• 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 sealing device for turbomachine bearing oil chamber, comprising a rotor shaft (4), an annular cover (6) integral with a turbomachine casing and arranged around the rotor shaft for defining therewith an oil chamber (2) for receiving a bearing (8) rotatably supporting the rotor shaft relative to the turbomachine housing, a labyrinth seal (32) mounted on the rotor shaft facing an end of the cover, an annular flange (26) mounted inside the cover, a dynamic annular seal (22) interposed radially between the flange and the rotor shaft, and a key (30) for axially locking the flange inside the cover comprising at least one latch radially through the flange and being housed radially inside a groove (40) formed in the cover.
    公开号:FR3035154A1
    申请号:FR1553466
    申请日:2015-04-17
    公开日:2016-10-21
    发明作者:Serge Rene Morreale；Dominik Igel
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The present invention relates to the general field of roller bearing oil bearing housings for turbomachines. It relates more specifically to a device for sealing such a chamber with respect to a neighboring air chamber. In known manner, a turbomachine comprises a number of rolling bearings which are intended to support in rotation the rotor shafts of the turbomachine, particularly with respect to a fixed support connected to the housing thereof. In operation, oil is typically injected on the bearings of these bearings so as to lubricate and cool them. To prevent oil from spreading throughout the engine, it is necessary to confine the rolling bearings inside oil chambers and to seal these oil chambers with respect to air adjacent to the engine that must be free of oil. More specifically, certain oil chambers are delimited between the rotor shaft rotatably supported by the rolling bearing and an annular cover integral with a fixed support connected to the turbomachine casing and arranged around the rotor shaft. A dynamic annular seal is generally positioned between the rotor shaft and the cover to provide a seal between the oil chamber and an air chamber adjacent thereto. Typically, the dynamic seal is mounted inside a flange itself fixed to the cover by means of a plurality of fixing screws. Such a configuration nevertheless has certain disadvantages. In particular, the screw heads for fixing the flange on the cover are in the circulation path of the oil injected into the oil chamber to lubricate and cool the bearings of the bearing, with the risk of causing splashing. oil and runoff from the oil may cause leakage to the nearby air enclosure. OBJECT AND SUMMARY OF THE INVENTION The present invention therefore relates to a sealing device for a turbomachine bearing oil chamber that does not have the aforementioned drawbacks. According to the invention, this object is achieved by means of a sealing device comprising a rotor shaft, an annular cover secured to a turbomachine casing and arranged around the rotor shaft to delimit with it. an oil chamber for receiving a bearing rotatably supporting the rotor shaft relative to the turbomachine casing, a labyrinth seal mounted on the rotor shaft opposite one end of the cover, an annular flange mounted to the rotor housing; inside the cover, a dynamic annular seal interposed radially between the flange and the rotor shaft, and an axial locking key 10 of the flange inside the cover comprising at least one latch radially crossing the flange and being housed radially inside a groove in the lid. The sealing device according to the invention is remarkable in particular that it is devoid of screws for fixing the flange on the lid. Indeed, this fixing is provided by the locking key which comprises a latch radially through the flange and being housed radially inside a groove (which may be an annular groove or notch) formed in the cover. The absence of screws thus avoids any risk of causing splashing of oil and any runoff of oil that can cause leaks to the nearby air chamber. According to one embodiment, the axial locking key comprises an elastic pin which is housed inside the flange and provided with a latch passing radially through the flange and which is housed radially inside the groove formed in the flange. cover, and means for locking the elastic pin inside the flange. In this embodiment, the axial locking key may comprise at least one latch integral with the elastic pin and intended to be housed radially in a hole made in the flange to lock the elastic pin inside the flange. . Alternatively, the axial locking key may comprise at least one lug mounted radially in force in a hole made in the flange and coming into radial abutment against the elastic pin to lock it inside the flange.
    [0002] According to another embodiment, the axial locking key comprises a rigid pin housed inside the flange and provided with a latch radially passing through the flange and being housed radially inside the groove formed in the flange. cover, and a flexible pin for holding the rigid pin inside the flange. In this other embodiment, the flexible holding pin 5 can come into circumferential abutment against the rigid pin and include bosses projecting radially outwardly and intended to block by expansion the flexible holding pin to the lug. inside the flange. Similarly, the flexible holding pin may comprise a latch radially through the flange and being housed radially inside the groove formed in the cover. In this case, the lock of the rigid pin and the lock of the flexible holding pin are preferably diametrically opposed to each other, which improves the axial locking of the flange inside the cover. Preferably, the flange comprises, at an upstream end, a shoulder protruding radially outwardly and axially upstream relative to the lid. The invention also relates to a turbomachine comprising at least one bearing oil chamber provided with a sealing device as defined above.
    [0003] BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the present invention will be apparent from the description given below, with reference to the accompanying drawings which illustrate exemplary embodiments thereof which are not limiting in any way. In the figures: - Figure 1 is a schematic sectional view of a sealing device according to the invention in its environment; - Figure 2 is a side view of an axial locking key of the sealing device according to one embodiment of the invention; FIG. 2A is a partial view showing an alternative embodiment of the locking of the key of the sealing device of FIG. 2; - Figures 3 to 5 are side views of an axial locking key of the sealing device according to other embodiments of the invention; and FIG. 6 is a sectional view along VI-VI of FIG.
    [0004] DETAILED DESCRIPTION OF THE INVENTION FIG. 1 schematically and partially shows a turbomachine bearing oil chamber 2 to which the invention applies.
    [0005] This oil chamber 2 is delimited, on the inner side, by a rotor shaft 4, and on the outer side by an annular cover 6 which is integral with a fixed support connected to the casing of the turbomachine and which is arranged around the This oil chamber 2 contains a bearing 8 comprising a plurality of rolling elements 10 engaged between an inner ring 12 mounted on the rotor shaft 4 of the turbomachine and an outer ring 14 integral with a rotor. casing of the turbomachine (not shown in the figure). In addition, oil is injected into the oil chamber 2 in order to lubricate and cool the rolling elements 10 of the bearing. For this purpose, the oil flows from upstream to downstream inside axial ducts 16 made along the rotor shaft 4 and opening radially, on the one hand at the level of the rolling elements 10. passing through the inner ring 12 of the bearing, and further downstream of the latter at a "drip" 18 for centrifuging the cooling oil of a seal 22 20 to the largest internal radius to the oil chamber and to deflect the oil particles outside the sealing device described below (the path of the oil is illustrated by arrows in Figure 1). Downstream of the drop nozzle 18, the oil chamber 2 comprises a sealing device according to the invention intended to seal this oil chamber with respect to an adjacent air chamber 20 which must be free of pressure. 'oil. For this purpose, the sealing device according to the invention comprises in particular a dynamic annular seal 22 which is associated with a rotating surface 24 of the dropper 18 carried by the rotor shaft 4.
    [0006] Typically, this dynamic seal 22 is composed of carbon ring segments and the bearing surface 24 is treated to improve segment / track slip. The dynamic seal 22 is held in an annular flange 26 itself mounted inside the cover 6. The flange 26 has an L-shaped section portion 26a which receives the dynamic seal 22 and which extends towards the downstream by an annular flange 26b.
    [0007] The flange 26 is mounted with a sliding fit inside the cover 6. The L-shaped portion 26a has on the outer side grooves receiving O-rings 28 for sealing with the cover 6. .
    [0008] Furthermore, the flange 26 is locked axially inside the cover 6 by means of an axial locking key 30, different embodiments of which will be described hereinafter with reference to FIGS. 2 to 6. Downstream of the dynamic seal 22, the sealing device of the oil chamber 2 according to the invention further comprises a labyrinth seal 32 which is mounted on the rotor shaft 4 and whose static portion 34 is carried by the cover 6, at a downstream end thereof. This labyrinth seal 32 makes it possible to limit the drop in air pressure in the air chamber 20 in the event of the destruction of the carbon segments constituting the seal 22 (this labyrinth seal 32 is therefore only useful to overcome this failure) . In connection with FIGS. 2, 2A, 3 to 6, various embodiments of the axial locking key of the flange 26 inside the cover 6 will now be described. In the embodiment of FIG. 2, the key 30 the axial locking pin comprises an elastic pin 36 which is housed radially inside the flange 26. This elastic pin 36 has a half-ring shape centered on the longitudinal axis XX of the turbomachine and comes, in position, to be housed inside an annular groove 37 centered on the axis XX and 25 formed in the collar 26b of the flange (Figure 1). The elastic pin is provided, at equal distance from these two free ends 36a, 36b of a latch 38 which, in position, crosses the flange (and more specifically the flange 26b thereof) radially from one end to the other. It is housed radially inside an annular groove 40 formed in the cover 6 over its entire circumference. Alternatively, as partially shown in FIG. 2A, the latch 38 of the elastic pin can pass radially through the flange and be housed inside a notch 40 'formed in the cover 6. Moreover, means are designed to lock in position 35 the elastic pin 36 inside the flange 6. Thus, in the embodiment of Figure 2, the key 30 of axial locking comprises two latches 3035154 6 42 which are each integral with a free end 36a, 36b of the elastic pin 36 and which each, in position, are housed radially in a hole 44 formed in the flange so as to lock the elastic pin inside the flange.
    [0009] Thus, in this embodiment, the latches 42 for locking the elastic pin inside the flange form an integral part of the elastic pin. When it is put in place, the elastic pin 36 is displaced axially from the downstream upstream to the inside of the flange 6 until it becomes lodged in the groove 37 of the latter and until the latches 42 are housed by expansion of the elastic pin inside the holes 44 of the flange and the latch 38 comes to fit into the annular groove 40 (or notch 40 '- Figure 2A) of the cover 6. FIG. 3 illustrates an alternative embodiment of the means for locking in position the elastic pin 36 inside the flange 6. In this variant, the axial locking key 30 comprises two lugs 46 which are mounted radially in force in holes 48 made in the flange 26 and which each come into radial abutment against a free end 36a of the elastic pin to lock it inside the flange. Thus, the lugs 46 and the elastic pin 36 block each other. FIG. 4 shows another embodiment of the key 30 'of axial locking of the flange 26 inside the cover 6. In this embodiment, the key 30' of axial locking 25 comprises a rigid pin 50 and a pin support flexible 52, each having a half-ring shape centered on the longitudinal axis XX of the turbomachine, which are both housed radially inside the flange 6. The rigid pin 50 is provided with a latch 54 which, in position, crosses the flange (and more precisely the flange 26b thereof) radially and is housed radially inside an annular groove 40 (or a notch identical to that described in connection with Figure 2A) made in the cover 6. Furthermore, the flexible holding pin 52 has the function of ensuring a maintenance of the rigid pin 50 inside the flange. To this effect, the flexible holding pin 52 is in circumferential abutment against each free end 50a of the rigid pin. To block the flexible holding pin 52 inside the flange, it is expected that the latter has bosses 56 (for example a boss at each of its free ends 52a and a boss at mid-distance from these ends free) protruding radially outwardly and coming into position, blocking by expansion the flexible holding pin within the groove 37 of the flange. The mounting of the key 30 'blocking is as follows. The rigid pin 50 is first introduced from the downstream upstream to the inside of the flange 6 to be housed in the groove 37 of the latter and until its latch 54 comes s insert in the annular groove 40 (or the notch) of the lid 6. Then, the flexible holding pin 52 is introduced in the same manner and its bosses 56 are wedged by expansion inside the groove 37 flange, thus holding the rigid pin in place. FIGS. 5 and 6 show yet another embodiment of the key 30 "for axially locking the flange 26 inside the cover 6.
    [0010] This key 30 "differs from that described with reference to FIG. 4 in that the flexible holding pin 52 further comprises an additional lock 58 which, in position, traverses the flange from one side to the other (and more precisely the flange 26b thereof) and is housed radially inside the annular groove 40 of the cover 6 (or, where appropriate, inside an additional notch). rigid pin 50 and the latch 58 of the flexible holding pin 52 are diametrically opposed to each other In this configuration, the flexible holding pin 52 has only two bosses 56, at each free end 52a of it.
    [0011] As shown in FIG. 6, the latch 58 of the flexible holding pin is advantageously articulated with respect to the flexible holding pin, which makes it possible to give the assembly an axis of clearance for the flexible pin of maintenance. According to an advantageous arrangement common to all of the described embodiments, the flange 6, and more particularly the L-shaped section portion 26a thereof, has a shoulder 62 at its upstream end. projecting radially outward and axially upstream relative to the cover 6. This shoulder 62 has a dual function. It allows, on the one hand to channel oil runoff to the lower part of the oil chamber bypassing the seal, and, on the other hand, to serve as an extractor for disassembling the flange 26 out of the cover (after disassembly of the axial locking pin) by means of a tool passing through the bore of the flange.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A sealing device for a turbomachine bearing oil chamber (2), comprising: a rotor shaft (4); an annular cover (6) secured to a turbomachine casing and arranged around the rotor shaft to define therewith an oil chamber (2) for receiving a bearing (8) rotatably supporting the shaft of rotor relative to the turbomachine casing; a labyrinth seal (32) mounted on the rotor shaft facing an end of the lid; an annular flange (26) mounted within the lid; a dynamic annular seal (22) interposed radially between the flange and the rotor shaft; and a key (30; 30 '; 30 ") for axially locking the flange inside the cover comprising at least one latch (38; 54; 58) extending radially through the flange and being housed radially inside the flange; a groove (40; 40 ') formed in the lid.
    [0002]
    2. Device according to claim 1, wherein the axial locking key comprises an elastic pin (36) housed inside the flange and provided with a latch (38) passing radially through the flange and being housed radially to the inside the groove (40; 40 ') formed in the lid, and means for locking the elastic pin inside the flange.
    [0003]
    3. Device according to claim 2, wherein the axial locking key comprises at least one latch (42) integral with the elastic pin (36) and intended to be housed radially in a hole (44) formed in the flange for lock the elastic pin inside the flange.
    [0004]
    4. Device according to claim 2, wherein the axial locking key comprises at least one lug (46) mounted radially in force in a hole (48) formed in the flange and abutting against the elastic pin 3035154 (36) to lock it inside the flange.
    [0005]
    5. Device according to claim 1, wherein the axial locking key comprises a rigid pin (50) housed inside the flange and provided with a latch (54) passing radially through the flange and being housed radially at the end. inside the groove (40; 40 ') formed in the cover, and a flexible holding pin (52) for the rigid pin inside the flange. 10
    [0006]
    6. Device according to claim 5, wherein the flexible holding pin (52) comes into circumferential abutment against the rigid pin (50) and comprises bosses (56) projecting radially outwardly and intended to come block by expanding the flexible holding pin inside the flange.
    [0007]
    7. Device according to one of claims 5 and 6, wherein the flexible holding pin (52) comprises a latch (58) extending radially through the flange and being housed radially inside the groove (40; 40 ') made in the lid.
    [0008]
    8. Device according to claim 7, wherein the lock (54) of the rigid pin (50) and the latch (58) of the flexible holding pin (52) are diametrically opposed to one another.
    [0009]
    9. Device according to any one of claims 1 to 8, wherein the flange (6) comprises, at an upstream end, a shoulder (62) projecting radially outwardly and axially upstream by compared to the lid.
    [0010]
    10. Turbomachine comprising at least one bearing oil chamber (2) provided with a sealing device according to any one of claims 1 to 9. 25
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    同族专利:
    公开号 | 公开日
    US9810095B2|2017-11-07|
    FR3035154B1|2017-05-05|
    GB2539543A|2016-12-21|
    GB2539543B|2021-01-06|
    US20160305283A1|2016-10-20|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB2315302A|1996-07-16|1998-01-28|Mtu Muenchen Gmbh|Sealing device for parts rotating relative to one another|
    US6382632B1|2001-02-21|2002-05-07|General Electric Company|Repositionable brush seal for turbomachinery|
    FR2997470A1|2012-10-30|2014-05-02|Snecma|Holding device for holding brush seal of lubrication enclosure of turbojet engine, has cylindrical part formed by cylindrical face and thread that is engaged with another thread to ensure axial translation of lock with respect to cover|
    FR2998611A1|2012-11-29|2014-05-30|Snecma|SEAL JOINT ASSEMBLY FOR A TURBOMACHINE COMPRISING A BRUSH JOINT|WO2021032924A1|2019-08-19|2021-02-25|Safran Aircraft Engines|Device for distributing oil from a rolling bearing for an aircraft turbine engine|
    FR3107310A1|2020-02-17|2021-08-20|Safran Aircraft Engines|OIL DISTRIBUTION DEVICE OF AN AIRCRAFT TURBOMACHINE BEARING BEARING|
    WO2021198583A1|2020-04-02|2021-10-07|Safran Aircraft Engines|Device for distributing oil from a rolling bearing for an aircraft turbine engine|US4754984A|1987-01-02|1988-07-05|The United States Of America As Represented By The Secretary Of The Navy|Dual-seal-ring shaft seal|
    FR2644205B1|1989-03-08|1991-05-03|Snecma|TURBOMACHINE BEARING WITH INTEGRATED SEAL|
    US20080157479A1|2006-06-21|2008-07-03|Thurai Manik Vasagar|Low and reverse pressure application hydrodynamic pressurizing seals|
    FR2957976B1|2010-03-26|2013-04-12|Snecma|SEALING DEVICE FOR AN OIL ENCLOSURE OF A TURBOJET ENGINE|
    DE102010026336A1|2010-07-07|2012-01-12|Siemens Aktiengesellschaft|A shaft sealing apparatus|
    FR2985764B1|2012-01-16|2014-02-28|Snecma|COAXIAL INTER-TREE SEALING DEVICE OF A TURBOMACHINE|
    FR2989116B1|2012-04-05|2014-04-25|Snecma|COAXIAL INTER-SHAFT SEALING DEVICE OF A TURBOMACHINE|EP2964935B1|2013-03-08|2018-12-12|United Technologies Corporation|Fluid-cooled seal arrangement for a gas turbine engine|
    US11028717B2|2017-06-26|2021-06-08|Raytheon Technologies Corporation|Bearing assembly for gas turbine engines|
    US10858955B2|2018-03-23|2020-12-08|Raytheon Technologies Corporation|Gas turbine engine having a sealing member|
    US10865657B2|2018-04-23|2020-12-15|Pratt & Whitney Canada Corp.|Sealing assembly for a gas turbine engine|
    US11248492B2|2019-03-18|2022-02-15|Raytheon Technologies Corporation|Seal assembly for a gas turbine engine|
    法律状态:
    2016-04-12| PLFP| Fee payment|Year of fee payment: 2 |
    2016-10-21| PLSC| Search report ready|Effective date: 20161021 |
    2017-04-06| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-03-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 6 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1553466A|FR3035154B1|2015-04-17|2015-04-17|SEALING DEVICE FOR TURBOMACHINE BEARING OIL ENCLOSURE|FR1553466A| FR3035154B1|2015-04-17|2015-04-17|SEALING DEVICE FOR TURBOMACHINE BEARING OIL ENCLOSURE|
    US15/099,880| US9810095B2|2015-04-17|2016-04-15|Sealing device for an oil enclosure in a turbine engine bearing|
    GB1606711.8A| GB2539543B|2015-04-17|2016-04-18|A sealing device for an oil enclosure in a turbine engine bearing|
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