• 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 device (2) for trapping particles, in particular grains of sand or dust, contained in the flow of air circulating inside a turbomachine, in particular the flow of air circulating in the zone. bypass (17) of the combustion chamber (13) of said turbomachine. This device is remarkable in that it comprises: at least one deflector (3, 3a, 3b, 3c) of particles, an element (5) for collecting and storing particles deflected by said deflector, means ( 6) for fixing said trapping device (2) on a part of the turbomachine, said deflector (3, 3a, 3b, 3c) being of annular shape and inclined with respect to its axis of revolution (X-X ') and being arranged to be turned towards said element (5) for collecting and storing the particles.
    公开号:FR3041036A1
    申请号:FR1558437
    申请日:2015-09-10
    公开日:2017-03-17
    发明作者:Amaury Paillard；Stephane Pascaud
    申请人:Turbomeca SA；
    IPC主号:
    专利说明:

    GENERAL TECHNICAL FIELD The invention is in the field of turbomachines equipping including aircraft or helicopters.
    It relates more specifically to a device for trapping particles, in particular grains of sand or dust, contained in the flow of air flowing inside said turbomachine. The invention also relates to a turbomachine equipped with such a trapping device.
    STATE OF THE ART
    As can be seen in the diagram of FIG. 1 attached, a turbomachine 1 generally comprises, from upstream to downstream, in the direction of flow of the gases, an air intake 11, one or more stages of compressor 12, (For example only one in said figure), an annular combustion chamber 13, one or more stages of turbines, for example a high-pressure turbine 14 and a low-pressure turbine 15, and finally a nozzle 16 for exhausting gases.
    In the rest of the description and the claims and in the figures, the terms "before" (reference AV) and "rear" (reference AR) are used with reference to the disposition of the turbomachine on the airplane or the helicopter . The air is sucked at the level of the air intake 11, is compressed in the compressor 12, then is directed into the bypass zone 17 of the combustion chamber 13.
    During the operation of the turbomachine, the walls 131 of the combustion chamber 13 are subjected to very high temperatures. The cooling of these walls is then generally ensured by the circulation of the air leaving the compressor 12, through a multi-piercing, that is to say very many holes of very small diameter, formed in the walls. 131 of said combustion chamber.
    Only a few of these holes, referenced 130, have been shown in FIG. 1. The air and the hot combustion gases leaving the combustion chamber 13 are then sent to the turbines 14, 15 and the exhaust nozzle. 16.
    However, it has been found that when the apparatus equipped with said turbomachine makes a flight in a dusty or sandy atmosphere, for example in a desert, clouds of particles P, such as grains of sand and dust, are ingested at of the air intake 11.
    These particles P then reach the bypass zone 17 and finally block the holes 130 formed in the walls 131 of the combustion chamber 13.
    However, if the holes 130 are obstructed, the air can no longer circulate in the combustion chamber 13, the cooling of its walls 131 is no longer ensured and the combustion chamber is rapidly degraded in contact with the flames. To date, no device makes it possible to retain the particles P ingested by the turbomachine, except for an air inlet grille, situated at the level of the air intakes 11, and which makes it possible to retain a part of the foreign bodies before their penetration into the turbomachine.
    However, P particles having a size smaller than the mesh of the grid are ingested.
    It is also not possible to install a filter with finer meshes, at the level of the air intake, because this would cause a loss of load too important and would cause a fall of the performances of the engine.
    PRESENTATION OF THE INVENTION The purpose of the invention is therefore to solve the aforementioned drawbacks of the state of the art and to provide a device for trapping particles, which makes it possible to retain them or at least a large part of them. before that do not obstruct the holes in the walls of the combustion chamber.
    Another object of the invention is to provide such a trapping device, which does not affect the operating performance of the turbomachine, and in particular that does not affect the flow of air within it.
    Finally, advantageously, such a trapping device must also allow the temporary storage of the trapped particles and their removal during maintenance operations of the turbomachine and to avoid an accumulation of these particles in the trapping device. For this purpose, the invention relates to a device for trapping particles, in particular grains of sand or dust, contained in the flow of air flowing inside a turbomachine, in particular the flow of air flowing in the zone bypass of the combustion chamber of said turbomachine.
    According to the invention, this device comprises: at least one particle deflector, an element for collecting and storing particles deflected by said deflector, means for fixing said trapping device on a portion of the turbomachine, said baffle being annular in shape and inclined with respect to its axis of revolution and being arranged to be turned towards said element for collecting and storing particles.
    Thanks to these characteristics of the invention, all the particles that abut against the deflector (s) are returned to the element for collecting and storing the particles and no longer block the holes in the wall of the chamber. of combustion.
    According to other advantageous and nonlimiting features of the invention, taken alone or in combination: the device comprises at least two particle deflectors, said deflectors being fixed on at least one support frame, so as to be coaxial and being spaced radially from each other or from each other, said deflectors being inclined in the same direction relative to their axis of revolution so as to be turned towards said element for collecting and storing the particles; the inside face of a deflector has an angle of inclination with respect to said axis of revolution greater than the angle of inclination with respect to this same axis of revolution of the inner face of a deflector arranged radially further to inside the device; the inside radius of an outermost baffle of a pair of adjacent baffles is less than or equal to the outer radius of a baffle further in; the device comprises three baffles; said deflector has a rectilinear cross-section; said deflector has a curved cross section whose concavity is turned towards the element for collecting and storing the particles; said supporting framework is a ring which extends in a plane perpendicular or substantially perpendicular to the axis of revolution of the deflectors, in that the deflectors of a pair of adjacent deflectors are respectively fixed along the outer circular edge and the inner circular edge of said annular support frame and in that this support frame is pierced with passage openings of the air flow; the collection and storage element comprises a solid ring coaxial with the axis of revolution of the deflector and which extends in a plane perpendicular or substantially perpendicular to this axis, this ring being extended towards said deflector by an annular rim; solid exterior and a solid inner annular flange, said collection and storage element being disposed opposite the deflector; said fixing means comprise a plane annular flange coaxial with the axis of revolution of the deflector and perpendicular to it and which extends towards the element for collecting and storing the particles, by a cylinder of longitudinal axis coaxial with said axis of revolution, in that said cylinder is pierced with a plurality of openings for passage of the air flow and in that said annular flange is pierced with a plurality of fastener passage holes.
    Finally, the invention also relates to a turbomachine equipped with the aforementioned particles trapping device.
    PRESENTATION OF THE FIGURES Other features and advantages of the invention will appear from the description which will now be made, with reference to the accompanying drawings, which represent, by way of indication but not limitation, a possible embodiment.
    In these drawings: FIG. 1 is a schematic view in longitudinal section of an exemplary embodiment of a turbomachine; FIG. 2 is a view of detail A of FIG. 1, on which the device has also been shown; According to the invention, FIGS. 3, 4 and 5 are partial and perspective views of one embodiment of the trapping device according to the invention, taken at three different angles of observation.
    DETAILED DESCRIPTION
    The particulate trapping device according to the invention is generally referred to as 2.
    As can be seen in FIG. 2, this device 2 is intended to be positioned in the zone 17 for bypassing the combustion chamber 13, more precisely outside the wall 131 of the combustion chamber 13 and at the outside. inside the outer casing 18 of the turbomachine.
    However, its precise position will be determined by calculation, as a function of the trajectory of the particles contained in the flow of air circulating inside this bypass zone 17. This calculation also takes into account the respective shapes of the wall 131 and the wall portion 180 of the outer casing 18, facing the rear end of the combustion chamber 13.
    The trapping device will thus be advantageously arranged where it will collect a maximum of particles, before it reaches the holes 130 of the wall of the combustion chamber.
    A particular embodiment of this trapping device 2 will now be described with reference to FIGS. 2 to 5.
    This trapping device 2 preferably comprises, from the front AV to the rear AR, at least one deflector 3, an element 5 for collecting and storing the particles and means for fixing 6 of said storage device on a part of the turbomachine. If there are at least two deflectors, then at least one of them is supported by a support frame 4.
    All these elements are made of a material that is heat resistant and preferably also abrasion resistant particles, for example metal or a composite material.
    These different elements will now be described in more detail.
    The device comprises at least one deflector 3, for example three as shown in the figures. One could also have more than three baffles.
    Each deflector has the shape of a ring, axis of revolution X, X '. When there are at least two deflectors 3, the latter are fixed on the support frame 4, so as to be coaxial axis X-X 'and spaced radially from each other.
    In the example described and shown in FIG. 3, these deflectors are referred to as "external" baffles 3a, "median" 3b and "internal" 3c, the outer baffle being that of larger diameter and thus located outermost. . Each deflector consists of an element having the shape of a full blade of small width closed on itself in the form of a ring.
    All the deflectors 3a, 3b, 3c are further fixed on the framework 4 so as to be inclined in the same direction with respect to their common axis of revolution X-X ', that is to say to be inclined by the outside and the front towards the axis of revolution X-X 'and the rear AR. In other words, they have a frustoconical shape. However, their inclination angles are preferably different. These deflectors are turned towards element 5.
    The inner face of the outer baffle 3a (that is to say the side facing the X-X 'axis) forms an angle α with the axis of revolution X-X', the inner face of the median baffle 3b, form with the axis X-X 'an angle 6 and finally the inner face of the inner deflector 3c forms an angle y with the axis X-X'. As can be seen in Figure 2, the angle is greater than the angle B which is itself greater than the angle y.
    Preferably, the angle a is between 65 ° and 75 °, more preferably equal to 70 °, the angle B is between 45 ° and 55 °, more preferably equal to 50 °, the angle y is between 25 ° and 35 °, more preferably equal to 30 °.
    Preferably, and as can be seen in FIG. 2, the deflectors 3a, 3b and 3c have a rectilinear cross-section. However, this could be curved, its concavity being directed towards the element for collecting and storing the particles.
    As best seen in Figures 2, 4 and 5, the frame 4 acts as a spacer between two adjacent deflectors. It has the shape of a ring which extends in a plane perpendicular or substantially perpendicular to the axis of revolution X-X '. The frame 4 is pierced with openings 40 allowing the passage of the air flow. These openings 40 are advantageously distributed at regular intervals and preferably constitute a large part of the surface of the frame 4. They also make it possible to lighten the framework.
    In the case where the trapping device 2 comprises more than one deflector, for example three as in the figures, it then comprises a frame 4 between each wall of contiguous baffles (see Figure (5). The deflectors of a pair of deflectors contiguous are respectively fixed along the outer circular edge and the inner circular edge of the annular framework 4.
    Advantageously, the baffles 3, 3a, 3b, 3c are fixed on the frames 4 by welding.
    Preferably, the baffles 3, 3a, 3b, 3c are fixed on the framework 4 so as to be aligned radially and are not shifted along the axis X-X ', so as not to occupy a place too much important between the wall 130 of the combustion chamber and the wall 180 of the housing and not to restrict the flow of air flowing there.
    As best shown in FIGS. 2 and 4, preferably, the element 5 for collecting and storing the particles comprises a solid ring 50, coaxial with the axis of revolution X-X 'of the deflectors 3a to 3c and which extends in a plane perpendicular or substantially perpendicular to this axis.
    This ring 50 extends forward AV by a solid outer annular flange 51 and a full inner annular flange 52.
    Preferably, the inner annular flange 52 is in the extension of the rear edge of the baffle 3c the innermost. More preferably, these two elements form a single piece.
    This element 5 thus has the general shape of a gutter facing the deflectors 3, 3a, 3b, 3c.
    Finally, as is best seen in Figures 2 to 4, preferably, the fastening means 6 comprise a flat annular flange 60, coaxial with the axis of revolution X-X 'deflectors and perpendicular to this axis X-X and which extends forwards by a cylinder 61 of longitudinal axis X-X '.
    The flange 60 is pierced with several orifices 62 which allow the passage of fasteners 7, such as for example screws. These screws make it possible to fix the flange on a part of the turbomachine.
    The cylinder 61 is pierced with a plurality of openings 63 allowing the passage of the circulating air flow inside the turbomachine. Similar to what has been described for the frames 4, these openings 63 represent a large part of the surface of the cylinder 61, so as not to slow down or restrict the flow of air. They also contribute to reducing the overall mass of the device.
    The cylinder 61 is bonded to the particle storage element 5. Preferably, the cylinder 61 is welded to the inner end of the ring 50 of the element 5.
    The operation of the device is as follows. The air coming from the compressor 12, loaded with particles P, penetrates inside the bypass zone 17, from the front AV to the rear AR between the radial outer wall 131 of the combustion chamber 13 and the casing. 18 (arrow F in Figure 2).
    This particle-laden flow of air strikes the wall 180, so that the particles ricochet against it and then strike the faces of the deflectors 3a, 3b and 3c oriented towards this wall 180. The stroke of the particles is slowed down, these slide inward (towards the axis XX), along the baffles until they are collected and collected in the element 5, from which they can not leave since the walls of the latter are full.
    The openings 40 however make it possible to limit the impact of the trapping device 2 on the circulation of the air flow and thus to limit the pressure losses. In other words, the particles are retained by the element 5 but the air flow can continue to circulate around the outer walls 131 of the combustion chamber 13, in order to penetrate the holes 130 and to ensure the function cooling of these walls.
    Finally, it will be noted that, advantageously, the inner radius R 1 of the outer baffle 3 a (i.e., its smallest radius) is less than or equal to the outer radius R2 of the adjacent median baffle 3 b (i.e. say its largest radius). It can be the same for each pair of contiguous baffles.
    Thus, if a particle were to ricochet against the wall 180 of the housing 18 and started forward in a direction parallel to the axis X-X ', it would still necessarily be trapped by the outer baffle 3a.
    Particle trajectory calculations must be carried out for each turbomachine, according to the shape of the walls delimiting the bypass zone 17 of the combustion chamber, so as to better position the particle trap 2, so that it retains almost all the particles ingested by the turbomachine, and entering the bypass of the combustion chamber.
    In addition, the values of the angles α, β and γ are also adjusted according to the shape of the wall 180 and may be different from those mentioned above.
    During maintenance operations of the turbomachine, the particles trapped in the element 5 can then be removed to prevent their accumulation.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. Device for trapping (2) particles, in particular grains of sand or dust, contained in the flow of air circulating inside a turbomachine, in particular the flow of air circulating in the bypass zone of the combustion chamber of said turbomachine, characterized in that it comprises: - at least one particle deflector (3, 3a, 3b, 3c), - an element (5) for collecting and storing the particles deflected by said deflector - means (6) for fixing said trapping device (2) on a part of the turbomachine, said deflector (3, 3a, 3b, 3c) being of annular shape and inclined with respect to its axis of revolution (X- X ') and being arranged to face said particle collecting and storage element (5).
    [2" id="c-fr-0002]
    2. Device according to claim 1, characterized in that it comprises at least two particle deflectors (3, 3a, 3b, 3c), said deflectors (3, 3a, 3b, 3c) being fixed on at least one frame of support (4), so as to be coaxial and spaced radially from each other or from each other, said deflectors (3, 3a, 3b, 3c) being inclined in the same direction with respect to their axis of revolution (XX) so as to be turned towards said element (5) for collecting and storing the particles.
    [3" id="c-fr-0003]
    3. Device according to claim 2, characterized in that the inner face of a deflector (3a, 3b) has an angle of inclination (a, 6) relative to said axis of revolution (XX) greater than the angle tilting (6, y) with respect to this same axis of revolution (XX) of the inner face of a deflector (3b, 3c) arranged radially further inside the device.
    [4" id="c-fr-0004]
    4. Device according to claim 2 or 3, characterized in that the inner radius (R1) of an outermost baffle of a pair of contiguous baffles is less than or equal to the outer radius (R2) of a deflector located further inland.
    [5" id="c-fr-0005]
    5. Device according to one of the preceding claims, characterized in that it comprises three baffles (3a, 3b, 3c).
    [6" id="c-fr-0006]
    6. Device according to one of the preceding claims, characterized in that said deflector (3, 3a, 3b, 3c) has a rectilinear cross section.
    [7" id="c-fr-0007]
    7. Device according to one of claims 1 to 5, characterized in that said deflector (3, 3a, 3b, 3c) has a curved cross section whose concavity is turned towards the element (5) for collection and storage particles.
    [8" id="c-fr-0008]
    8. Device according to one of claims 2 to 7, characterized in that said support frame (4) is a ring which extends in a plane perpendicular or substantially perpendicular to the axis of revolution (XX) of the baffles ( 3, 3a, 3b, 3c), in that the deflectors of a pair of contiguous baffles are respectively fixed along the outer circular edge and the inner circular edge of said annular supporting framework (4) and in that this framework (4) support is pierced with openings (40) for passage of the air flow.
    [9" id="c-fr-0009]
    9. Device according to one of the preceding claims, characterized in that the element (5) for collection and storage comprises a solid ring (50) coaxial with the axis of revolution (XX) of the deflector (3, 3a, 3b, 3c) and extending in a plane perpendicular or substantially perpendicular to said axis, said ring (50) being extended towards said deflector by a solid outer annular flange (51) and a solid inner annular flange (52) , said element (5) for collection and storage being arranged opposite the deflector.
    [10" id="c-fr-0010]
    10. Device according to one of the preceding claims, characterized in that said means (6) for fixing comprises a flat annular flange (60) coaxial with the axis of revolution (XX) of the deflector (3, 3a, 3b, 3c ) and perpendicular to it and which extends towards the element (5) for collecting and storing the particles, by a cylinder (61) of longitudinal axis coaxial with said axis of revolution (X-X '), in that said cylinder (61) is pierced with a plurality of openings (63) for the flow of air and in that said annular flange (60) is pierced with a plurality of holes (62) for the passage of fasteners (7). ).
    [11" id="c-fr-0011]
    11. Turbomachine (1) comprising a combustion chamber (13) and a bypass zone (17) formed between the wall (131) of said combustion chamber (13) and an outer casing (18) of said turbomachine, characterized in that it is equipped with the particle trapping device (2) according to any preceding claim and in that the device (2) is disposed within said bypass zone (17).
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    WO2017042493A1|2017-03-16|
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    RU2018112315A|2019-10-10|
    US20180266278A1|2018-09-20|
    FR3041036B1|2018-07-13|
    US10767512B2|2020-09-08|
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    法律状态:
    2016-09-14| PLFP| Fee payment|Year of fee payment: 2 |
    2017-03-17| PLSC| Search report ready|Effective date: 20170317 |
    2017-05-04| PLFP| Fee payment|Year of fee payment: 3 |
    2018-08-17| CD| Change of name or company name|Owner name: SAFRAN HELICOPTER ENGINES, FR Effective date: 20180717 |
    2018-08-22| PLFP| Fee payment|Year of fee payment: 4 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-08-19| PLFP| Fee payment|Year of fee payment: 6 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1558437|2015-09-10|
    FR1558437A|FR3041036B1|2015-09-10|2015-09-10|DEVICE FOR TRAPPING PARTICLES CIRCULATING IN A TURBOMACHINE AND TURBOMACHINE EQUIPPED WITH SUCH A DEVICE.|FR1558437A| FR3041036B1|2015-09-10|2015-09-10|DEVICE FOR TRAPPING PARTICLES CIRCULATING IN A TURBOMACHINE AND TURBOMACHINE EQUIPPED WITH SUCH A DEVICE.|
    CN201680052279.5A| CN108027143B|2015-09-10|2016-09-08|Particle trap device for a turbomachine and turbomachine having such a device|
    JP2018512997A| JP6877411B2|2015-09-10|2016-09-08|Particle collectors for turbo machines, and turbo machines with such devices|
    US15/758,337| US10767512B2|2015-09-10|2016-09-08|Particle-trapping device for a turbomachine and turbomachine with such a device|
    PCT/FR2016/052241| WO2017042493A1|2015-09-10|2016-09-08|Particle-trapping device for a turbomachine and turbomachine with such a device|
    CA2997812A| CA2997812A1|2015-09-10|2016-09-08|Particle-trapping device for a turbomachine and turbomachine with such a device|
    EP16774518.1A| EP3347648B1|2015-09-10|2016-09-08|Particle-trapping device for a turbomachine and turbomachine with such a device|
    KR1020187008819A| KR20180052650A|2015-09-10|2016-09-08|Particle-collecting apparatus for turbo machines and turbo machines equipped with such apparatus|
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