• 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 rotating front part (1) of an aircraft turbine engine receiver, comprising studs (34) for fixing a cone point (20a) on an inner support (22), each stud comprising a rear end (50) screwed into the support (22) and a front end (56) receiving a clamping nut (58), an anti-rotation portion (62) of non-circular section of each stud (34) cooperating with a drilling (46) of corresponding section of a rotational locking ring (48). Also, extraction studs (36) are provided, a rear end (66) of which is screwed into the shim (26), each stud (36) passing through a cone tip flange (20a '). Finally, the invention is configured so that after removing the nuts (58), pulling forward on the studs (36) can remove an assembly comprising the tip (20a) and the shim (26), while maintaining the studs (34) screwed on the support (22).
    公开号:FR3051174A1
    申请号:FR1654156
    申请日:2016-05-10
    公开日:2017-11-17
    发明作者:Sylvie Judith Devaux；Pierre Yves Heinry；Olivier Richard Lefebvre
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    FRONT ROTATING PART OF AN AIRCRAFT TURBOMACHINE RECEIVER,
    IMPROVED DESIGN FOR REPEAT REMOVAL FROM THE TIP OF CONE
    DESCRIPTION
    TECHNICAL AREA
    The present invention relates to the field of aircraft turbomachines, and in particular to their receivers, such as for example the fan of a turbojet engine.
    It aims in particular the design of the outer front cone and its environment, and more specifically the design of the means for fixing a cone tip on an inner support carrying a turbomachine equipment.
    STATE OF THE PRIOR ART
    In a conventional manner, the fan of a turbojet engine comprises an outer front cone located upstream of the rotating fan blades, as is known for example from document FR 2 943 725. The same is true for a turboprop propeller, which comprises this same type of outer cone aerodynamic shape.
    In some cases, the outer front cone may be equipped at its front end with a removable cone tip, fixed on an inner support carrying any equipment, such as an antenna transmitting a telemetry device otherwise equipped with one or more batteries. In this case, a protective cover of the equipment is interposed between the cone tip and the inner support.
    In certain circumstances, especially in the turbomachine testing phase, access to the equipment must be frequent. In the example proposed above, the batteries must be recharged regularly during this test phase, for example every day. There are therefore means for fixing the cone point which, once removed, allow the extraction of this cone tip and access to the protective cover of the equipment. Specifically, to remove the cone tip, it is expected to initially install an extraction wedge between a protective cover flange, and a cone tip flange. Therefore, once the attachment means removed, it is sufficient to mount an appropriate tool on the extraction wedge to move it forward so that it carries with it the cone tip. Once the extraction is completed, the operator then has access to the protective cover, on which it can for example install a battery charging tool.
    The aforementioned fixing means take the form of screws whose head is oriented towards the front, and whose threaded rod cooperates at its rear end with the inner support. More precisely, self-locking threads are provided in holes in the inner support. These nets have the function of avoiding the loosening of the screws rotating with the rest of the fan, and subjected to a vibratory environment.
    However, the self-braking nets tend to lose their braking capacity after several cycles of mounting / dismounting the fastening screws, for example after a series of five to ten cycles. Since screw braking is an indispensable function in the vibratory environment to which they are subjected, the self-braking nets must be regularly replaced. These replacement operations require specific tools, as well as the prior disassembly of the protective cover of the equipment it covers, and the internal support. The time devoted to the implementation of all these operations may sometimes be incompatible with the scheduling and downtime constraints of the aircraft on the ground. This disadvantage is even more problematic when the removal of the cone tip must be performed very regularly, for example daily, as is the case for the needs of recharging batteries during a test phase of the turbomachine. Nevertheless, as indicated above, this problem exists whatever the nature of the on-board equipment.
    STATEMENT OF THE INVENTION
    To at least partially address the above problem relating to the embodiments of the prior art, the invention firstly relates to a rotating front portion of an aircraft turbine engine receiver comprising: - an inner support; - equipment mounted on the inner support; - a protective cover covering the equipment; an outer front cone equipped at its front end with a cone tip covering the protective cap; an extraction block interposed between a protective cover flange and a cone point flange; and - fixing means of the cone point on the inner support, said fastening means passing through the cone tip flange, the extraction wedge, and the protective cap flange.
    According to the invention, said fixing means comprise a plurality of fixing studs, a threaded rear end of which is screwed into said inner support and of which a threaded front end receives a tightening nut intended to force the cone point flange towards the inner support. , said fastening means also comprising, arranged axially between the inner support and the cone point flange, a rotation locking ring of the fastening studs, each of which has an anti-rotation portion of non-circular section cooperating with a drilling of corresponding section of the rotating locking ring.
    In addition, the front portion also comprises a plurality of extraction studs, a threaded rear end of which is screwed into the extraction wedge, each extraction stud passing through the cone tip flange, said front portion being configured so that after removal of said clamping nuts, pulling forward on the extraction studs removes a detachable assembly including the cone tip and the extraction wedge, while keeping the fastening studs screwed onto the inner support .
    The design proposed by the present invention simplifies the operations of extraction of the cone tip, in particular by allowing to leave the fixing studs on the internal support, during these extraction operations to give access to the protective cover covering the equipment. In addition, since the fixing studs remain permanently on the inner support, it is therefore no longer necessary to implement binding operations to replace any self-locking nets present on the mounting studs.
    The proposed solution thus makes it possible to envisage frequent extractions of the cone tip, while satisfying the various planning and downtime constraints of the aircraft on the ground. The invention also has at least one of the following optional features, taken alone or in combination.
    The anti-rotation portion of each fastening stud has a section comprising two parallel straight segments, and the associated hole made through the rotational locking ring has an oblong shape, the two parallel side flanks cooperate respectively with the two straight segments. anti-rotation portion of the fixing stud. The oblong shape advantageously provides a tolerance in the relative positioning between the anti-rotation portion of the fixing stud and the bore, while providing the desired rotational locking function.
    In this case, it is expected that the anti-rotation portion of each fixing pin has for example a polygonal section, preferably hexagonal.
    The fastening means comprise three fastening studs, and the three oblong holes are oriented: for two of them, substantially tangentially with respect to an axis of rotation of the front part; and - for the third hole, substantially radially in relation to the axis of rotation of the front portion.
    This particular assembly makes it possible to limit the problems of assembly in the case where the holes of the rotational locking ring are not perfectly indexed with the orifices of the inner support receiving the fixing studs. Therefore, mounting is possible even without the use of tight manufacturing tolerances on the parts concerned.
    Preferably, the three holes are arranged at 120 ° from each other.
    The extraction studs have a threaded front end receiving a nut which is sealing a sealing washer against the cone point flange, and the tightening nuts screwed to the fastening studs also each press a sealing washer against the clamping flange. cone point. The washers thus make it possible to ensure the sealing function between the equipment and the external environment. The threaded rear end of each extraction pin is locked in rotation in a threaded orifice of the extraction wedge, with the aid of a fretted pin oriented along a screw axis and arranged at the interface between the Threaded rear end of the pull-out stud and the threaded hole of the pull-out. This is a simple solution to implement, allowing to achieve the desired result of rotational locking of each extraction pin in its corresponding threaded hole of the extraction wedge.
    In addition, just like the other elements of the invention, this fretted pin solution is simple to implement on existing receivers, without requiring substantial modifications on the original parts. The equipment covered by the protective cover and mounted on the support corresponds to an antenna transmitting a telemetry device also equipped with at least one battery, and preferably equipped with several batteries, for example six. Nevertheless, it could be any other type of equipment, without departing from the scope of the invention.
    Preferably, said cone tip is made of two adjacent parts succeeding each other axially. Nevertheless, it could be a single piece, made in one piece or by several elements fixedly attached to each other. The invention also relates to an aircraft turbomachine comprising a receiver whose rotating front portion is as described above, the receiver being preferentially a fan.
    Finally, the subject of the invention is a method of disassembling the rotating front part described above, said method aiming at having access to the protective cover covering the equipment, and comprising the following steps: removal of the nuts clamping devices on the threaded front end of the fastening studs; then - forward displacement of the extraction bolts so as to remove the assembly comprising the cone point and the extraction shim, withdrawal during which the fixing bolts, which remain fixed on said inner support, slide relatively at the cone point flange and the extraction wedge. Other advantages and features of the invention will become apparent in the detailed non-limiting description below.
    BRIEF DESCRIPTION OF THE DRAWINGS
    This description will be made with reference to the appended drawings among which; - Figure 1 shows a schematic view of a turbojet according to the invention, in longitudinal section; FIG. 2 represents a front view of the turbojet, showing the rotating front portion which is in the form of a preferred embodiment of the invention; FIG. 3 represents a perspective view of the rotating front portion, cut along line III-III of FIG. 2; FIG. 4 is a partial and enlarged view of that shown in FIG. 3, showing more specifically the means for fixing a cone point on an inner support of the rotating front part; - Figure 5 is a sectional view taken along the plane V of Figure 4; FIG. 6 is a partial and enlarged view of that shown in FIG. 3, more specifically showing the extraction means of the cone tip; and FIGS. 7a to 7e represent different steps of a method of disassembling the rotating front part shown in the preceding figures, so as to have access to a protective cover covering a turbomachine equipment.
    Referring firstly to Figure 1, there is shown an aircraft turbomachine 100 for integrating a rotating front portion 1 according to the invention. This is a turbojet engine with double flow and double body. Nevertheless, it could be a turbomachine of another type, for example a turboprop, without departing from the scope of the invention.
    The turbomachine 100 has a longitudinal axis 3 around which its various components extend. It comprises, from upstream to downstream in a main direction of flow of gases through this turbomachine, a fan 2, a low pressure compressor 4, a high pressure compressor 6, a combustion chamber 8, a high pressure turbine 10 and a low-pressure turbine 12. These elements delimit a primary stream 14 traversed by a primary stream 14 ', while a secondary stream 16 surrounds the primary stream being partially delimited by a fan casing 18 and traversed by a flow of secondary air 16 '.
    The fan 2, which corresponds to the receiver of the turbomachine 100, comprises at its upstream end the rotating front part 1 according to the invention. This front part 1 which is downstream of the fan blades 9 will be written below, in detail with reference to the following figures.
    In the following description, the terms "front" and "rear" are considered in a direction opposite to the main direction 5 of gas flow within the turbojet, and parallel to the axis 3. In contrast, the terms "upstream" and "downstream" are considered according to this same main flow direction 5.
    Referring to FIGS. 2 to 6, there is shown the rotating front part 1 of the blower, which comprises a cone-shaped outer casing of axis 3. This cone, said outer front cone 20, has an aerodynamic outer surface intended for be married by the air before it passes through the fan blades. It is for example divided into three axially succeeding sections, namely a cone tip 20a, a main central section 20b, and a rear end 20c.
    The cone tip 20a is located at the front end of the part 1, and extends axially over a short length relative to the total axial length of the cone 20, for example on only 10 to 20% of it.
    The outer front cone 20 is hollow, and incorporates several elements integral in rotation of the same cone. It is first of all a device 22, here an antenna transmitting a telemetry device 23 equipped with batteries 25 and a data acquisition system 27. The device 23 is thus capable of collecting data. data in test phases of the turbomachine, then to restore them in real time to a fixed point outside the turbomachine, via the antenna 22. As illustrative examples, the data collected are of the type dynamic gauges and thermocouples, measured by sensors judiciously placed within the turbomachine. The equipment 22 is mounted on an inner support 24 of the front part 1, this support 24 being centered on the axis 3. The inner support 24 is radially surrounded essentially by the main central section 20b of the cone 20, and, at its front end, surrounded by a rear portion of the cone tip 20a. At its front end, the equipment 22 is covered axially and radially by a protective cover 26, of generally conical shape and centered on the axis 3. This same cover 26, preferably corresponding to an antenna cover, is covered axially and radially essentially by the cone tip 20a of the cone 20, and at its rear end covered by the main central section 20b of this cone 20.
    The protective cover 26 comprises a flange 26 'for its fixing on the rotating part 1, and more precisely on the inner support 24 having a shoulder 24' axially aligned with the flange 26 'along the axis 3.
    The rotating front portion 1 also comprises a substantially annular extraction shim 28 of axis 3. This shim 28 comprises, alternately in the circumferential direction, through holes 30 and threaded holes 32. The extraction shim 28 is gripped axially between the flange 26 'of the protective cover 26, and a flange 20a' for fixing the front tip 20a. In this regard, it is stated that the front tip 20a could be made in one piece, or made in two adjacent parts 20al, 20a2 succeeding one another axially and being nested one inside the other, as has been shown on the figures. For reasons of simplicity and clarity of the description, thereafter, the cone tip 20a will be considered as one and the same entity.
    The rotating front part 1 also comprises fixing studs 34 as well as extraction studs 36, arranged alternately and regularly spaced about the axis 3. As illustrated in FIG. preferably three fixing studs 34 arranged at 120 ° from each other, and three extraction studs 36 also arranged at 120 ° from each other.
    Referring more specifically to Figure 4, each fixing pin 34 is arranged substantially axially, and passes successively, from front to rear, a through hole 40 in the fixing flange 20a 'of the cone tip, a through hole 30 of the extraction wedge 28, a through hole 42 in the fastening flange 26 'of the protective cap 26, and through a bore 46 of a ring 48 for locking in rotation of the fastening stud 34.
    On either side of the traversed elements described above, each stud 34 comprises a threaded rear end 50 screwed into a threaded orifice 52 of the inner support 24, and a threaded front end 56 receiving a clamping nut 58 for forcing the flange 20a 'cone tip towards the inner support 24. In addition, a sealing washer 60 is interposed axially between the nut 58 and the flange 20a', this washer thus sealing the passage hole 40.
    Preferably, each clamping nut 58 has a braking function to respond to the stresses encountered in the vibratory environment to which it is subjected. The self-braking threads may tend to lose their braking capability after several cycles of mounting / disassembling the nuts 58, but these can be easily changed when necessary.
    In the same way, self-locking threads are preferably retained at the threaded rear end 50 of the fastening studs 34.
    The ring 48 is clamped axially between the flange 26 'of the protective cover 26 and the shoulder 24' of the inner support 24. It is shown enlarged in FIG. 5, showing the three bores 46 spaced at 120 ° from each other. others and coinciding with the position of the three fastening studs. Each bore 46 has an oblong shape, whose two parallel lateral flanks respectively cooperate with two straight segments of an anti-rotation portion 62 of the associated fastening pin 34. More preferably, the anti-rotation portion 62 has a hexagonal shaped section. , which corresponds to a shape complementary to that of the oblong bore 46 since the two parallel lateral flanks thereof respectively cooperate with two opposite straight segments of the hexagonal section of the anti-rotation portion 62. Only a weak clearance can be provided between the flat surfaces facing two by two, ensuring the anti-rotation function of the stud 34 according to its own longitudinal axis. Therefore, the risks that the fixing studs are unscrewed are advantageously reduced to nothing.
    To facilitate the establishment of the studs 34 through the holes 46 and in the threaded holes 52 of the inner support 24, two of the holes 46 are oriented substantially tangentially with respect to the axis 3 also corresponding to the axis of rotation of the rotating front portion 1, while the third hole 46 is oriented substantially radially relative to the same axis 3. This allows to adopt manufacturing tolerances of little severity, reducing production costs.
    Referring more specifically to Figure 6, each extraction pin 36 is arranged substantially axially, and passes through the fixing flange 20a 'of the cone tip 20a. Each stud 36 comprises a threaded rear end 66 screwed into a threaded orifice 68 of the extraction wedge 28, and a threaded front end 70 receiving a nut 72. In addition, a sealing washer 74 is interposed axially between the nut. 72 and the flange 20a ', this washer thus sealing the passage hole 40. Also here, each nut 72 has a braking function to respond to the stresses encountered in the vibratory environment to which it is subjected.
    To ensure the locking in rotation of each extraction pin 36 extending rearwardly only to the extraction wedge 28, there is provided a hoop pin 80 oriented along a screwing axis of the stud 36 and arranged at the interface 82 between the threaded rear end 66 and the threaded orifice 68. This is a simple and effective technical solution for securing in translation and in rotation the two elements 28, 36, in the direction of the Axis 3. The hoop pin 80 has a small diameter, for example about 2 mm.
    This fretted pawn solution is particularly advantageous in an already highly congested environment, with restricted access. In addition, it can easily be implemented on existing turbomachines.
    Referring now to Figures 7a to 7e, there will be described a method of disassembling the rotating front portion 1 which has just been presented.
    The purpose of this disassembly is to have access to the protective cover 26, so as to come to install on it a tool for charging the batteries 25 of the equipment, for example provided in the number of six and arranged around of axis 3.
    Firstly with reference to Figure 7a, it is proceeded to the withdrawal of the clamping nuts 58 initially present on the threaded front end 56 of the fixing studs 34. The sealing washers 60 are also extracted from the front end Although not shown, the same type of shrinkage is achieved for the nuts 72 and the sealing washers 74 initially cooperating with the threaded front end 70 of the extraction studs 36.
    Then, as shown in Figure 7b, a particular tool 88 is mounted on the front end of the extraction studs 36. This tool allows to move forward these studs 36, along the axis 3. This displacement simultaneously causes the translation towards the front of the extraction wedge 28 which, by its axial support with the flange 20a 'of the cone tip 20a, also drives the latter in translation forwardly along the axis 3. In other words, the action performed via the tool 88 makes it possible to remove a removable assembly comprising the cone tip 20a, the extraction bolts 36 and the extraction wedge 28.
    As has been shown schematically in FIG. 7c, during this extraction, the fixing studs 34 remain fixed on the inner support 24. As a result, the fastening studs 34 slide relative to the flange 20a 'of the cone tip 20a and relative to the extraction wedge 28, and that respectively through the through holes 40 and 30.
    Preferably, during this extraction, the protective cap 26 also remains in place, just like the crown 48.
    Once the removable assembly removed as shown in Figure 7d, the front end of the protective cover 26 becomes fully accessible, and a tool 90 for charging the batteries 25 can be easily assembled on this protective cover, as it has was schematized in Figure 7e.
    After recharging the batteries 25, the reassembly of the elements on the rotating front part 1 is performed in the reverse order to that described above for disassembly operations.
    Of course, various modifications may be made by those skilled in the art to the invention which has just been described, solely by way of non-limiting examples.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    A rotating front part (1) of an aircraft turbine engine receiver comprising: - an inner support (24); - equipment (22) mounted on the inner support; - a protective cover (26) covering the equipment; an outer front cone (20) equipped at its front end with a cone point (20a) covering the protective cap (26); - an extraction wedge (28) interposed between a protective cover flange (26 ') and a cone point flange (20a'); and - fixing means (34) of the cone tip (20a) on the inner support (22), said fastening means passing through the cone tip flange (20a '), the extraction wedge (28), as well as the protective cover flange (26 '), characterized in that said fixing means comprise a plurality of fastening studs (34), a threaded rear end (50) of which is screwed into said inner support (22) and one end of which threaded front (56) receives a clamping nut (58) for forcing the cone tip flange (20a ') towards the inner support, said fastening means also comprising, arranged axially between the inner support (22) and the cone point flange (20a '), a ring (48) for locking in rotation of the fixing bolts (34), each of which has an anti-rotation portion (62) of non-circular section cooperating with a bore ( 46) of corresponding section of the rotating locking ring (48), and in that the front portion also has a plurality of extraction studs (36), a threaded rear end (66) of which is screwed into the extraction wedge (28), each extraction stud passing through the cone point flange (20a '), said front portion being configured such that after removal of said clamping nuts (58), pulling forward on the extraction studs (36) removes a removable assembly comprising the cone point (20a) and the extraction wedge (28), while maintaining the fastening studs (34) screwed onto the inner support (22).
    [2" id="c-fr-0002]
    Rotary front part according to claim 1, characterized in that the anti-rotation portion (62) of each fastening stud (34) has a section comprising two parallel straight segments, and in that the associated piercing (46) practiced through the rotational locking ring (48) has an oblong shape, whose two parallel lateral flanks cooperate respectively with the two straight segments of the anti-rotation portion (62) of the fixing pin (34).
    [3" id="c-fr-0003]
    3. Front rotating part according to claim 2, characterized in that the anti-rotation portion (62) of each fastening stud has a polygonal cross-section, preferably hexagonal.
    [4" id="c-fr-0004]
    4. rotating front part according to claim 2 or claim 3, characterized in that the fastening means comprise three fastening studs (34), and in that the three holes (46) of oblong shape are oriented: - for two of them, substantially tangentially with respect to an axis of rotation (3) of the front part; and - for the third hole, substantially radially in relation to the axis of rotation (3) of the front part.
    [5" id="c-fr-0005]
    5. Front rotating part according to claim 4, characterized in that the three bores (46) are arranged at 120 ° from each other.
    [6" id="c-fr-0006]
    6. rotating front part according to any one of the preceding claims, characterized in that the extraction bolts (36) comprise a threaded front end (70) receiving a nut (72) pressing a sealing washer (74) against the cone point flange (20a '), and in that the tightening nuts (58) screwed to the fastening studs (34) also each press a sealing washer (60) against the cone point flange ( 20a ').
    [7" id="c-fr-0007]
    Rotary front portion according to one of the preceding claims, characterized in that the threaded rear end (66) of each extraction bolt (36) is locked in rotation in a threaded hole (68) of the shim. extraction (28), using a fretted peg (80) oriented along a screw axis and arranged at the interface (82) between the threaded rear end (66) of the extraction bolt (36) and the threaded orifice (68) of the extraction wedge (28).
    [8" id="c-fr-0008]
    8. rotating front part according to any one of the preceding claims, characterized in that the equipment (22) covered by the protective cover (26) and mounted on the inner support (24) corresponds to a transmitting antenna of a telemetry device (23) furthermore equipped with at least one battery (25).
    [9" id="c-fr-0009]
    9. Aircraft turbomachine (10) comprising a receiver (2) whose rotating front portion (1) is according to any one of the preceding claims, the receiver being preferably a blower.
    [10" id="c-fr-0010]
    10. A method of disassembling the rotating front portion (1) according to any one of claims 1 to 8, said method for providing access to the protective cover (26) covering the equipment (22), and comprising the following steps: - removal of the clamping nuts (58) on the threaded front end (56) of the fastening studs (34); then - forward movement of the extraction bolts (36) so as to remove the assembly comprising the cone point (20a) and the extraction wedge (28), withdrawal during which the fixing bolts (34) ), which remain fixed on said inner support (22), slide relatively to the cone point flange (20a ') and the extraction wedge (28).
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    同族专利:
    公开号 | 公开日
    GB201818389D0|2018-12-26|
    US10669011B2|2020-06-02|
    US20190127045A1|2019-05-02|
    WO2017194866A1|2017-11-16|
    GB2564812B|2021-04-14|
    GB2564812A|2019-01-23|
    FR3051174B1|2018-06-01|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1970537A1|2007-03-16|2008-09-17|Snecma|Turbomachine fan|
    FR2921422A1|2007-09-26|2009-03-27|Snecma Sa|Annular piece e.g. ring cowling, for e.g. jet engine of aircraft, has annular sheet connected on clamp and comprising rim for allowing cooperation of nuts by stopping to prevent turning of nuts in orifices of clamp|
    US20100226786A1|2009-03-05|2010-09-09|Mahan Vance A|Nose cone assembly|
    FR2943725A1|2009-03-31|2010-10-01|Snecma|Rotating inlet cowl for turbine engine i.e. jet engine, of aircraft, has front end taking shape of rod, where rod comprises axis parallely merged with rotation axis and made of inconel alloy|FR3097200A1|2019-06-14|2020-12-18|Safran Aircraft Engines|INPUT CONE FOR AN AIRCRAFT TURBOMACHINE|US2401247A|1941-09-20|1946-05-28|Goodrich Co B F|Spinner assembly|
    FR2621554B1|1987-10-07|1990-01-05|Snecma|NON-ROTATING INPUT COVER OF CENTRALLY FIXED TURBOREACTOR AND TURBOREACTOR THUS EQUIPPED|
    GB9828812D0|1998-12-29|1999-02-17|Rolls Royce Plc|Gas turbine nose cone assembly|
    US6416280B1|2000-11-27|2002-07-09|General Electric Company|One piece spinner|
    US7303377B2|2004-04-14|2007-12-04|Pratt & Whitney Canada Corp.|Apparatus and method of balancing a shaft|
    GB0903012D0|2009-02-24|2009-04-08|Rolls Royce Plc|Mounting arrangement|DE102016215807A1|2016-08-23|2018-03-01|MTU Aero Engines AG|Inner ring for a vane ring of a turbomachine|
    DE102017109952A1|2017-05-09|2018-11-15|Rolls-Royce Deutschland Ltd & Co Kg|Rotor device of a turbomachine|
    DE102018210601A1|2018-06-28|2020-01-02|MTU Aero Engines AG|SEGMENT RING FOR ASSEMBLY IN A FLOWING MACHINE|
    法律状态:
    2017-04-13| PLFP| Fee payment|Year of fee payment: 2 |
    2017-11-17| PLSC| Search report ready|Effective date: 20171117 |
    2018-04-23| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 4 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 5 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1654156|2016-05-10|
    FR1654156A|FR3051174B1|2016-05-10|2016-05-10|FRONT ROTATING PART OF AN AIRCRAFT TURBOMACHINE RECEIVER WITH IMPROVED DESIGN FOR RELEASE OF THE CONE TIP|FR1654156A| FR3051174B1|2016-05-10|2016-05-10|FRONT ROTATING PART OF AN AIRCRAFT TURBOMACHINE RECEIVER WITH IMPROVED DESIGN FOR RELEASE OF THE CONE TIP|
    US16/098,528| US10669011B2|2016-05-10|2017-05-09|Rotating front part of an aircraft turbomachine intake, of improved design permitting repeated removal of the cone tip|
    GB1818389.7A| GB2564812B|2016-05-10|2017-05-09|Rotating front part of an aircraft turbomachine intake, of improved design permitting repeated removal of the cone tip|
    PCT/FR2017/051098| WO2017194866A1|2016-05-10|2017-05-09|Rotating front part of an aircraft turbomachine intake, of improved design permitting repeated removal of the cone tip|
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