• 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 annular duct (33) for the flow of air from a turbomachine, such as a turbojet engine or a turboprop engine, traversed by an instrumented rod (50) comprising means for measuring the characteristics of a flow that can flow. traverse the vein, said rod extending between an outer annular wall (48) and an inner annular wall (42) of the vein. External linkage means (60, 86) attach an outer end (58) of the instrumented shaft to the outer wall rigidly in all directions, and inner linkage means (62) attaches an inner end ( 56) from the instrumented shaft to the inner wall rigidly in the circumferential direction and with a degree of freedom in displacement only in a given direction (51) extending between the inner (42) and outer (48) walls of the vein and having at least one radial component.
    公开号:FR3036735A1
    申请号:FR1554724
    申请日:2015-05-26
    公开日:2016-12-02
    发明作者:Nicolas Lamarche；Jeremy Giordan
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The invention relates to an annular vein of air flow traversed by an instrumented rod, this vein being located generally in a turbomachine. Conventionally, a turbofan engine 10, as illustrated in FIG. 1, consists of a gas turbine 12 having an axis 14 driving a fan 16, or fan, which fan is generally placed upstream ( AM) of the engine. The mass of air sucked by the engine is divided into a primary air flow (arrow A), which flows in the gas turbine or primary body, and a secondary air flow (arrow B), which comes from the blower 16 and surrounding the primary body, the primary and secondary air streams being concentric. In a well known manner, the primary air flow (arrow A) is generally compressed by a first compressor 18, said low pressure (BP) or booster, the BP shaft is connected to the shaft of the fan 14 and driven in rotation by the shaft of a downstream low pressure turbine (not shown), then in a second downstream compressor (AV), said high pressure (HP), whose HP shaft is rotated by the shaft of a high pressure turbine arranged at the outlet of a combustion chamber and upstream of the low pressure turbine (not shown). In such a double-body turbojet engine, an intermediate casing 22 is usually designated a casing whose hub is arranged between a casing 24 of the low-pressure compressor 18 and a casing 26 of the high-pressure compressor 20. The intermediate casing 22 comprises an annular wall. internal wall 28 delimiting externally the annular flow duct 18 of the primary air flow, an intermediate annular wall 30 internally defining the annular flow vein 33 of the secondary air flow, and an outer wall 35 delimiting the annular vein externally; 33 flow of the secondary air flow. Moreover, such a turbojet engine is generally equipped with devices called discharge valves 32 or VBV (for Variable Bleed Valve, in English), which make it possible to return part of the primary air flow at the outlet of the compressor BP 18. in the annular channel 33 of the secondary air stream. This discharge has the effect, by lowering the pressure downstream of the compressor BP 18, to lower the operating point thereof and to reduce the risks of pumping the compressor 18, 20 consisting of a sudden inversion of the flow. the hot gas flow of the combustion chamber, which can damage the compressor 18, 20. In addition, in case of accidental water penetration, especially in the form of rain or hail, or of various debris, which are susceptible to impede the operation of the turbojet engine, these valves make it possible to recover this water or these debris and to eject them outside the primary vein supplying air to the combustion chamber. Thus, the discharge valves 32 are formed in the inner annular shell 28 of the hub of the intermediate housing 22 and communicate with a space between the inner annular shell 28 and the intermediate shell 30 of the intermediate housing 22. To allow the discharge of air, the hub of the intermediate casing 22 comprises a downstream transverse flange 34 arranged upstream of the high-pressure compressor 20 of the turbojet and mutually connecting the downstream ends of the inner annular ferrule 28 and intermediate ring 30. The downstream flange 34 comprises a plurality of first openings 36 distributed around the axis 14 of the turbojet engine 10 and communicating each upstream with the inside of the hub and downstream with a conduit 38 whose downstream end opens at a ferrule 40 perforated by second openings, downstream an outer annular ring 42 formed in the downstream extension of the intermediate annular wall 30 of the intermediate casing 22.
    [0002] As shown in FIG. 1, the hub of the intermediate casing 22 carries stator vanes 44 extending between the intermediate wall 30 and the outer wall 35 of the intermediate casing 22. The stator vanes 44, also called OGV, are intended to straighten the flow of secondary air from the upstream fan 16. In the development of the turbomachine, it is necessary to measure and verify its performance. In particular, it is sought to measure the flow parameters of the flow in the secondary vein, such as its speed, its pressure and its temperature. To this end, it has been determined that it is preferable to have the measurement sensors at certain precise locations of the secondary vein. One of these 10 locations is located downstream of the stator vanes 44 of the intermediate casing 22, according to a particular inclination plane with respect to the axis of the turbomachine passing through the perforated ferrule 40. This location makes it possible to measure effectively the performance of the blower torque 16 and 44 of straightening vanes. In order to perform exhaustive measurements of the flux at this location, it is desired to arrange several sensors at different heights of the secondary vein, again according to this plan. These sensors, even if they are intrusively integrated, must not influence the normal operation of the turbomachine, and must be able to withstand their environment during the tests carried out, the latter generally covering all the possible operating ranges. of the turbomachine. During these tests, it will be possible to observe variations in temperature, pressure, relative positioning of the parts due to the different mounting sets and differential expansions.
    [0003] The present invention provides a simple, effective and economical solution for integrating flow measurement instruments through the aforementioned vein. To this end, it proposes an annular airflow vein of a turbomachine, such as a turbojet engine or a turboprop, traversed by an instrumented rod comprising means for measuring characteristics of a flow that can traverse the vein. said rod extending between an outer annular wall and an inner annular wall of the vein, characterized in that external connecting means attach an outer end of the instrumented rod to the outer wall rigidly in all directions, and in that internal connecting means fix an inner end of the instrumented shaft to the inner wall rigidly in the circumferential direction and with a degree of freedom in displacement only in a given direction extending between the inner and outer walls of the vein and having at least one radial component. Thanks to the invention, it is possible to position sensors over the entire length of the rod, and thus over the entire height of the vein, which makes it possible to exhaustively measure the flow of the flux on the predefined plane. The rod may for example comprise a cable duct opening through the outer wall of the vein, in order to connect the sensors of the rod to external data collection devices 15. Thanks to the degree of freedom in the given direction extending between the internal and external vein walls, left at the inner end of the rod relative to the internal wall of the vein, the stem will not undergo structural constraints in case differential expansion of the inner wall of the vein relative to the outer wall, or in case of relative displacement of these two walls in operation authorized by the various mounting sets of the assembly. According to the invention, the inner end of the rod can move in the given direction, the displacement of the rod only in the axial direction is thus prevented.
    [0004] Advantageously, the internal connection means comprise a shoe fixed rigidly to the inner wall, and fixed rigidly to the inner end of the instrumented rod in the circumferential direction, and with a degree of freedom in displacement in said given direction having at least a radial component.
    [0005] Preferably, the shoe and the inner end of the instrumented rod are slidably engaged with each other in said given direction. In one embodiment of the invention, the shoe comprises a first shoe portion and a second shoe portion integral with each other and defining a housing in which said inner end of the rod is able to move in said direction given. The adjustment between the shoe and the inner end of the instrumented rod may be of the H7 / g6 type. Thus, it is allowed a relative movement between the shoe and the inner end of the rod. According to a feature of the invention, the housing may be delimited by a U-shaped open towards the downstream of the first shoe portion and by a downstream flange extending outwardly of the second shoe portion. The second shoe portion may be L-shaped with an axial wall carrying the downstream flange extending between the first shoe portion and the inner wall. According to another characteristic of the invention, the axial wall of the second shoe portion is engaged axially in an axial groove of an inner face of the first shoe portion. Preferably, the thickness of said axial wall is greater than the depth of said axial groove, which makes it possible to clamp the second shoe portion to the inner annular wall by the first shoe portion. In a practical embodiment of the invention, the inner end of the rod is mounted with an initial clearance J to the mounting, for example three millimeters, with the second shoe portion. This clearance J can be formed between the inner end of the rod and the axial wall of the second shoe portion. Advantageously, the shoe is fixed rigidly to a first ferrule forming the internal wall of the vein, said ferrule being arranged downstream of an annular row of blades which extends through the vein and upstream of a second ferrule perforated air discharge, and wherein the outer end of the rod is fixed relative to the downstream outer wall 3036735 6 of said row of blades. The perforated shell where the air discharge duct opens is in fact not adapted to support the instrumented rod in this type of configuration. In addition, the shoe may comprise a downstream portion arranged axially facing the second ferrule and radially radially remote from the latter, the shoe being fixed to the inner end of the rod at the downstream portion. This allows the rod to be connected to the inner wall of the vein while respecting the measurement plane passing through the ferrule where the air discharge conduit opens, in the configuration 10 defined above. In order to respect the measurement plane, the inner end of the instrumented rod may be located upstream relative to the outer end of the instrumented rod. A shim may be mounted between the outer end of the instrumented rod and the outer wall of the vein. The invention also relates to a turbomachine, such as a turbojet or a turboprop, comprising an annular vein as described above. Other advantages and features of the invention will become apparent on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which: FIG. 1, already described, is a diagrammatic half-view in axial section of an aircraft turbojet of a known type; Figure 2 is a half-view of a vein adaptable in the turbojet illustrated in Figure 1; Figures 3 and 4 are complementary views of the connection between the shoe and the inner end of the instrumented rod according to one embodiment; Figures 5 and 6 are complementary views of the connection between the outer end of the instrumented shaft and the outer wall of the vein; Figure 7 is an enlargement of Figure 2 in the shoe area; Figures 8 to 10 are schematic perspective views of a second embodiment of an instrumented rod; Figs. 11A, 11B and 11C are schematic views of the assembly sequence of the inner end of an instrumented rod according to the second embodiment; Figure 12 is an enlarged view of the dashed area in Figure 11C. FIG. 2 represents an integration of an instrumented rod in a turbomachine of the type represented in FIG. 1. There is thus a secondary vein 33 traversed radially by a plurality of OGV vanes 44 of an intermediate casing 22. Form the internal limit of the vein, respectively from upstream to downstream, the intermediate wall 30 of the intermediate casing, a first shell 42, and a second perforated shell 40 where 15 open discharge ducts of the primary stream 18 of the turbomachine. Form the outer limit of the vein 33, upstream to downstream, the outer wall 35 of the intermediate casing 22, an air / oil heat exchanger 46, and an outer casing 48 of the turbomachine.
    [0006] It is proposed to arrange an instrumented rod 50 through the vein 33 described above to perform the desired flow measurements. The rigid rod 50 is of the longitudinal type, and carries on its upstream edge nozzles 52 whose openings are oriented towards the secondary flow B. The nozzles 52 are connected to cables 54 passing through a duct formed within the rod 50, and opening out of the vein 33, in order to be able to connect the cables 54 to devices (not shown) for collecting and processing the measured information. The instrumented shaft 50 extends between the inner wall 30 and the outer wall 35 of the vein in a first given direction 51 located in a plane perpendicular to a circumferential direction. This direction 51 has a component along a radial axis 53 and a component along an axial axis 55. This first direction 51 is in a radial plane, that is to say containing the axis of the vein. The rod 50 is inclined from upstream to downstream between its inner end 56 and its outer end 58, respectively. This inclination follows the optimal flow measurement plan at the chosen location. The outer end 58 of the rod 50 is bent upstream and outward, and is fixed to the outer casing 48 of the turbomachine, downstream of the air / oil exchanger 46, via a shim 60. The inner end 56 of the instrumented rod 50 is connected to a shoe 62, which is itself connected to the first ferrule 42 of the internal wall of the vein, situated axially between the intermediate wall 30 of the intermediate casing 22. and the perforated ferrule 40 comprising the openings of the discharge ducts of the primary vein. Figures 3 and 4 describe in more detail the shoe 62 and its method of connection with the inner end 56 of the instrumented rod 50. The shoe 15 comprises an upstream base 64 pierced radially for the passage of a screw 66 for fixing to the aforementioned ferrule 42 of the inner wall of the vein 33. A slight clearance is formed between the aforementioned screw 66 and the orifice 68 of the base 64 so as to compensate for the axial and circumferential dimensional dispersions of the vein during assembly of the set described. The base 64 is connected downstream to a downstream portion or a sleeve 70 facing downstream and outward. The handle 70 is pierced circumferentially, the bore forming an oblong orifice 72 whose long extension direction is oriented according to the orientation of the rod and extends over a distance noted 72a, and whose short extension direction is perpendicular to the long extension direction 72a and extends a distance noted 72b. The inner end 56 of the instrumented rod 50 comprises a housing 74 sized to receive the handle 70 of the shoe 62. The inner end 46 of the instrumented rod 50 thus comprises two walls or fingers 76, 78 whose internal faces vis-à-vis circumferentially delimit the handle 70. The two walls 76, 78 and each are circumferentially pierced, so as to form orifices 80, 82 aligned with the oblong orifice 72 of the handle 70. The orifices 80, 82 of the pins 76, 78 of the rod are circular and of sections included in the oblong hole 72 of the handle 70. More particularly, the diameter of each of the orifices 80, 82 is smaller than the long dimension 72a and the short dimension 72a of the oblong orifice 72. A threaded rod 84, of diameter corresponding to the orifices 80, 82 of the fingers 76, 78, is inserted and locked through the orifices 80, 82 mentioned above and the oblong orifice 72 of the handle 70. The rod file The tee has a head 85 at one of its ends, 10 applied to one of the outer faces of the fingers 76, 78, a tightening nut 87 being applied to the other of the outer faces of the fingers 76, 78. It is understood that and the inner end of the stem comprises a degree of freedom in the first direction corresponding to the direction 51 and in a second given direction 111 substantially perpendicular to the first given direction 51. The adjustment between the handle 70 of the shoe 62 and the housing 74 of the rod 50 is of the sliding type, and preferably of the H7 / g6 type. The bolt formed by the threaded rod 84 and the nut 87 is self-locking, and the self-locking tightening of the bolt is configured to prevent deformation of the walls 76, 78 of the housing 74 and to constrain them to the handle 70, in the purpose of maintaining a sliding fit. It is thus permissible for the handle 70 to slide axially and radially into the housing 74 within the limits of the possible displacement of the threaded rod 84 in the oblong hole 72 of the handle 70, while blocking the rod 50 with respect to the shoe 62 in the direction circumferentially. This avoids in particular the vibration of the rod 50 during measurements, and allows the longitudinal expansion of the rod during testing. Preferably, a minimum clearance of 2 mm will be formed all around the threaded rod 84 in the oblong hole 72 of the handle 70, in order to compensate for the axial and radial dimensional tolerances or dispersions of the component parts of the vein during the assembly of the set described.
    [0007] With reference to FIGS. 5 and 6, it can be seen that the outer end 58 of the instrumented rod 50 is fixed to the outer casing 48 of the turbomachine by means of a shim 60. Thanks to this shim 60, it is possible to form the rod 50 with a length facilitating its mounting in the vein.
    [0008] The shim 60 cooperates with the outer end face of the rod 50 and the inner face of the outer casing 48. The shim has through holes 86, 88 aligned with holes (not visible) of the outer casing 48 and holes 86 ', 88' formed on flanges at the outer end 58 of the rod 50, these flanges being lateral and extending circumferentially. It is thus possible to insert threaded rods 86 ", 88" into the set of aligned holes in order to lock the outer end of the rod 50 rigidly to the outer casing 48, by bolting with nuts. . FIG. 7 makes it possible to better understand the relative positioning of the shoe 62 and of the internal wall of the vein 33. The second perforated ferrule 40 has a structure and a mechanical strength which does not make it possible to fix the instrumented rod 50 thereon. The optimal plan for measuring the flow of the vein however passes through this ferrule 42. The shoe 62 therefore allows axially offset means of attachment respectively with the rod 50 and the internal wall of the vein, to keep the rod 50 in the plane of 20 above, while using as support for fixing to the inner wall of the vein, the first ferrule 42 located just downstream of the intermediate casing 22, which responds to the structural constraints necessary to support the rod 50 during tests. Furthermore, while the base 64 of the shoe 62 is in direct contact 25 with its internal surface with the first ferrule 42 located immediately downstream of the intermediate casing 22, in order to provide a secure support and a good relative fixing, the part downstream of the base 64 is however not in contact with the second perforated ferrule 40, the inner surface of the base 64 comprising a downstream projection 90 or recess to the outside at this level. Thus, it is ensured that the shoe 62 has no support on the second perforated ferrule 40.
    [0009] FIGS. 8 to 12 show another method of integrating an instrumented rod 92 into an annular duct of a secondary air flow of a turbojet engine already described with reference to FIG. 1. Although not shown in FIG. Figures 8 to 12, the inner end 93 of the rod 92 is offset axially with respect to its outer end. The rod also comprises an inner end 93 connected to the rest of the rod 92 by a shoulder 94. In this embodiment and unlike the previous embodiment, the shoe 95 comprises a first portion 96 and a second portion 97.
    [0010] The first shoe portion 96 includes a base 98 upstream and a downstream portion or downstream handle 99 extending outwardly in the direction 51. The inner surface of the base 98 includes an axial groove 100. The base 96 also includes a radial orifice 101 therethrough and opening internally in the bottom wall of the groove 100. The handle 99 comprises a recess 102 U open downstream and communicating internally with the downstream end of the groove 100. The base 98 comprises an outer surface of which a first upstream surface portion 103 arranged axially between the upstream end of the base 98 and the orifice 101 is substantially flat and two second portions of lateral surfaces 104 substantially convex. In a plane containing the axial axis 55 and the radial axis 33, the first surface portion 103 has an inclination with the internal surface of the base 98 which is such that the air impacting this external surface 103 is not deflected towards the nozzles 52 of the inner end of the rod 92.
    [0011] The second shoe portion 97 has an L shape formed of a downstream flange 105 extending outwardly in the aforesaid direction 51 and a wall 106 extending axially upstream from the downstream flange. 105 and intended to engage axially in the groove 100 of the inner face of the base 98. The thickness of the axial wall 106 of the second shoe portion 97 is greater than the depth of the groove 100 so as to allow tightening of this axial wall 106 between the base 98 and the inner ferrule 30 (FIG. 11C and FIG. 12). The upstream end of the axial wall 106 of the second shoe portion 97 comprises an orifice 107. According to the invention, the U-shaped recess 102 of the handle 99 and the downstream rim 105 of the second shoe portion 97 define a housing. in which is slidably engaged the inner end 93 of the rod 92 as shown in Figures 10 and 11C. The inner end 93 of the rod 92 is mounted in the housing with an initial clearance to the assembly J with the axial wall 106 of the second portion 97 of the shoe. This game J can be for example of the order of three millimeters. The assembly of the inner end 93 of the rod 92 with the shoe 95 is made in the following manner. The first shoe portion 96 is axially displaced downstream so that the inner end 93 of the rod 92 fits into the U-shaped downstream recess 102 of the handle 99 of the first shoe portion 96. shoulder 94 of the rod 92 coming opposite the outer edge 108 of the handle (FIG. 10 and FIG. 11A). Simultaneously with the previous step, the second shoe portion 97 is engaged axially from upstream so that its axial wall 106 is housed in the groove 100 of the inner surface of the base 98 20 (Figure 11B). In the mounting position (FIG. 11C), the axis of the orifice 101 of the base 98 and the axis of the orifice 107 of the second shoe portion 97 are aligned radially. As can be seen in FIGS. 11A, 11B, 11C and more precisely in FIG. 12, the hole 101 of the base 98 has a first outer portion 109 of larger diameter than the second inner portion 110 so that a head of a fixing screw can be housed integrally and thus avoid impacting the flow of air flowing in the secondary vein. The second portion 110 of the hole 101 of the base 98 has a diameter identical to the orifice 107 of the axial wall 106 of the second portion 97 of the shoe.
    [0012] The connecting means of the outer end of the rod 92 to the outer casing can be in all respects similar to those exposed in relation to the previous embodiment. In this second embodiment, the rod 92 also extends in the first given direction 51 having a component along a radial axis 53 and a component along an axial axis 55. The instrumented rod 92 is movable in translation only in the direction given 51, the movement only in the second direction 111 substantially perpendicular to the first direction 51 is prevented by the downstream handle 99 and the downstream flange 105. It is understood that the first direction extends substantially along an average line of the rod 50 92. The invention is of course applicable to a rod which would not be rectilinear as in the embodiments shown in the figures and which would have, for example, corrugations between its inner and outer ends. Although the description here is made in connection with an annular vein of the type that can be found in a turbomachine, it is clear that the invention also applies, as it seems obvious to the skilled person, any vein bounded transversely by two walls, or for example by a single annular wall, and within which the instrumented shaft will be arranged as described above.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. Annular vein (33) for the air flow of a turbomachine, such as a turbojet engine or a turboprop engine, provided with an instrumented rod (50) which passes through it and which comprises means for measuring characteristics of a flow being able to traverse the vein, said rod extending between an outer annular wall (48) and an internal annular wall (42) of the vein, characterized in that external connecting means (60, 86) fix an outer end (58). ) of the instrumented shaft to the outer wall rigidly in all directions, and internal connecting means (95) attaching an inner end (93) of the instrumented shaft to the inner wall, rigidly in the circumferential direction of the vein and with a degree of freedom in displacement only in a given direction (51) extending between the inner (42) and outer (48) walls of the vein and having at least one radial component.
    [0002]
    2. A vein according to claim 1, wherein the internal connecting means comprise a shoe (95) rigidly fixed to the inner wall (42), and rigidly fixed to the inner end (93) of the instrumented rod (92) in the circumferential direction, and with a degree of freedom in displacement only in a given direction (51) extending between the inner (42) and outer (48) walls and having at least one radial component.
    [0003]
    3. A vein according to claim 2, wherein the shoe (62) and the inner end (93) of the instrumented rod (92) are slidably engaged with each other in said given direction (51).
    [0004]
    4. Vein according to claim 3, wherein the shoe comprises a first shoe portion (96) and a second shoe portion (97) integral with one another and defining a housing in which said inner end (93). the rod (92) is able to move in said given direction (51). 3036735 15
    [0005]
    5. A vein according to claim 4, wherein the housing is delimited by a recess (102) U open downstream of the first portion (96) of shoe and a downstream flange (105) extending towards the outside the second shoe part (97). 5
    [0006]
    A vein according to claim 5, wherein the second shoe portion (97) is L-shaped with an axial wall (106) carrying the downstream flange (105) extending between the first shoe portion (96). and the inner wall (42).
    [0007]
    7. A vein according to claim 6, wherein the axial wall of the second shoe portion (97) is axially engaged in an axial groove (100) of an inner face of the first shoe portion (96).
    [0008]
    8. A vein according to claim 7, wherein the thickness of said axial wall (106) is greater than the depth of said axial groove (100). 15
    [0009]
    9. Vein according to one of claims 4 to 8, wherein the inner end (93) of the rod (92) is mounted with a clearance J, for example three millimeters, with the second portion (97) of hoof .
    [0010]
    10. Vein according to one of claims 2 to 9, wherein the shoe (97) is rigidly attached to a first ferrule (42) forming the inner wall of the vein (33), said ferrule being arranged downstream of an annular array of vanes extending through the vein and upstream of a second air-vented ferrule (40), and wherein the outer end (58) of the rod (92) is fixed relative to the outer wall downstream of said row of vanes. 25
    [0011]
    11. Turbomachine, such as a turbojet or a turboprop, characterized in that it comprises a vein according to one of the preceding claims.
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    引用文献:
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    法律状态:
    2016-05-17| PLFP| Fee payment|Year of fee payment: 2 |
    2016-12-02| PLSC| Search report ready|Effective date: 20161202 |
    2017-04-13| PLFP| Fee payment|Year of fee payment: 3 |
    2018-04-23| PLFP| Fee payment|Year of fee payment: 4 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 6 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1554724|2015-05-26|
    FR1554724A|FR3036735B1|2015-05-26|2015-05-26|INSTRUMENTED VEIN OF TURBOMACHINE|FR1554724A| FR3036735B1|2015-05-26|2015-05-26|INSTRUMENTED VEIN OF TURBOMACHINE|
    US14/722,877| US9856743B2|2014-05-28|2015-05-27|Instrumented flow passage of a turbine engine|
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