• 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 one-piece bladed disk (14) for a turbomachine blower such as a turbojet engine, said monobloc blisk disk (14) comprising a hub (16) having a general shape of revolution about an axis of rotation (AX) , this hub (16) comprising an outer peripheral face (18) carrying blades (17) of radial orientation. According to the invention, the hub (16) comprises between each pair of blades (17) consecutive, a radial slot (19) opening at its outer peripheral face (18) and extending towards the longitudinal axis, to delimit between each pair of radial slots (19) a base (23) carrying a blade.
    公开号:FR3027340A1
    申请号:FR1459873
    申请日:2014-10-15
    公开日:2016-04-22
    发明作者:Damien Merlot；Etienne Ide
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The invention relates to a fan disc of a turbojet type engine, this disc being of the bladed monoblock type, that is to say that it comprises a hub and blades forming a single piece indissociable.
    [0002] STATE OF THE PRIOR ART A turbofan engine 1 of the type such as that of FIG. 1 comprises an inlet sleeve 2 in which the air is admitted before being sucked by the blades of a fan 3. After passing the fan region, the air splits into a central primary flow and a secondary flow that surrounds the primary flow. The primary air flow then passes through a compressor 4 located immediately after the fan 3 while the secondary flow is propelled backwards to directly generate additional thrust by being blown around the primary flow.
    [0003] The primary flow then passes through a high-pressure compressor 6, before reaching a chamber 7 where its combustion takes place after injection and vaporization of a fuel. After combustion, this primary flow is expanded in a high pressure turbine 8 and then in a low pressure turbine to drive in rotation the compression stages and the fan, before being expelled to the rear of the engine to generate thrust. Each turbine and each compressor comprises a succession of stages each comprising a series of blades oriented radially and regularly spaced around a rotation shaft of the engine. This central shaft or rotor which extends along a longitudinal axis AX carries the rotary elements of the turbine as well as the rotary elements of the compressor and the fan.
    [0004] The blades of the blower may be elements attached to a disk, called a fan disk which is first fixed by splined connection to the motor shaft. After fixing the disk, the vanes are engaged by the front of the disk by being engaged in longitudinal grooves formed at the periphery of the disk and which are called cells. In the case of a bladed disc blower monobloc, the series of blades of the blower is carried by a hub forming with it a single piece and inseparable. A part of such an integral blisk, corresponding to an angular sector around the axis AX, shown schematically in Figure 2 by being identified by 11. The hub 12 of this blisk disc is connected to the blades 3 at the level of regions marked by 13 corresponding to the lower parts of these blades. In case of ingestion by the turbojet engine of a foreign body, it first strikes a set of blades of the fan, giving rise to a mechanical stress likely to lead to the degradation of one or more blades, or even to tearing blade. In the case of a monobloc blisk, as in the case of FIG. 2, the ingestion of a foreign body gives rise to a mechanical stress concentration which is maximum at the level of the base 13 of the struck blades. that is to say at the junction of each of these blades 3 with the hub 12. This situation is due to the fact that the monobloc structure gives rise to greater rigidity of the blades 3 at their connection 13 with the hub 12 forming disc. This tends to increase the mechanical stress when the blades 3 are strongly stressed in bending, which is the case when ingesting a foreign body. It is this stress concentration at the bottom of the blade that is likely to lead to tearing. The object of the invention is to propose a solution for reducing the level of stress in the blade base, particularly in the case of ingestion of foreign matter.
    [0005] PRESENTATION OF THE INVENTION The invention relates to a bladed blower disk for a turbomachine such as a turbojet, said blisk having a hub having a general shape of revolution about a longitudinal axis of rotation, this hub comprising a face external device carrying blades of radial orientation, characterized in that said hub comprises between each pair of consecutive blades, a radial slot opening at its outer peripheral face and extending towards the longitudinal axis, to delimit between each pair radial slots a base carrying a blade.
    [0006] Each base provides additional flexibility to the blade that it bears being able to flex towards one or the other of the radial slots that delimit it in case of shock. This structure thus makes it possible to reduce the mechanical rigidity of the monoblock bladed disc at the level of the bases of its blades, in order to reduce the level of mechanical stress in these regions in the event of ingestion of foreign bodies by the engine. The hub thus participates in the dissipation of energy in the event of the impact of a foreign body on a blade, because it is the entire assembly comprising the base and the blade which is able to flex to absorb the impact. The invention also relates to a disc thus defined, wherein each radial slot opens into an upstream face of the hub to increase the flexibility at the leading edges of the blades. The invention also relates to a disc thus defined, wherein each radial slot opens into a downstream face of the hub to increase the flexibility at the vanishing edges of the blades. The invention also relates to a disc thus defined, comprising inserts closing each radial slot. The invention also relates to a disk thus defined, wherein each radial slot has a bottom delimited by a longitudinal orientation bore which opens into the upstream face and the downstream face of the hub.
    [0007] The invention also relates to a disc thus defined, wherein each bore delimiting a radial slot bottom is dimensioned to receive a disc fixing member to a low pressure compressor. The invention also relates to a turbomachine fan comprising a disk thus defined. The invention also relates to a turbojet type aircraft engine, comprising a monobloc blisk thus defined. BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is an overall view of a turbojet engine shown in longitudinal section; FIG. 2 is a partial view of a monobloc bladed disk according to the state of the art showing an angular sector of this monobloc disk comprising two blades; Figure 3 is a partial view of a monobloc blisk according to the invention showing an angular sector corresponding to four blades. Figure 4 is a local sectional view schematically illustrating the attachment of the bladed disc according to the invention to the low pressure compressor of a motor; Figure 5 is a partial view of a monobloc blisk according to the invention having a recess of its hub in the rear part. DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS The one-piece bladed disk according to the invention, which is partially shown in FIG. 3, is indicated by 14 and has a hub or rim 16 corresponding to its central portion, and which carries a series of blades. The bases of four of these blades are visible in FIG. 3 by being indicated by 17. The hub 16, which has a generally annular shape extending around its axis of rotation AX, forms a whole with the vanes 17 that it door, that is to say a single piece that can be for example a forged hub bearing rolled blades reported by friction.
    [0008] The hub 16 of the one-piece bladed disc 14 has an outer peripheral face 18 having a general shape of revolution around the axis AX, which is here frustoconical, and from which the bases of each of the blades 17, which are spaced from each other, start from around the AX axis.
    [0009] This hub 16 has as visible in Figure 3 a series of radial slots 19 of longitudinal orientations, that is to say substantially parallel to the axis AX. Each radial slot 19 is located between the bases of two consecutive blades 17 about the axis AX, and it extends radially from the outer peripheral face 18 of the hub 16 in which it opens up to a certain depth counted radially, that is to say up to a certain distance from the axis AX where it is closed by its longitudinal orientation bottom. In practice, the distance between the peripheral face and the bottom of a radial slot 19 remains less than two thirds of the thickness of the hub. Each radial slot 19 opens advantageously in the upstream face 21 of the hub and in the downstream face of the hub, these faces being of generally normal orientation to the axis AX. The upstream face is that which faces the flow of air entering the engine, the downstream face being that by which the blisk is integral rigidly to the low pressure compressor of the engine. Each radial slot thus extends over the entire length of the hub, so as to increase the flexibility of the root of the blade from its leading edge to its trailing edge. As can be seen in FIG. 3, the bottom of each of the radial slots 19 is stopped or delimited by a hole or bore 22 that can be substantially inclined with respect to the axis AX, and which opens, like the radial slot itself, into face upstream and downstream face of the hub 16 of the monobloc blisk. These holes 22 make it possible to confer on the bottom of each radial slot a rounded shape, here in an arc of a circle, in particular to constitute a regular surface avoiding the appearance of stress concentrations at the bottom of the slot. Irregularities or angulations could constitute rupture primers, since the bottom of these radial slots coincides with the birth of the bases 23 which they delimit, and thus with zones of high mechanical stresses in the event of loading of the blades. bending around the axis AX. To further reduce the stress concentration at the bottom of the radial slots 19, the hub or rim 16 may advantageously be reinforced, for example by having a greater length along the axis AX in the central region delimited by the bottoms of the radial slots 19. In other words, the hub may be longer in its central part than at its periphery so that the bottoms of its slots 19 are longer. In the example illustrated in FIG. 3, the bores 22 have circular sections, but other shapes can be envisaged, for example holes with an elliptical section or the like, the shape to be adopted being conditioned by the distribution of the stresses in the disk. bladed monoblock considered as a whole. Complementarily, each radial slot is closed by an unrepresented piece, insert type, to seal the space that it leaves empty, to preserve the aerodynamics of the blisk, and if necessary to contribute to the shock absorption . The material used may be a deformable material of elastomer type or the like. More concretely, the filling by parts closing each radial slot makes it possible to give back to the monobloc blisk the external shape of a disk of the state of the art, so as not to disturb the fluid flow of the internal vein, it is that is, the incoming air stream via the blower. The invention thus has no impact on the aerodynamics of the engine. The unrepresented filling pieces are advantageously chosen from a material suitable for damping the narrowing of a radial slot which occurs when the blade contiguous to this radial slot strikes a foreign body, in order to contribute to the absorption of the energy of the shock. corresponding. The holes 22 which delimit the bottom slots allow to give a rounded shape to the bottom of the slots to prevent the occurrence of breakouts, but they also simplify the fixing of the bladed disk to the rotor of the engine.
    [0010] As illustrated schematically in FIG. 4, these holes 22 are advantageously provided for receiving fastening screws making it possible to secure the monoblock bladed disc to the low pressure compressor which is marked at 24 in FIG. 4. As such, these holes 22 are shaped to unblock face upstream and downstream face of the disc so that it can be crossed by fixing screws for securing the monobloc blisk to the rotor 24 by bolting directly from the front of the engine. Furthermore, in order to further increase the flexibility introduced by the radial slots 19 which delimit a base for each blade, the hub 16 may comprise a recess for reducing the length of the bases 23 to a value less than the distance separating the edge of the blade. attack of the trailing edge for each blade. In the example of FIG. 5, the hub 16 thus has a recess at its rear part, indicated by E, so that the downstream face of this hub 16 is offset forwards with respect to the trailing edges of the 17. The bases 23 and have a nominal length less than the length of the blades, which gives them greater flexibility, but also greater flexibility in torsion around the radial axis, so as to further promote the absorption shocks that these blades can suffer. The same type of recess can be made at the leading edges of the blades to move the upstream face of the hub 16 rearward at the bases defined by the slots.
    权利要求:
    Claims (7)
    [0001]
    REVENDICATIONS1. A bladed rotor (14) for a turbomachine such as a turbojet engine, said blisk (14) comprising a hub (16) having a general shape of revolution about a longitudinal axis of rotation (AX), this hub ( 16) comprising an outer peripheral face (18) carrying blades (17) of radial orientation, characterized in that this hub (16) comprises between each pair of blades (17) consecutive, a radial slot (19) opening to its outer peripheral face (18) and extending towards the longitudinal axis of rotation, to define between each pair of radial slots (19) a base (23) carrying a blade to increase the flexibility of this blade.
    [0002]
    The disk of claim 1, wherein each radial slot (19) opens into an upstream face of the hub (16) to increase flexibility at the leading edges of the blades (17).
    [0003]
    Disk according to claim 1 or 2, wherein each radial slot (19) opens into a downstream face of the hub (16) to increase the flexibility at the trailing edges of the blades (17).
    [0004]
    4. Disk according to one of claims 1 to 3, comprising inserts closing each radial slot (19).
    [0005]
    5. Disk according to claims 2 and 3, wherein each radial slot (19) has a bottom defined by a bore (22) of longitudinal orientation which opens into the upstream face and into the downstream face of the hub (16).
    [0006]
    6. Disc according to claim 5, wherein each bore (22) defining a radial slot bottom is sized to receive a disc fixing member to a low pressure compressor.
    [0007]
    7. A turbomachine blower comprising a disk according to one of claims 1 to 6. S. turbojet type aircraft engine, comprising a blisk in one piece according to one of claims 1 to 6.
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3027340B1|2019-06-21|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20030223873A1|2002-05-30|2003-12-04|Carrier Charles William|Inertia welding of blades to rotors|
    US20060099078A1|2004-02-03|2006-05-11|Honeywell International Inc.,|Hoop stress relief mechanism for gas turbine engines|
    GB2440345A|2006-07-26|2008-01-30|Rolls Royce Plc|Integrally bladed rotor having blades made of metallic and non-metallic materials|
    EP2000631A2|2007-06-07|2008-12-10|Honeywell International Inc.|Bladed rotor and corresponding manufacturing method|FR3052805A1|2016-06-20|2017-12-22|Snecma|IMPROVED MONOBLOC AUBING DISK, ROTATING PART OF A TURBOMACHINE COMPRISING SUCH A DISK AND ASSOCIATED TURBOMACHINE|
    FR3056630A1|2016-09-26|2018-03-30|Safran Aircraft Engines|FLOW MONOBLOC BLOWER DISK FOR AIRCRAFT TURBOMACHINE|
    GB2567210A|2017-10-06|2019-04-10|Rolls Royce Plc|A blisk|
    FR3076570A1|2018-01-11|2019-07-12|Safran Aircraft Engines|MONOBLOC AUBING DISC OF A BLOWER COMPRISING ORIFICES IN THE RIM|
    EP3708778A1|2019-03-11|2020-09-16|United Technologies Corporation|Inserts for slotted integrally bladed rotor|
    法律状态:
    2015-10-09| PLFP| Fee payment|Year of fee payment: 2 |
    2016-04-22| PLSC| Search report ready|Effective date: 20160422 |
    2016-10-06| PLFP| Fee payment|Year of fee payment: 3 |
    2017-09-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-09-19| PLFP| Fee payment|Year of fee payment: 5 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 7 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1459873A|FR3027340B1|2014-10-15|2014-10-15|MONOBLOC DRAWING DISK HAVING A HUB PROVIDED WITH RADIAL SLOTS DELIMINATING BLADE PADS|
    FR1459873|2014-10-15|FR1459873A| FR3027340B1|2014-10-15|2014-10-15|MONOBLOC DRAWING DISK HAVING A HUB PROVIDED WITH RADIAL SLOTS DELIMINATING BLADE PADS|
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