• 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 main object of the invention is a device (1) for lubricating a turbomachine bearing, comprising a main body (12) provided with an internal cavity (9) for the flow of a lubricating fluid, the body main (12) having, at its inner end (12a), at least one ejection nozzle (4a, 4b), in fluid communication with the internal cavity (9), for ejection of the lubricating fluid in the direction of at least the bearing, characterized in that the axial dimension (Da, Db) of the internal cavity (9) of the main body (12) is smaller in at least a first cavity portion (9a) extending from said at least one ejection nozzle (4a, 4b) at the inner end (12a) of the main body (12) as in at least a second cavity portion (9b) extending from the outer end ( 12b) of the main body (12).
    公开号:FR3026135A1
    申请号:FR1458905
    申请日:2014-09-22
    公开日:2016-03-25
    发明作者:Christophe Lima；Dimitri Marquie
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present invention relates to the field of aircraft turbomachines, and more particularly to the general field of lubrication of turbomachine bearings, in particular by means of lubrication devices of the nozzle type. SUMMARY OF THE INVENTION The invention can be applied to all types of aircraft turbomachines, for example such as turbojets and turboprops. More preferentially, the invention applies to a double-body and dual-flow turbojet engine. It thus relates more specifically to a lubrication device for a turbomachine bearing, a turbomachine comprising such a device, and an associated assembly method. STATE OF THE ART Conventionally, a turbomachine bearing supporting a rotating shaft inside a fixed casing comprises a bearing disposed in an enclosure, which is lubricated by lubricating means in the form of nozzles provided with nozzles. ejection of a lubricating fluid. FIG. 1 shows, in axial section and partially, an example of a turbomachine 10 comprising a lubrication device 1 of the nozzle type for cooling at least one downstream bearing 2 of a turbomachine. More specifically, in this example, the nozzle 1 is mounted on a bearing support 5 and extends radially through a flexible ring 3, located under the bearing support 5, and comprises two upstream nozzles 4a and 4b downstream d ejection of lubricating oil H, at its inner end la. In order to avoid in particular the migration of oil H towards certain compartments of the turbomachine 10, a seal is also provided upstream of the nozzle 1 by the presence of a seal 6, for example of the segmented radial seal type ( JRS), S 56806 JLJ-P 2 comprising in particular a static sealing ring consisting of carbon segments. The cooling of the seal 6 is provided by the upstream nozzle 4a of the nozzle 1, which ejects an upstream jet of oil Ja in the form of a cone towards an upstream zone Za to cool the seal 6. In parallel, the cooling of the downstream bearing 2 is provided by the downstream nozzle 4b of the nozzle 1, which ejects a downstream jet of oil Jb in the form of a cone towards a downstream zone Zb to be cooled from the bearing 2 In Figure 2, in perspective, the lubrication device 1 of Figure 1 of the nozzle type has also been shown in isolation. The lubrication device 1 thus consists of at least three main elements, namely: a main body 12, also called nozzle body, whose inner end 12a corresponds to the inner end 1a of the nozzle 1; an interface element 11, also called nipple, located at the outer end 1b of the nozzle 1 and intended to interface with a servitude tube; an intermediate duct 13, also called a bent or bent tube, which makes it possible to connect the nozzle body 12 to the nipple 11. The bent tube 13 is advantageously designed to have a bending radius Rc equal to at least twice the diameter of the bent tube 13. In order to ensure efficient lubrication, and in particular effective cooling, upstream Za and downstream zones Zb respectively associated with the seal 6 and the downstream bearing 2, the lubricating device 1 must be able to guarantee a certain flow rate. lubricating oil H, but also a well targeted ejection of the lubricating oil H to reach the upstream zones Za and downstream Zb to cool, as can be seen in Figure 1. Thus, the efficiency of the lubrication requires precise ejection towards target portions of the upstream zones Za and downstream Zb, so as to avoid any projection of lubricating oil H to prohibited areas Zi. However, obtaining a suitable and precise targeting of the lubricating oil H projected by the nozzle 1 towards the upstream zones Za and downstream zone Zb is complicated by the fact of having zones Za, Zb to be lubricated. small and distant from each other.
    [0002] S 56806 JLJ-P 3 It is nevertheless known that the precision, and therefore the improvement of the targeting, of the jet jets Ja, Jb of the nozzles 4a, 4b of the nozzle 1 depends strongly on the ratio between the length L and the diameter D in particular, in the usual manner, it is required to have such an L / D ratio which is greater than or equal to 3.
    [0003] In order to illustrate this aspect, FIG. 3 partially shows, in axial section and in perspective, the internal end 1a of the nozzle 1 of FIG. 1 and the drilling of the downstream nozzle 4b. The drilling of the downstream nozzle 4b consists in producing an ejection duct 7b of length L and a circular ejection opening 8b of diameter D, so that the lubricating oil H contained in the cavity internal 9 of the nozzle 1 through the ejection duct 7b and the ejection opening 8b to be projected towards the downstream zone Zb to cool. According to the embodiments of the prior art, and in the case of the downstream nozzle 4b shown in Figure 3, the L / D ratio may be about 2.05. In the non-illustrated case of the upstream nozzle 4a, the L / D ratio can be about 2.36. Also, these two ratios are lower than the recommended theoretical ratio of 3, so that there is a need to implement solutions to increase the L / D ratio. Thus, to increase this L / D ratio, a first solution consists of a decrease in the diameter D of the ejection opening 8b. However, such a solution is not acceptable because it requires reducing the ejection flow rate of the lubricating oil H for which a minimum is required to ensure the proper operation of the nozzle 1. A second solution then consists of a increasing the length L of the ejection duct 7b. Nevertheless, the mounting environment of the nozzle 1 on the turbomachine 10 does not necessarily allow to consider such an extension of the nozzles 4a, 4b. Indeed, as shown in partial perspective in Figure 4, the inner end of the nozzle 1, carrying the upstream 4a and downstream 4b nozzles, can be located in the immediate vicinity of its environment, including the flexible ring 3. Thus, when the nozzle 1 is in place on the bearing support 5, the proximity to the nominal of the S 56806 JLJ-P 4 nozzle 1 with the flexible ring 3 generates a spacing S very small which does not allow to consider the extension of upstream 4a and downstream 4b nozzles. Furthermore, to ensure the assembly of the lubricating device 1 as shown in Figure 2, it is necessary to provide the attachment of the bent tube 13 between the nipple 11 and the nozzle body 12, in particular between the outer end 12b of the nozzle body 12 and the nipple 11. The outer end 12b of the nozzle body 12 is that which is at the interface with the bearing support 5. The assembly of the bent tube 13 at the nipple 11 and to the nozzle body 12 can be done by welding the inner end 13a of the bent tube 13 on the outer end 12b of the nozzle body 12 and by welding the outer end 13b of the bent tube 13 on the nipple 11. Nevertheless , in order to be carried out under optimal conditions, the welding of the inner end 13b of the bent tube 13 on the outer end 12b of the nozzle body 12 requires a plane distance dp from the outer end 12b of the body nozzle 12 and a dist plane dp 'of the inner end 13a of the bent tube 13, on both sides of the weld, which are at least 5 mm. Otherwise, the feasibility of welding is strongly questioned because of its significant thickness and the impossibility of torch passage. However, usually, the plane distance dp at the nozzle body 12 is of the order of 2.35 mm and the plane distance dp 'at the bent tube 13 is of the order of 1.1 mm, ie less than the minimum required distance of 5 mm to complete the weld. SUMMARY OF THE INVENTION Therefore, there is a need to propose an alternative solution to allow the improvement of the accuracy and targeting of a jet of lubrication fluid ejected by a lubricating device of at least one turbomachine bearing. . In particular, there is a need to allow an increase in the ratio between the drilling length and the drilling diameter of an ejection nozzle of such a lubricating device.
    [0004] S 56806 JLJ-P There is also a need to propose an alternative solution for assembling a device for lubricating at least one turbomachine bearing, and in particular for allowing the assembly of a bent tube of the lubrication device. between a main body of the lubricating device provided with lubricating fluid ejection nozzles and a nipple of the lubricating device for interfacing with servitudes. The object of the invention is to remedy at least partially the needs mentioned above and the drawbacks relating to the embodiments of the prior art. The invention thus has, according to one of its aspects, a lubrication device for a turbomachine bearing, in particular of the nozzle type, comprising a main body provided with an internal cavity for the flow of a lubricating fluid. , in particular lubricating oil, the main body comprising, at its inner end, at least one ejection nozzle, in particular at least two ejection nozzles, in fluid communication with the internal cavity, for ejection lubricating fluid towards at least the bearing, characterized in that the axial dimension, in particular the diameter, of the internal cavity of the main body is lower in at least a first cavity portion extending from said at least one an ejection nozzle at the inner end of the main body as in at least a second cavity portion extending from the outer end of the main body. Thus, the axial dimension of the internal cavity of the main body may decrease from the outer end to the inner end of the main body. To do this, a stepped bore can be made to form the cavity of the main body. Thanks to the invention, it is possible to obtain an improvement in the precision, the targeting and the orientation of the lubricating fluid outlet jet of a device for lubricating at least one turbomachine bearing, in particular by means of by increasing the ratio between the length and the drilling diameter of an ejection nozzle of such a device. The invention allows such an increase by the implementation of a double bore in the main body of the lubrication device, which is an easy solution to implement with tools and conventional processes. Moreover, as explained below, the invention can make it possible to assemble such a lubrication device in a simple manner, even in a very limited environment, by means of an alternative solution to the weld when it is not feasible.
    [0005] The lubricating device according to the invention may further comprise one or more of the following characteristics taken separately or in any possible technical combinations. The axial dimension, in particular the diameter, of said at least one first cavity portion may advantageously be less than or equal to 3.5 mm.
    [0006] In addition, the radial dimension, in particular the length, of said at least one first cavity portion may be less than or equal to 32 mm. Said at least one ejection nozzle may comprise an ejection duct, in fluid communication with said at least one first cavity portion, and an ejection opening, into which the ejection duct opens so that the lubricating fluid contained in the internal cavity of the main body is ejected. The length of the ejection duct may be greater than or equal to 4 mm, better still greater than or equal to 4.2 mm, more preferably greater than or equal to 4.5 mm. The ejection opening may be circular. The ratio of the length of the ejection duct to the diameter of the ejection opening may be greater than or equal to 3. Furthermore, the lubrication device may comprise an interface element, located at the outer end of the ejection duct. lubricating device and intended to be in interface with servo elements of the turbomachine, and an intermediate conduit bent, connecting the main body and the interface element.
    [0007] The intermediate pipe bent can advantageously be assembled on the main body of the lubrication device by brazing the inner end of the intermediate conduit in the outer end of the main body. The assembly of the intermediate duct on the interface element can also be achieved by brazing or else welding.
    [0008] According to another of its aspects, the invention also relates to a turbomachine, characterized in that it comprises a lubricating device as defined above. The turbomachine may comprise a bearing intended to be lubricated by the lubricating device, this bearing being in particular located downstream of the lubricating device. In addition, the turbomachine may comprise a seal, in particular of the segmented radial seal (JRS) type, comprising in particular a static sealing ring consisting of carbon segments, intended to be lubricated by the lubricating device, this seal sealing being in particular located upstream of the lubrication device. In addition, the invention also relates, in another of its aspects, to a method of assembling a lubrication device for a turbomachine bearing, the lubricating device being in particular as defined above, the device comprising a body main body having an internal cavity for the flow of a lubricating fluid, the main body having, at its inner end, at least one ejection nozzle in fluid communication with the internal cavity for the ejection of the fluid lubricating in the direction of at least the bearing, the device further comprising an interface element, located at the outer end of the device and intended to be in interface with servo elements of the turbomachine, and an intermediate pipe bent connecting the main body and the interface element, the method comprising at least the brazing step of the inner end of the intermediate conduit in the end external of the main body and / or step step of drilling the internal cavity of the lubricating device to form at least a first cavity portion of axial dimension smaller than the axial dimension of at least a second cavity portion. By the term "stepped drilling" is meant that the drilling of the internal cavity of the main body is performed so as to obtain at least two cavity portions having different axial dimensions.
    [0009] S 56806 JLJ-P 8 The lubricating device, the turbomachine and the assembly method according to the invention may comprise any of the characteristics set out in the description, taken separately or in any technically possible combination with other characteristics.
    [0010] BRIEF DESCRIPTION OF THE DRAWINGS The invention will be better understood on reading the following detailed description of an example of non-limiting implementation thereof, and the examination of the figures, diagrammatic and partial. of the accompanying drawing, in which: - Figure 1 shows, in axial section and partly, an example of a turbomachine comprising a lubricating device for cooling at least one downstream turbine engine bearing, - Figure 2 shows in isolation In perspective, the lubrication device of FIG. 1; FIG. 3 partially shows, in axial section and in perspective, the internal end of the lubricating device of FIG. 1; FIG. internal end of the lubricating device of Figure 1 in its environment during assembly, - Figure 5 shows, in partial axial section, an example of lubrication device according to the prior art 6 shows, in partial axial section, an example of a lubricating device according to the invention, FIG. 7 partially shows, in axial section and in perspective, the internal end of the lubricating device of FIG. 6, and - Figure 8 shows, in partial axial section, the assembly of the lubrication device of Figure 6. In all of these figures, identical references may designate identical or similar elements. In addition, the different parts shown in the figures are not necessarily in a uniform scale, to make the figures more readable.
    [0011] S 56806 JLJ-P 9 DETAILED DESCRIPTION OF A PARTICULAR EMBODIMENT Throughout the description, it is noted that the upstream and downstream terms are to be considered with respect to a main direction F of normal gas flow (upstream downstream) for a turbomachine 10. In addition, the axis T of the turbomachine 10 is called the axis of radial symmetry of the turbomachine 10. The axial direction of the turbomachine 10 corresponds to the axis of rotation of the turbomachine 10, which is the direction of the axis T of the turbomachine 10. A radial direction of the turbomachine 10 is a direction perpendicular to the axis T of the turbomachine 10. In addition, unless otherwise stated, the adjectives and adverbs axial, radial, axially and radially are used with reference to the aforementioned axial and radial directions. In addition, unless otherwise stated, the terms inner (or inner) and outer (or outer) are used with reference to a radial direction so that the inner part of an element is closer to the T-axis of the turbomachine 10 than the outer part of the same element. Figures 1 to 4 have already been described above in the part relating to the technical context of the invention. With reference to FIGS. 6 to 8, there is shown an exemplary embodiment of a lubricating device 1 according to the invention. FIG. 5 represents, in partial axial section, an example of a lubricating device 1 according to the prior art. More precisely, FIG. 6 represents, in partial axial section, an example of a lubricating device 1 according to the invention. FIG. 7 partially shows, in section and in perspective, the internal end 1a of the lubricating device 1 of FIG. 6 in a view similar to that of FIG. 3. Finally, FIG. 8 represents, in partial axial section, assembly of the lubricating device 1 of FIG. 6.
    [0012] The lubricating device 1 may in particular be of the lubricating nozzle 1 type, comprising two upstream 4a and 4b downstream ejection nozzles, as previously described. In particular, the lubricating device 1 may be such as that described with reference to FIG. 2. In addition, the lubricating device 1 may make it possible to lubricate at least one turbomachine bearing, or even a seal, in a manner S 56806 JLJ-P 10 similar to that previously presented with reference to Figure 1. The technical context of the invention shown in Figures 1 to 4 is also applicable to the embodiment described here. The device 1 thus comprises a main body or nozzle body 12 in which is formed an internal cavity 9 to allow the flow of lubricating oil H. To allow the ejection of the lubricating oil H outside the device 1 , the main body 12 comprises, at its inner end 12a coincides with the inner end of the device 1, two ejection nozzles 4a and 4b, in particular an upstream ejection nozzle 4a for the lubrication of a seal 6 and a downstream nozzle 4b for lubricating a downstream bearing 2. The two ejection nozzles 4a and 4b are in fluid communication with the internal cavity 9 so that the lubricating oil H circulating in the inner cavity 9 can flow through the ejection nozzles 4a and 4b to be projected.
    [0013] More particularly, each ejection nozzle 4a, 4b comprises an ejection duct in fluid communication with the internal cavity 9 and an ejection opening into which the ejection duct opens. Thus, for example, FIG. 7 represents the ejection duct 7b of the downstream ejection nozzle 4b formed between the internal cavity 9 of the main body 12 and the ejection opening 8b of the downstream ejection nozzle 4b. .
    [0014] Furthermore, the device 1 further comprises an interface element 11 or nipple 11, located at the outer end 1b of the lubricating device 1 and intended to interface with servo elements of the turbomachine 10, and an intermediate conduit 13 bent or curved tube 13, connecting the main body 12 and the nipple 11. According to the prior embodiment of the lubrication device 1 of Figure 5, the main body 12 has an internal cavity 9 of uniform diameter Da over the entire length L1 of the internal cavity 9. Thus, conventionally, the internal cavity 9 has a diameter Da of about 6.15 mm and a radial length L1 of about 71.5 mm. For the realization of the main body 12, an internal cavity 9 is thus pierced inside the main body 12 with a single drilling diameter Da. This drilling diameter Da S 56806 JLJ-P 11 corresponds in particular to the inlet diameter of the lubricating oil H at the nipple 11. In order to improve the precision of the targeting of the lubricating oil jets H coming out of the ejection nozzles 4a and 4b of the device 1, the device 1 according to the invention of Figures 6 to 8 is provided with a decrease in the internal bore of the inner cavity 9 to increase the length L of the nozzle ejection ducts ejection 4a, 4b. More precisely, as seen in FIG. 6, the diameter of the internal cavity 9 of the main body 12 is smaller in a first cavity portion 9a extending from the ejection nozzles 4a, 4b at the level of the internal end 12a of the main body 12 only in a second cavity portion 9b extending from the outer end 12b of the main body 12. Thus, the diameter of the inner cavity 9 decreases from the outer end 1b to the inner end 12 of the main body 12. In other words, a stepped bore is formed inside the main body 12 so as to form a first cavity portion 9a with a drilling diameter Db and a second cavity portion 9b with a diameter of Da drilling, the drilling diameter Db being smaller than the drilling diameter Da. The first cavity portion 9a has a radial length L3 of about 31.5 mm, while the second cavity portion 9b has a radial length L2 of about 40 mm.
    [0015] The diameter Da of the second cavity portion 9b is maintained at a value of approximately 6.15 mm as in the device 1 of the prior art of FIG. 5. On the other hand, the diameter Db of the first cavity portion 9a is reduced significantly to a value of about 3.5 mm. As can be seen in FIG. 4, this reduction in the diameter Db directly impacts the dimensions of the ejection nozzle 4b. More specifically, the length L of the ejection duct 7b is increased while the diameter D of the ejection opening 8b remains unchanged. Thus, the L / D ratio between the length L of the ejection duct 7b and the diameter D of the ejection opening 8b is also increased. Now, this L / D ratio has an immediate effect on the targeting and precision performance of the lubricating oil outlet jets H of the ejection nozzles 4a, 4b. In particular, when it is greater than or equal to 3, the performance of the ejector nozzles 4a and 4b is acceptable. In the present case, the reduction of the diameter Db of the first cavity portion 9a to a value of approximately 3.5 mm makes it possible to obtain an L / D ratio of approximately 3.04 for the upstream ejection nozzle 4a. (against about 2.05 for the device of FIG. 5 according to the prior art), and an L / D ratio of about 3.59 for the downstream ejection nozzle 4b (against about 2.36 for the device of FIG. Figure 5 according to the prior art). Also, the invention makes it possible to obtain the minimum value of 3 for the L / D ratio, which implies a significant improvement in the targeting of the lubricating oil jets H coming out of the ejection nozzles 4a, 4b. Moreover, the narrowing of the diameter of the internal cavity 9 at the first cavity portion 9a does not bring about a change in the measured value of the flow of lubricating oil H coming out of the ejection nozzles 4a and 4b. A method of assembling the lubricating device 1 of FIG. 6 will now be described with reference to FIG. 8. As shown in FIG. 8, the bent tube 13 is assembled on the main body 12 of the device 1. for brazing lubrication of the inner end 13a of the bent tube 13 in the outer end 12b of the main body 12. More specifically, the inner end 13a of the bent tube 13 is brazed along a brazing zone ZB formed at the inside of the outer end 12b of the main body 12. To enable this brazing to be carried out, the bent tube 13 advantageously has a plane distance Dp between its inner end 13a and its bent portion which is sufficiently large, this type of operation, and by example of about 5 mm. The use of brazing to allow the assembly of the bent tube 13 to the main body 12 of the lubricating device 1 can facilitate the industrial realization of the device 1. Moreover, the assembly of the bent tube 13 on the nipple 11 can also be done by brazing the outer end 13b of the bent tube 13 in the inner end of the nipple 11, or conventionally by welding the outer end 13b of the bent tube 13 on the nipple 11.
    [0016] S 56806 JLJ-P 13 Of course, the invention is not limited to the embodiment which has just been described. Various modifications may be made by the skilled person. The phrase "with one" shall be understood as being synonymous with "having at least one" unless the contrary is specified.5
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Lubrication device (1) for turbomachine bearing (2), comprising a main body (12) provided with an internal cavity (9) for the flow of a lubricating fluid (H), the main body (12) having, at its inner end (12a), at least one ejection nozzle (4a, 4b), in fluid communication with the internal cavity (9), for ejection of the lubricating fluid (H) in the direction of at least the bearing (2), characterized in that the axial dimension (Da, Db), in particular the diameter, of the internal cavity (9) of the main body (12) is lower in at least a first cavity portion (9a) extending from said at least one ejection nozzle (4a, 4b) at the inner end (12a) of the main body (12) as in at least a second cavity portion (9b) ) extending from the outer end (12b) of the main body (12).
    [0002]
    2. Device according to claim 1, characterized in that the axial dimension (Db), in particular the diameter, of said at least one first cavity portion (9a) is less than or equal to 3.5 mm.
    [0003]
    3. Device according to claim 1 or 2, characterized in that the radial dimension (L3), in particular the length, of said at least one first cavity portion (9a) is less than or equal to 32 mm.
    [0004]
    4. Device according to one of the preceding claims, characterized in that said at least one ejection nozzle (4a, 4b) comprises an ejection duct (7b), in fluid communication with said at least a first cavity portion. (9a), and an ejection opening (8b) into which the ejection duct (7b) opens so that the lubricating fluid (H) contained in the internal cavity (9) of the main body (12) is ejected. .S 56806 JU-P 15
    [0005]
    5. Device according to claim 4, characterized in that the length (L) of the ejection duct (7b) is greater than or equal to 4 mm, in particular greater than or equal to 4.2 mm, in particular still greater than or equal to 4 , 5 mm.
    [0006]
    6. Device according to claim 4 or 5, characterized in that the ejection opening (8b) is circular, and in that the ratio of the length (L) of the ejection duct (7b) to the diameter ( D) of the ejection opening (8b) is greater than or equal to 3.
    [0007]
    7. Device according to any one of the preceding claims, characterized in that it further comprises an interface element (11), located at the outer end (lb) of the lubricating device (1) and intended to be in interface with servo elements of the turbomachine (10), and an intermediate duct (13) bent, connecting the main body (12) and the interface element (11).
    [0008]
    8. Device according to claim 7, characterized in that the intermediate duct (13) bent is assembled on the main body (12) of the device (1) for brazing lubrication of the inner end (13a) of the intermediate duct (13). ) in the outer end (12b) of the main body (12).
    [0009]
    9. Turbomachine (10), characterized in that it comprises a device (1) for lubricating according to any one of the preceding claims.
    [0010]
    10. A method of assembling a device (1) for lubricating for bearing (2) turbomachine (10), the device (1) being according to any one of claims 1 to 8, the device (1) comprising a main body (12) provided with an internal cavity (9) for the flow of a lubricating fluid (H), the main body (12) having, at its inner end (12a), at least one nozzle ejection means (4a, 4b) in fluid communication with the internal cavity (9) for ejection of the lubricating fluid (H) towards at least the bearing (2), the device (1) further comprising a interface element (11), located at the outer end (1b) of the device (1) and intended to be connected to servo elements of the turbomachine (10), and an intermediate duct ( 13), connecting the main body (12) and the interface element (11), the method comprising at least the brazing step of the inner end (13a) of the intermediate duct (13) in the outer end (12b) of the main body (12) and / or the stepped drilling step of the internal cavity (9) of the lubricating device (1) to form at least a first portion cavity (9a) of axial dimension (Db) smaller than the axial dimension (Da) of at least a second cavity portion (9b).
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    同族专利:
    公开号 | 公开日
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    引用文献:
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    GB2574714A|2018-04-26|2019-12-18|Safran Aircraft Engines|Lubrication device for a turbo machine|
    FR3091903A1|2019-01-23|2020-07-24|Safran Aircraft Engines|Limited flow lubricating liquid nozzle|
    FR3094403A1|2019-04-01|2020-10-02|Safran Transmission Systems|Turbomachine jet comprising an oblique face ejection head|
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    2016-03-25| PLSC| Search report ready|Effective date: 20160325 |
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    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1458905A|FR3026135B1|2014-09-22|2014-09-22|TURBOMACHINE BEARING LUBRICATION DEVICE|FR1458905A| FR3026135B1|2014-09-22|2014-09-22|TURBOMACHINE BEARING LUBRICATION DEVICE|
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