• 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 turbomachine element comprising a stator (2), a rotor (1), and a first sealing means (9) between the rotor (1) and the stator (2) arranged to be active when the rotor is in its operating position about its axis of rotation (LL), characterized in that it comprises an auxiliary sealing means (20, 22) in pressure, between the rotor (1) and the stator (2) , and that it is arranged so that both sealing means are active when the rotor (1) is placed along its axis of rotation (LL) during a mounting operation in a test position, the rotor (1) and the stator (2) forming, in this test position, an enclosure (8) between said two sealing means.
    公开号:FR3024492A1
    申请号:FR1457350
    申请日:2014-07-29
    公开日:2016-02-05
    发明作者:Florence Irene Noelle Leutard；Thibault Jamon；Olivier Renon
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION AND STATE OF THE ART The present invention relates to the field of turbomachines and more particularly to the design of seals between a rotor and a stator, in particular near a bearing of rotor guidance. It relates in particular to a test method for checking a seal in a lubrication chamber around such a bearing. A turbine engine generally comprises, upstream to downstream in the direction of the gas flow, a fan, one or more stages of compressors, a combustion chamber, one or more turbine stages and a gas exhaust nozzle. Rotors, which can be coupled together by different transmission and gear systems, correspond to these different elements. Furthermore, in order to allow lubrication and cooling of the guide bearings of the rotating bodies, the turbojet engine comprises, in a conventional manner, a lubrication circuit. The lubrication circuit of a bearing comprises a lubrication chamber which is formed by an inner casing portion of the turbomachine surrounding a rotor portion on either side of the bearing. The axial ends of this lubrication chamber are traversed by the rotor. To confine the oil in the enclosure, the passages of the rotor through the enclosure are generally equipped with labyrinth type joints. Under certain conditions, an oil flow can escape from the enclosure. The patent application FR1260598 has for example a journal designed to recover this oil and send it back into the lubrication circuit without it escaping into the air flow passing through the turbomachine. Another complementary way of limiting oil losses is to create a depressurization of the lubrication chamber. The patent application WO2013083917 describes, for example, a system using annular seals at the passage of the rotor to ensure a seal between the enclosure and an adjoining external volume, so as to allow to create this depressurization. Furthermore, patent application WO2014006338 discloses a way of using a segmented radial seal (JRS) in this context.
    [0002] Installed upstream of the lubrication chamber, this segmented radial seal makes it possible to control its pressure. Downstream of this same enclosure, the seal can be provided by a labyrinth at the passage of the rotating body. The depressurization of the enclosure causes the air to arrive from outside. In this way the pressure difference ensures the sealing of the labyrinth seal with respect to the oil. However, it is essential to ensure the proper functioning of the JRS joint because it plays a major role in the pressure balance in the enclosure. Or mounting the rotor is usually from downstream to upstream. The segmented radial seal is fragile and can be damaged when the rotor is mounted in the housing if it encounters it by not being properly aligned. In addition, the segmented radial seal is in this case no longer accessible for a visual check of its state.
    [0003] The invention has the primary objective of providing a means to simply control the operation of the segmented radial seal when the rotor is installed in the housing. Furthermore, downstream, oil projections from the bearing can affect the effectiveness of the sealing means if they reach them. One solution would be to move the bearings away from the bearing, but the axial space in the environment of the turbomachine is limited. Another object of the invention is to allow a design of the enclosure around the guide bearing which is compact axially while protecting the joints from oil projections. SUMMARY OF THE INVENTION For this purpose, the invention relates to an element comprising a stator, a rotor, and a first sealing means between the rotor and the stator arranged to be active when the rotor is in its operating position. around its axis of rotation, characterized in that it comprises an auxiliary pressure sealing means between the rotor and the stator, arranged so that said two sealing means are active when the rotor is placed along its axis of rotation during a mounting operation in a test position, the rotor and the stator forming, in this test position, an enclosure between said two sealing means. The term pressure seal means that the means is sufficiently gas-tight to maintain a pressure difference across. Conversely, we will also talk about oil seal to mean that the means is able to block the oil but not necessarily to prevent gas leaks. The invention achieves its objective by the fact that when the enclosure is formed between the two sealing means when the rotor is placed in the test position, it is possible to establish a pressure difference between the closed enclosure and its environment. and testing the state of the first sealing means by observing the evolution of the pressure in the enclosure or outside. It is therefore not necessary, especially when the seal is inaccessible when the rotor is in the stator, to disassemble the element to check the operating state of the sealing means.
    [0004] Advantageously, the auxiliary pressure sealing means is arranged to be inactive when the rotor is placed in its operating position and rotates at a speed at least equal to a determined value, said determined value being zero. In general this determined value corresponds to the speed of rotation when the turbomachine is running. In this way, the auxiliary sealing means does not cause unnecessary friction during operation of the turbomachine. Advantageously, the stator and the rotor are arranged to form a lubrication chamber of a device located axially between said two sealing means when the rotor is in its operating position. The lubrication chamber will be able to serve here as depressurization chamber between the first seal and the auxiliary seal under pressure. Advantageously, the lubrication chamber, designed to retain the oil around the bearing has no openings other than the passages of the rotor through the stator and the oil passage holes between the enclosure and the circuit lubrication. By putting the rotor in the test position, the first sealing means and the pressurized auxiliary sealing means plug the rotor passages. It is then sufficient to close the oil passage holes except one to suck the air into the lubrication chamber and create a vacuum to test the state of the first seal. Preferably, the assembly comprises radial oil seal means between the rotor and the stator, located between the bearing and the second pressure sealing means and active when the rotor is in the first axial position. In this way, these oil sealing means prevent pollution of the second pressure sealing means by the oil of the lubrication chamber. Preferably, the first sealing means comprises a radial pressure seal, for example a segmented radial seal, integral with one of the bodies of the rotor or the stator, arranged to press on a cylindrical surface of sealing, secured to the other body, when said first means is active. It is therefore a pressure sealing means when the rotor is in the operating position, for example to control the depressurization of the lubrication chamber when the turbomachine is operating. In an alternative embodiment, the auxiliary pressure sealing means comprises a pressure seal integral with one of the rotor or stator bodies, arranged to press a cylindrical sealing surface when the rotor is fixed in rotation with respect to the stator and to be eliminated when the rotor rotates. Such a seal, for example beeswax, can be removed by heat caused by friction. With this technique, the test position can be axially the same as the operating position, this avoids manipulation and makes more compact the overall device. In another variant, the pressurized auxiliary sealing means (20, 22) comprises a seal (20) in pressure integral with one of the bodies of the rotor or the stator, arranged to press on a surface cylindrical (22) seal when the rotor is in a test position axially offset by a determined distance (d4) from the operating position and to be disengaged when the rotor (1) is in the operating position. The seal may be a "PTFE" type seal, for polytetrafluoroethylene, which comprises a ring of this type. Advantageously, the element further comprises a bearing between the stator and the rotor, said bearing comprising bearings between a first and a second ring, one of them being integral with the stator and the other being secured to the rotor, the first ring of which permits axial sliding of the bearings and comprises an axial extension 30 arranged to serve rotor guide surface on the axis of rotation when moving from the operating position to the test position or vice versa.
    [0005] This makes it possible to guide the rotor between the operating and test positions, thus limiting the risk of damage to the first sealing means. Advantageously, the rotor being arranged to be mounted in the stator in a direction of mounting along the axis, the test position is before the operating position in said mounting direction. This naturally integrates a test of the first sealing means in the mounting procedure. Thus one can start by installing the rotor in the stator, stop in an intermediate position to perform the test, then complete the installation by continuing the translation of the rotor in the same direction. Furthermore, it is not necessary to provide arrangements to be able to exceed the operating position along the axis before returning to the operating position, which can be difficult or impossible in the turbomachine. Preferably, the radial seal is radially external to the cylindrical sealing surface. This makes it possible, especially when the mounting direction causes the first seal to be upstream of the bearing, to prevent the radial seal from passing through the bearing during assembly and to be damaged. This also makes it possible to use an extension of the sealing surface cooperating with the radial seal to place between it and the bearing, a means, for example a swirler, cooperating with this sealing surface to protect the seal. oil from the lubrication chamber. Advantageously, said first seal being placed radially on the outside, the cylindrical sealing surface extends axially in the direction of the mounting direction, beyond its portion in contact with the radial seal in the position of operation, at a distance at least equal to that separating the operating position from the test position. In this manner, the cylindrical sealing surface extends axially so that the radial seal is in continuous contact with the sealing surface when the rotor is moved between the test and operating positions. This makes it possible to avoid shocks from encountering the seal with these surfaces between the tests and the operation, which may deteriorate it.
    [0006] In general, the stator radially surrounds the rotor. The parts of a sealing means connected to the stator are in this case radially external to the corresponding parts connected to the rotor. Advantageously, an annular cover surrounding the bearing is arranged to prevent radial projections of the oil having lubricated the bearing, and at least one sealing means inside the enclosure comprises, in the direction of the bearing, a ring in continuity with its radially innermost part, said ring having an outside diameter at least equal to the inside diameter of said cap. Preferably, said ring at least partially covers said annular cover when the rotor is in the first axial position. This avoids direct projections of oil from the bearing. Preferably, said ring at least partially covers said cover when the rotor is in the first axial position. The invention also relates to a turbomachine comprising an element as described above. The invention also relates to a method of testing a first sealing means in a turbomachine element according to the invention, comprising a step consisting in installing the rotor in said test position, in producing a suction port of air in the chamber, then to establish a vacuum in the chamber between the first sealing means and the auxiliary pressure sealing means, sucking the air through said orifice. BRIEF DESCRIPTION OF THE FIGURES: The present invention will be better understood and other details, features and advantages of the present invention will become more apparent upon reading the description of a non-limiting example which follows, with reference to the accompanying drawings in which: : Figure 1 schematically shows a meridian section of a stator and a rotor according to one embodiment of the invention when the rotor is in the operating position in a turbomachine. FIG. 2a schematically shows a meridional section of the stator and the rotor of FIG. 1, in the separated position and ready to be assembled.
    [0007] Figure 2b schematically shows a meridian section of a stator and a rotor according to an alternative embodiment of the invention, in the separated position and ready to be assembled. FIG. 3 schematically shows a meridional section of the stator and the rotor of FIG. 1, in an intermediate test position. Figure 4 schematically shows a meridian section of a stator and a rotor according to an alternative embodiment of the invention when the rotor is in the operating position in a turbomachine. DESCRIPTION OF THE EMBODIMENT FIG. 1 represents a turbomachine shaft 1 rotatable about an axis LL, installed in an operating position in a casing 2, at a bearing 3 for guiding the shaft 1 in the turbomachine. In Figure 1 and the following, the main flow of gas in the turbomachine 15 goes from left to right. The elements represented in the example corresponding to the figures are in a part of the turbomachine surrounded by this main flow. In the rest of the description, the upstream and downstream terms refer to this main flow. The guide bearing 3 is formed in particular by an outer ring 4, fixed to the casing 2, and an inner ring 5, fixed to the shaft 1, between which rollers 6 can roll freely. The bearing 3 is designed such that the rollers 6 remain held in the inner ring 5 when the shaft 1 is moved out of its operating position, for assembly or disassembly operations. Other bearings than the rollers, for example balls, can be used. It is also conceivable to design a bearing 3, illustrated in Figure 2b, where the bearings 6 are held on the side of the outer ring 4 when the rotating shaft 1 is removed. The outer ring 4 is connected to the casing 2 by a bearing support piece 7 of the bearing 3. The inner ring 5 is generally fixed to the surface of the rotary shaft 1. The casing 2 and the rotary shaft 1 are arranged to form an enclosure 8 of lubrication 4 around the bearing 3. This enclosure 8 comprises a passage of the shaft 1 upstream of the bearing 3 and a passage of the shaft 1 downstream of the bearing 3.
    [0008] The chamber 8 of lubrication is part of the lubrication circuit of the turbomachine. The oil enters the chamber 8 through an inlet, not shown in the figure and is directed towards the bearing 3 to lubricate. The oil having lubricated the bearing 3 comes out being projected in different directions. The purpose of the enclosure 8 is to recover the oil so that it goes back through an outlet, not shown also in the figure, so as to return to the lubrication circuit. To avoid oil losses, the passages of the shaft 1 in the chamber 8 are equipped with radial sealing means 9, 10, particularly able to block the oil. In addition, particularly with a view to improving the sealing of these radial sealing means 9, 10, during the rotation of the shaft 1, the element is designed so that the pressure PO of the enclosure 8 is lower. at the pressures P1, P2, located outside the passages of the shaft 1, when the turbomachine is operating. This depressurization contributes to the sealing of the enclosure 8. To obtain this result, the radial sealing means 9 of the upstream passage here comprises a segmented radial seal 11 (JRS) consisting of a sealing ring of carbon segments held pressed against each other, integral with the casing 2. This segmented radial sealing gasket 11 cooperates with a cylindrical surface 12 coming into contact with its inner surface. The cylindrical surface 12 is mounted on a sleeve 13 integral with the rotary shaft 1, whose section in a meridian plane has a shape of U parallel to the axis of rotation LL. This form allows sufficient elasticity for the shaft 1 can be installed in the housing 2 by going here from the right to the left along the axis of rotation LL, then the segmented radial seal 11 and the cylindrical surface 12 are in support when the shaft 1 is in the operating position relative to the housing 2.
    [0009] The design of the segmented radial seal 11 provides a sufficient seal to slow the passage of air and thus establish a pressure difference between its two sides. In this way, when the turbomachine is operating, the pressure PO of the chamber 8 can be maintained at a value lower than the pressure P1 which is established in the space upstream of the radial sealing means 9 of the upstream passage, which is in communication with higher pressure zones in the turbomachine.
    [0010] The radial sealing means 9 is completed by a swirler 14, inside the enclosure 8 with respect to the segmented radial seal 11. This swirler 14 cooperates with a part of the cylindrical surface 12 extending downstream from that cooperating with the segmented radial seal 11. The function of the auger 14 is to return to the chamber 8 the oil that can reach the upstream passage and protect the segmented radial seal 11 of this oil. The radial sealing means 10 of the downstream passage of the rotary shaft 1 comprises a labyrinth seal, consisting of wipers 15 integral with the shaft 1 which meet a cylindrical surface 16 integral with the casing 2, of abradable material. This labyrinth seal 15, 16, allows a good seal to the passage of the oil. The labyrinth seal 15, 16 is not as effective as the segmented radial seal 11, 12 for establishing a gas pressure difference between its ends. However, in the example presented, the flow of gases around the lubrication chamber 8 is from left to right and the segmented radial seal 11 blocking the flow of air upstream, this is sufficient to that the pressure PO in the chamber 8 also remains lower than the pressure P2 which is established in the space downstream of the labyrinth seal 15, 16. The radial sealing means 10 of the downstream passage is here also completed by a tendril 17, placed upstream of the labyrinth seal 15, 16. This swirler 17 cooperates with a ring 18 which extends upstream of the cylindrical surface 16 of the labyrinth seal. The function of the auger 17 is to return to the enclosure 8 the oil that can reach the downstream passage and to protect the labyrinth seal 15, 16, of this oil. The ring 18 cooperating with the swirler 17 is substantially aligned with the wiper support 15 of the labyrinth seal. The element is held by a flange 19 extending from the rotary shaft 1. According to one aspect of the invention, the flange 19 extends radially so that the diameter of the ring 18 cooperating with the the twist is slightly greater than that of the outer ring 4 of the bearing 3. In addition, with reference to FIG. 2a, in one embodiment where the bearings 30 6 of the bearing 3 slide on the outer ring 4, the extension towards the downstream of the outer ring 4 of the bearing and the extension upstream of the ring 18 cooperating with the swirler 17 are here arranged so that the ring 18 of the swirler 17 partially covers the outer ring 4 of the bearing 3. This arrangement makes that there is no direct path between the bearing 3 and the swirl 17 of the downstream passage. The oil projections, represented by an arrow in FIG. 1, are thus stopped by the ring. This makes it possible to have a compact configuration downstream of the bearing 3, where the radial sealing means 10 of the downstream passage is close to the bearing 3 but where the swirler 17 is protected from the projections of oil. In the alternative shown, with the shaft 1 and the casing in the detached position in FIG. 2b, it is possible to envisage that it is not the outer ring 4 of the bearing 3 which extends under the ring 18 of the twist 17 but a part 7b of the support part 7 of the bearing 3. This part 7b of the bearing support does not function as a track for the bearings 6 but it then forms a cover radially surrounding the bearing 3 on the downstream side and which can pass inside the ring 18 of the swirler 17 when the shaft 1 is in the operating position.
    [0011] According to another aspect of the invention, the rotary shaft 1 is installed in the casing 2 by being translated along the axis of rotation LL. On the examples presented, with reference to Figures 2a and 2b, the shaft 1 in the detached position is downstream of the housing 2 and the mounting is in a direction from downstream to upstream for the rotor. FIG. 2a shows the assembly of the shaft just before the docking for the embodiment of FIG. 1. The elongation of the outer ring 4 of the bearing 3 is such that the bearings 6, integral with the shaft 1, come into contact with it before the upstream end of the cylindrical surface 12 cooperating with the segmented radial seal 11 meets the downstream portion of the auger 14 of the upstream passage. This corresponds, with reference to FIG. 1, to the fact that, when the shaft 1 is installed in the operating position, the distance d1 separating the downstream end of the outer ring 4 from the upstream end of the bearings 6 of the bearing 3 is greater than the distance d2, separating the upstream end of the cylindrical surface 12 from the downstream end of the vrillel4, for the radial upstream sealing means 9. In this way, the parts of the radial sealing means 9 of the the upstream passage of the shaft 1 accost those of the housing 3 while the bearings 6 of the bearing 3 are already engaged in the outer ring 4 rolling. The movements of the shaft 1 in the translation for mounting are therefore guided by the bearing 3 which limits the risk of shock to the docking or parasitic forces during installation in the radial means of sealing 9. In a variant, one can simply protect the segmented radial seal 11, which is the most fragile. In this case, the distance d1 separating the downstream end of the outer ring 4 from the upstream end of the bearings 6 of the bearing 3 is greater than the distance d3 separating the upstream end of the cylindrical surface 12 from the downstream end of the segmented radial seal 11. It may also be noted that in this configuration, the extension needs of the outer ring 4 towards the downstream match for the mounting function of the segment radial seal 11 and for the protection function of the swirler 17 In a preferred embodiment, with reference to FIGS. 1 and 2a, the bearings 6 connected to the shaft 1 also accost the outer ring 4 before the ring 18 cooperating with the spin 17 downstream meets the cylindrical surface 16 cooperating with the wipers 15 of the labyrinth seal. This also makes it possible to protect the radial sealing means 10 from the downstream passage during assembly. In an alternative embodiment, shown in Figure 2b, the bearings 6 are integral with the outer ring 4, fixed to the housing 2. In this case, it is the inner ring 5 which has an extension upstream to the -where the bearing is made when the shaft 1 is in the operating position. This extension is such that the inner ring 5 encounters the bearings 6 before the integral parts of the housing 2 and the shaft 2 of the radial sealing means 9, 10, are encountered. In yet another aspect of the invention, with reference to FIG. 3, a pressure seal 20 is installed on a ring 21 downstream of the cylindrical surface 16 cooperating with the wipers 15 of the labyrinth seal. The shaft 1 and the casing 2 are configured so that this pressure seal 20 presses on a ring 22, integral with the shaft 1 and extending the labyrinth seal 15, when the shaft 1 is in a determined position , offset from the operating position, as illustrated in FIG. 3.
    [0012] The pressure seal 20 is here a "PTFE" seal, for polytetrafluoroethylene, which comprises a ring made of this material and enclosed by a circular spring which presses against the ring 22 of the shaft 1. This type of seal ensures good pressure tightness with low friction. In addition, these seals withstand high temperatures, which can be encountered at this point in a turbomachine in operation. However, it is conceivable to use seals formed from other materials, provided that they make it possible to ensure pressure tightness around the shaft as it passes through the enclosure and that they withstand the conditions of environment of a turbomachine. By cons, as will be seen later in the conditions of use, it is not necessary that they operate with low friction when the shaft 1 is rotating. In FIG. 3, the shaft 1 and the casing 2 already shown in FIGS. 1 and 2a are in a configuration where the shaft is translated to an intermediate position, the shaft being shifted by a distance d4 towards the downstream from the operating position of FIG. 1. This distance d4 corresponds in FIG. 1 to an offset of the "PTFE" seal 20 with respect to its bearing position on the ring 22, so that it is released from this ring 22 when the shaft 1 is in the operating position. In this way, when the shaft 1 is in the operating position, as can be seen in FIG. 1, the "PTFE" seal 20 is disengaged from the ring 22. In the example presented, this seal 20 does not is not active when the shaft 1 is in the operating position and the means 21, 22, with which it cooperates, do not interact together or with other elements of the turbomachine when the shaft 1 is in the position of operation. These means 20, 21, 22 do not introduce friction or disturbance when the turbomachine works. In addition, in the example, being outside the enclosure 8, means 20, 21, 22 are not likely to be polluted by oil projections of the bearing 3. Moreover, the distance d4 of translation to the intermediate position is less than the distance d1 previously described in FIG. 1, necessary to disengage the bearings 6 from the bearing 3 of the outer ring 4. Thus, from the operating position to the intermediate position and vice versa, by translating the shaft 1 with respect to the housing 2 along the axis of rotation LL, the shaft 1 being guided by the contact of the bearings 6 of the bearing 3 with the inner and outer rings 5 and 4. Moreover, Referring to FIG. 2a or 2b, the "PTFE" seal 20 and its support ring 21 preferably have a diameter slightly greater than that of the parts 18, 15 integral with the shaft 1 of the radial sealing means 10, for the downstream passage. It is therefore possible to install the shaft 1 in the casing 2 without the "PTFE" seal 20 coming to rub on these elements 18, 15. On the other hand, at the level of the upstream radial sealing means 9, the cylindrical surface 12 is here increased upstream by a value at least equal to the offset distance d4 between the operating position and the intermediate position. In this way, as can be seen in FIG. 3, when the shaft is in the intermediate position, the segmented radial seal 11 cooperates with the cylindrical surface 12 and the "PTFE" seal 20 cooperates with the ring 22 in such a way that at the same time, a pressure seal is provided at the two passages of the shaft 1 in the lubrication chamber 8. This intermediate position advantageously defines a test position for the segmented radial seal 11. In fact, the segmented radial seal 11 being in the upstream passage of the shaft 1, it becomes inaccessible when it is installed in the housing 2. It is then impossible to carry out direct checks to check its state. In an alternative embodiment, illustrated in Figure 4, the test position is the same as the operating position. In this variant, a ring gasket 23b is inserted into a groove 23b formed in a portion of the cylindrical surface 18 of the rotor cooperating with the swirler 17 on the stator. This ring seal 23b bears in this position against the cylindrical surface 16 of the stator cooperating with the labyrinth 15 of the stator so as to provide a pressure seal when the rotor is not rotating. The ring gasket 23b is made here of a material, for example beeswax, which melts under the effect of the heat caused by friction when the rotor is rotated during its operating conditions. In this way, it is eliminated when the turbomachine operates and does not create friction losses.
    [0013] With the configuration illustrated in Figure 3, the mounting procedure can be advantageously completed by a test procedure. For this, after making the docking of the bearings 6 and the corresponding ring 4 of the bearing 3, a first step is to continue one continues the translation of the shaft 1 upstream to the intermediate position. In this position, the seal "PTFE" 20 seals pressure in the downstream passage of the shaft 1 in the lubrication chamber 8. On the other hand, if the segmented radial seal 11 is working properly, it ensures the pressure sealing at the upstream passage cooperating with the extension provided for this purpose of the cylindrical surface 12 10 integral with the shaft 1. It is therefore possible to carry out a test step in this position, using, for example, the orifices of passage of the oil in the lubrication chamber 8 to suck the air and create a vacuum in the chamber 8. The observation of the evolution of the pressure in the lubrication chamber 8 then informs about the state If it has been damaged, for example when it encounters the cylindrical surface 12, it will leave too great leaks which will cause the pressure to rise rapidly. If the depressurization test shows, on the other hand, that the segmented radial seal 11 is in good condition, the next step consists in continuing the translation of the shaft 1 towards upstream 20 to bring it to its operating position in the casing 2. Advantageously, the portions of the cylindrical surface 12, integral with the shaft 1, cooperating with the segmented radial seal 11 in the operating position and in the intermediate test position, form a single continuous face. In this way, when the shaft 1 is translated from one position to the other, the segmented radial seal 11 remains in contact with that face. There is therefore no risk of deterioration of the seal 11 by shocks at the meeting of different faces. In a variant, the test of the segmented radial seal 11 can be made after a period of operation of the turbomachine. In this case, the first step is to shift the shaft 1 downstream of the distance d4 from the operating position to the intermediate test position and then to perform the depressurization test. If the test is conclusive, we can then replace the shaft 1 in its operating position, without having to remove it completely from the housing 2. With the embodiment variant corresponding to Figure 4, the first step of the procedure of assembly test consists, after making the docking of the bearings 6 and the corresponding ring 4 of the bearing 3, to continue the translation of the shaft 1 upstream to the operating position, which is also the position test. During this step, the material of the ring seal 23a can deform to slide against the cylindrical surface 17, while being held in position on the rotor 1 by the groove 23b.
    [0014] Then, the rotor being kept motionless, it is possible to carry out the same steps as in the preceding variant to carry out the test of the radial seal, the ring seal 23a sealing at the other end by pressure against the cylindrical surface 17 On the other hand, there is no translation step after the test since the rotor is already in its operating position.
    [0015] Then in a subsequent step, when the turbomachine is assembled the ring gasket 23a, here made of beeswax, melts during the first operation of the turbomachine and disappears. Its disappearance causes that there is no contact at this point between the rotor and the stator, so that friction losses are zero. The advantage of this variant is that it is not necessary to provide radial extension complementary to the cylindrical surface 12 so that the radial seal 11 is active during the assembly test procedure. The whole can be more compact.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Turbomachine element comprising a stator (2), a rotor (1), and a first sealing means (9) between the rotor (1) and the stator (2) arranged to be active when the rotor is in its position of operating around its axis of rotation (LL), characterized in that it comprises an auxiliary sealing means (20, 22) in pressure, between the rotor (1) and the stator (2), and that is arranged so that said two sealing means are active when the rotor (1) is placed along its axis of rotation (LL) during a mounting operation in a test position, the rotor (1) and the stator (2) forming, in this test position, an enclosure (8) between said two sealing means (9, 20-21).
    [0002]
    A turbomachine element according to claim 1, wherein the pressure-sealing auxiliary means (20, 21) is arranged to be inactive when the rotor (1) is placed in its operating position and rotates at a speed of at least equal to a determined value, said determined value being able to be zero.
    [0003]
    3. turbomachine element according to one of claims 1 and 2, wherein the stator (2) and the rotor (1) are arranged to form a housing (8) for lubricating a device (3) located axially between said two sealing means (9, 2021) when the rotor (1) is in its operating position.
    [0004]
    4. turbomachine element according to one of claims 1 to 3, wherein the first sealing means (9) comprises a radial seal (11) pressure, for example a segmented radial seal, integral with the one of the bodies of the rotor or the stator, arranged to press on a cylindrical sealing surface (12), integral with the other body, when said first means is active.
    [0005]
    5. turbomachine element according to one of claims 1 to 4, wherein the auxiliary sealing means (23a, 23b, 16) under pressure comprises a seal (23a) pressure integral with one of the bodies among the rotor or the stator, arranged to press on a cylindrical sealing surface (16) when the rotor is fixed in rotation relative to the stator and to be eliminated when the rotor rotates.
    [0006]
    6. turbomachine element according to one of claims 1 to 4, wherein the auxiliary sealing means (20, 22) in pressure comprises a seal (20) in pressure integral with one of the bodies of the rotor or stator, arranged to press a cylindrical sealing surface (22) when the rotor is in a test position axially offset by a determined distance (d4) from the operating position and to be disengaged therefrom when the rotor (1) is in the operating position.
    [0007]
    A turbomachine element according to claim 6, further comprising a bearing (3) between the stator (1) and the rotor (2), said bearing (3) having bearings (6) between a first (4) and a second (5) ring, one (4) of which is integral with the stator (2) and the other (5) is integral with the rotor (1), characterized in that the first ring (4) allows a axial sliding of the bearings (6) and that its axial extension is arranged to serve as a guide surface of the rotor on the axis of rotation (LL) during a displacement of the operating position to the test position or vice versa.
    [0008]
    Turbomachine element according to one of claims 6 and 7, wherein the rotor (1) being arranged to be mounted in the stator (1) in a direction of mounting along the axis (LL), the test position. is located before the operating position in said mounting direction.
    [0009]
    9. Turbomachine comprising an element according to one of claims 1 to 8.
    [0010]
    10. A method of testing a first sealing means (9) in a turbomachine element according to one of claims 1 to 8, comprising a step of installing the rotor (1) in said test position, to achieve an air intake opening in the chamber (8), then establishing a vacuum in the chamber (8) between the first sealing means (9) and the auxiliary means (20,21) sealing in pressure, sucking air through said orifice.
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    CA2876347C|2020-05-12|Pivot pin for a turbine engine comprising a ring for recovering a flow of lubricating oil with a plurality of lubricating oil discharge ports
    FR3036441B1|2019-06-07|CAPOTE OIL SPRINKLER
    EP2643069B1|2016-02-03|Oil discharge device and turbomachine comprising such a device
    EP3256698B1|2019-04-03|Retainer nut for axial blockage of a bearing in a turbomachine
    FR2989116A1|2013-10-11|COAXIAL INTER-SHAFT SEALING DEVICE OF A TURBOMACHINE
    FR3067057A1|2018-12-07|TURBOMACHINE COMPRISING AN OPTIMIZED SPEED RATE SPEAKER
    FR3024493A1|2016-02-05|TURBOMACHINE ELEMENT COMPRISING A SEAL BETWEEN A STATOR AND A ROTOR, AND METHOD OF MOUNTING
    FR2983909A1|2013-06-14|Lubricated chamber for turboshaft engine of aircraft, has interior space including support bearing ring for supporting outer annular track, and labyrinth seal including abradable material track attached to upstream end of ring
    FR3071549A1|2019-03-29|LUBRICATED ENGINE ENCLOSURE COMPRISING AN IMPROVED DEPRESSURIZATION SYSTEM
    WO2019122739A1|2019-06-27|Dynamic sealing between two rotors of an aircraft turbomachine
    FR3075252A1|2019-06-21|SEALING ASSEMBLY
    FR3094396A1|2020-10-02|Turbomachine lubrication enclosure comprising a pressurization valve
    FR2985763A1|2013-07-19|Sealing device for sealing e.g. high pressure shaft of turboshaft engine, has fixing units arranged at free ends of segment, where units cooperate with each other and maintain segment in pre-maintenance position by elastic recoil
    WO2019122625A1|2019-06-27|Dynamic seal bewteen two rotors of an aircraft turbine engine
    FR3035686A1|2016-11-04|ELECTRICAL COMPRESSOR WITH IMPROVED DYNAMIC SYSTEM OF SEALING
    同族专利:
    公开号 | 公开日
    JP6499211B2|2019-04-10|
    US10502083B2|2019-12-10|
    RU2016150381A|2018-08-28|
    US20170152754A1|2017-06-01|
    FR3024492B1|2019-08-23|
    CA2952928A1|2016-02-04|
    EP3175091B1|2018-10-31|
    JP2017530283A|2017-10-12|
    CN106661942A|2017-05-10|
    RU2016150381A3|2019-01-14|
    EP3175091A1|2017-06-07|
    CN106661942B|2018-10-09|
    BR112016029958A2|2017-08-22|
    WO2016016545A1|2016-02-04|
    RU2682301C2|2019-03-18|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2644843A1|1989-03-23|1990-09-28|Snecma|Method for mounting the low-pressure turbine on the high-pressure casing of a turbomachine with inter-shaft bearing, and tooling for implementing the method|
    EP1577495A1|2004-03-05|2005-09-21|Snecma|Turbomachine rolling bearing assembly having a reduced space requirement|
    EP1757777A1|2005-08-26|2007-02-28|Snecma|Method to assemble a turbomachine|
    FR1260598A|1960-01-30|1961-05-12|Filter paper for filtering coffee, tea or the like|
    FR2705733B1|1993-05-25|1995-06-30|Snecma|Device for depressurizing the lubrication chambers surrounding the bearings of a turbomachine.|
    US5975537A|1997-07-01|1999-11-02|General Electric Company|Rotor and stator assembly configured as an aspirating face seal|
    US6203273B1|1998-12-22|2001-03-20|United Technologies Corporation|Rotary machine|
    GB2359863B|2000-03-04|2003-03-26|Alstom|Turbocharger|
    US6966622B2|2001-09-28|2005-11-22|Hewlett-Packard Development Company, L.P.|Thermal sense resistor for a replaceable printer component|
    US6887038B2|2003-09-02|2005-05-03|General Electric Company|Methods and apparatus to facilitate sealing between rotating turbine shafts|
    DE502005004418D1|2005-10-24|2008-07-24|Borgwarner Inc|turbocharger|
    US7360434B1|2005-12-31|2008-04-22|Florida Turbine Technologies, Inc.|Apparatus and method to measure air pressure within a turbine airfoil|
    DE102006052786B4|2006-11-09|2011-06-30|MTU Aero Engines GmbH, 80995|turbomachinery|
    US20130106061A1|2011-10-28|2013-05-02|General Electric Company|High temperature seal system|
    FR2983908B1|2011-12-08|2015-02-20|Snecma|SYSTEM FOR ENSURING SEALING BETWEEN AN OIL ENCLOSURE AND AN OUTER VOLUME ATTACHED AND TURBOMACHINE EQUIPPED WITH SUCH A SEALING SYSTEM.|
    US9353647B2|2012-04-27|2016-05-31|General Electric Company|Wide discourager tooth|
    FR2993024B1|2012-07-06|2014-08-08|Snecma|TURBOMACHINE BEARING SEAL SEAL DEVICE WITH TWO ELASTIC JOINTS|US9976561B2|2016-04-11|2018-05-22|Borgwarner Inc.|Method for securing stator in high speed electric motors|
    FR3062679B1|2017-02-07|2019-04-19|Safran Aircraft Engines|VIROLE FOR REDUCING THE PRESSURE REDUCTION IN THE NEIGHBORHOOD OF THE UPPER JOINT OF A TURBOJET ENGINE BEARING ENCLOSURE|
    FR3067057B1|2017-05-30|2020-01-10|Safran Aircraft Engines|TURBOMACHINE COMPRISING AN OPTIMIZED LEAKAGE FLOW ENCLOSURE|
    US10458267B2|2017-09-20|2019-10-29|General Electric Company|Seal assembly for counter rotating turbine assembly|
    法律状态:
    2015-08-07| PLFP| Fee payment|Year of fee payment: 2 |
    2016-02-05| PLSC| Publication of the preliminary search report|Effective date: 20160205 |
    2016-05-06| RM| Correction of a material error|Effective date: 20160404 |
    2016-07-20| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-27| PLFP| Fee payment|Year of fee payment: 4 |
    2017-11-10| CD| Change of name or company name|Owner name: SNECMA, FR Effective date: 20170713 |
    2018-06-21| PLFP| Fee payment|Year of fee payment: 5 |
    2019-06-21| PLFP| Fee payment|Year of fee payment: 6 |
    2020-06-23| PLFP| Fee payment|Year of fee payment: 7 |
    2021-06-23| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1457350A|FR3024492B1|2014-07-29|2014-07-29|ELEMENT COMPRISING A STATOR AND A TURBOMACHINE ROTOR WITH A SEAL AND TESTING THIS SEAL|
    FR1457350|2014-07-29|FR1457350A| FR3024492B1|2014-07-29|2014-07-29|ELEMENT COMPRISING A STATOR AND A TURBOMACHINE ROTOR WITH A SEAL AND TESTING THIS SEAL|
    EP15751051.2A| EP3175091B1|2014-07-29|2015-07-21|Device of a turbimachine with an auxiliary sealing mean and a process for testing this device|
    US15/320,937| US10502083B2|2014-07-29|2015-07-21|Turbomachine element comprising an auxiliary sealing means, and method for testing this element|
    JP2016574252A| JP6499211B2|2014-07-29|2015-07-21|Turbomachine element with auxiliary sealing means and method for testing this element|
    RU2016150381A| RU2682301C2|2014-07-29|2015-07-21|Turbomachine element comprising auxiliary sealing means and method for testing this element|
    BR112016029958A| BR112016029958A2|2014-07-29|2015-07-21|turbomachine element including auxiliary sealing means and method for testing this element|
    PCT/FR2015/052004| WO2016016545A1|2014-07-29|2015-07-21|Turbomachine element comprising an auxiliary sealing means, and method for testing this element|
    CN201580033678.2A| CN106661942B|2014-07-29|2015-07-21|Turbine element including auxiliary sealing device and the method for testing the element|
    CA2952928A| CA2952928A1|2014-07-29|2015-07-21|Turbomachine element comprising an auxiliary sealing means, and method for testing this element|
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