• 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 bearing housing (E) of a turbomachine comprising a fixed wall (9), a rotating shaft (5) and a first and a second seal (10) between the wall and the shaft. . The enclosure is characterized in that an air guiding means (30) is arranged along the surface of the wall (9) of the enclosure, external to it, so that at least a portion of the air leaving the guide means passes between the seal (10) and the shaft, the guide means being supplied with air by an air intake radially distant from the shaft, the air being at a higher pressure than at the shaft.
    公开号:FR3016661A1
    申请号:FR1450570
    申请日:2014-01-23
    公开日:2015-07-24
    发明作者:Jeremy Lucien Jacques Bioud；Sebastien Bourget；Gael Evain；Eddy Stephane Joel Fontanel；Florence Irene Noelle Leutard；Christophe Lima；Giuliana Elisa Rossi
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] Field of the Invention The field of the present invention is that of turbomachines, in particular that of gas turbine engines intended for the propulsion of aircraft. The invention relates to the equilibrium of the pressures at the terminals of the sealing members between rotating elements and fixed elements of the turbomachine, in particular, in the region of the bearings supporting the rotor shafts, the tightness of the enclosures in which ones are housed. State of the art An aircraft turbomachine generally comprises, upstream to downstream in the direction of the gas flow, a fan, one or more stages of compressors, for example a low pressure compressor, LP, and a high pressure compressor. , HP, a combustion chamber, one or more stages of turbines, for example a high pressure turbine, and a low pressure turbine, and a gas exhaust nozzle. Each compressor may correspond to a turbine, both being connected by a shaft, thus forming, for example, a high pressure body, HP, and a low pressure body, BP. The shafts are supported upstream and downstream by bearings that are housed in enclosures isolating them from the rest of the engine. The enclosures thus contain bearings which are interposed between a rotating member of the motor and a fixed part which supports it or between two rotating parts, both rotating at different speeds of rotation such as a journal integral with the HP shaft and the BP tree. The bearings are lubricated and cooled by oil. The oil, projected by the rotating parts, forms a mist of droplets in suspension. These enclosures are formed and delimited by walls of the fixed structure of the engine but also by the rotating elements. Sealing means are provided in the areas where the fixed and movable parts meet. These means must allow the passage through them of a flow of air, in order to pressurize the enclosure and retain the maximum oil inside thereof. This is why the sealing between the fixed elements and the rotating elements of an oil chamber is a particularly delicate problem. Tightness is commonly achieved using a labyrinth seal which is the simplest, most robust and most common sealing solution in turbomachinery. Such a seal comprises, on the one hand, wipers, or thin ribs, which are integral with a rotating part and, on the other hand, an abradable material, positioned vis-à-vis the wipers, which is integral with a fixed room. As we are close to a bearing, we impose a game between the wipers and the abradable so that the wipers do not dig the abradable and do not create chips with the material constituting it: The bearings are sensitive to metal particles that are likely to damage them. Each wiper creates in cooperation with the abradable which faces him a loss of load and it is the sum of these losses of loads which ensures the required sealing. Other joint techniques are also possible, such as brush seals, as described in the patent application in the name of the Applicant, FR 1261694 where a labyrinth seal is associated with a brush seal to control the flow rates. leakage through the seal regardless of engine speed. The patent application FR 2 929 325 in the name of the applicant is a bearing chamber with a control of the leakage rate by that of the pressure inside the enclosure according to the regime also. In this application are mentioned segmented radial type joints which is also referred to by the acronym JRS. The application of this type of seal to a turbomachine is described in the patent in the name of the Applicant EP 387.122. A bearing housing generally comprises two seals along the shaft, one upstream of the bearing contained in the enclosure, the other downstream of the latter. However some bearing enclosures may include one or more additional seals and the enclosure itself may comprise several bearings. As indicated above, these seals are traversed by a flow of gas from the outside of the seals towards the interior of the enclosure in order to prevent, during the operation of the engine, the oil contained in the enclosure do not escape and pollute the other engine parts. This gas is air from a source of pressurized air, including compressors.
    [0002] The enclosure may be in communication with the open air and be maintained at a pressure close to atmospheric pressure. The bearings inside the enclosures are bathed by a mist of oil which is extracted from the enclosure continuously and separated in a de-oiler.
    [0003] The enclosure may also not be in direct communication with the open air and may not include de-oiling. An oil recovery pump connected to a recovery port, placed at 6 o'clock, at the low point of the engine, recovers the oil and the air from the enclosure and thus creates a suction of air through the joints of the engine. oil enclosure. The pump advantageously has a pumping rate greater than that of the oil inlet in the chamber for lubricating the bearing. In this case it is important to have a flow of air through the two upstream and downstream seals, in order to retain the oil at the two seals. And for there to be air flow through the two oil chamber joints, it is necessary to have a pressure balance upstream of the two joints. By this pressure balance, no preferential path is created which would favor one joint rather than the other and which would thus compromise the sealing performance of the latter. The present invention aims to solve the problem of the pressure balance outside the two joints of the chamber by increasing the pressure upstream of the seal whose pressure level is the lower of the two. According to a known arrangement, the air dedicated to the pressurization of the seals, coming from the compressors, enters the chamber in which the bearing chamber is located through an opening located near the shaft and is guided along the outer surface of the bearing housing radially and then axially through appropriate passages to the downstream chamber to supply the downstream seal. The analysis of the pressure levels of this pressurization air flow shows that there is a pressure gradient between the air inlet opening and the region located at a higher radial level. This pressure gradient results from the recompression vortex in this chamber located upstream of the upstream seal of the bearing chamber.
    [0004] By the expression "recompression vortex" is meant the phenomenon that links the radial deviation to a pressure difference in the presence of a rotating flow. Here the flow is rotated because it is driven by the rotation of the shaft of the turbomachine. The pressurizing air flow coming from the compressor being introduced into the chamber through an opening located radially at the level of the shaft, the rotation of the shaft induces the rotation of this air flow which swirls radially to a annular discharge channel which is located at a radius greater than that of the inlet opening in the chamber. This swirling motion creates a radial pressure gradient on the ventilation airflow. DESCRIPTION OF THE INVENTION The present invention makes use of this pressure gradient to recover air at a higher pressure than at the seal to precisely guarantee a sufficient pressure level upstream of a first seal. and a balance between the pressures outside the two joints of the enclosure. Sufficient air flow through the two seals to prevent oil leakage is ensured. According to the invention, a bearing housing of a turbomachine comprising a fixed wall, a rotating shaft and a first and a second seals between the wall and the shaft, is characterized in that a means of air guiding is arranged along a portion of the surface of the fixed wall of the enclosure external thereto, so that at least a portion of the air exiting the guiding means passes through the first seal, this guide means being supplied with air by an air intake radially distant from the shaft, the air being at a higher pressure than at the shaft. Thus, it is given the means to control the pressure at the first seal in such a way that the respective pressures at the two seals are balanced.
    [0005] According to an advantageous embodiment, insofar as the wall of the bearing housing comprises a radially oriented portion, the guide means comprises a guide plate, in the form of a single sheet for example, arranged radially parallel to said portion. wall of the enclosure. More particularly, the first seal being supported by a flange which is fixed to a flange of the enclosure, and the wall portion of the enclosure being formed by said support, this guide plate is attached to the wall of the enclosure and bolted with the support of the seal on the flange, for example. Preferably, the sheet-shaped guide plate defines a slight clearance with the shaft. This is indeed to prevent too much of the air guided between the plate and the wall of the enclosure returns to the upstream chamber. The air is intended to cross the seal at the level of the shaft. Pressure recovery is further improved along the wall of the bearing enclosure with a guiding means comprising a device arranged to guide the flow of air radially with - at the output of this device - a low tangential velocity component by relative to the radial component. Reducing the rotation of the air reduces the pressure drop along the guide means.
    [0006] The tangential velocity component of this air flow is advantageously reduced by arranging a ring pierced with radial orifices, in particular of oblong shape, or comprising fins orienting the flow radially, or else a honeycomb ring.
    [0007] The invention applies in particular to an enclosure whose first seal is a segmented radial seal. Indeed this type of seal is very effective. The second seal may be a labyrinth seal. The solution of the invention is particularly applicable to the case where the radially distant air intake corresponds to a vortex compression zone. Finally, the invention relates more specifically to a turbomachine comprising a bearing chamber according to the invention with an annular chamber upstream of the bearing chamber. This chamber is supplied with air through a feed opening near the shaft and comprises an annular channel-shaped air outlet opening radially spaced from the shaft. There is therefore a radial gap between the air supply opening of the upstream chamber and its air exhaust opening. The air intake of the pressurizing air guiding means of the first seal, radially distant, is disposed near said air exhaust opening.
    [0008] The turbomachine also comprises an annular chamber downstream of the bearing housing, fed with pressurizing air from the second seal from said exhaust opening of the upstream annular chamber. Part of the pressurizing air of the seal passes into said bearing chamber through the second seal. BRIEF DESCRIPTION OF THE FIGURES Other features and advantages will become apparent from the following description of a non-limiting embodiment of the invention with reference to the accompanying drawings, in which FIG. 1 shows in axial half-section a diagrammatic view of a turbojet engine, according to the prior art; FIG. 2 represents a schematic view in axial section of a bearing enclosure according to the prior art; FIG. 3 represents the bearing housing of FIG. 2 on which the device of the invention has been mounted. Figure 4 shows an example of mounting of the device of the invention. DETAILED DESCRIPTION OF AN EMBODIMENT OF THE INVENTION Referring to FIG. 1, a turbojet engine 1 of the prior art is shown which conventionally comprises a fan S, a low pressure compressor LP, a compressor high pressure HP lb, a combustion chamber 1c, an HP high pressure turbine ld and a LP low pressure turbine. The high-pressure compressor 1b and the high-pressure turbine 1d are connected by a high-pressure shaft 4 and form with it an HP high-pressure body. The low pressure compressor 1a and the low pressure turbine 1c are connected by a low pressure shaft 5 and form with it a low pressure body LP. These bodies are carried by fixed structural parts, called intermediate housing 2 for the support of their bearings located upstream and exhaust housing 3 for the support of their bearings downstream. To ensure their lubrication, these bearings are enclosed in enclosures, approximately leaktight, which are formed by a juxtaposition of fixed walls connected to the intermediate casing 2, respectively to the exhaust casing 3, and movable elements connected to the high shafts and low pressure respectively. A turbomachine thus comprises, generally, an upstream enclosure El associated with the intermediate casing 2 and a downstream enclosure E2 associated with the exhaust casing 3. As indicated above these enclosures are bathed in an atmosphere containing oil for the lubrication of the various organs and they are traversed by a controlled flow of air for pressurizing purposes.
    [0009] In Figure 2, there is shown a bearing in its enclosure according to an arrangement of the prior art. This is the rear bearing associated with the exhaust casing with its enclosure E2.
    [0010] The downstream end of the LP shaft 5 is supported by a bearing 7 whose fixed ring 7a is mounted in a bearing support 9 integral with the exhaust casing of the engine. The bearing is bathed in an oil mist produced by means not shown. The bearing support 9 is shaped so as to arrange with the shaft an enclosure E2 enveloping the bearing 7. Ahead of the bearing a first seal 10 seals between the fixed support 9 and the shaft 5 Downstream of the bearing 7 a second seal 20 seals between the support and the shaft 5. The first seal is here a segmented radial seal the second seal is a labyrinth seal. The bearing support 9 comprises a wall portion 16 upstream which extends perpendicularly to the shaft 5.
    [0011] The labyrinth seal 20 comprises wipers cooperating with an element of abradable material. A spin as for the first seal brings back to the enclosure oil that tends to accumulate against the seal.
    [0012] The arrows indicate the circulation of the pressurizing air of the joints. The air Fl coming from the compressors enters through an opening 19a close to the shaft in the chamber Cam formed between the upstream wall of the enclosure E2 and a stator plate 19. This air swirls inside this chamber due to of the rotation of the shaft 5. It undergoes a swirling compression, or a recompression vortex and escapes partly in F2 through the exhaust opening 19b, remote from the shaft, formed by the annular channel formed between the enclosure E2 and the plate 19. The pressure is determined so that a portion F10 of the air in this chamber Cam passes through the first seal 10 in the bearing chamber so as to prevent any leakage of oil through this joint. The air F2 follows a path F3 then F4 into the downstream chamber Cav on the second bearing side 20. A portion F20 of the air passes through the seal 20. The air pressure increases from Fl to F2, as indicated above, then decreases in F3 until F4 because of the pressure drops in the circuit between the two chambers Cam and Cav. It can be seen that in this configuration, the pressure at A just upstream of the first bearing 10 remains lower than the pressure at B just at the inlet of the second seal despite the pressure drops at F3 and F4.
    [0013] The pressure at B is at a level sufficient relative to the pressure inside the chamber to prevent the oil from escaping through the labyrinth seal 20.
    [0014] The pressure deficit at A is likely to lead to an oil leakage through the seal 10. Based on the finding that there is a pressure gradient between the Fl inlet and the outlet 5 of the upstream chamber Cam F2, air guiding means for pressurizing the seal between the pressure zone F2 and the inlet A of the seal 10 has been added in accordance with the invention. Figure 3 shows the arrangement of the invention. A plate 30 has been mounted, with interposition 10 of a spacer 32, on the wall portion 16 of the bearing support 9. This plate 30 defines a passageway forming said air guide means which extends radially between the shaft 5 and the annular outlet channel 19b of the chamber Cam. A weak clearance J is present between the shaft and the sheet. By this arrangement, the air in this passage is at the pressure prevailing at F2 with the pressure drop close and a centripetal air flow is created in the passage which passes through the seal 10 and the clearance J due to lower pressure level in Fl and in the bearing enclosure. By ensuring that the clearance J is as small as possible, an air flow passes through the seal 10. In addition to the pressure increase upstream of the first seal, the sheet also has the advantage of being to overcome pressure variations that may occur in the Cam chamber at all radial heights. These variations in undesirable pressures can be caused by the shape of the housing and the force of the vortex. The pressure obtained upstream of the joint is in this way only slightly subject to variations in its environment.
    [0015] Pressure recovery is further improved by straightening the centripetal airflow. This is made possible by rectifying means which cancel or at least reduce the tangential component of speed of the centripetal air flow. These flow rectifying means are, for example, suitably oriented orifices, for example of oblong shape, formed in the spacer 32. Instead of orifices, radial fins or any other means may be provided, a honeycomb ring. for example. Figure 4 shows an example of practical mounting with a segmented radial seal. The seal 10 comprises, according to one embodiment as described in patent EP 387122, a segmented ring 12, for example made of graphite, the segments of which are secured by means of an elastic ring and are housed in a groove of a support plate of 16. The segments are in abutment against an annular track arranged on the surface of the shaft. The joint support plate 16 forms the upstream portion of the bearing enclosure. The joint support plate 16 extends in a plane transverse to the shaft, and is bolted to an upstream flange 18 of the bearing support 9. As is also known, a swirler 14 is disposed downstream of the joint of which the function is to collect the oil that accumulates against the seal and guide it to the enclosure. By the solution of the invention, the pressure generated by the vortex movement of the air is recovered to adjust the inlet pressure of the first seal. This pressure is adjusted to reduce and even virtually cancel the pressure difference with the inlet of the second seal downstream and thus balance the pressures across the bearing housing. This solution is advantageously robust because the equilibrium of the pressures is not dependent on the vortex force but only the pressure losses of the path between the two upstream and downstream chambers. It is thus possible to adjust the pressure losses of the guiding device and thus almost perfectly balance the pressures. The invention has been described in the case where it is necessary to adjust the pressure level immediately upstream of the upstream seal of the bearing housing of the low-pressure shaft of a double-body motor. However it is not limited to this application. It can be transposed to all cases where it is necessary to adjust the pressure at a seal of a bearing chamber and where there is a source of pressure nearby, in particular resulting from a recompression vortex .25
    权利要求:
    Claims (8)
    [0001]
    REVENDICATIONS1. A bearing housing of a turbomachine comprising a fixed wall (9), a rotating shaft (5) and a first and a second seals (10) between the wall and the shaft, characterized in that a means (30) is arranged along the surface of the wall (9) of the enclosure, external thereto, so that at least a portion of the air leaving the guide means passes through the first seal, this guide means being supplied with air by an air intake radially distant from the shaft, the air being at a higher pressure than at the shaft.
    [0002]
    2. Enclosure according to the preceding claim, the guide means comprises a plate (30) arranged radially along and away from the wall of the enclosure.
    [0003]
    3. Enclosure according to the preceding claim, the plate defines a clearance (J) with the shaft (5) such that a portion of the air guided between the plate and the wall of the enclosure is oriented through the first seal .
    [0004]
    4. Enclosure according to one of the preceding claims, the guide means comprises a device arranged to guide the air flow radially with a low tangential velocity component relative to the radial component.
    [0005]
    5. Enclosure according to the preceding claim wherein said device is formed of a spacer (32) in the form of a ring pierced with radial orifices, or provided with a honeycomb or with fins.
    [0006]
    6. Enclosure according to one of the preceding claims wherein the first seal (10) is a segmented radial seal.
    [0007]
    7. Enclosure according to one of the preceding claims comprising a second seal (20), including a labyrinth seal.
    [0008]
    8. Enclosure according to one of the preceding claims, the radially distant air intake corresponds to a vortex compression zone. A turbomachine comprising a bearing chamber according to one of the preceding claims with an annular chamber (Cam) upstream of the enclosure (E), supplied with air through an opening (19a) close to the shaft (5) and with an exhaust opening (19b) radially spaced from the shaft, said radially distant air intake being arranged near said exhaust opening. 10. Turbomachine according to the preceding claim comprising a downstream annular chamber (Cav) downstream of the enclosure (E) supplied with air from said exhaust opening (19b) of the upstream annular chamber (Cam), a part of the air passing through said enclosure (E).
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    同族专利:
    公开号 | 公开日
    EP3097272A1|2016-11-30|
    WO2015110744A1|2015-07-30|
    EP3097272B1|2019-03-06|
    JP2017506299A|2017-03-02|
    JP6535015B2|2019-06-26|
    FR3016661B1|2019-05-03|
    CN105899763B|2019-03-15|
    RU2016127794A|2018-03-01|
    RU2685749C2|2019-04-23|
    US20160341059A1|2016-11-24|
    CA2935314A1|2015-07-30|
    CN105899763A|2016-08-24|
    BR112016015612A2|2017-09-26|
    US10502081B2|2019-12-10|
    RU2016127794A3|2018-09-28|
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    法律状态:
    2015-01-16| PLFP| Fee payment|Year of fee payment: 2 |
    2016-01-12| PLFP| Fee payment|Year of fee payment: 3 |
    2016-05-06| RM| Correction of a material error|Effective date: 20160404 |
    2017-01-13| PLFP| Fee payment|Year of fee payment: 4 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 5 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-12-20| PLFP| Fee payment|Year of fee payment: 6 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 7 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 8 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1450570A|FR3016661B1|2014-01-23|2014-01-23|BEARING ENCLOSURE OF A TURBOMACHINE|
    FR1450570|2014-01-23|FR1450570A| FR3016661B1|2014-01-23|2014-01-23|BEARING ENCLOSURE OF A TURBOMACHINE|
    BR112016015612A| BR112016015612A2|2014-01-23|2015-01-15|bearing enclosure of a turbomachine|
    PCT/FR2015/050102| WO2015110744A1|2014-01-23|2015-01-15|Turbomachine bearing housing|
    US15/110,905| US10502081B2|2014-01-23|2015-01-15|Turbomachine bearing housing|
    CA2935314A| CA2935314A1|2014-01-23|2015-01-15|Turbomachine bearing housing|
    JP2016546102A| JP6535015B2|2014-01-23|2015-01-15|Turbo machine bearing housing|
    EP15704338.1A| EP3097272B1|2014-01-23|2015-01-15|Turbomachine bearing housing|
    RU2016127794A| RU2685749C2|2014-01-23|2015-01-15|Support chamber of gas turbine engine|
    CN201580004395.5A| CN105899763B|2014-01-23|2015-01-15|Turbine bearing shell|
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