• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a device for cooling a disk of a turbine extending along an axis, the disk comprising on its circumference at least one cell surrounded by disk teeth each having an upstream face, the cell having a bottom in fluid communication with an upstream cavity via at least one lunula, the lunula having lateral surfaces, characterized in that the lateral surfaces are inclined with respect to the radial plane which constitutes the plane of symmetry of the cell in which the lunula opens.
    公开号:FR3064667A1
    申请号:FR1752751
    申请日:2017-03-31
    公开日:2018-10-05
    发明作者:Pascal Gregory CASALIGGI
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    GENERAL TECHNICAL AREA AND PRIOR ART
    The invention relates generally to turbomachinery, and more particularly to the ventilation of the stages of a turbine. Fields of application of the invention are the turbojet and turboprop aircraft and industrial gas turbines.
    A turbomachine conventionally comprises a nacelle whose opening allows the admission of a determined flow of air towards the engine proper. Conventionally, the gases flow from upstream to downstream through the turbomachine.
    Generally, the turbomachine comprises one or more sections for compressing the air admitted into the engine (generally a low pressure section and a high pressure section). The air thus compressed is admitted into the combustion chamber and mixed with fuel before being burned there.
    The hot combustion gases from this combustion are then expanded in different stages of the turbine. A first expansion is made in a high pressure stage immediately downstream of the combustion chamber and which receives the gases at the highest temperature. The gases are expanded again by being guided through the so-called low pressure turbine stages.
    A turbine T of axis X, an example of which is illustrated in FIG. 1, low pressure or high pressure conventionally comprises one or more stages, each consisting of a row of fixed vanes 1, also called a distributor, followed by a row of movable vanes 2, which form the rotor 3. The distributor 1 deflects the flow of gas taken from the combustion chamber towards the movable vanes 2 of the turbine at an appropriate angle and speed in order to rotate these movable blades 2 and the rotor 3 of the turbine T.
    The rotor generally comprises an assembly of several discs 4, an example of which is shown in FIG. 1.
    These discs 4 generally comprise, as in the embodiment shown in FIG. 2, peripheral grooves such as assembly indentations or cells 5 in which the movable blades 2 are put and held in position, in particular thanks to the particular profile of the " teeth "6 of the disc framing each cavity 5 (or cell) in which the blades 2 are inserted.
    A disc tooth 6 has a profile comprising a first 7 and a second 8 bearing surfaces forming an assembly cooperating with complementary surfaces formed on the movable blade 2. These bearings 7 and 8 ensure a radial and tangential stop at the blade root by report to disk. Other geometries can also perform these functions, such as for example a blade root having a dovetail section.
    The axial stop of the movable blade 2 on the disk 4 can be ensured by the friction between the blade 2 and the teeth 6 of the disk, or by upstream 11 and downstream 12 flanges shown in FIG. 3.
    A specific ventilation circuit for the rotor discs 4 has been designed to limit the effects due to the extreme thermal environment to which the rotor 3 is subjected.
    The ventilation circuit directs a flow F of pressurized air taken upstream of the turbine T, typically at one of the compressors, to introduce it into the rotor 3 in order to cool its discs 4, in particular its blades 2 .
    To this end, the blade has a series of internal channels allowing the cooling flow F to circulate inside them and to cool the blade 2 more effectively.
    The blade 2 does not completely fill the cell 5, forming a bottom 10 of the cell 5 extending substantially along the axis X, the bottom 10 of the cell 5 being located upstream (in the direction d 'gas flow) of the internal channels allowing circulation of the cooling flow F to the latter.
    This cooling flow F passes through several enclosures delimited by the rotor discs 4 and upstream 11 and downstream 12 flanges provided for this purpose, the different successive enclosures being placed in fluid communication.
    The axial and radial positioning necessary for the flanges 11 and 12 with respect to the rotor discs 4 to fulfill their role is conventionally achieved by dogs 13 located in the extension of the disc teeth 6. In the example illustrated, these dogs 13 form an additional thickness at the level of the upstream surface of the disc 4, this additional thickness forming an axial shoulder 131 allowing it to be brought into axial position and a short centering 132 allowing it to be brought into radial position of the ring. seal 11 on the rotor disc 4.
    The dogs 13 frame lunulas 14, which are depressions extending substantially radially with respect to the axis X of the turbomachine, and are usually machined directly on the upstream face of the rotor disc 4.
    These lunules 14 ensure the continuity of the ventilation circuit by forming a fluid communication between a cavity 15 located upstream in the direction of flow of the fluids and the bottom of the cells 10 located in the cells 5.
    In the prior art illustrated in FIG. 4a (see patent FR 2 981 979), the lunules 14 have a level offset as well as an inclination relative to the upstream surfaces 16 of the teeth 6 of the disc. This embodiment has the disadvantage of forming an intermediate cavity 17 just upstream of the cells 5. The cooling flow F circulates from an upstream cavity 15 to the intermediate cavity 17 by the lunulas 14.
    In this intermediate cavity 17, the cooling flow F has a lower tangential speed than that of the cells 5, this phenomenon being shown in FIG. 4b. This tangential speed difference prevents the cooling flow F from flowing optimally towards the cells 5 and reduces the performance of the cooling system.
    With reference to FIG. 5a, a second embodiment presents lunulas 14 produced in withdrawal and not inclined with respect to the upstream surfaces 16 of the teeth 6 of the disc.
    In this way, the flow F passing through a lunula 14 is more able to circulate in the cells 5, the effects of this embodiment being illustrated in FIG. 5b.
    The disc teeth 6 may include keying devices 18 securing the assembly steps by avoiding the mounting of vanes 2 upside down axially on the discs.
    Referring to Figure 6, the blade 2 is inserted into the disc cavity, and has a geometry cooperating with the keying device 18 to prevent the blade from being inserted in the wrong direction.
    The polarizers 18 can also be used to balance the disc.
    The relative total pressure of the gases at the bottom of the cell 10, represented in FIGS. 7a and 7b, makes it possible to emphasize the impact of this modification on the distribution of the cooling flow F in the cells 5.
    FIG. 7a representing the distribution of the pressure of the gases in the bottom of the cell 10 in an embodiment where the lunules 14 have an angular and level offset upstream relative to the upstream surfaces 16 of the teeth 6 of the disc, FIG. 7b representing the same parameter in the embodiment where the lunula 14 is set back downstream relative to the upstream surfaces 16 of the teeth 6 of the disc.
    The zones having lower relative total pressure levels 25 supply the cooling channels of the blades less efficiently, which reduces the performance of the cooling system and therefore the life of the blades 2.
    It is easily observable that the location of the lunules 14 in withdrawal from the upstream surfaces 16 of the disc teeth 6 makes it possible to limit the disparities in the distribution of the load and to obtain a more homogeneous flow, therefore better cooling.
    If this modification brings a performance gain for the cooling system, it nevertheless brings a disadvantage for the lifetime of the rotor disc 4. Indeed, the edge 19 between the lunula 14 and the cell 5 has stress concentration zones, shown in FIG. 8.
    These stress peaks severely limit the life of the disks
    4. The flow of the cooling flow further comprising several bends, the overall pressure drop of the circuit also represents a factor significantly reducing the performance of the cooling system of the blades 2, and therefore limits the gain in service life of the blades 2 .
    OVERVIEW OF THE INVENTION
    An object of the invention is to increase the life of the rotor discs.
    Another aim is to increase the lifespan of the blades.
    Another aim is to increase the performance of the cooling system.
    Another object is to reduce the pressure drops in the cooling system.
    Another aim is to reduce the stress concentrations around the lunules.
    Another object of the invention is to reduce the flow rate of the flow taken upstream of the turbines to supply the cooling system.
    According to one aspect, the invention provides a device for cooling a disc of a turbine extending along an axis, the disc comprising on its circumference at least one cell framed by disc teeth each having an upstream face, l cell having a bottom in fluid communication with an upstream cavity by means of at least one lunula, the lunula comprising portions of lateral surfaces, characterized in that the portions of lateral surfaces are inclined relative to the radial plane which constitutes the plane of symmetry of the cell in which the lunula opens.
    Such a device is advantageously supplemented by the following different characteristics taken alone or in combination:
    - The lunula has a bottom set back downstream relative to the upstream faces of the disc teeth;
    - The limit between the bottom of the lunula and the bottom of the cell of the ventilation circuit has a broken edge;
    - the broken edge includes an edge fillet which has an evolving radius of curvature;
    the lunula comprises a curved portion called the lower surface and a curved portion called the upper surface joining the portions of lateral surfaces and the bottom of said lunula, each curved portion comprising a plurality of radii of curvature;
    the radii of curvature of the curved portion called the lower surface are different from the radii of curvature of the curved portion called the upper surface;
    - the portions of lateral surfaces of the lunula are curved;
    - An axis normal to the bottom of the lunula is defined as being perpendicular to a straight line passing through the ends of the bottom of the lunula, this normal axis being inclined relative to the axis of the turbine in a first direction;
    - The axis normal to the bottom of the lunula is inclined relative to the axis of the turbine in a second direction;
    the cell extends along an axis inclined by a broaching angle relative to the axis of the turbomachine, the broaching angle being between 0 and 20 °, preferably between 3 ° and 16 °, particular 6 ° and 12 °;
    According to another aspect, the invention provides a rotor comprising such a device for cooling a disc.
    According to another aspect, the invention proposes a turbomachine comprising such a device for cooling a disc.
    PRESENTATION OF THE FIGURES
    Other characteristics and advantages of the invention will emerge from the description which follows, which is purely illustrative and not limiting, and should be read with reference to the appended figures in which:
    Figure 1 is a schematic representation of a profile sectional view of a portion of a turbomachine turbine;
    FIG. 2 is a 3D modeling centered on the circumferential profile of a rotor disc;
    Figure 3 is an axial sectional view centered on the assembly area between a rotor disc and a blade;
    Figure 4a is an axial sectional view of a first embodiment of the prior art lunula, which symbolizes the path of the flow of the coolant;
    FIG. 4b is a 3D modeling of a first embodiment of the prior art lunula, which symbolizes the trajectory of the flow of the cooling fluid;
    FIG. 5a is a profile section view of a second embodiment of the prior art lunula, which symbolizes the path of the flow of the cooling fluid;
    FIG. 5b is a 3D modeling of a second embodiment of a lunula of the prior art, which symbolizes the trajectory of the flow of the cooling fluid;
    Figure 6a is a schematic profile view of the mounting of a blade in a cell in a first direction;
    Figure 6b is a schematic side view of the mounting of a blade in a cell in a second direction;
    FIG. 7a is a representation of a simulation of the relative total pressure of the cooling fluid in the cells in the first embodiment of the prior art;
    FIG. 7b is a representation of a simulation of the total relative pressure of the cooling fluid in the cells in the second embodiment of the prior art;
    FIG. 8 is a simulation by finite elements of the distribution of the surface stresses at the level of the lunule / cell interface zone;
    Figure 9a is a partial top sectional view of the lunula;
    Figure 9a is a partial sectional view in profile centered on the lunula;
    FIG. 9c is a partial sectional view in profile centered on the lunula;
    FIG. 9d is a 3D representation of a portion of a disc centered on the alveoli and the lunules;
    FIG. 10a is a schematic front view of a portion of a disc showing an embodiment of the right lunula;
    FIG. 10b is a schematic front view of a portion of a disc showing an embodiment of an inclined lunula and the effect on the flow of the flow of such an inclination;
    Figure 11 is a schematic front view of a disc portion showing an embodiment of a curved lunula.
    DESCRIPTION OF DONATION OR SEVERAL MODES OF IMPLEMENTATION AND
    PRODUCTION
    The embodiments described below relate to the case of a turbine T comprising a series of distributors (or stators) alternated along the axis X of rotation of the turbomachine with a series of mobile disks 4 (or rotor). This is not, however, limiting, insofar as the turbine T could comprise a different number of stages, which may be single or multi-stage.
    The discs 4 have lunules 14 whose geometry is optimized to facilitate the flow of the fluid in the ventilation circuit and therefore the performance of the cooling system, while minimizing the concentrations of internal stresses in the room at the lunules 14.
    With reference to FIG. 9a, the bottom 20 of a lunula 14 extends substantially radially with respect to the axis X of the turbomachine and can be defined by a normal axis n.
    The bottom 20 of lunula 14 can have various geometries, the normal axis n can be defined as perpendicular to a straight line passing through the ends of the bottom 20 of lunula 14.
    The normal axis n is inclined at an angle a relative to the axis X of the turbomachine about a first radial axis Y of the rotor disc 4.
    In certain embodiments, the cells extend along a pinning axis A which can be inclined by a pinning angle Φ relative to the axis X of the turbomachine T.
    This pinout angle Φ can be between 0 and 20 ° relative to the axial direction X, preferably between 3 ° and 16 °, in particular between 6 ° and 12 ° .This inclination can be oriented in all directions, from so that the potential orientation of the broaching axis is included in a cone with an axis parallel to the axis X of the turbomachine and an opening of 20 °.
    ίο
    The lunula 14 is also delimited by lateral surface portions 21 extending substantially radially, and two curved surface portions called intrados 22a and called extrados 22b joining the bottom 20 of the lunula 14 and the lateral surfaces 21 of the lunula 14. The curved surface portions respectively intrados 22a and extrados 22b here correspond to a surface portion arranged on the respective intrados and extrados side of the blade of the blade 2 assembled in the corresponding cavity 5.
    The portions of curved surface called intrados 22a and called extrados 22b of the lunulas 14 have radii of curvature Ri (i is a natural number) maximized to minimize the stress concentration coefficients.
    Each curved portion 22a and 22b may comprise several radii of curvature Ri different depending on the location of the point concerned.
    Due to the asymmetrical concentration of the stresses at the lunula 14, a symmetrical geometry of the lunula 14 may not have a significant effect on the reduction of the maximum stress peak simulated in the disc 4 at the lunula 14.
    For this reason, each of the curved surface portions 22a and 22b has its own radius or radii of curvature Ri, the radii of curvature Ri ′ of the curved portion called the underside 22a may be identical or different from the radii of curvature Ri of those of the portion of curved surface called upper surface 22b.
    Referring to Figure 9b, the normal axis n is inclined at an angle β relative to the axis X of the turbomachine about the second radial axis Z of the rotor disc 4.
    In one embodiment, the second radial axis Z is a tangential axis perpendicular to the first radial axis Y.
    With reference to FIG. 9c, a critical factor for the concentration of stresses at the level of the lunula 14 is the presence of a sharp edge 19 between the lunula 14 and the cell 5.
    This edge 19 may have a geometry studied to reduce the stress concentration factor in this area.
    This geometry may include a chamfer, a fillet, a rounding, a boss, an additional thickness or any mechanical or thermal treatment making it possible to reduce the maximum stress peak noted in the area of the lunula or making it possible to locally increase the mechanical characteristics of the room.
    In the case of an edge leave, the leave may have an evolving radius of curvature r depending on the point of the leave. This embodiment makes it possible to significantly reduce the phenomenon of concentration of stresses in the area of the lunula 14.
    In addition to reducing the concentration of stresses in lunula 14, this modification makes it possible to reduce the criticality of the part in an abacus established by a consortium of engine manufacturers (Rotor Integrity Sub-Committee (RISC)).
    This classification (RoMan) associates a degree of criticality with a part according to the geometrical elements which it presents and makes it possible to determine the manufacturing process which will be applied to realize this part.
    The lower the criticality, the less demanding and therefore expensive the manufacturing processes.
    The removal of a sharp edge 19 in favor of an edge 19 having a fillet makes it possible to reduce the criticality of the disc 4. The reduction in the criticality of the disc 4 makes it possible to produce it by methods simpler to implement and to reduce its manufacturing cost.
    In an embodiment illustrated in FIG. 9d, the lateral surface portions 21 of the lunula 14 are inclined (angle δ) relative to the radial plane which constitutes the plane of symmetry of the cell 5 into which the lunula 14 opens.
    In fact, despite the positioning of the lunulas 14 set back from the upstream surfaces 16 of the disc teeth 6, a tangential speed difference remains between the cooling flow F and the alveoli 5. The cooling flow F first circulates axially for reach the upstream cavity 15, then radially to reach the lunules and finally axially to enter the cells 5 despite the tangential speed of the latter due to the rotation of the discs 4.
    With reference to FIG. 10a, at the level of the upstream mouth of a lunula 14, the cooling fluid circulates at a tangential speed VI while the point of the disc 4 at this radius has a tangential speed V2 greater than that of the fluid .
    The fluid therefore has a relative speed V3 relative to the disc 4, oriented inversely with respect to the speed VI of the disc 4 at this point.
    The fluid therefore circulates with respect to the disc 4 in the opposite direction to the rotation of the disc 4.
    Consequently, to reduce the incidence i of the elbow in the flow of the cooling fluid, the side walls of the lunules 14 are inclined (angle δ).
    The inclination of the lateral surface portions 21 of the lunulas 14 (angle δ) reduces the elbow in the direction of the flow of cooling F at the level of the lunula 14. It promotes its admission into the alveolus 5 by reducing the singular pressure drop in this area, thereby increasing the efficiency of the cooling system.
    The inclination direction is chosen as a function of the direction of rotation expected for the disc 4 in operation in order to reduce the bend which the cooling flow F must cross.
    With reference to FIG. 11, in order to limit the impact of the elbows in the flow, the lateral surface portions 21 of the lunulas 14 may have a curvature, thereby making it possible to reduce the losses of singular loads in the ventilation circuit and thus increase the performance thereof.
    This curvature can be a simple curvature or a more complex curvature (with twist for example).
    The curvature of the lateral surface portions 21 can be constant or have a variable radius of curvature configured to minimize the pressure drops along the lunula 14.
    The curvature of the lateral surface portions 21 makes it possible to further reduce the incidence i in the bend of the flow of cooling fluid.
    In fact, the inclination of the portions of lateral surfaces 21 of the lunulas 14 cannot exceed a certain limit due to the geometrical characteristics of the disc 4, its method of manufacture and the mechanical characteristics to be respected.
    A curvature makes it possible to reduce the incidence of the elbow of the flow of cooling fluid while reducing the inclination of the lateral surface portions 21 for an equal incidence.
    The reduction in pressure drops in the cooling system improves its performance, thus increasing the life of the discs 4 and the blades 2.
    This reduction in pressure drops also makes it possible to reduce the flow rate of the flow taken upstream of the turbine to supply the cooling system, thus minimizing the impact of the cooling system on the performance of the turbomachine.
    权利要求:
    Claims (11)
    [1]
    1. Device for cooling a disc (4) of a turbine (T) extending along an axis (X), the disc (4) comprising on its circumference at least one cell (5) framed by teeth ( 6) of a disc each having an upstream face (16), the cell (5) comprising a bottom (10) in fluid communication with an upstream cavity (15) by means of at least one lunula (14), the lunula (14) comprising portions of lateral surfaces (21), characterized in that the portions of lateral surfaces (21) are inclined (angle δ) relative to the radial plane which constitutes the plane of symmetry of the cell (5) into which opens the lunula (14).
    [2]
    2. Device according to one of the preceding claims, characterized in that the lunula (14) has a bottom (20) set back downstream relative to the upstream faces (16) of the teeth (6) of the disc.
    [3]
    3. Device according to claim 2, characterized in that the limit between the bottom of the lunula (20) and the bottom of the cell (10) of the ventilation circuit has a broken edge (19).
    [4]
    4. Device according to claim 3, characterized in that the broken stop (19) comprises an edge leave which has, in profile section, a radius of curvature (r) evolving.
    [5]
    5. Device according to one of claims 2 to 4 characterized in that the lunula (14) comprises a curved portion called the lower surface (22a) and a curved portion called the upper surface (22b) joining the portions of the lateral surfaces (21) and the bottom (20) of said lunula (14), each curved portion (22a, 22b) comprising a plurality of radii of curvature (Ri ', Ri).
    [6]
    6. Device according to claim 5, characterized in that the radii of curvature (Ri ') of the so-called lower surface curved portion (22a) are different from the radii of curvature (Ri) of the so-called upper surface curved portion (22b).
    5
    [7]
    7. Device according to one of the preceding claims, characterized in that the portions of lateral surfaces (21) of the lunula (14) are curved.
    [8]
    8. Device according to claim 3, characterized in that an axis
    [9]
    10 normal (n) at the bottom of the lunula (20) is defined as being perpendicular to a straight line passing through the ends of the bottom of the lunula (14), this normal axis (n) being inclined (angle a) relative to the axis (X) of the turbine in a first direction.
    15 9. Device according to one of claims 3 or 4, characterized in that the normal axis (n) at the bottom of the lunula (20) is inclined (angle β) relative to the axis (X) of the turbine (T) in a second direction.
    10. Device according to one of the preceding claims, characterized in
    20 that the cell (5) extends along an axis (A) inclined by a broaching angle (Φ) relative to the axis (X) of the turbomachine, the broaching angle (Φ) being between 0 and 20 °, preferably between 3 ° and 16 °, in particular 6 ° and 12 °.
    25
    [10]
    11. Rotor (3) comprising a device according to one of the preceding claims.
    [11]
    12. Turbomachine comprising a rotor (3) according to claim 11.
    1/9 ► <
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    同族专利:
    公开号 | 公开日
    FR3064667B1|2020-05-15|
    CN108691569A|2018-10-23|
    US10808536B2|2020-10-20|
    EP3382146B1|2021-01-06|
    EP3382146A1|2018-10-03|
    US20180283178A1|2018-10-04|
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    法律状态:
    2018-02-19| PLFP| Fee payment|Year of fee payment: 2 |
    2018-10-05| PLSC| Publication of the preliminary search report|Effective date: 20181005 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 4 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 5 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1752751A|FR3064667B1|2017-03-31|2017-03-31|DEVICE FOR COOLING A TURBOMACHINE ROTOR|
    FR1752751|2017-03-31|FR1752751A| FR3064667B1|2017-03-31|2017-03-31|DEVICE FOR COOLING A TURBOMACHINE ROTOR|
    US15/941,802| US10808536B2|2017-03-31|2018-03-30|Device for cooling a turbomachine rotor|
    EP18165331.2A| EP3382146B1|2017-03-31|2018-03-30|Cooling device for a turbine disk and corresponding turbomachine|
    CN201810283403.XA| CN108691569A|2017-03-31|2018-04-02|A kind of device for cooling down turbine rotor|
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