined diameter extending from a side wall (24A) of said plurality of core parts and intended to form said plurality of cooling bores, and
    - a plurality of second ceramic rods (42, 46, 48) of a second determined diameter extending vertically from a top (22B, 24B) of said plurality of core parts and intended to form said plurality of dusting holes, said second determined diameter being greater than said first determined diameter, characterized in that a core portion (24) intended to form a rising cavity (25) of the blade is devoid of a second at its top (22B, 24B) ceramic rod intended to form a dusting hole and a first ceramic rod (50) intended to form in its side wall (24A) an inclined cooling hole also serving as a dusting hole in order to cool said bath wall, has a first diameter at least equal to said second predetermined diameter, and in that said core part (24) has at its apex (24B) an inclined plane and one at the center ns (30) of the other core parts of said plurality of core parts has an increase in volume (52) opposite said apex of said core part.
    [8" id="c-fr-0008]
    8. Ceramic core according to claim 7, characterized in that
    5 that said increase in volume (52) is substantially equal to the volume resulting from the introduction of said inclined plane at the top of said core portion (24).
    [9" id="c-fr-0009]
    9. Ceramic core according to claim 7 or claim
    [10" id="c-fr-0010]
    10 8, characterized in that said increase in volume (52) is a projecting part centered on said core part (24) having a width and a height substantially equal to those of said inclined plane without however exceeding the top of said part of core (24).
    [11" id="c-fr-0011]
    10. Use of a ceramic core according to any one of claims 7 to 9 for the manufacture of a hollow turbine engine turbine blade according to the lost wax casting technique.
    类似技术:
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    FR3056631A1|2018-03-30|IMPROVED COOLING CIRCUIT FOR AUBES
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    FR3099074A1|2021-01-29|Manufacturing process of a hollow blade
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    CA3146412A1|2021-02-04|Turbomachine moving blade with cooling circuit having a double row of discharge slots
    FR3108145A1|2021-09-17|TURBOMACHINE HOLLOW Dawn
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    FR3081497A1|2019-11-29|RAW FOUNDRY DRAWING WITH MODIFIED LEAK EDGE GEOMETRY
    FR3066551A1|2018-11-23|MOVABLE DAWN OF A TURBINE COMPRISING AN INTERNAL COOLING CIRCUIT
    同族专利:
    公开号 | 公开日
    EP3697552B1|2021-09-01|
    EP3697552A1|2020-08-26|
    CN111163877A|2020-05-15|
    FR3072415B1|2020-11-06|
    US20210187594A1|2021-06-24|
    WO2019077237A1|2019-04-25|
    CN111163877B|2022-01-25|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US6264428B1|1999-01-21|2001-07-24|Rolls-Royce Plc|Cooled aerofoil for a gas turbine engine|
    US20040020629A1|2001-10-24|2004-02-05|United Technologies Corporation|Cores for use in precision investment casting|
    FR2986982A1|2012-02-22|2013-08-23|Snecma|FOUNDRY CORE ASSEMBLY FOR MANUFACTURING A TURBOMACHINE BLADE, METHOD FOR MANUFACTURING A BLADE AND AUBE ASSOCIATED|
    US20160341046A1|2014-05-29|2016-11-24|General Electric Company|Dust holes|
    US20170087630A1|2014-06-18|2017-03-30|Siemens Energy, Inc.|Turbine airfoil cooling system with leading edge impingement cooling system turbine blade investment casting using film hole protrusions for integral wall thickness control|WO2020224995A1|2019-05-09|2020-11-12|Safran|Turbine vane of a turbomachine, turbine, turbomachine and associated ceramic core for manufacturing a turbine vane of a turbomachine|
    EP3757351A3|2019-06-26|2021-01-06|Raytheon Technologies Corporation|Airfoil and core assembly for gas turbine engine and method of manufacture|
    EP3757352A3|2019-06-26|2021-01-13|Raytheon Technologies Corporation|Airfoil and core assembly for gas turbine engine and method of manufacture|
    EP3808941A1|2019-10-16|2021-04-21|Raytheon Technologies Corporation|Angled tip rods in a casting core for a turbine blade|RU1625078C|1989-04-27|1994-05-15|Акционерное общество "Авиадвигатель"|Cooled blade for gas-turbine engine|
    US7377747B2|2005-06-06|2008-05-27|General Electric Company|Turbine airfoil with integrated impingement and serpentine cooling circuit|
    US7695243B2|2006-07-27|2010-04-13|General Electric Company|Dust hole dome blade|
    法律状态:
    2019-04-19| PLSC| Publication of the preliminary search report|Effective date: 20190419 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 3 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 4 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1759722|2017-10-17|
    FR1759722A|FR3072415B1|2017-10-17|2017-10-17|HOLLOW TURBINE BLADE WITH REDUCED COOLING AIR INTAKE|FR1759722A| FR3072415B1|2017-10-17|2017-10-17|HOLLOW TURBINE BLADE WITH REDUCED COOLING AIR INTAKE|
    EP18799584.0A| EP3697552B1|2017-10-17|2018-10-11|Hollow turbine blade with reduced cooling air consumption|
    US16/756,194| US20210187594A1|2017-10-17|2018-10-11|Hollow turbine blade with reduced cooling air extraction|
    PCT/FR2018/052536| WO2019077237A1|2017-10-17|2018-10-11|Hollow turbine blade with reduced intake of cooling air|
    CN201880063947.3A| CN111163877B|2017-10-17|2018-10-11|Hollow turbine blade with reduced cooling air extraction|
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