• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
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    • 专利摘要:
    The invention relates to a power transmission system of a turbomachine, comprising: - a speed reducer (12) comprising a sun gear (15) integral in rotation with a power shaft (5) of longitudinal axis, a crown external rotor (18) driving a rotor shaft in rotation along the longitudinal axis, and a planet carrier (17), and - an oil recovery device (40) ejected by centrifugal effect and comprising an annular gutter (41). intended to recover the ejected oil, the gutter being secured to a fixed casing (26) annular and having a recovery chamber (42) and a first wall portion (43) disposed at least partly facing ejection means (30) speed reducer oil to direct the oil to the recovery chamber. According to the invention, the recovery chamber is provided with an inlet opening (45) oriented radially outwards and defined in a plane radially smaller than a plane where an outlet orifice (33) is defined. 'ejection.
    公开号:FR3081513A1
    申请号:FR1854532
    申请日:2018-05-28
    公开日:2019-11-29
    发明作者:Joel Luc Chevillot Fabrice；Fabien Patrick Becoulet Julien；Nicolas Negri Arnaud；Pierre Dimitri Patsouris Emmanuel
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    POWER TRANSMISSION SYSTEM COMPRISING A LUBRICATING OIL RECOVERY DEVICE AND TURBOMACHINE EQUIPPED WITH SUCH A POWER TRANSMISSION SYSTEM
    1. Field of the invention
    The field of the present invention is that of aeronautical propulsion and more particularly that of turbomachinery comprising rotary members requiring significant lubrication.
    2. State of the art
    Certain turbomachinery such as turbofan engines or turboprop aircraft with twin contra-rotating propellers are equipped with a power transmission mechanism such as a differential speed reducer with planetary gear train or a speed reducer with gear train. planetary gear (designated by the acronym "RGB" for "Reduction Gear Box"). The planetary gear differential gearboxes, that is to say all the members are mobile, are applicable to propeller twin turboprop engines. Planetary reducers, that is to say that the planet carrier is fixed and the crown is mobile, are applicable to a turboprop with a propeller or to a turbofan engine equipped with a blower. We are more particularly interested in this latter case (double-flow turbojet with blower). In general, a power transmission shaft drives the fan shaft of the turbofan engine or the rotor shaft of the propellers via the speed reducer. The fan shafts or the propeller shafts are supported and guided by bearings which include rolling elements such as balls or rollers. Such speed reducers are equipped with several wheels and / or rotary gears whose lubrication is a key aspect for the proper functioning of the turbomachine and its efficiency. When the speed reducer is not sufficiently lubricated, friction between the teeth of the wheels and / or gear wheels or at the bearings results in their premature wear and thus a reduction in the efficiency of the speed reducer. These bearings, wheels and / or pinions of gearboxes of speed reducers can generate a very high thermal power to guarantee a good performance implying the need of a lubrication system designed to send a significant oil flow which can reach several thousands of liters per hour, for example more than 5000 liters per hour to lubricate the speed reducer and the bearings. One of the drawbacks of such a lubrication system is the difficulty of being able to recover and evacuate such a flow of oil.
    The lubrication system comprises one or more casings forming an enclosure in which the speed reducer and the bearings are contained. The oil is generally evacuated to the lower part of the enclosure (six hours). The enclosure also includes means of discharge such as lines which return the oil to the lubrication system. In the case of a speed reducer with a planetary gear train, that is to say that the sun gear and the planet carrier are rotary while the outer ring is fixed, means of evacuation are provided, complexly, in the lower part of the outer ring so as to drain the oil from the internal parts of the speed reducer to the lower part of the enclosure. Conversely, in the case of a planetary speed reducer with the rotating outer ring, the evacuation is more complex. Indeed, during the rotation of the outer ring, the oil is sprayed by centrifugal effect on the entire wall of the enclosure whose volume is quite large. The oil progresses by gravity towards the lower part of the enclosure for its evacuation. However, recovery is not rapid and efficient given the high flow rate of oil circulating in the enclosure and in the lubrication system.
    Patent n ° FR3052322 describes an example of reducing differential speed with planetary gear train and an oil recovery device preventing oil from accumulating in the enclosure by forming accumulation zones and evacuating the oil quickly. The recovery device comprises an annular gutter formed around the outer ring of the speed reducer. The gutter includes a recovery chamber and a first portion of wall disposed at least partially opposite oil ejection means so as to guide the oil sprayed thereon towards the oil recovery chamber. The first wall portion is a fin which forms an orifice oriented towards the ejection means. This fin is surrounded by other portions of annular walls forming a bowl and the chamber has a side entry opening through which the oil passes. One of the drawbacks of this gutter is its radial size which influences the mass of the turbomachine. Furthermore, this gutter is complex due to its numerous walls, fins and bowls formed to avoid oil retention and the guiding of the oil towards the recovery chamber, which influences the manufacturing cost and the feasibility of the device. recovery and turbomachine.
    3. Object of the invention
    The object of the present invention is in particular to provide an improved recovery device making it possible to quickly recover, contain and evacuate a large flow of oil to a lubrication circuit while being simple in design and reducing the radial size of the gutter.
    4. Statement of the invention
    This objective is achieved in accordance with the invention thanks to a power transmission system between a rotor shaft of longitudinal axis X of a turbomachine and a power shaft of longitudinal axis X, the transmission system comprising:
    a speed reducer capable of reducing the speed of the rotor shaft, said speed reducer comprising a sun gear integral in rotation with the power shaft, an outer ring driving in rotation the rotor shaft along the longitudinal axis X , and a satellite carrier, a device for recovering oil ejected by centrifugal effect in the turbomachine, the recovery device comprising an annular gutter intended to recover the oil ejected from the speed reducer, the gutter being secured to a surrounding annular fixed casing said gutter and comprising a recovery chamber and a first portion of wall disposed at least partially opposite means for ejecting oil from the speed reducer so as to direct the oil sprayed onto it towards the recovery chamber oil, the recovery chamber being provided with an inlet opening oriented radially ve rs outside and defined in a plane radially lower than a plane in which is defined an outlet orifice of the ejection means.
    Thus, this solution achieves the above-mentioned objective. In particular, the position of the recovery chamber makes it possible not to impact the radial space requirement in an already congested enclosure of the speed reducer and the bearings since the chamber does not extend beyond this outlet port of the speed reducer. speed. In addition, the configuration of the gutter is easy to manufacture and implement while allowing relative movements between the outer ring of the speed reducer and the gutter. The recovery chamber is therefore as close as possible to the periphery of the outer ring of the speed reducer to reduce the radial size.
    According to a characteristic of the invention, the speed reducer is a differential reducer or a planetary reducer.
    According to another characteristic of the invention, the planet carrier is fixed relative to the planet.
    According to another characteristic of the invention, the outer ring comprises an annular tab with an annular periphery and extending along a radial axis Z perpendicular to the longitudinal axis X, the orthogonal projection of the annular periphery being arranged radially to the outside of the recovery chamber.
    According to another characteristic of the invention, the gutter comprises a second wall portion connected at one of its ends to the first wall portion and at another of its ends to the recovery chamber, the inlet opening being arranged opposite part of the second wall portion.
    According to another characteristic of the invention, the recovery chamber is arranged upstream of the annular tab of the outer ring, the first wall portion being connected to a third wall portion extending downstream of the annular tab.
    According to another characteristic of the invention, the recovery chamber has an axial section substantially in the shape of a U so as to store a large quantity of oil and to prevent the oil from spilling into the enclosure of the turbomachine and in particular on the speed reducer which is installed in this enclosure with the gutter.
    According to a characteristic of the invention, the gutter comprises an annular retention wall secured to one of the side walls forming a branch of the U of the recovery chamber and bordering at least part of the inlet opening. Such a retention wall makes it possible to improve the retention of the recovery chamber and makes it possible to prevent the oil from overflowing from it.
    According to a characteristic of the invention, the first portion of wall is conical or frustoconical so as to favor the guiding of the oil towards the recovery chamber and prevent the oil from being directed towards the reducer.
    Advantageously, the first wall portion is arranged axially opposite the recovery chamber so as to promote the progression of the oil towards the recovery chamber.
    According to another characteristic, the gutter is provided with a radial axis outlet opening located in a lower part of the turbomachine along the radial axis and oriented towards the outside of the turbomachine so as to allow evacuation oil from the gutter to the bottom of the enclosure.
    Advantageously, but not limited to, the gutter is made from a sheet. This allows for a light and economical gutter.
    According to another characteristic, the recovery chamber is provided with an inlet opening oriented radially opposite the wall of the gutter.
    According to one embodiment of the invention, the gutter comprises two axially opposite recovery chambers and arranged on either side of the oil ejection means.
    According to another embodiment of the invention, the oil ejection means has an angular orientation relative to the radial axis, the orientation comprising an axial component along the longitudinal axis X towards the gutter. Such a configuration can prevent splashing on the wall of the gutter when ejecting the oil by centrifugation.
    According to a characteristic of the invention, the outer ring is fixed to the fan shaft by means of a flange which at least partly comprises the oil ejection means by which the oil is ejected by centrifugal effect .
    According to another characteristic, the flange is formed of an annular bearing secured to the fan shaft and extending radially outwards, and of an annular tab of the external crown which extends radially outwards , the annular tab and the annular bearing bearing against one another, the ejection means comprising channels formed between the annular bearing and the annular tab.
    According to a characteristic of the invention, the outer crown is in one piece.
    According to another embodiment of the invention, the outer crown is formed in two parts with a first crown part and a second crown part, and the flange is formed in three parts with a first part of annular leg extending radially outward and integral with the first part of the crown, a second annular leg portion extending radially outward and integral with the second portion of the crown, and an annular bearing extending radially outward and integral with the fan shaft, the oil ejection means comprising channels formed at least between the bearing surface, the first and second parts of the annular tab.
    The invention also relates to a turbomachine comprising, a rotor shaft of longitudinal axis X, a power shaft and a power transmission system having any of the aforementioned characteristics, between the rotor shaft and the power, the oil recovery device being arranged to recover and contain the oil ejected by the centrifugal effect of the speed reducer.
    5. Brief description of the figures
    The invention will be better understood, and other objects, details, characteristics and advantages thereof will appear more clearly on reading the detailed explanatory description which follows, of embodiments of the invention given by way of purely illustrative and nonlimiting examples, with reference to the appended schematic drawings in which:
    FIG. 1 represents an axial and partial section of a turbomachine comprising a fan module, the fan shaft of which is driven by a power shaft via a speed reducer installed in a lubrication enclosure;
    Figure 2 is a schematic, axial and partial view of a gutter of a lubricant recovery device ejected from an outer ring of a planetary speed reducer with gear train according to the invention;
    FIG. 3 represents the lower part of the gutter of the recovery device illustrated in FIG. 2;
    FIG. 4 represents a variant of FIG. 2 with a gutter, a portion of the wall of which is bent;
    FIG. 5 schematically illustrates another variant of the gutter according to the previous figure in which a retention wall prevents the lubricant from overflowing from a gutter recovery chamber;
    FIG. 6 represents the lower part of a gutter according to another variant of FIG. 2, one wall of which widens towards a recovery chamber;
    Figure 7 shows another alternative embodiment in which a recovery chamber is arranged upstream of the gutter and a radially outer flange of the outer ring of the speed reducer;
    FIG. 8 illustrates another embodiment of the invention with a gutter of a lubricant recovery device comprising two recovery chambers;
    FIG. 9 illustrates another embodiment of the invention in which lubricant ejection means are oriented in a direction inclined by a ratio to a radial axis; and,
    FIG. 10 is a view in axial and partial section of a part of a speed reducer comprising ejection means with several channels for ejecting the oil at the periphery of a flange of the speed reducer.
    6. Description of embodiments of the invention
    FIG. 1 shows a view in axial and partial section of a turbomachine of longitudinal axis X, in particular a double-flow turbomachine to which the invention applies. Of course, the invention is not limited to this turbomachine. It can apply, for example, to a turbomachine comprising a doublet of counter-rotating propellers rotating around a longitudinal axis and designated by the expression "open rotor" in English for non-faired propellers.
    The turbomachine 1 double flow generally comprises an external nacelle (not shown) enveloping a gas generator 2 upstream of which is mounted a fan 3. In the present invention, and generally, the terms “upstream” and “downstream >> are defined with respect to the circulation of gases in the turbomachine which is substantially parallel to the longitudinal axis X. Similarly, the terms "radial", "internal >>," external >>, "lower >>," upper >>, "below" and "above" are defined with respect to a radial axis Z perpendicular to the longitudinal axis X and with regard to the distance from the longitudinal axis X. The gas generator 2 comprises for example, from upstream to downstream, a low pressure compressor 4, a high pressure compressor, a combustion chamber, a high pressure turbine and a low pressure turbine. The high pressure compressor is connected to the high pressure turbine via a high pressure shaft to form a high pressure body. Likewise, the low pressure compressor 4 is connected to the low pressure turbine via a low pressure shaft 5 to form a low pressure body. The low pressure shaft 5 and the high pressure shaft are centered on the longitudinal axis X.
    The fan 3 is here faired by a fan casing (not shown) secured to the external nacelle. The blower 3 compresses the air entering the turbomachine which is divided into a primary flow circulating in an annular primary stream 6 which passes through the gas generator 2 and a secondary stream circulating in an annular secondary stream 7 around the gas generator 2. In particular, the primary vein 6 and the secondary vein 7 are separated by an annular inter-vein casing 8 surrounding the gas generator 2. The blower 3 comprises a series of blades 11 which each extend radially outwards and are delimited radially by the fan casing.
    The blower module is arranged upstream of an internal casing 9 of the turbomachine which is crossed by a rotor shaft 10, here the blower shaft which is centered on the longitudinal axis X. The blower shaft 10 is driven in rotation by a power shaft of the turbomachine via a power transmission mechanism, of a power transmission system, making it possible to reduce the speed of rotation of the fan 3. This power shaft is the low pressure shaft 5 in this example. The power transmission mechanism allows the arrangement of a blower with a large diameter which generates an increase in the dilution rate.
    The power transmission mechanism includes a speed reducer 12 formed by a gear train and known by the acronym RGB for "Reduction Gear Box". The speed reducer is here planetary.
    This includes, as shown schematically in FIG. 1, an internal sun gear here called planetary 15, satellites 16, a satellite carrier 17 and an external sun gear here called external ring 18. In the present example, the entry of the speed reducer 12 is coupled to the low pressure shaft 5 while the output of the speed reducer 12 is coupled to the blower shaft 10.
    The speed reducer 12 comprises an input shaft 19, centered on the longitudinal axis X, integral in rotation with the low pressure shaft 5 and with the sun gear 15 along the longitudinal axis X. The outer ring 18, also centered on the longitudinal axis X, is integral in rotation with the fan shaft 10 around the longitudinal axis X. The satellites 16, for example five in number, are carried by the planet carrier 17 which is mounted fixed. The satellites 16 each rotate around an axis substantially parallel to the longitudinal axis X. Each of the satellites 16, in the form of a pinion, has teeth which mesh with those of the sun gear 15, in the form of a toothed wheel, and with the outer ring 18 provided with internal teeth. In operation, the sun gear 15 is rotated by the low pressure shaft 5 at a first speed of rotation. The satellites 16 are rotated by the sun gear 15 about their axis at a second speed of rotation. The outer ring 18 which meshes with the satellites 16 is rotated about the longitudinal axis X and drives the fan shaft 10. The outer ring 18 rotates at a third speed of rotation and in a direction opposite to that of the planet 15.
    Alternatively, the speed reducer may be a differential speed reducer with planetary gear train. In this case, the planet, the satellites, the planet carrier and the outer ring are all mobile.
    With reference to FIG. 1, first and second bearings 20 and 21 allow the fan shaft 10 to be carried and guided in rotation in order to support the radial and axial loads which it undergoes. These first and second bearings 20, 21 comprise rolling elements which are each mounted between a first and a second ring. Each first ring is mounted on the fan shaft 10 and each second ring is mounted on a ferrule 22. The rolling elements of the first bearing 20, mounted in the vicinity of the speed reducer 12, are here balls while the rolling elements of the second bearing 21 are rollers. The first and second bearings are mounted upstream of the speed reducer 12. More precisely still, the second bearing 21 is mounted upstream of the first bearing 20. Likewise, a third bearing 23 is also provided for carrying and guiding in rotation the low pressure shaft 5. This third bearing 23 is located downstream of the speed reducer 12. The third bearing 23 also includes an internal ring carried by the low pressure shaft 5 and an external ring carried by a downstream support 24.
    The first, second, and third bearings 20, 21, 23, as well as the gear wheels and pinions of the speed reducer 12 are contained in an annular lubrication enclosure 25 formed by one or more fixed casing (s) 26 of the turbomachine. The ferrule 22 and the downstream support 24 are fixed to the fixed annular casing 26. This fixed casing 26 is itself secured to the internal casing 9 of the turbomachine. The enclosure 25 extends axially and radially on either side of the speed reducer 12. As illustrated in FIG. 1, this enclosure 25 is traversed at least partially axially by the fan shaft 10 and by the low pressure shaft 5.
    In the enclosure 25 circulates a lubricant such as oil making it possible to permanently lubricate and cool the bearings and the rotary members of the speed reducer during the operation of the turbomachine to guarantee the proper functioning of the bearings and the speed reducer . For this, a lubrication system (not shown) comprises pipes which spray oil through the sun gear 15. The oil is injected into the rotary members at the level of the satellites 16 and of the sun gear 15 and then of the outer ring 18 The oil is then ejected outside the outer ring 18 by centrifugation using ejection means 30 shown in more detail in FIG. 2 and the following. The oil is also injected at the first, second and third stages 20, 21,23.
    In Figure 2 is illustrated an example of attachment between the fan shaft 10 and the outer ring 18 of the speed reducer 12 in the upper part of the latter (high point, at noon). In this exemplary embodiment, the crown 18 is in one piece (that is to say in one piece). In particular, the outer ring 18 includes an annular tab 27 extending radially outward. This annular tab 27 is fixed to an annular bearing 28 of the fan shaft 10 via fixing means 29 such as screws. The annular surface 28 extends along the radial axis Z at a free end of the fan shaft 10. This surface 28 is defined in a plane parallel or substantially parallel to that in which the annular tab 27 is defined. The tab annular 27 and the bearing 28 form a flange 35. The oil is ejected from the outer ring 18 at the level of this flange 35 via oil ejection means 30. The ejection means 30 here comprise one or more channels 31 which are regularly distributed at least on the circumference of the outer ring 18.
    Advantageously, but not limited to, first channels 31a extend substantially along the radial axis Z. Each first channel 31a extends radially between an inlet orifice 32a and an outlet orifice 33. The orifice of entry 32a is defined in an internal surface 34 of the external ring 18 on which the internal teeth are defined (not shown). As for the outlet orifice 33, this opens onto the periphery of the flange 35 (annular periphery 36 of the annular tab 27 and that of the bearing surface 28 which are flush). Preferably, but not limited to, there are several outlet orifices 33 distributed circumferentially on the periphery of the flange 35. There are at least three outlet orifices 33 provided on the periphery of the flange 35. The oil circulates from the inside the outer ring 18 towards the outside of the latter via the channel or channels 31.
    The oil which circulates at the circumference of the outer ring 18 is also evacuated between the fan shaft 10 and the outer ring 18, and in particular the flange 35, via the channel (s) 31. From advantageously, but not limited to, second channels 31b extend substantially along the longitudinal axis X. Each second channel 31b extends axially from an inlet orifice 32b and a first channel 31a. In other words, the second channels 31b lead into the first channels 31a.
    The lubricating oil is expelled through the channels 31 with a radial speed corresponding to the centrifugation exerted by the passage in the outer ring 18 and a tangential speed corresponding to the rotation drive at the third speed in the direction of rotation of the outer crown 18.
    The power transmission system is completed by an oil recovery device 40 which is designed to quickly recover and evacuate the oil ejected by centrifugal effect in the turbomachine and in particular in the enclosure 25. This recovery device 40 comprises an annular gutter 41 intended to recover the oil ejected from the speed reducer 12. The gutter 41, centered on the longitudinal axis X, is arranged around the outer ring 18. The gutter 41 is fixed on the fixed casing 26. The gutter 41 includes a recovery chamber 42 in which a large quantity of oil passes before it is discharged to the lower part of the enclosure 25. The size of the recovery chamber makes it possible to temporarily accumulate or store the oil so to limit overflows. The gutter 41 also comprises a first portion of wall 43 disposed at least in part opposite the oil ejection means 30, here the channels 31, 31a, 31b and configured so as to direct the oil sprayed on it -to recovery chamber 42.
    As illustrated in FIG. 2, the recovery chamber 42 is arranged downstream of the gutter 41, and here downstream of the flange 35. The recovery chamber 42 is open. The chamber is oriented substantially radially outwards. In particular, the recovery chamber 42 has a substantially U-shaped axial section with a bottom 44, an inlet opening 45 radially opposite the bottom 44, a first and a second side wall 46a, 46b (relative to the longitudinal axis X). The side walls 46a, 46b each form a branch of the U. The inlet opening 45 is oriented radially outwards. The first wall portion 43 is located opposite the flange 35. The latter is connected to a second wall portion 47 which is connected to one of the side walls 46a, 46b of the recovery chamber 42 (here the first side wall 46a). The second wall portion 47 extends substantially along the longitudinal axis X with a part opposite the ejection means and the outer ring 18. As we can also see in Figure 2, the inlet opening 45 is arranged opposite the wall of the gutter 41 (and in particular of part of the second wall portion 47). The bottom 44 of the recovery chamber 42 is oriented towards the outer ring 18. The connection between the second wall portion 47 and the first side wall 46a here has substantially a right angle.
    The first portion of wall 43 has a conical or frustoconical axial section so as to deflect the oil towards the recovery chamber 42, in the present example downstream of the gutter 41. In other words, the first portion of conical or frustoconical wall 43 is arranged axially opposite the recovery chamber 42.
    The oil sprayed on the first wall portion 43 progresses along the second wall portion 47 towards the inlet opening 45 of the recovery chamber 42. A free end 48 of the first wall portion 43 is oriented towards inside the turbomachine (towards the speed reducer 12). The free end 48 is located upstream of the flange 35 and in particular upstream of the annular surface 28 of the fan shaft 10. The oil cannot therefore be projected beyond the free end 48, towards enclosure 25.
    Furthermore, the gutter 41 includes a third wall portion 49 which is fixed to the fixed casing 26 by fixing members 50 such as bolts or screws. The third wall portion 49 is coupled to one of the side walls 46a, 46b of the recovery chamber. In the example shown, the third wall portion 49 is secured to the second side wall 46b adjacent to the annular tab 27 of the outer ring 18. We also see that the third wall portion 49 has a first radial part 49a which is fixed to the second side wall 46b and a second part 49b which extends radially below the bottom 44 of the recovery chamber 42. At its downstream end an annular flange 49c of radial axis Z is fixed on the fixed casing 26 .
    In order to reduce the radial size of the gutter, the inlet opening 45 is defined in the same plane or in a substantially radially lower plane in which the outlet orifice 33 of the ejection means is defined, here the channels 31 and the outlet orifices 33. The recovery chamber 42 does not extend beyond the outlet orifice 33 of the channels. In other words, the radius RC of the recovery chamber 42 is equal to or less than the external radial height (radius RP) of the annular tab 27 or of the flange 35. The radius RP is defined as the distance between l longitudinal axis X and the annular periphery 36 of the annular tab 27 or of the flange 35 while the radius RC of the recovery chamber 42 is considered to be the distance between the longitudinal axis X and the inlet opening 45 The recovery chamber 42 has a height along the radial axis substantially equal to or less than that of the annular tab 27. We can also say, in the context of FIG. 2, that the orthogonal projection of the annular periphery 36 (of the annular tab 27) on the side wall 46a of the recovery chamber 42 forms a line at point 36P which is arranged radially outside the recovery chamber. Likewise, the flange 35 is located radially inside the gutter 41.
    In FIG. 3, the gutter 41 is also provided with an outlet opening 37 with a radial axis oriented towards the inside of the turbomachine. Of course, the recovery chamber may include several outlet openings 37. Each outlet opening 37 is formed in the second wall portion 47 of the gutter. As illustrated in FIGS. 3 and 6, the outlet opening 37 is located at least partially opposite the recovery chamber 42. The oil is removed from the lower part of the gutter 41 and towards the lower part of the enclosure 45, at six o'clock, to return to the lubrication circuit of the lubrication system.
    The gutter 41 is made of a metallic material. Advantageously, but not limited to, the gutter 41 is made from a sheet to lighten the weight thereof. The walls 43, 44, 47, 46a, 46b, 49 are obtained by folding or by welding. Folding and welding are easy and quick to implement and require very little equipment to make the gutter.
    FIG. 4 illustrates a variant of the embodiment described above. The gutter 41 of this variant is substantially identical to that described in Figures 2 and 3 except the configuration of the second wall portion 47 of the gutter. Indeed, in this example, the second wall portion 47 has a conical or frustoconical axial section. Its upstream end, integral with the first wall portion 43, is oriented towards the inside of the turbomachine. In other words, the second portion of wall 47 widens downstream. The second wall portion 47 comprises a bent portion 52 which is connected to the first side wall 46a of the recovery chamber 42 so as to optimize the circulation of the oil towards the recovery chamber 42.
    In operation, the oil passes through the speed reducer and is ejected by centrifugal effect from the outer ring 18 by penetrating through the orifice or the orifice orifices 32a according to the arrow F1. The oil which surrounds the speed reducer also progresses on the periphery of the outer ring 18 by centrifugal effect to enter the inlet orifice 32b according to arrow F10. The oil then progresses through the channels 31 which are formed between the walls of the blower shaft 10 and the outer ring 18 according to the arrows F2 and F11 until the latter is projected onto the first portion of the wall. 43 of the gutter 41. The oil then progresses along the second portion of wall 47 along arrow F3 towards the inlet opening 45 of the recovery chamber 42. This finally enters the recovery chamber 42 along arrow F4.
    In FIG. 5 is also illustrated another alternative embodiment of the gutter 41 according to the invention. In this variant, the second wall portion 47 has a conical or frustoconical axial section and the bent part 52 downstream of the gutter 41 as has been described for the figure
    4. In this example, the gutter 41 comprises an annular retention wall 51 which is secured to the second side wall 46b of the recovery chamber 42 to improve the retention of the latter. The retention wall 51 borders the inlet opening 45 of the recovery chamber 42. Furthermore, the retention wall 51 has an inclination relative to the radial axis Z. This is in particular oriented towards the upstream of the gutter, or towards the first wall portion 43 of the gutter 41. This retention wall is formed by folding or attached and then welded to the second side wall 46b. The oil is sprayed from the channels 31 towards the gutter 41 and then into the recovery chamber 42 thereof along the same path described in relation to FIG. 4.
    FIG. 7 illustrates another embodiment in which the recovery chamber 42 is arranged upstream of the gutter 41. More specifically, the recovery chamber 42 is located upstream of the annular bearing surface 28 of the blower shaft 10 and upstream of the oil ejection means 30 here comprising the channels 31. The first wall portion 43, axially opposite to the recovery chamber 42, is disposed opposite the oil ejection means 30 and surrounds them this. In this example, the third wall portion 49, secured to the fixed casing 26, is connected to the first wall portion 43 conical or frustoconical. This third portion of wall 49 extends downstream of the annular tab 27 of the outer ring 18. In this embodiment, the oil passes through the speed reducer and is ejected by centrifugal effect from the outer ring 18 by penetrating through the inlet orifice (s) 32a according to arrow F1. The oil which surrounds the speed reducer also progresses on the periphery of the outer ring 18 by centrifugal effect to enter the inlet orifice 32b according to arrow F10. The oil then progresses through the channels 31 which are formed between the walls of the fan shaft and of the outer ring 18 according to the arrows F2 and F11 until the latter is projected onto the first portion of the wall 43 of the gutter 41. The oil then progresses along the second portion of wall 47 along arrow F3 'towards the inlet opening 45 of the recovery chamber 42. This finally enters the recovery chamber 42 along arrow F4.
    Another embodiment is also illustrated in FIG. 8. In this example, the gutter 41 comprises two recovery chambers 42a, 42b which are axially opposite and arranged on either side of the means 30 for ejecting oil. These recovery chambers 42a, 42b each have dimensions smaller than those of the previous embodiments, which also makes it possible to reduce the radial size. In this case, the gutter 41 comprises two first portions 43a, 43b of conical or frustoconical wall facing the oil ejection means 30. These form a V whose apex is oriented towards the ejection means 30. Each of the first wall portions 43a, 43b guides the oil to a recovery chamber 42a, 42b. Advantageously, but not limited to, each first portion of wall 43a, 43b widens respectively towards the corresponding recovery chamber 42a, 42b in which the oil is deflected. Each first wall portion 43a, 43b is connected to a side wall of the recovery chamber by means of a second wall portion 47a, 47b. In this example, the second wall portions 47a, 47b extend along the longitudinal axis, but these can of course flare towards a recovery chamber (conical or frustoconical section) as shown in FIGS. 4 and 5. The side wall 46a can connect the second wall portion 47b with a bent portion 52 or at a right angle. When the oil is sprayed onto the first wall portion 43a (downstream of the flange 35 in FIG. 8), the oil is directed towards the recovery chamber 42a (downstream of the flange 35) progressing along the second wall 47a. The oil sprayed on the first wall portion 43b is directed to the recovery chamber 42b (upstream of the flange 35) in the same way.
    In FIG. 9 is illustrated a variant of the gutters described in relation to FIGS. 2 to 8. In this exemplary embodiment, the ejection means 30 have at least one part with an angular orientation relative to the radial axis Z. In particular, each ejection channel 31a of the ejection means 30 has a portion which is inclined at an angle of approximately 45 ° with the radial axis Z and is oriented towards the second wall portion 47. Advantageously, each channel 31a is oriented (towards the outer radial end of the latter) in the direction of the recovery chamber 42 depending on whether the latter is upstream or downstream of the ejection means 30 or the flange 35 to prevent oil splashing in the gutter and in the enclosure 25. In this example, the oil is sprayed directly onto the second wall 47 (arrow F3) then progresses along it until it reaches the recovery chamber (arrow F 4). The first wall portion 43 also makes it possible in this case to orient any oil splashes towards the recovery chamber 42.
    According to another embodiment illustrated in Figure 10, the outer ring 18 'is formed in two parts. It is therefore no longer in one piece as illustrated in FIGS. 2 to 9. The annular tab carried by the outer ring 18 ’is also made in two parts. In other words, the flange 35 ’is made up of three parts (bearing and annular tab in two parts). Such a configuration makes it possible to manufacture the crown even more easily and to facilitate the recovery of the oil. Indeed, the external crown 18 ′ comprises a first part 18a of the crown which is provided with a first part of annular tab 27a. The latter extends radially outwards. The crown comprises a second part 18b of the crown which is provided with a second part of annular tab 27b. The second annular leg portion 27b extends radially outward. The first crown part comprises an annular projection 53 which extends along the longitudinal axis from the internal radial end of the first annular tab part 27a. The projection 53 is arranged radially below the second part of the annular tab 27b and of a portion of the second part of the crown 18b. In other words, the second annular leg portion 27b rests on the projection 53. The first portion 18a of the crown is arranged axially between the fan shaft 10 and the second portion 18b of the crown. Likewise, the first annular leg portion 27a is arranged axially between the annular bearing 28 ′ of the fan shaft 10 and the second annular leg part 27b. First channels 310a are formed between the radial face of the bearing surface 28 and a first radial wall 38a of the first part of annular tab 27a. Each first channel 310a is connected to a second channel 310b formed on the circumference of the first ring portion 18a.
    First channels 310a ’are also formed between a second radial wall 38b of the first annular tab portion 27a and the radial surface of the second annular tab portion 27b. The first and second radial walls 38a, 38b are axially opposite one another. Each first channel 310a 'is connected to a second channel 310b' formed on the circumference of the first ring portion 18b (in particular on the circumference of the projection 53). In this way, the oil passes through the speed reducer 12 and is ejected by centrifugal effect from the external ring 18 ’by penetrating through the orifice or the inlet orifices 32a’ according to arrow F1. The oil which surrounds the speed reducer also progresses on the periphery of the outer ring 18 ’by centrifugal effect to enter the inlet 32b’ according to arrow F10. The oil then progresses in the second channels 310b, 310b ', then in the first channels 310a, 310a' which are formed between the walls of the blower shaft 10 and the first and second annular leg portions 27a, 27b of the outer ring 18 'according to the arrows F11, F1 T, F2, F2' until the latter is projected onto the gutter 41 then into a recovery chamber 42 or into two recovery chambers 42a, 42b.
    Thus, with a gutter of this kind, the radial dimensions and possibly the axial dimensions in the turbomachine are reduced, in particular with an outer ring 18, 18 ′ rotating relative to a fixed casing, so as not to impact the mass of it. The recovery room
    42a, 42b allows total recovery of the oil centrifuged through the outer ring 18, 18 ’of the speed reducer 12.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    1. Power transmission system of a turbomachine between a rotor shaft (10) of longitudinal axis X and a power shaft (5) of longitudinal axis X, the transmission system comprising:
    a speed reducer (12) capable of reducing the speed of the rotor shaft (10), said speed reducer (12) comprising a sun gear (15) integral in rotation with the power shaft (5), a outer ring (18; 18 ') rotating the rotor shaft (10) along the longitudinal axis X, and a planet carrier (17), and
    - a recovery device (40) of oil ejected by centrifugal effect in the turbomachine (1), the recovery device (40) comprising an annular gutter (41) intended to recover the oil ejected from the speed reducer (12) , the gutter (41) being secured to a fixed annular casing (26) surrounding said gutter (41) and comprising a recovery chamber (42; 42a, 42b) and a first wall portion (43; 43a, 43b) disposed at the at least partially opposite means for ejecting (30) oil from the speed reducer (12) so as to direct the oil projected onto it towards the recovery chamber (42; 42a, 42b), characterized in that the recovery chamber (42; 42a, 42b) is provided with an inlet opening (45) oriented radially outward and defined in a plane radially less than a plane in which an outlet orifice is defined ( 33) that includes the ejection means (30).
    [2" id="c-fr-0002]
    2. Power transmission system according to the preceding claim, characterized in that the outer ring (18) comprises an annular tab (27; 27a, 27b) with an annular periphery (36) and extending along a perpendicular radial axis Z to the longitudinal axis X, the orthogonal projection of the annular periphery (36) being arranged radially outside the recovery chamber (42; 42a, 42b).
    [3" id="c-fr-0003]
    3. Power transmission system according to the preceding claim, characterized in that the recovery chamber (42) is arranged upstream of the annular tab (27) of the outer ring (18, 18 '), the first portion of the wall (43) being connected to a third wall portion (49) extending downstream of the annular tab (27).
    [4" id="c-fr-0004]
    4. Power transmission system according to any one of the preceding claims, characterized in that the recovery chamber (42; 42a, 42b) has an axial section substantially U-shaped.
    [5" id="c-fr-0005]
    5. Power transmission system according to the preceding claim, characterized in that the recovery chamber (42; 42a, 42b) comprises an annular retention wall (51) secured to one of the side walls (46a, 46b) forming a branch of the U of the recovery chamber (42; 42a, 42b) and bordering at least part of the inlet opening (45).
    [6" id="c-fr-0006]
    6. Power transmission system according to any one of the preceding claims, characterized in that the first wall portion (43; 42a, 43b) has a conical or frustoconical axial section.
    [7" id="c-fr-0007]
    7. Power transmission system according to any one of the preceding claims, characterized in that the first wall portion (43; 43a, 43b) is arranged axially opposite the recovery chamber (42; 42a, 42b ).
    [8" id="c-fr-0008]
    8. Power transmission system according to any one of the preceding claims, characterized in that the gutter (41) is provided with an outlet opening (37) with a radial axis located in a lower part of the turbomachine along the radial axis and oriented towards the outside of the turbomachine.
    [9" id="c-fr-0009]
    9. Power transmission system according to any one of the preceding claims, characterized in that the gutter (41) is made from a sheet.
    [10" id="c-fr-0010]
    10. Power transmission system according to any one of the preceding claims, characterized in that the gutter (41) comprises two recovery chambers (42a, 42b) axially opposite and arranged on either side of the ejection means (30) oil.
    [11" id="c-fr-0011]
    11. Power transmission system according to any one of the preceding claims, characterized in that the oil ejection means (30) have an angular orientation relative to the radial axis, the orientation comprising an axial component along the longitudinal axis towards the gutter (41).
    [12" id="c-fr-0012]
    12. Turbomachine (1) comprising a rotor shaft (10), a power shaft (5) and a power transmission system according to any one of the preceding claims, between the rotor shaft (10) and the power shaft (5), the recovery device (40) being arranged to recover the oil ejected by centrifugal effect from the speed reducer (12).
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    同族专利:
    公开号 | 公开日
    FR3081513B1|2021-06-18|
    US11125318B2|2021-09-21|
    EP3575562A1|2019-12-04|
    EP3575562B1|2021-06-30|
    US20190360578A1|2019-11-28|
    CN110541760A|2019-12-06|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DE376381C|1920-08-03|1923-05-28|Luftfahrzeugbau Schuette Lanz|Circulating lubrication, especially for planetary gear drives|
    US20150300255A1|2012-02-23|2015-10-22|Snecma|Device for recovering lubricating oil from an epicyclic reduction gear|
    US20170254407A1|2014-08-01|2017-09-07|Ge Avio S.R.L.|Mechanical gear transmission|
    FR3054264A1|2016-07-25|2018-01-26|Safran Aircraft Engines|TURBOMACHINE WITH REDUCER WITH EPICYCLOIDAL TRAIN|FR3107089A1|2020-02-07|2021-08-13|Safran Aircraft Engines|Axial retention of a fan in a turbojet|US3097546A|1963-07-16|Transmission mechanism |
    US4530331A|1984-03-27|1985-07-23|Caterpillar Tractor Co.|Thrust and planetary gear coupling for a rotor of a distributor fuel injection pump|
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    FR3052322B1|2016-06-02|2018-07-06|Maple High Tech|METHOD FOR SYNCHRONIZING NODES IN A WIRELESS SENSOR NETWORK|
    FR3052522B1|2016-06-10|2018-06-01|Safran Aircraft Engines|DEVICE FOR RECOVERING LUBRICATING OIL EJECTED BY CENTRIFUGAL EFFECT IN A TURBOMACHINE|FR3086341B1|2018-09-24|2020-11-27|Safran Aircraft Engines|TURBOMACHINE WITH REDUCER FOR AN AIRCRAFT|
    FR3110194A1|2020-05-13|2021-11-19|Safran Aircraft Engines|AIRCRAFT TURBOMACHINE INCLUDING A BEARING LUBRICATION DEVICE|
    法律状态:
    2019-04-18| PLFP| Fee payment|Year of fee payment: 2 |
    2019-11-29| PLSC| Search report ready|Effective date: 20191129 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 3 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1854532|2018-05-28|
    FR1854532A|FR3081513B1|2018-05-28|2018-05-28|POWER TRANSMISSION SYSTEM INCLUDING A LUBRICATING OIL RECOVERY AND TURBOMACHINE EQUIPPED WITH SUCH A POWER TRANSMISSION SYSTEM|FR1854532A| FR3081513B1|2018-05-28|2018-05-28|POWER TRANSMISSION SYSTEM INCLUDING A LUBRICATING OIL RECOVERY AND TURBOMACHINE EQUIPPED WITH SUCH A POWER TRANSMISSION SYSTEM|
    US16/421,140| US11125318B2|2018-05-28|2019-05-23|Power transmission system including a lubrication oil recovery device and turbomachine provided with such a power transmission system|
    EP19176601.3A| EP3575562B1|2018-05-28|2019-05-24|Power transmission system comprising a device for recovering lubricating oil and turbine engine equipped with such a power transmission system|
    CN201910449909.8A| CN110541760A|2018-05-28|2019-05-28|Power transmission system and turbine provided with such a power transmission system|
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