• 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 an assembly (100) for an aircraft turbomachine comprising a first stator element (102) and a second stator element (104) between which a sensitive space (108) is defined with respect to a fluid, the assembly comprising a fluid circulation device (110) adapted to pass through the sensing space (108) and including a first fluid flow channel (120). According to the invention, the device (110) also comprises a second pipe (122), first and second sealing means (128, 132) being interposed between the second pipe (122) and each of the first and second elements (102). 104), the second pipe (122) being arranged around the first pipe (120) and defining therewith a leak fluid collection chamber (124) having discharge means (134) arranged downstream of the second sealing means (132).
    公开号:FR3014478A1
    申请号:FR1362245
    申请日:2013-12-06
    公开日:2015-06-12
    发明作者:Augustin Curlier
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The invention relates to the general field of the management of any leakage of fluid within a turbomachine. aircraft.
    [0002] It relates more particularly, but not exclusively, the management of any leakage of fluid ducts passing through the vein of an aircraft turbomachine with twin counter-rotating contra-rotating propellers. This type of turbomachine, also called "open rotor" turbine engine, is described for example in the document FR 2 942 203.
    [0003] STATE OF THE PRIOR ART On the "pusher" type open rotor turbomachinery, the receiver with a pair of counter-rotating and un-careened propellers is located in the rear continuity of the gas generator. This receiver generally includes an exhaust casing of the turbomachine, whose arms running through the vein allow the passage of hydraulic and electrical servitudes, such as oil circulation pipes. It may for example be hydraulic control lines of cylinders to change the wedge in incidence of the blades of a turbomachine propeller, or of the circulation ducts of a lubricant. In the latter case, the lubricant is conveyed for cooling a gearbox and / or bearings.
    [0004] The pair of contra-rotating propellers is generally located downstream of the exhaust casing, intended in particular for supporting these rotating parts. Therefore, in case of leakage of a pipe, the leakage fluid could end up under the vein through the ventilation circuits, then be driven into the rotating parts of the propellers with a risk to the integrity of the turbomachine. As an indication, this risk relates to the creation of oil pockets and firing thereof. In fact, whether at the exhaust casing or the propellers, the leakage fluid would then be in contact with the vein formed by a flow of hot, high-pressure, non-rotating gas capable of causing the combustion of this fluid. leakage, especially when it comes to oil. There is therefore a need for optimization of the design of the turbomachine, to reduce the risk identified above. Naturally, this need not only concerns the application that has just been described, but more generally relates to any other turbomachine assembly in which a fluid circulation duct passes through a sensitive space vis-à-vis the fluid. DISCLOSURE OF THE INVENTION The object of the invention is therefore to remedy at least partially the disadvantages mentioned above, relating to the embodiments of the prior art. To do this, the object of the invention is an assembly for an aircraft turbomachine comprising a first stator element and a second stator element between which a fluid-sensitive space is defined, the assembly comprising: in addition a fluid circulation device designed to allow the fluid to flow successively, in a direction of flow of the fluid, through the first stator element, the sensitive space then the second stator element, the circulation device comprising a first flow channel of the fluid passing through the first stator element, the sensitive space and the second stator element. According to the invention, the circulation device also comprises a second pipe passing through the first stator element, the sensitive space and the second stator element, first and second sealing means being respectively interposed between the second pipe and each of the first and second stator elements, said second pipe being arranged around the first pipe and defining therewith a leak fluid collection chamber having exhaust means arranged downstream of said second sealing means, in said direction fluid circulation. The invention provides a simple solution, clever and compact, responding to the problem of risk of leakage of the first pipe. Indeed, in the event that such a leak would occur on the first pipe, the leakage fluid would then enter the collection chamber before being discharged outside the sensitive space, by the dedicated evacuation means. In addition, this evacuation could be favored by the pressure of the fluid in the chamber, resulting from the pressure initially delivered to the inlet of the first pipe. Also, the evacuation of the leakage fluid outside the collection chamber does not need to be gravity, so that the fluid circulation device can be implanted in different locations of the turbomachine, and in different orientations. This advantageously offers great freedom of positioning. The invention also has at least one of the following optional features, taken individually or in combination. Said evacuation means are evacuation orifices made in the second duct, these evacuation orifices preferably being arranged radially with respect to an axis of said second duct. Alternatively, the evacuation means could be arranged at the junction between the first and second pipes, for example at the level of sealing means between them, which would then have a controlled permeability. Preferably, said first pipe has first axial abutment means; said second pipe has second axial abutment means; the assembly comprises an attachment flange mounted on the first stator element so that said first axial abutment means are contained axially between said fixing flange and a seat for receiving the first axial abutment means, provided on the second duct; ; and said second axial abutment means are axially sandwiched between said first axial abutment means and the first stator element. The fixing flange and the first and second abutment means are designed so as to allow a rotational displacement between the first stator element and the assembly formed by the first and second pipes, as well as a lateral deflection between the first and second pipes at said first stator element. In addition, an annular linear type link is formed between the second conduit and the second stator element, and an annular linear type linkage is formed between the first and second conduit at an end of the second conduit located on the side of the second stator element. It is noted that the annular linear links could be replaced by slides or links of the sliding pivot type, without departing from the scope of the invention. The degrees of freedom offered by the links / deflections described above essentially allow to accompany any relative displacements between the first and second stator elements, under mechanical and / or thermal loads, without overly constraining the components of the circulation device. of fluid. Preferably, the first and second stator elements are substantially annular, said first stator element surrounding the second stator element which delimits a fluid enclosure for recovery of the leakage fluid. It is noted, however, that this chamber is essentially dedicated to the recovery of cooling oil and lubrication of the mechanical transmission device and bearings of the engine. In this case, the assembly preferably comprises means for evacuating the leakage fluid outside said fluid chamber, said means for evacuating the leakage fluid passing through said sensitive space.
    [0005] Preferably, the inlet of these evacuation means is located on or near a low point of the enclosure for gravity drainage of the leakage fluid introduced into the fluid chamber. Preferably, said circulation device is intended for the circulation of a lubricant and / or the circulation of a control fluid of a jack for changing the pitch in incidence of the blades of a propeller of the turbomachine. Preferably, the assembly comprises, in said sensitive space, one or more casing arms of an exhaust casing of a turbomachine, preferably with a pair of counter-rotating non-ducted propellers located downstream of the exhaust casing and downstream of a gas generator, said casing arm surrounding one or more fluid circulation devices. The invention also relates to a turbomachine comprising an assembly as described above, the turbomachine preferably comprising a pair of contra-rotating propellers not careened.
    [0006] Finally, the invention relates to a method of mounting an assembly as described above, comprising the following steps: - implementation of the first and second pipes on the first and second stator elements, inserting them from said first stator element, according to said direction of circulation; and - fixing the flange on the first stator element. It is noted that to facilitate the establishment of the pipes on the stator elements, these pipes can be assembled beforehand to each other. Also, the design of the invention allows easy mounting and disassembly of the fluid circulation device, requiring only an outward access to the operator assembly, on the side of the first stator element. Other advantages and features of the invention will become apparent in the detailed non-limiting description below.
    [0007] BRIEF DESCRIPTION OF THE DRAWINGS This description will be made with reference to the appended drawings among which; - Figure 1 shows a schematic longitudinal half-sectional view of a turbine engine type "open rotor" for integrating an assembly according to the invention; - Figure 2 shows an enlarged partial view of that of the previous figure, on which the assembly according to the invention has been shown; - Figure 3 is a perspective view of that shown in the previous figure; FIG. 4 is a sectional view on which part of the assembly shown in FIGS. 2 and 3 has been detailed; - Figure 4a is a view similar to that of Figure 4, according to an alternative embodiment; and - Figure 5 is a half-sectional view similar to that of Figure 2, taken in another section plane passing through a lower part of the turbomachine. DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS With reference to FIG. 1, a "open rotor" type turbine engine 1 is shown schematically, intended to integrate an assembly according to the invention. In this figure, some elements of the turbomachine have been voluntarily omitted for reasons of clarity. The direction A corresponds to the longitudinal direction or axial direction of the turbomachine, parallel to the longitudinal axis 2 of the turbomachine. The direction B corresponds to the radial direction of the turbomachine. In addition, the arrow 4 schematizes the direction of advance of the aircraft under the action of the thrust of the turbomachine 1, this advancement direction being contrary to the main direction of flow of gas within the turbomachine, schematized by the arrow 5. In the front part, the turbomachine has an air inlet 6 continuing towards the rear by a nacelle 8, the latter comprising generally an outer skin 10 and an inner skin 12, both centered on the axis 2 and radially offset from each other. The inner skin 12 forms an outer radial casing for a gas generator 14, conventionally comprising, from front to rear, a low pressure compressor 16, a high pressure compressor 18, a combustion chamber 20, a high turbine pressure 22, and an intermediate pressure turbine 24. The compressor 16 and the turbine 24 are mechanically connected by a shaft 26, thus forming a low pressure body, while the compressor 18 and the turbine 22 are mechanically connected by a shaft 28 , forming a higher pressure body. Therefore, the gas generator 14 preferably has a conventional double-body design. Downstream of the intermediate pressure turbine 24, there is a receiver 30 of the turbomachine, this receiver forming a system of non-keeled contra-rotating propellers, and more precisely a pair of counter-rotating propellers.
    [0008] The receiver 30 comprises a free power turbine 32, forming a low-pressure turbine and located just behind the gas generator 14. It comprises a rotor 32a constituting the inner part of the turbine, and a stator 32b constituting the external part of this turbine, which is fixedly connected to a fixed casing assembly 34 of this propeller system, centered on the longitudinal axis 2 of the system. This stator 34 is in known manner intended to be integral with other casings of the turbomachine. As mentioned above, it is stated that the receiver 30 is designed so that the propellers are devoid of outer radial fairing surrounding them, as can be seen in FIG. 1. In addition, downstream of the counter-rotating turbine 32, the receiver 30 incorporates a first helix 7 or downstream propeller, carrying blades 7a. Similarly, the system 30 comprises a second propeller 9 or upstream propeller, carrying blades 9a. Thus, the propellers 7, 9 are offset from each other in the direction 4, and both located downstream of the free turbine 32.
    [0009] The two propellers 7, 9 are intended to rotate in opposite directions around the axis 2 on which they are centered, the rotations being effected relative to the stator 34 remaining stationary. For the rotational drive of these two propellers 7, 9, there is provided a mechanical transmission device 13, forming a reducer and comprising in particular an epicyclic train 15. The train 15 is provided with a sun gear 17 centered on the longitudinal axis 2, and carried by a planet shaft 19 of the same axis, connected integrally upstream to the rotor 32a, by means of a flange 38. Thus, the rotor 32a directly drives the sun gear 17 in rotation, the latter taking the form a gear wheel externally. The train 15 also comprises a satellite 21, and preferably several as can be seen in FIG. 2, each of them meshing with the sun gear 17. Each satellite 21 is carried by a satellite shaft 23 with an eccentric axis with respect to the 2 axis, and takes the form of a toothed wheel externally.
    [0010] In addition, the train 15 is equipped with a planet carrier 25 centered on the longitudinal axis 2, and rotatably carrying each of the satellites 21, through the shafts 23, respectively. The planet carrier 25 is carried by a planet carrier shaft 29 of the same axis, integral with the first propeller 7, as can be seen in FIG. 1, so as to be able to drive it directly in rotation.
    [0011] Finally, the train 15 has a ring 31 centered on the axis 2 and carried by a crown shaft 33 of the same axis, this ring 31 meshing with each satellite 21. The shaft 33 extends downstream in being secured to the second propeller 9, so as to be able to drive it directly in rotation. For example, this shaft 33 is located around the planet carrier shaft 29 with which it is concentric. The ring 31 takes the form of a toothed wheel internally. The epicyclic gear train 15 is located at the right and inside a housing 42 interposed between the free power turbine 32 and the propellers 7, 9. This housing 42, also called exhaust casing or "static frame", carries a motor attachment 44 intended to ensure the attachment of the turbomachine on the structure of the aircraft. In general, it is stated that the mechanical transmission device is housed in the hub 43 of the housing 42, the latter also comprising an outer shell 47 connected to the hub by radial arms 45. The outer shell 47 is located in the rear continuity of the stator casing 32b. The casing 42, downstream of which are the propellers and upstream of which the power turbine 32 is located, comprises a casing extension 46 extending in the downstream direction relative to a central portion of this casing. This extension 46 takes the form of a hollow cylinder centered on the axis 2, supporting in rotation a hub 48b of the second propeller, this hub 48b coinciding with the crown shaft 33, as can be seen in FIG. This rotating support is effected by means of two rolling bearings 50 spaced from each other in the direction A, and interposed between the extension 46 and the hub 48b. The second propeller 9 also comprises an outer shell 56b concentrically disposed at the hub 48b, and participating in the radially outward delimitation of a main annular vein 58, this vein being also delimited between the hub 43 and the outer shell 47 at the of the exhaust casing 42. At the housing 42, the vein 58 is then traversed radially by the arms 45. In addition, it also comprises a plurality of connecting arms 60b connecting the outer shell 56b to the hub 48b. The connecting arms 60b carry a second intermediate ferrule 62b disposed between the hub 48b and the outer ferrule 56b, this ferrule 62b participating in the radially inward delimitation of the main annular groove 58. In addition, each blade 9a is mounted in in order to be piloted / wedged in incidence around its pivot axis 64b, by its variable timing system (not shown), known to those skilled in the art.
    [0012] The crown shaft 33 takes the form of a hollow cylinder centered on the axis 2, rotating a hub 48a of the first propeller, this hub 48a coinciding with the planet carrier shaft 29, as is This rotating support is effected by means of two rolling bearings 66 spaced from each other in the direction A, and interposed between the two hubs 48b, 48a.
    [0013] The first propeller 7 also comprises an outer shell 56a concentrically disposed at the hub 48a, and participating in the radially outward delimitation of the main annular stream 58. It is located in the downstream aerodynamic extension of the outer shell 56b of the second propeller .
    [0014] In addition, it also comprises a plurality of connecting arms 60a connecting the outer shell 56a to the hub 48a. In addition, the connecting arms 60a of the first propeller carry a first intermediate shell 62a disposed between the hub 48a and the outer shell 56a, this shell 62a also participating in the radially inward delimitation of the main annular stream 58. is located in the downstream aerodynamic extension of the intermediate shell 62b of the second propeller. Each blade 7a is also mounted so as to be piloted / wedged in incidence around its pivot axis 64a, by its variable timing system (not shown), known to those skilled in the art. In addition, the housing 42 includes a housing extension 51 extending in the upstream direction relative to a central portion of this housing. This extension 47 takes the form of a hollow cylinder centered on the axis 2, rotatingly supporting the sun shaft 19, via two rolling bearings 49 spaced apart from each other in the direction A. Referring now together with Figures 2 and 3, there is shown an assembly 100 according to a preferred embodiment of the invention. The assembly 100 comprises the exhaust casing 42, as well as the specific elements of the invention which will be described below. Firstly, the assembly 100 comprises a first stator element 102, substantially annular in shape and centered on the axis 2. Here, the element 102 is a pressurizing cover arranged externally around the outer shell 47. L assembly also comprises a second stator element 104, also of substantially annular shape and centered on the axis 2, arranged internally with respect to the surface of the hub 43 delimiting the vein 58. Internally, the element 104 delimits an enclosure of lubricating oil 106 in which is located the mechanical transmission device 13 to epicyclic train, and possibly at least some of the aforementioned rolling bearings 50, 66, 49. As will be explained later, the stator element 104 fills a Oil recovery sump function. Between the two stator elements 102, 104 is defined a sensitive space 108 vis-à-vis the oil, this space 108 comprising the portion of the vein 58 through the housing 42. Here, the space 108 is substantially annular, and traversed by one or more fluid circulation devices 110 specific to the invention. In the example shown in FIGS. 2 and 3, there are two oil circulation devices 110, both passing through the same housing arm 45 which surround them at the level of the vein 58. These devices 110 are extend radially on either side beyond the arm 45, to cross each of the two stator elements 102, 104. Each oil circulation device 110 is provided for circulating oil in a direction of rotation. flow 114 from the element 102 to the element 104, successively through the element 102, the sensitive space 108 and the element 104. In this regard, it is noted that the receiver comprises a lubrication circuit 70 for supplying lubricating oil the transmission device 13, and more particularly its epicyclic tain. To do this, the circuit 70 integrates the circulation device 110 shown on the left in FIG. 2, which thus travels radially through one of the arms 45, to circulate the fresh lubricant coming radially from the outside of the pressurizing housing. 102. In particular, the circulation device 110 is connected to a downstream part of the circuit 70 supplying on the one hand the transmission device 13 located at the right of the element 104, via the section referenced 74, and feeding other one or more rolling bearing housings via another section (not shown), in particular the enclosure integrating the rolling bearings 49 above. The aforesaid sections / ducts, shown schematically by a simple pipe in FIG. 2, travel through the hub 43 before joining other elements of the circuit 70, as known to those skilled in the art. Moreover, it is noted that the oil chamber 106 housing the transmission device 13 can be considered as an integral part of the circuit 70.
    [0015] In a known manner, the lubricant flowing continuously in the circuit 70 is recirculated to be brought again upstream of the circulation device 110 passing through the arm of the exhaust casing. Furthermore, the receiver comprises a hydraulic circuit 82 for controlling a cylinder to change the wedge in incidence of the blades of the propeller. To do this, the circuit 82 integrates the circulation device 110 shown on the right in FIG. 2. This device 110 thus also travels radially through this arm 45 and the sensitive space 108, while being filled with a fluid, preferably oil, for the control of the blade setting cylinder. The circulation device 110 is thus connected to a downstream part of the circuit 82 supplying the control jack, via the section referenced 86 running through the hub 43, before joining the jack (not shown) as is known to the man of career. An elbow connector 88 may conventionally be attached between the device 110 traveling radially and the section 86 running axially in the downstream direction, towards the cylinder. The two devices 110 therefore run side by side over at least a portion of the length of the arm 45 through which they pass, the two adjacent portions preferably being parallel and not far from each other. Referring now to FIGS. 2 to 4, the design of one of the oil circulation devices 110 will be described, it being understood that the design of the two devices 110 is identical or similar. Firstly, the device 110 comprises a first oil circulation pipe 120 passing through the first stator element 102, the sensitive space 108 and the second stator element 104. The pipe 120 may comprise a tube 120a constituting its part. main, and a first connector 120b located at its upstream end. The connector 120b, passing through the first stator element 102, is preferably welded to the upstream end of the tube 120a. In addition, the connector 120b can securely carry a connection member 120c for connecting the device 110 to the other elements of the oil circuit. The assembly can here also be performed by welding.
    [0016] The connection member 120c may be in the form of a nipple or the like.
    [0017] Under normal conditions, the oil is intended to circulate through the first pipe 120 in the direction 114. Nevertheless, in the event of oil leakage at this pipe 120, the device 110 is equipped with particular means avoiding the risks of diffusion of this leak oil into the vein 58.
    [0018] It is essentially the presence of a second pipe 122 also passing through the first stator element 102, the sensitive space 108 and the second stator element 104. The pipe 122 may comprise a tube 122a constituting its main part, and a second connector 122b located at its upstream end. The coupling 122b, passing through the first stator element 102, is preferably welded to the upstream end of the tube 122a. The second pipe 122 is arranged around the first pipe 120 and defines therewith a leakage fluid collection chamber 124. The two pipes 120, 122 being preferably concentric, the collection chamber 124 is then annular, centered on the axis of the pipes which are preferably straight, for example of circular sections. Upstream, the chamber 124 is sealed by an O-ring seal 126 arranged between the outer surface of the fitting 120b, and the inner surface of the fitting 122b. It is the same downstream, where the chamber 124 is sealed by an O-ring seal 127 arranged between the outer surface of the tube 120a, and the inner surface of the tube 122a, at the downstream end thereof latest. Laterally, the collection chamber 124 is defined between the two pipes 120, 122, and in particular by their tubes 120a, 122a. First sealing means are arranged between the second coupling 122b and the element 102 having a through-hole of the device 110. These first means take the form of an O-ring 128 interposed between a shoulder 130 of the coupling 122b forming means. axial abutment, and the portion of the radially outer surface of the stator element 102 located near the through hole. Second sealing means are arranged between the second tube 122a and the element 104 also having a through hole of the device 110. These second means take the form of an O-ring 132 interposed between the outer lateral surface of the tube 122a, and the through-hole formed in the stator element 104. Downstream of the O-ring 132, in the direction 114 of circulation of the oil in the device 110, the chamber is equipped with means for evacuating the oil from the oil. leak. These are evacuation orifices 134 made through the second tube 122a, these discharge orifices being arranged radially with respect to the axis of the tube. The orifices 134 are for example made around the tube 122a. Also, the orifices 134 open into the oil chamber 106 defined by the oil recovery casing 104. Therefore, in case of leakage occurring at the first pipe 120, the leakage oil enters the chamber 124 and is ejected into the chamber 106 through the orifices 134. It is preferentially the initial pressure of the oil in the pipe 120 which generates the pressure in the chamber 124, and thus causes the extraction through the orifices 134 whatever the position of the device 110 around the engine. In other words, the leakage oil can even be extracted from the collection chamber 124 by counteracting the effect of gravity. In this regard, it is stated that the volume of the chamber 124 corresponds to a small percentage of the internal volume defined by the portion of the pipe 120 surrounded by the chamber. With this small percentage, in case of leakage, the pressure in the collection chamber 124 may be substantially similar to the pressure of the oil introduced into the first pipe 120.
    [0019] Below, it is proposed combinations of pipes 120, 122 with standardized dimensions satisfying satisfactorily the identified need. Inner diameter of the pipe 122 Outer diameter of the pipe (mm) 120 (mm) 4,775 2,997 6,35 4,572 7,925 6,147 9,525 7,747 12,7 10,922 15,875 14,097 19,05 17,272 25,4 23,622 31,75 29,972 34,925 33,147 38, 1 36.322 44.54 42.762 50.8 49.022 Once conveyed into the oil enclosure 106, the leakage oil can then be directed by gravity towards the bottom of the oil recovery casing 104 defining this enclosure, to be extracted by means of evacuation type drain 150 shown in Figure 5. The inlet 152 of the drain 150 is in fact located on or near a low point of the chamber 106, for a gravity drainage of the fluid of leak, which then crosses again the lower part of the vein 58 via this drain 150 housed in another housing arm 45. At the exit of this drain through the sensitive space 108, the leakage oil is preferably recirculated d a similar way to the rest of the oil circulating in the turbomachine. Of course, in the drain 150, the leakage oil flows in a direction opposite to the direction 114. Returning to FIG. 4, it is noted that the first connector 120b has first axial stop means 138, in the form of a flange / shoulder extending around the axis of the pipe 120. Similarly, as mentioned above, the second connector 122b has a flange / a shoulder 130 also forming axial abutment means. In addition, at the level of the stator element 102, the assembly 100 comprises a fastening flange 140 externally mounted by screwing on this element 102, at one or more bosses 142 for mounting the fastening screws (no represented) of the flange. The flange 140 comprises a periphery 140a for mounting the fixing screws, an annular body 140b surrounding the aforementioned flanges 130, 138, and an axial stop 140c ensuring the plating of the flanges 130, 138 against the outer surface of the element 102. More specifically, the flange 138 of the first connector 120b is gripped axially between the abutment 140c of the flange and a seat 144 provided on the second connector at the outer surface of the flange 130. This seat 144 is similar to an impression in which is housed the collar 138.
    [0020] In addition, the flange 130 is in turn sandwiched axially between the flange 138 and the outer surface of the element 102 receiving the seal 128. On the other hand, there is provision for games between the various elements to be able to accompany the possible displacements relative between the elements 102, 104, under mechanical and / or thermal loads. This is first of all a clearance between the inside diameter of the flange body 140b and the corresponding outside diameter of the flange 130 of the second coupling 122b. It is also a clearance between the inner diameter of the second coupling 122b and the corresponding outer diameter of the outer portion of the first coupling 120b carrying the seal 126. These sets are used to obtain, at the level of the passage of the device 110 through the element 102, a limited amplitude swiveling deflection between this element 102 and the assembly formed by the first and second connectors 120b, 122b, and a lateral deflection between the first and second pipes 120, 122 to level of the same first stator element 102. The games on the outermost part are mainly implemented to allow assembly of the assembly. Once the flange 140b mounted, there remains only a slight mobility of the assembly connected to the O-ring 128 (swiveling + lateral displacement). The joints allowing the most important deflections are those most towards the enclosure delimited by the element 104.
    [0021] The lateral deflection between the first and second pipes 120, 122 at the first stator element 102 essentially limits the mechanical loads transmitted by the second pipe 122 to the first pipe 120, and thus limits the stresses in the sensitive parts. of the assembly, including the welds, this assembly still remaining sealed thanks to the seal 126. The aforementioned rotational movement serves for its part essentially to be able to absorb the differential movements between the two elements 102, 104, without too much mechanically constrain the circulation device 110. In parallel, thanks to the seal 132 and a small clearance between the portion of the tube 122a and the passage hole of the element 104 cooperating with this seal 132, a linear annular type connection is obtained between the second tube 122a and the second element 104, at the passage hole formed in the latter. Also, in the event of a displacement of the pipes 120, 122 at the level of the stator element 102, the internal part of the device 110 can follow this deflection by means of the connection of the linear annular type.
    [0022] Likewise, thanks to the seal 127 and a small clearance between the two parts of the tubes 120a, 122a cooperating with this seal 127, a linear annular type connection is obtained between the two tubes at the downstream end. of the second pipe 122. This allows to accompany the movement of the ball joints 120, 122 at the stator element 102, but also allows a relative movement between the two tubes along their axis. The design of the invention facilitates the assembly and disassembly of the oil circulation device 110. Indeed, the first and second pipes 120, 122 can easily be put in place on the first and second stator elements 102, 104. inserting them from the first element 102, in the direction 114, to the sliding of the tube 122a through the passage opening of the stator element 104. To facilitate this implementation, the pipes 120, 122 are previously assembled one to the other. Once this introduction from the outside of the assembly on the side of the element 102, then simply proceed to the fixing of the flange 140 on the same stator element 102. Since the disassembly operations of the device 110 are exactly those mentioned above, but performed in the reverse order, the interchangeability of these devices 110 is therefore easy, and requires only an external access on the side of the element 102, usually corresponding to the zone nacelle easily accessible to the operator. Naturally, the interlocking of the first pipe 120 in the second pipe 122 can be carried out before having made the establishment of the second pipe on the elements 102, 104. Nevertheless, as mentioned above, this assembly of two pipes 120, 122 is preferably made before mounting on the elements 102, 104. In the case of the presence of a nipple 120c large diameter on the first pipe, this nipple can be welded to the fitting 120b only after the introduction of the flange 140 around the same connection 120b. This does not prevent mounting the system on the engine and then tighten the flange 140 after the welding of the fitting, which can be done in the workshop and not on site assembly. Here, by "workshop", it is understood a coin production area comprising for example a welding station. The operations can be multiple: welding, threading seal with possibly cooling the area that receives the seal if it is heated by welding. On the contrary, the "assembly site" serves only to assemble the subassemblies together. It uses mounting tools such as keys / sockets, or it is used soldering processes. It is a question of limiting the interventions to the strict assembly of the sub-elements between them. Finally, with reference to FIG. 4a, an alternative embodiment is shown in which the stator element 104 comprises a boss 105 defining the bent element 88 made by recess of material in this boss, this part being preferably made of foundry. The bent element 88 thus makes it possible to collect the control oil from the jack. At the end of this element 88, it is intended to mount a connector with another pipe to continue the oil circuit. In the boss 105, there is provided an orifice 107 allowing the evacuation of the fluid in case of breakage of the pipe 120. In fact, in this case, the fluid leaking from the pipe 120 escapes through the orifices. 134 of the other duct 122, then enters the port 107 to join the enclosure 106. Of course, various modifications may be made by those skilled in the art to the invention which has just been described, only as non-limiting examples.25
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. An aircraft turbomachine assembly (100) comprising a first stator element (102) and a second stator element (104) between which a fluid-sensitive space (108) is defined, the assembly further comprising a fluid circulation device (110) adapted to allow the fluid to flow successively, in a fluid flow direction (114), through the first stator element (102), the sensitive space (108). then the second stator element (104), the circulation device comprising a first fluid flow channel (120) passing through the first stator element (102), the sensitive space (108) and the second stator element (104). ), characterized in that the circulation device (110) also comprises a second pipe (122) passing through the first stator element (102), the sensitive space (108) and the second stator element (104), first and second sealing means (128, 132) being respectively interposed between the second pipe (122) and each of the first and second stator members (102, 104), said second pipe (122) being arranged around the first pipe (120) and defining therewith a a leak fluid collection chamber (124) having discharge means (134) arranged downstream of said second sealing means (132) in said fluid flow direction (114).
    [0002]
    2. Assembly according to claim 1, characterized in that said evacuation means are discharge orifices (134) formed in the second pipe (122), said discharge orifices preferably being arranged radially with respect to an axis. of said second pipe.
    [0003]
    3. Assembly according to claim 1 or claim 2, characterized in that: - said first pipe (120) has first axial abutment means (138); said second pipe (122) has second axial abutment means (130); the assembly comprises a fastening flange (140) mounted on the first stator element (102) so that said first axial abutment means (138) are contained axially between said fastening flange (140) and a seat (144); ) receiving the first axial stop means (138) provided on the second pipe (122); and - said second axial abutment means (130) are axially sandwiched between said first axial abutment means (138) and the first stator element (102).
    [0004]
    4. An assembly according to claim 3, characterized in that the fastening flange (140) and the first and second abutment means (138, 130) are designed to allow a rotational movement between the first stator element (102). and the assembly formed by the first and second conduits (120, 122), as well as a lateral deflection between the first and second lines at said first stator member, in that an annular linear type connection is formed between the second pipe (122) and the second stator element (104), and and that an annular linear type connection is formed between the first and second pipes (120, 122) at an end of the second pipe (122) located on the side of the second stator element (104).
    [0005]
    5. An assembly according to any one of the preceding claims, characterized in that the first and second stator elements (102, 104) are substantially annular, said first stator element (102) surrounding the second stator element (104) which defines a fluid enclosure (106) for recovering the leakage fluid.
    [0006]
    6. An assembly according to claim 5, characterized in that it comprises means (150) for evacuation of the leakage fluid outside said fluid chamber (106), said means for evacuating the leakage fluid passing through said space sensitive (108).
    [0007]
    7. Assembly according to any one of the preceding claims, characterized in that said circulation device (110) is intended for the circulation of a lubricant and / or the circulation of a control fluid of a jack for changing the wedging in incidence of the blades of a propeller of the turbomachine.
    [0008]
    8. An assembly according to any one of the preceding claims, characterized in that it comprises, in said sensitive space (108), one or more casing arms (45) of an exhaust casing (42) of a turbomachine (1), preferably with a pair of counter-rotating non-ducted propellers located downstream of the exhaust casing and downstream of a gas generator (14), said casing arm (45) surrounding one or more circulation devices of fluid (110).
    [0009]
    9. A turbomachine (1) comprising an assembly (100) according to any one of the preceding claims, the turbomachine preferably comprising a pair of counter-rotating propellers not carinated.
    [0010]
    10. A method of mounting an assembly (100) according to claim 3, characterized in that it comprises the following steps: - establishment of the first and second pipes (120, 122) on the first and second stator elements (102, 104), inserting them from said first stator element (102) in said flow direction (114); and - attaching the flange (140) to the first stator member (102).
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    同族专利:
    公开号 | 公开日
    FR3014478B1|2016-01-22|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2942203A1|2009-02-13|2010-08-20|Snecma|SYSTEM OF CONTRAROTATIVE PROPELLERS WITH REDUCED SIZE|
    US20110085895A1|2009-10-09|2011-04-14|Pratt & Whitney Canada Corp.|Oil tube with integrated heat shield|
    US20130189071A1|2012-01-24|2013-07-25|Pratt & Whitney Canada Corp.|Oil purge system for a mid turbine frame|FR3049980A1|2016-04-12|2017-10-13|Snecma|TURBOMACHINE ASSEMBLY COMPRISING A FLUID FLOW DEVIATION SYSTEM BETWEEN AN ENCLOSURE OF SAID FLUID AND A SEALING DEVICE|
    EP3318729A1|2016-11-04|2018-05-09|United Technologies Corporation|Apparatus and method for providing fluid to a bearing damper|
    US10385710B2|2017-02-06|2019-08-20|United Technologies Corporation|Multiwall tube and fitting for bearing oil supply|
    US10393303B2|2017-02-06|2019-08-27|United Technologies Corporation|Threaded fitting for tube|
    US10465828B2|2017-02-06|2019-11-05|United Technologies Corporation|Tube fitting|
    US10830139B2|2017-02-06|2020-11-10|Raytheon Technologies Corporation|Fitting for multiwall tube|
    WO2021058882A1|2019-09-27|2021-04-01|Safran Aircraft Engines|Aircraft turbine engine|
    法律状态:
    2015-12-15| PLFP| Fee payment|Year of fee payment: 3 |
    2016-12-05| PLFP| Fee payment|Year of fee payment: 4 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 5 |
    2018-06-29| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 8 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1362245A|FR3014478B1|2013-12-06|2013-12-06|AIRCRAFT TURBOMACHINE ASSEMBLY COMPRISING A FLUID CIRCULATION DEVICE WITH IMPROVED DESIGN WITH RESPECT TO LEAKAGE HAZARDS|FR1362245A| FR3014478B1|2013-12-06|2013-12-06|AIRCRAFT TURBOMACHINE ASSEMBLY COMPRISING A FLUID CIRCULATION DEVICE WITH IMPROVED DESIGN WITH RESPECT TO LEAKAGE HAZARDS|
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