• 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 proposes a blower, in particular for a small turbomachine such as a turbojet, having a hub ratio, which corresponds to the ratio of the diameter of the internal limit of the air inlet duct (26) to level of the radially inner ends of the attack edges of the fan blades (10), divided by the diameter of the circle or pass the outer ends of the fan blades, of value between 0.25 and 0.27.
    公开号:FR3014151A1
    申请号:FR1361906
    申请日:2013-11-29
    公开日:2015-06-05
    发明作者:Christophe Perdrigeon；Laurent Jablonski；Philippe Gerard Edmond Joly
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to obtaining a particular design of a blower, in particular for a turbomachine, such as a turbojet engine. The invention is a real technical challenge, and is of particular interest when it concerns turbomachines whose external dimensions have been planned to adapt to the field of business aviation. Typically, these turbomachines, of relatively small size, have an inlet diameter, defined by the diameter upstream of the turbomachine vein, between 900 mm and 1550 mm, in order to have dimensions closely related to a total mass and adapted to an assembly on aircraft type business jets. As with any type of turbomachine, the developments concerning this type of small turbomachine essentially concern the improvement of the performances, a reduction of the consumption and a gain in mass. The axes of development are in this sense numerous and can for example concern material choices, the study of the shapes of the blades, an optimization of the mechanical links between the parts, the prevention of the leaks, etc. One of the axes of development generally followed consists in reducing the hub ratio of the turbomachine blower. This hub ratio is the ratio between the outer diameter of the leading edge hub of the fan blades, and the diameter of the circle where the radial ends of these fan blades pass. The reduction of the hub ratio generally involves a radial reduction in the hub size, and therefore a gain in mass, but also implies an increase in the suction section of the turbomachine, implying an increase in the air flow propelling the turbomachine. , and therefore a gain in performance.
    [0002] However, given the current know-how in the design and manufacture of small turbomachinery, such as those having an inlet diameter defined above, this type of turbomachine is considered as not permitting a reduction in the outer diameter of the hub, particularly at the leading edge of the fan blades, below the diameter currently used which is typically between 570 and 585 mm. Indeed, the current dimensions of the mechanical elements composing the hub are considered as nonreducible, mainly for obvious considerations of radial blade mechanical strength, torsional strength, tolerances and manufacturing methods, accessibility by the tools, etc.
    [0003] Going against these technical prejudices, the invention proposes a particular dimensioning choice of a turbomachine blower offering a significant gain in performance and mass. For this purpose, the invention proposes a blower, in particular for a turbomachine such as a turbojet, the blower comprising, at the inlet, fan blades, an annular casing, a hub rotating about an axis of the turbomachine and bearing the blades, which extend radially with respect to said axis in an annular groove delimited internally by the hub and externally by the annular housing, said hub comprising a fan disk having at its outer periphery substantially axial ribs formed alternately with grooves in which are engaged the blade roots, said fan having an inlet diameter, which corresponds to the diameter of the circle comprising the radially outer ends of the blades, of value between 900 mm and 1550 mm, and having a hub ratio, which corresponds to the ratio of the diameter of the internal limit of the vein at the radially internal ends of the the fan blades attack, divided by the input diameter, between 0.20 and 0.265. It is more particularly proposed an input diameter of value between 900 mm and 1200 mm, in order to provide even more advantageous results in terms of mass. As will be explained later, the particular choice of such an outer diameter is the subject of a technical prejudice all the more important. In addition, the invention proposes a specific mechanical arrangement of the rotor of this fan which is particularly well suited to this choice of dimensioning. Generally, the rotor of a fan of a turbomachine comprises a disc carrying at its outer periphery blades whose feet are engaged in substantially axial grooves of the outer periphery of the disc. The vanes are retained radially on the disc by cooperation of shapes of their feet with the grooves of the disk, the blade roots being for example of the dovetail type. Inter-blade platforms are mounted on the disc between the fan blades. The disc is usually equipped with balancing leeks extending radially inwards.
    [0004] In the present art, the vanes are held axially on the disk by means which are mounted on the disk, upstream and downstream of the blades, and which prevent the blade roots from moving axially in the grooves of the disk. The holding means located downstream of the blades comprise for example at least one blade root hook which is engaged in a notch machined on an upstream end portion of the low pressure compressor arranged downstream of the fan. In order to allow the mounting of these hooks in the notches of the low pressure compressor, it is necessary to radially enlarge the grooves of the disc relative to the blade roots. Thus, it is possible to move the vanes axially at the bottom of the grooves and to position the hooks of the blade roots in radial alignment with respect to the notches. The blades may then be radially raised in the grooves with sufficiently thick wedges, arranged at the bottom of the grooves, in order to engage the hooks of the blade roots in the notches and to keep the blades in the up position.
    [0005] The holding means located upstream comprise for example an annular flange reported and fixed on the upstream end of the disc. The flange is mounted coaxially on the disc and has a scalloped portion cooperating with a corresponding scalloped portion of the disc.
    [0006] This flange axially blocks the ring on the disk and is immobilized in rotation relative to the disk. The outer periphery of the flange bears axially on the blade roots for their axial retention downstream, its inner periphery being applied and fixed on a corresponding annular flange of the disc. The outer periphery of the flange further comprises catching pins of the upstream ends of the inter-blade platforms. A ferrule of substantially frustoconical shape mounted on the disk, upstream of the blades, internally delimits the annular air inlet vein in the turbomachine. This shell comprises in the vicinity of its downstream end a radially inner annular flange which is applied axially on the aforementioned flange and which is fixed with the flange on the disk flange by bolts. A frustoconical cap is further mounted on the above-mentioned shell, at the upstream portion thereof, by means of other bolts, engaged in holes in the flanges of the cover and the shell and which are located radially at the inside the bolts attaching the ferrule to the disc. Such a structure can not be used when the blower has a small diameter. Indeed, the radial space is not sufficient to accommodate all the aforementioned bolts and flanges. In particular, it is difficult to accommodate the bolts and flanges used for fixing the cover on the shell. In addition, the disk is fixed to a drive shaft by means of nuts screwed onto the shaft via radial flanges. In order to assemble and disassemble the fan rotor, it is necessary to be able to axially access these nuts with a tool.
    [0007] For this, the operator must have sufficient space around the central axis. In the case where the fan is of small diameter, the structure described above of the prior art does not allow access to the aforementioned fixing means of the disc on the shaft. The prior art therefore does not allow, in accordance with the aforementioned technical prejudice, to form a fan of size and hub ratio defined by the invention. The document EP 1 357 254 also discloses a fan rotor whose structure has a large radial and axial space. The document WO 2012/114032 presents a structure that authorizes the production of a compact small-diameter fan, using a ring fixed to the disk and having axial anti-rotation teeth of the flange. However, this structure is not perfect in terms of overall mass and stability of the flange, which means that the axial maintenance of the blades operated upstream is not optimal and completely effective. In addition, this structure is not suitable when the disk, for reasons of optimization and reduction in size, comprises an upstream flange extending inwardly for bolting the frustoconical cap and bolting a locking ring in rotation of the axial retaining flange of the blades. Providing a simple, effective and economical solution to this problem is a goal sought here, including as such, possibly independently of the aforementioned and claimed input diameter and hub ratio constraints. For this purpose, it is proposed that an annular cover is provided mounted on the disk upstream of the blades, and axial retaining means of the blades on the disk having a flange mounted in an annular groove of the disk and forming an axial support. blade roots, the flange having a scalloped radial annular flange and cooperating with a radial annular flange festooned with the annular groove of the disk, so as to ensure axial locking of the flange in the annular groove of the disk, and immobilizing means in rotation of the flange, comprising a ring provided with ears extending radially inwards and formed with fastening means on an upstream radial face of the disc, said cap being fixed to the disc by fastening means common to the means fixing at least some ears of the ring on the disc, characterized in that said ring further comprises at least one radial projection cooperating with a complementary stop flange, so as to lock in rotation the flange relative to the ring. The structure defined above allows a more compact assembly than in the prior art, which allows a location and a more radially external concentration of the fastening means between the cover, the flange and the disk, for greater design flexibility of the surrounding turbomachine. In addition, the fixing ring used in the invention described above has a smaller mass than the ring used in WO 2012/114032, because it does not include teeth extending axially downstream. . According to a particular embodiment, the disc comprises an upstream flange extending inwards, and having holes aligned with holes of the ears for the passage of axial screws for fixing the ring on the disc. The screws provide a rigid fixation ensuring the antirotation between the ring and the disc. Advantageously, the ring comprises a cylindrical portion from which the radial projections extend radially outwards, the lugs extending radially inwardly from the upstream edge of the cylindrical portion, the cylindrical portion of the ring being in radial support on said disk flange. Thus, the ring matches the shape of the flange where it is fixed for a reduction in the space required to attach the ring to the disc.
    [0008] Preferably, the abutments of the flange cooperating with the radial projections of the ring are formed by festoons formed on an upstream edge of the flange. The flange maintained in axial support on the blades at its downstream edge is thus held fixed in rotation at its upstream edge by the projections of the ring. This maintenance provided at each edge of the flange gives it greater stability than the flanges used in the prior art. According to another characteristic, one of the festoons is formed on the upstream edge of the flange, in axial alignment with each rib of the disc. The festoons may furthermore be arranged only in the alignment of these ribs. This gives a better balance in rotation of the fan rotor. Advantageously, a radial projection of the ring is inserted every two festoons of the flange. This is enough to ensure the anti-rotation of the flange while decreasing the mass of the ring. According to yet another characteristic, the cover comprises, in its median part, an inner annular rim in which are formed axial blind holes opening downstream and serving to accommodate the heads of the screws for fixing the ring on the disc, and through axial holes for the passage of screws for fixing the cover and the ring to the disk. In this way, some ears of the ring are traversed by screws for fixing the cover and the ring on the disc and other ears of the ring are crossed by screws used only for fixing the ring on the disc. In addition, in the case where the cover is made of a lightweight material such as aluminum, there is a risk of tearing the latter, for example in case of ingestion of a bird in the blower. In such a case, the pulling of the cover can not lead to the separation of the ring and the disc. Indeed, the hood tearing has no effect on the screws used only for fixing the ring and disk. This avoids any output of the axial holding flange blades and therefore any accidental ejection of one or blades of the fan. Preferably, the fastening screws of the ring on the disc are alternating with the screws for fixing the cover and the ring to the disk. In one embodiment, an indexing pin is mounted in one of the aligned holes of the ring and disk and includes an upstream head received in a blind hole of the inner radial rim of the hood. This indexing pin provides an angular reference between the ring and the useful disk during disassembly and assembly of the fan rotor. Also concerned is a turbomachine, comprising a fan rotor as described above. It is further proposed a ring for a fan rotor as described above, comprising a cylindrical portion having an inner cylindrical face and an outer cylindrical face from which radial projections extend regularly radially outwardly, ears extending radially inwardly of the cylindrical portion from an edge of the cylindrical portion, each lug being located substantially between each pair of adjacent projections.
    [0009] Finally, there is an annular flange for a fan rotor as described above, comprising a substantially frustoconical wall of variable thickness, the end of which is the largest diameter is connected to an annular flange extending inwardly and being scalloped regularly, and whose smallest diameter end is scalloped regularly. The fan rotor described above, the particular design of which derives directly from the choice of hub ratio made in the context of the realization of small turbomachine, also has an unexpected and particularly advantageous technical effect, in the context of context. described below. The particular choice of the hub ratio mentioned in this patent application implies in fact a general reduction in the dimensions of the fan disk of the turbomachine with respect to the prior art. This disc has an outer diameter, at its outer limit formed by the outer ends of the ribs, the value of which is then typically between 245 and 275 mm. It remains necessary, however, that this disk responds to the constraints relating to the continued operation of the fan blades, whose number and dimensions remain relatively identical compared to the prior art. For this purpose the number of blades is preferably between 17 and 21 blades, and more particularly between 18 and 20 blades. The height and the width of the grooves of the disc must, in addition, according to the state of the art, not undergo dimensional reduction, in order firstly to allow the engagement of the downstream hooks for axial retention of the evoked blades. in this application, and secondly to be adapted to the size of the blade feet whose dimensions have not been reduced to support the blades rotating. The simultaneous requirements of maintaining the dimensions of the grooves of the disk, and of reducing the overall diameter of the disk, then necessarily imply a reduction in the width, that is to say the circumferential dimension, of the ribs of the disk. The ribs of the fan disk, which are thinner than in the prior art with a higher hub ratio, therefore have greater brittleness and a greater risk of rupture, compared with the torque supported in operation, than the ribs of the prior art. In order to remedy this problem, it has been advised to form the fan disc made of an alloy known under the trademark inconel, which is very resistant. This alloy is however very heavy, which affects the overall performance of the turbomachine, and therefore does not constitute a satisfactory solution.
    [0010] In the context of the fan rotor described above, it has unexpectedly been observed that the axial blocking of the blades operated by the retention flange of the invention was sufficiently effective and resistant to dispense with the axial blocking effected by the hooks downstream of the 5 blade roots engaged in the low-pressure compressor, with regard to a turbomachine whose dimensions have been previously specified. The inventors have therefore advantageously removed the downstream hook, and have consequently had the possibility of reducing the radial height of the grooves of the fan disk, which corresponds to their radial dimension taken between their bottom and the top of the ribs, part of which was previously reserved for mounting downstream hooks, at a height typically between 18 and 22 mm. Yet another aspect of the present subject is the wedges which are then used in groove bottoms to keep the blades up against the ribs. These wedges must then perform the functions of limiting the travel of the blade roots in the grooves in operation, to protect the bottoms of the grooves, and to dampen the blades in case of their rupture or during the ingestion of a body bulky by the turbomachine. In order to respect these constraints optimally, especially in the new context described above, the shims retained here have been radially thinned with respect to the pre-existing solutions, and individually has a radial thickness typically between 1 and 3 mm, and more particularly equal to 2 mm, it being specified that such shims could be provided even out of the aforementioned input diameter and hub ratio constraints. Each shim is more particularly in the form of a two-sided board, elongated along the axis of the fan and placed against the bottom of one of the grooves. This wedge is symmetrical in the three axial, radial, and circumferential directions, which avoids possible assembly errors. Each face of the shim preferably has lateral or circumferential chamfered edges, the chamfers each forming an angle of 10 °, plus or minus 2 °, with one face. The chamfers of each face radially vis-à-vis meet at the lateral ends of the wedge so as to form the two side edges of the wedge. The junction angles between the faces of the shim and the chamfers are preferably softened so as to have a curvature of radius of between 1.50 mm and 1.80 mm, and more particularly equal to 1.65 mm, and the angles junctions between the chamfers forming the lateral edges of the shim are preferably softened so as to have a radius curvature of between 0.45 mm and 0.75 mm, and more particularly equal to 0.6 mm. Each shim preferably has a lateral dimension of between 17.0 mm and 18.2 mm, and more particularly equal to 17.6 mm.
    [0011] The reduction of the radial dimension of the grooves directly implies a radial reduction of the ribs, the proportions of which are then more compact and better withstand the bending torques in operation. Thanks to the solution presented here, the structure of the ribs of the fan disk provides a structure sufficiently strong to be formed of titanium alloy much lighter than a brand-name alloy inconel. It is thus possible to provide a fan rotor without means for axial retention of the fan blades on the fan disk, downstream of the blades. This fan rotor comprises only as means for axial retention of the blades upstream flange as described in this patent application. This feature is particularly relevant in the context of small turbomachinery blowers relating to the invention, and having the dimensions and the hub ratio described above. It is therefore proposed here, for this type of fan, to form the titanium alloy fan disk, more particularly an TA6V or TI17 type alloy (TA5CD4). In addition, the reduction of the radial dimension of the grooves of the fan disk allows forming the inner face of this disk, with a balancing profile resulting from a frustoconical bore coaxial with the axis of the fan, and the radius increases from upstream to downstream, the upstream end of the balancing profile, which is therefore also its inner end, thus forming the internal boundary of the disk. This balancing profile, in addition to well balancing the fan disk, has a minimum diameter, upstream, typically between 120 and 140 mm, which is larger than the minimum diameter of the leek balancing profile. used for grooves of greater height, with external diameter of the equivalent disk. This new disk balancing profile provides a larger annular space in the middle of the fan disk for the axial passage of tools necessary for mounting and clamping the fan disk fastening means on the shaft of the turbomachine, these means being disposed downstream of the disk. The various aspects of the solutions presented here will be better understood and other details, characteristics and advantages thereof will appear more clearly on reading the following description given by way of non-limiting example and with reference to the accompanying drawings, in which: which: - Figure 1 is a perspective view with partial tearing of a turbomachine according to the prior art, - Figure 2 is a partial schematic partial half-view in axial section of a turbomachine fan rotor according to the prior art, FIG. 3 is a perspective view of an updated blower rotor with the hood torn off; FIG. 4 is seen from the front and with the hood torn off; FIGS. 5, 6 and 7 are respective views of FIG. sections AA, BB and CC of FIG. 4; FIG. 8 is a partial schematic half-view in axial section, on a scale, of a turbomachine fan according to the invention; FIG. perspective of a wedge used in the blower according to the invention, - Figure 10 is a cross-sectional view of the same wedge. We first refer to Figures 1 and 2 which therefore represent a turbomachine blower according to the prior art to the present invention. This fan comprises vanes 10 carried by a disk 12 and between which are interposed platforms 14 inter-blades, the disc 12 being attached to the upstream end of a shaft 13 of a turbomachine.
    [0012] Each fan blade 10 comprises a blade 16 connected at its radially inner end to a foot 18 which is engaged in a substantially axial groove 20 of complementary shape of the disc 12, formed between two ribs 22 of the disc 12, and for retaining radially this blade 26 on the disk 12. A shim 24 is interposed between the foot 18 of each blade 10 and the bottom of the corresponding groove 20 of the disk 12 to radially immobilize the blade 10 on the disk 12. The platforms 14 blades form a wall which delimits internally a vein 26 of the air flow entering the turbomachine, and comprises means which cooperate with corresponding means provided on the disk 12, between the grooves 20, to fix the platforms on the disk . The fan blades 10 are retained axially in the grooves 20 of the disc 12 by means of suitable means mounted on the disk 12, upstream and downstream of the blades 10. The retaining means located upstream comprise an annular flange 28 reported and fixed coaxially on the upstream end of the disc 12.
    [0013] The flange 28 comprises an inner annular flange 30 which is scalloped or crenellated and which cooperates with an outer annular rim 32 crenellated or scalloped disc 12 to axially immobilize the flange 28 on the disc 12. This flange 28 is supported by an outer rim 34 on the holds 24 of the dawn feet 18.
    [0014] The flange 28 further comprises an inner annular flange 36 which is interposed between a corresponding annular flange 38 of the disc 12 and an inner annular flange 40 of a ferrule 42 arranged upstream of the fan disc 12. The flanges 36, 38, 40 comprise axial orifices (not visible) for the passage of screws 44 or the like for clamping the flanges together.
    [0015] The ferrule 42 has a substantially frustoconical shape flaring downstream, the wall defined by the inter-blade platforms extending in the axial extension of this ferrule 42. This ferrule comprises radial holes 46 for the mounting of balancing screw and a flange 48 located at its upstream end. A hood 50 of conical shape is mounted on the upstream part of the shell 42. More particularly, the cover 50 comprises a flange 52 at its downstream end, fixed to the upstream flange 48 of the shell 42 by means of screws 54. Downstream of the blade 10, the axial retention is permitted by a hook 120 formed at the downstream end of the blade 10 and which engages in a notch 122 formed at the upstream end of a compressor 124 extending the vein 26 downstream of the blower. Such a structure has the drawbacks described above. In particular, it is not suitable for a fan having a relatively small diameter. FIGS. 3 to 7 illustrate an embodiment of a fan rotor according to the solution developed in this patent application, comprising in the same manner as above, a disc 56 carrying vanes (not shown) whose feet are engaged in substantially axial grooves 58 of the outer periphery of the disc 56. The disc comprises an annular rim 60 devoid of balancing leeks and extended upstream by an annular portion having an annular groove 62 delimited between an upstream face of the rim and a radial flange 64 extending outwardly. The upstream end of the annular portion comprises a flange 66 extending radially inwards and spaced from the flange 64, and having, regularly distributed over its entire circumference, axial screwthread holes 68, 72. 64 is scalloped or crenellated and includes solid portions alternating with hollow portions.
    [0016] The fan rotor is equipped with axial retaining means upstream of the blades on the disk. These comprise a flange 74 mounted in the annular groove 62 of the disk 56 and forming an axial support of the blade roots. The flange 74 comprises a substantially frustoconical wall 76 flaring downstream, and whose thickness increases downstream. The flange 74 is delimited at its downstream end by a radial face 78 bearing against the blades. The flange 74 comprises at its downstream end an inner annular flange 80 which is scalloped or crenellated and comprises alternating solid portions with hollow portions and forms substantially complementary to those of the flange 64 of the disc 56 to allow assembly and disassembly flange 74 in the annular groove 62 by axial translation, a rotation of the flange 74 relative to the disc 56, and an axial locking of the flange 74 in the groove 62 of the disc by pressing the solid portions of the flange 80 of the flange against the solid parts edge 64 of the disc.
    [0017] The flange 74 finally comprises festoons 82 or hollow portions formed alternately with solid portions 84 on its upstream edge. The flange 74 is immobilized in rotation by means of a ring 86 having a cylindrical portion 88 delimited by internal and external cylindrical faces. The outer face has projections 90 extending radially outwardly and circumferentially along said outer surface of the cylindrical portion 88, and fitting into the festoons 82 of the upstream edge of the flange 74 and providing a stop against the solid portions 84 of the upstream edge of the flange 74 to provide anti-rotation. The upstream edge of the ring is connected to radially inwardly extending lugs 92 formed with screw holes 94. These lugs are in axial contact upstream against the flange 66 of the disc 56 so that the holes 94 of the lugs 92 are aligned with the holes 68 of the flange 66 and the cylindrical portion 88 of the ring is in abutment. axial from the outside against the flange 66 of the disc. The ring 86 can be made of high alloyed steel, so as to resist tearing.
    [0018] The flange 74 is thus immobilized in rotation by abutment of its solid portions 84 against the projections 90 of the ring. A cover 96, for example made of aluminum and of conical shape, is fixed on the disc 12. For this, the cover 96 comprises, in its median part, an annular rim 98 in which are formed axial holes 100 through (FIG. ), situated opposite a hole 94 on two of the ring 86 aligned with certain holes 68 of the flange 66 of the disk 56. These holes 100 are traversed by the screws 70 cooperating with nuts 102 housed against the downstream of the flange 66 of the disc 56 and for fixing together the cover 96, the ring 86 and the disc 56. The downstream part of the cover 96 covers the ring 86 and the flange 74 so that the inner vein 26 defined by the inter-blade platforms extend in the axial extension of the downstream part of the cover 96. As can be seen in FIG. 7, all the other holes 94 of the ring, except one, located opposite other holes 68 of the flange 66 of the disk 56, are traversed by screws 72 cooperating with nuts 104 and Only the fixing of the ring 86 on the disc 56. The heads of these screws are housed in blind holes 106 formed in the inner rim 98 of the cover 96.
    [0019] The inner rim 98 of the cover 96 also comprises a cylindrical flange 108 extending downstream, the end of which bears against the inner end of the flange 66 of the disc. The cover 96 further comprises radial threads 110 for mounting balancing screws, as is well known in the prior art.
    [0020] To ensure the correct position of these screws, it is necessary to index the position of the cover 96 relative to the fan rotor. For this, as shown in Figure 6, an indexing pin 112 is mounted in the last hole 94 of the ring aligned with a hole 68 of the flange 66 of the disc 56. The pin 112 comprises a head 116 housed in a blind hole 114 of the inner rim 98 of the cover 96, the diameter of the head 116 of the pin 112 being determined so that it can not be inserted into another blind hole 106, provided for the housing of the heads of the screws 72 Referring now to Figure 8 which shows an overall view on the scale of the fan according to the invention, comprising the rotor described above. The disc 56 is arranged around the axis 130 of the turbomachine, and is rotated by a downstream drive shaft (not shown). Blades 132, between which inter-blade platforms 134 are interposed, are carried by the disc 56. Each fan blade 132 comprises a blade 136 connected at its radially inner end to a root 138 which is engaged in a groove 58 substantially axial complementary shape of the disk 56, formed between two ribs 140 of the disk 56, and for retaining radially this blade 132 on the disk 56. The fan blades 132 are retained axially in the grooves 58 of the disk 56 via means 74, 86, 70, 96 described above and arranged upstream of the blades 132. A shim 142 is interposed between the root 138 of each blade 132 and the bottom of the corresponding groove 58 of the disk 56 to immobilize the dawn radially. 132 on the disc 56.
    [0021] The inter-blade platforms 134 form a wall which internally delimits the stream 144 of the air flow entering the turbomachine, and comprises means which cooperate with corresponding means provided on the disk 56, between the grooves 58, to fix the platforms on the disk.
    [0022] The blades 132 are surrounded by an outer annular casing 146 defining the air inlet of the turbomachine. The outer casing 146 comprises an inner annular wall 148 externally defining the vein 144 of the air flow entering the turbomachine, and with respect to which the outer ends of the blades 132 move circumferentially in rotation.
    [0023] The ratio of the hub of the blower represented corresponds to the ratio of the distance B between the axis 130 of the turbomachine and the internal limit of the vein 144 at the leading edge of the blade 132, divided by the distance A between the axis 130 of the turbomachine and the outer ends of the blades 132. The fan shown in FIG. 8 has been designed to obtain a hub ratio that can be between 0.25 and 0.27, whereas the distance A has a value between 450 and 600 mm. This choice of hub ratio involves the use of a disk whose outer limit, at the vertices of the ribs, is between 115 mm and 145 mm. Finally, as already mentioned above, the means 74, 86, 70, 96 of axial retention of the blades 132 are effective enough that, unlike the fan of the prior art shown in Figures 1 and 2, the fan according to the invention shown in Figure 8 is devoid of axial retaining hooks of the blades 132 arranged downstream of the blades 132. On the contrary, as can be seen, the low pressure compressor 150 arranged downstream of the disk 56 of the fan is directly in position. bearing against the downstream ends of the blade roots 138 and ribs 140 of the disk. There is thus no longer any constraint of radial depth of the ribs related to the engagement of the downstream hooks. Therefore, the grooves 58 are radially shallower, with a height of between 18 mm and 22 mm, the grooves adapted for the establishment of an axial retaining hook blades. The wedges 142, used to keep the blade roots 138 in radial abutment against the ribs 140, are also radially less thick. The ribs 140, by the same fact less elongated, are then sufficiently compact to resist deformation and breakage. This gain in resistance of the ribs 140 makes it possible to form the disk in a relatively light titanium alloy with respect to a trademarked inconel alloy for example. In addition, considering the new disk mass distribution that results from the change in the height of the grooves, the inner wall 152 of the disk 56 has been formed to have a different disk balance profile 56 than that of the disk. prior art having leeks. This profile of the wall 152 is frustoconical flaring downstream. Proportionally to the disc, this balancing profile extends less than leeks inwardly of the turbomachine, to a minimum radius within the scope of the invention between 60 mm and 70 mm, which represents the limit internal disk. This profile therefore allows the passage of larger tool in the axial access space from the upstream located in the center of the disc 56, and commonly used during assembly of the turbomachine. Reference is now made to FIGS. 9 and 10, which represent the wedges 142, the latter having been adapted to the reduction in depth of the grooves 58. Each wedge is more particularly in the form of a two-sided board 154 extended according to FIG. axis of the blower, and placed against the bottom of one of the grooves 58. This wedge is symmetrical in the three axial directions, radial, and circumferential, which avoids possible assembly errors. Each face of the wedge has its side edges 156, or circumferential chamfered chamfers 158 each forming an angle of 10 ° with a face. The chamfers 158 of each face 154 radially vis-à-vis meet at the lateral ends of the wedge so as to form the two side edges 156 of the wedge. The angles of junction between the faces 154 of the shim and the chamfers 158 are softened so as to have a curvature of radius between 1.50 mm and 1.80 mm, and more particularly equal to 1.65 mm. The junction angles between the respective chamfers 158 forming the lateral edges 156 of the shim are softened so as to have a radius curvature of between 0.45 mm and 0.75 mm, and more particularly equal to 0.6 mm. Each shim 142 has a radial thickness of between 1 mm and 3 mm, more particularly equal to 2 mm, and a lateral dimension of between 17.0 mm and 18.2 mm, more particularly equal to 17.6 mm.
    权利要求:
    Claims (17)
    [0001]
    REVENDICATIONS1. Blower, in particular for a turbomachine such as a turbojet engine, comprising, at the inlet of the fan blades (132), an annular casing, a hub rotating about an axis (130) of the turbomachine and carrying the blades, which blades extend radially with respect to said axis in an annular channel (144) delimited internally by the hub and externally by the annular housing (146), said hub comprising a fan disk (56) having at its outer periphery ribs (140) substantially axial formed alternately with grooves (58) in which are engaged the feet (138) of the blades, said fan having an inlet diameter (A), which corresponds to the diameter of the circle comprising the radially outer ends of the blades, of value between 900 mm and 1550 mm, and having a hub ratio, which corresponds to the ratio of the diameter (B) of the internal boundary of the vein to the radially interfering ends. the attack edges of the fan blades, divided by the input diameter, between 0.20 and 0.265.
    [0002]
    2. Blower according to claim 1, characterized in that the inlet diameter is more particularly between 900 mm and 1200 mm.
    [0003]
    3. blower according to one of claims 1 or 2, characterized in that it comprises an annular cap (96) mounted on the disc (56) upstream of the blades (132), and axial retaining means of the blades on the disk comprising a flange (74) mounted in an annular groove (62) of the disk and forming an axial support of the blade roots (138), the flange (74) comprising a radial annular flange (80) festooned and cooperating with a radial annular flange (64) festooned with the annular groove (62) of the disc, so as to ensure axial locking of the flange in the annular groove 30 of the disc, and means for immobilizing the flange (74) in rotation, comprising a ring (86) having lugs (92) extending inwardly and formed with attachment means (68,94,70,72) on an upstream radial face of the disk (56), said hood (96) being fixed on the disc by fastening means (100, 68, 94, 70) partially common to the fastening means of a u at least some ears (92) of the ring on the disc, characterized in that said ring (86) further comprises at least one radial projection (90) cooperating with a stop (84) complementary to the flange, so as to block in rotation the flange (74) relative to the ring (86).
    [0004]
    4. Blower according to claim 3, characterized in that the disk (56) comprises an upstream flange (66) extending inwards, and having holes (68) aligned with holes (94) of the ears ( 92) for the passage of axial screws (70, 72) so as to form the fixing means of the ring on the disk.
    [0005]
    5. Blower according to claim 4, characterized in that the ring (86) comprises a cylindrical part (88) from which the radial projections (90) extend radially outwards, the ears (92). extending radially inwardly from the upstream edge of the cylindrical portion (88), the cylindrical portion of the ring being radially supported on said flange (66) of the disc. 20
    [0006]
    6. Blower according to one of claims 3 to 5, characterized in that the stops (84) of the flange cooperating with the radial projections (90) of the ring are formed by festoons (82) formed on an upstream edge of the flange (74).
    [0007]
    7. Blower according to claim 6, characterized in that for all the ribs (140) and for all the festoons (82), one of the festoons is formed on the upstream edge of the flange in axial alignment with one of the ribs of the disc.
    [0008]
    8. Blower according to one of claims 3 to 7, characterized in that the cover (96) comprises, in its middle part, an inner annular rim (98) in which are formed axial blind holes (106) opening towards downstream and serving for housing the heads of the fixing screws (72) of the ring on the disk, and axial through holes (100) for the passage of the fastening screw (70) common hood (96) and the ring (86) on the disc.
    [0009]
    9. Ring (86) for a blower according to one of claims 3 to 8, 5 comprising a cylindrical portion (88) comprising an inner cylindrical face and an outer cylindrical face from which radial projections (90) extend regularly radially outwardly, lugs (92) extending radially inwardly of the cylindrical portion from an edge of the cylindrical portion, each lug being located substantially between each pair of adjacent projections.
    [0010]
    10. annular flange (74) for a blower according to one of claims 3 to 8, comprising a substantially frustoconical wall (76) of variable thickness, whose end of largest diameter is connected to an annular rim (80). extending inwardly and being regularly scalloped, and the smallest diameter end of which is regularly festooned.
    [0011]
    11. Blower according to one of claims 1 to 8, characterized in that the disc (56) has an outer boundary, formed by the outer ends of the ribs (140), whose diameter is between 245 mm and 275 mm , and an inner limit, formed by the inner end of a disk balancing profile, whose diameter is between 120 mm and 140 mm.
    [0012]
    12. Blower according to one of claims 1 to 8 or 11, characterized in that the disc (56) has an outer limit, formed by the outer ends of the ribs (140), whose diameter is between 245 mm and 275 mm, and in that the grooves (58) of the disc have a radial dimension, between the bottom of the grooves (58) and the top of the ribs (140), of value between 18 mm and 22 mm.
    [0013]
    13. Blower according to one of claims 1 to 8 or 11 or 12, characterized in that a shim (142) of radial thickness between 1 mm and 3 mm is interposed radially between a blade root (138) and a groove bottom (58).
    [0014]
    14. Blower according to one of claims 11 to 13, characterized in that the balance profile of the disc (56) is formed by an internal bore whose frustoconical shape flares downstream, the upstream end of this bore forming the internal limit of the disk.
    [0015]
    15. Blower according to one of claims 1 to 8 or 11 to 14, characterized in that the disk carries between 17 and 21 blades, preferably between 18 and 20 blades.
    [0016]
    16. Blower according to one of claims 1 to 8 or 11 to 15, characterized in that the disc is made of titanium alloy, and more particularly alloy TA6V or TI17 (TA5CD4).
    [0017]
    17. Turbomachine, such as a turbojet, characterized in that it comprises a blower according to one of claims 1 to 8 or 11 to 16.
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    同族专利:
    公开号 | 公开日
    WO2015079154A1|2015-06-04|
    CA2931768C|2021-10-19|
    CA2931768A1|2015-06-04|
    CN105849420A|2016-08-10|
    US10436212B2|2019-10-08|
    US20160298642A1|2016-10-13|
    CN105849420B|2020-03-24|
    JP6660298B2|2020-03-11|
    RU2016120632A|2018-01-09|
    RU2677769C1|2019-01-21|
    EP3074639A1|2016-10-05|
    JP2016540924A|2016-12-28|
    EP3074639B1|2020-02-05|
    FR3014151B1|2015-12-04|
    引用文献:
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    EP1995467A1|2006-03-13|2008-11-26|IHI Corporation|Holding structure of fan blade|
    EP2128450A1|2007-03-27|2009-12-02|IHI Corporation|Fan rotor blade support structure and turbofan engine having the same|
    FR2971822A1|2011-02-21|2012-08-24|Snecma|BLOWER ROTOR, ESPECIALLY FOR A TURBOMACHINE|FR3106615A1|2020-01-23|2021-07-30|Safran Aircraft Engines|Turbomachine assembly|RU2018037C1|1990-10-17|1994-08-15|Виталий Сергеевич Максимов|Turbomachine working wheel|
    US5160243A|1991-01-15|1992-11-03|General Electric Company|Turbine blade wear protection system with multilayer shim|
    US5240375A|1992-01-10|1993-08-31|General Electric Company|Wear protection system for turbine engine rotor and blade|
    GB2382382B|2001-11-23|2005-08-10|Rolls Royce Plc|A fan for a turbofan gas turbine engine|
    US7516547B2|2005-12-21|2009-04-14|General Electric Company|Dovetail surface enhancement for durability|
    FR2911632B1|2007-01-18|2009-08-21|Snecma Sa|ROTOR DISC OF TURBOMACHINE BLOWER|
    FR2914008B1|2007-03-21|2009-10-09|Snecma Sa|ROTARY ASSEMBLY OF A TURBOMACHINE BLOWER|
    FR2930595B1|2008-04-24|2011-10-14|Snecma|BLOWER ROTOR OF A TURBOMACHINE OR A TEST ENGINE|
    WO2009142973A2|2008-05-13|2009-11-26|Rotating Composite Technologies Llc|Fan blade retention and variable pitch system|
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    US8573947B2|2010-03-10|2013-11-05|United Technologies Corporation|Composite fan blade dovetail root|
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    US9303589B2|2012-11-28|2016-04-05|Pratt & Whitney Canada Corp.|Low hub-to-tip ratio fan for a turbofan gas turbine engine|
    EP3933181A4|2013-08-20|2022-01-05|Raytheon Tech Corp|High thrust geared gas turbine engine|
    FR3014151B1|2013-11-29|2015-12-04|Snecma|BLOWER, ESPECIALLY FOR A TURBOMACHINE|
    FR3014150B1|2013-11-29|2018-03-02|Safran Aircraft Engines|BLOWER, ESPECIALLY FOR A TURBOMACHINE|US9303589B2|2012-11-28|2016-04-05|Pratt & Whitney Canada Corp.|Low hub-to-tip ratio fan for a turbofan gas turbine engine|
    FR3014151B1|2013-11-29|2015-12-04|Snecma|BLOWER, ESPECIALLY FOR A TURBOMACHINE|
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    US10280767B2|2017-08-29|2019-05-07|United Technologies Corporation|Fan hub attachment for leading and trailing edges of fan blades|
    JP6990639B2|2018-09-26|2022-01-12|本田技研工業株式会社|Turbofan engine|
    CN109630465A|2018-12-16|2019-04-16|中国航发沈阳发动机研究所|A kind of fan gasket|
    CN111852906B|2019-04-28|2022-02-22|中国航发商用航空发动机有限责任公司|Aircraft engine fan device and aircraft engine|
    法律状态:
    2015-11-04| PLFP| Fee payment|Year of fee payment: 3 |
    2016-11-08| PLFP| Fee payment|Year of fee payment: 4 |
    2017-10-20| PLFP| Fee payment|Year of fee payment: 5 |
    2017-11-10| CD| Change of name or company name|Owner name: SNECMA, FR Effective date: 20170713 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 6 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 7 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 8 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1361906A|FR3014151B1|2013-11-29|2013-11-29|BLOWER, ESPECIALLY FOR A TURBOMACHINE|FR1361906A| FR3014151B1|2013-11-29|2013-11-29|BLOWER, ESPECIALLY FOR A TURBOMACHINE|
    US15/100,475| US10436212B2|2013-11-29|2014-11-24|Fan, in particular for a turbine engine|
    CN201480070536.9A| CN105849420B|2013-11-29|2014-11-24|Fan for a turbine engine|
    RU2016120632A| RU2677769C1|2013-11-29|2014-11-24|Fan, in particular, for turbine engine|
    PCT/FR2014/053017| WO2015079154A1|2013-11-29|2014-11-24|Fan, in particular for a turbine engine|
    JP2016534900A| JP6660298B2|2013-11-29|2014-11-24|Fans especially for turbine engines|
    CA2931768A| CA2931768C|2013-11-29|2014-11-24|Fan, in particular for a turbine engine|
    EP14821734.2A| EP3074639B1|2013-11-29|2014-11-24|Fan, in particular for a turbo engine, and flange for said fan|
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