• 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:
    Is concerned a radial diffuser (12) for the air supply of a combustion chamber in a turbomachine, the radial diffuser comprising two annular flanges (22, 24) connected by blades (26) which are fixed to the at least one of said flanges by brazing alloys, characterized in that the brazing alloys are ductile.
    公开号:FR3024887A1
    申请号:FR1457848
    申请日:2014-08-15
    公开日:2016-02-19
    发明作者:Cedric Louis Joseph Laurent；Laurent Donatien Behaghel；Sebastien Marcelino Juste；Pauline Anne Lancesseur
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The invention relates to a radial diffuser for supplying air to a combustion chamber in a turbomachine such as an airplane turbojet or turboprop engine. In some embodiments, the last stage of the supply compressor (high pressure, HP) in a turbomachine is a centrifugal stage whose output is surrounded by a radial annular diffuser. This diffuser is connected at the output to an axial diffuser, a priori annular and cylindrical, which feeds an annular combustion chamber. The manufacture of the respectively radial and axial diffusers poses a certain number of problems. Indeed, in solutions already proposed, at least part of all of these two diffusers is cut in the mass, the other part being made of foundry or mechanically welded and fixed by bolting to the first part or to a crankcase. However, the small thickness of the blades and flanges and ferrules makes it very difficult to achieve these parts, which results in waste rates in manufacturing too high, or problems of supply and significant cost.
    [0002] It has already been proposed in EP1882821, in particular a radial diffuser for the air supply of a combustion chamber in a turbomachine, the radial diffuser having two annular flanges connected by blades which are fixed to the at least one of said flanges by brazing alloys.
    [0003] The solders then serve as a method of assembly between the flange or plates and the blades, as well as sealing at their interfaces. In this context, solder alloys containing the relatively high concentrations of titanium are known. Typically, the titanium content is greater than about 7% by weight. These alloys are rigid, hard, and during soldering, a brittle dispersed phase is present.
    [0004] 3024 887 2 This technology and method of assembly works well on centrifugal stage diffusers of less mechanically stressed helicopter engines than aircraft turbine engines. This is less convincing if high temperatures encountered in operation (more than 500, see 550 ° C) lead to a high level of localized stress on the solder at the junction of the two flanges, upstream and downstream of the blades which connect them. The level of stress may not be compatible with the mechanical strength of the solder, which is a fragile material. This high level of stress can then lead to cracks in the solder, which may spread and lead to the dissociation of the flanges in operation, which is not acceptable. The object of the invention is in particular to provide a simple, satisfactory and economical solution to this problem.
    [0005] It proposes for this purpose that the brazing alloys used for the abovementioned solders are ductile. Examples of such ductile brazing alloys can be found in EP 0104623 or EP 0185954. Up to now, on an aircraft engine, in particular a turbojet or turboprop, it has been considered that a radial diffuser, which is a part noticeably stressed in temperature (more than 500 or 550 ° C) and in various mechanical stresses, retained a quality of manufacture and durability in operation with traditional solders, therefore non-ductile.
    [0006] Assembling a radial diffuser using ductile solders thus goes against current prejudices, to the knowledge of the inventors where the mechanical strength at the location of the braze itself is a decisive criterion. In the present case, on the contrary, it is accepted that the solder is "softer", with a lower mechanical strength, but a plasticizing capacity 3024887 3 during a mechanical stress. The deformations are accepted, without breaking, and the seal is then preserved. According to another characteristic of the invention, the or each said annular flange to which the blades are attached comprises openings which at least one of the ends of the blades passes through and where the ductile brazing alloys are located. Such engagement blades in such openings will promote stability of these blades and thus increased safety as to the holding of solders. By a relatively tight engagement of the blades, they will be mechanically secured, and all the more with such an arrangement on the flange concerned, or even the two flanges: upstream and downstream. In the latter case, the upstream commitment will secure (participate in maintaining) the downstream solder and vice versa. It is the same if, as advised, the ends of the blades which pass through the openings define local growths on the blades. The blades will be reinforced. An advantage can also be derived from this blade end engagement in openings. Indeed, by extending the ends of the blades which pass through the openings beyond the openings and the opposite face of the or each annular flange, it will be possible to make these blade ends are retained at the same time. against their withdrawal out of the openings by means of mechanical assembly. Thus, beyond the support that the blade finds in its opening, these 25 mechanical assembly means will promote the retention of the blade and thus prevent any spacing of the flanges relative to each other, if necessary was. In addition, this restraint will promote the control of the axial prestressing to ensure that the two flanges and the blades, laterally, are well plated together. The control of the vein height will be secured, which is important for the aerodynamic performance of the radial diffuser.
    [0007] For the sake of practicality, efficient and safe maintenance, simplicity of implementation and control of costs and implementation times, it is furthermore recommended that, if the aforementioned mechanical assembly means are actually provided, such as Advantageously, these comprise tabs engaged in orifices, grooves or notches formed through the ends of the blades. In this case, to further secure the maintenance, while anticipating a possible maintenance requiring removal of the tabs, it is preferably provided that the tabs are engaged transversely to the direction in which the ends of the blades pass through the openings, or that the legs are engaged obliquely in the notches. Providing curved legs, for example L, belonging to a ring coaxial to the annular flanges and along which said tabs will be distributed will engage (or even release for maintenance) 15 the legs together, in a single rotational movement of the ring vis-à-vis the engagement passages of these legs. In addition to the aforementioned radial diffuser, the assembly comprising this radial diffuser and an axial diffuser arranged at the outlet of the radial diffuser, at least the brazing alloy used in the radial diffuser for attachment to its blades, are also concerned. at least one flange being ductile. In addition, the turbomachine, such as the turbojet engine or the turboprop engine in question, which will be equipped with the aforementioned radial diffuser, isolated or in combination with the axial diffuser which is adjacent thereto, is also concerned.
    [0008] The invention will be better understood and other characteristics, details and advantages thereof will appear more clearly on reading the description which follows, given by way of example with reference to the appended drawings in which: FIG. 1 is a schematic view in axial section of a diffuser assembly according to the invention; - Figures 2,3 are two schematic perspective views of a portion of the radial diffuser showing, for Figure 3, a prestressed engagement of a few blades of the radial diffuser; and FIGS. 4,5,6,7,8,9,10,11 are diagrammatic perspective views which, partly by transparency, show several versions of maintaining the engagement of the blades of the radial diffuser, here with respect to one of the two flanges, Figures 9-11 relating to the same solution. In the figures, the dashed parts or lines refer to hidden areas, the lines continuous to visible areas.
    [0009] The assembly 10 shown in FIG. 1 comprises a radial annular diffuser 12 connected at the output to an annular axial diffuser (or straightener) 14 which may be cylindrical. The term "axial" is appreciated with respect to the axis 1 of the turbomachine 15 in question here, which is the axis of rotation of the compressor and the one about which the upstream annular flange 22 and the downstream annular flange 24 are centered. below. The "radial" direction is substantially and globally perpendicular thereto. The assembly 10 is intended to be mounted at the output of the last centrifugal stage 16 of an aircraft HP compressor belonging to a turbojet engine 20 or turboprop. This stage comprises a wheel 17 for rotating along the axis 1 of rotation of the compressor. The inlet 18 of the radial diffuser 12 is radially aligned with the outlet of the centrifugal stage 16, the outlet 19 of the axial diffuser 14 supplying gas 25 to an annular combustion chamber 20, in a manner known to those skilled in the art . The radial diffuser 12 comprises an upstream annular flange 22 and a downstream annular flange 24, which are substantially parallel and extend annularly around the axis of rotation 1 of the compressor and which are interconnected by blades 26; see figure 2.
    [0010] The expressions upstream (AM) and downstream (AV) are to be considered in relation to the overall direction of flow of the gases flowing from upstream to downstream according to the arrow 23 of FIG. 1. The blades 26 are preferably with a substantially helical orientation around the axis of rotation 1 of the compressor. The axial diffuser 14 comprises two cylindrical outer cylinders 28 and inner 30, which are coaxial, arranged one inside the other and connected by blades 32 substantially radial.
    [0011] The annular flanges 22 and 24 of the radial diffuser and the cylindrical shells 28 and 30 of the axial diffuser are formed of thin members of thickness, such as sheets or thinned parts cut into the mass (metal, typically steel), to which the ends of the The blades 26 and 32, respectively, are fixed or with which one of these ends is integrally joined (typically due to mass production in accordance with an important characteristic mentioned above with respect to the radial diffuser 12, its blades 26 are fixed by ductile solders to at least one of the faces of at least one of the upstream and downstream flanges 24 (see 20 marks 33 FIGS. 4 to 7), after at least one of the ends of the flanges. 26 blades has been engaged in openings made to the shape of the relevant end of the blades 26, such as openings 34 of Figure 2 formed in the flange 22. Certainly, the two flanges 22 and 24 may be well 25 but it may be advantageous that only these flanges is concerned (as the upstream flange in Figure 2) by fixing via the solder. For the other side (as the downstream flange 24 in Figure 2), the blades and the flange can be cut together in the mass. The flange concerned and the blades 26 will then be monoblock, made in one piece, on this side (see zones of structural continuity in FIG. 2).
    [0012] An advantage can be found in this, since the one-piece manufacture retains the integrity of the block from which this flange-blade unit assembly is manufactured. It will indeed be possible to apply axial prestressing only between the other flange and these blades. In addition, it will be possible to take advantage of the relative flexibility of the blades towards their free end, where the ductile solders are to be realized. As shown in FIG. 1, an elbow here makes it possible to connect the flanges 22, 24 of the radial diffuser and the annular ferrules, respectively outer 28 and inner 30, of the axial diffuser 14. These rounded walls allow the air supplied into the diffuser 12 to move from a generally radial circulation to a generally axial circulation, before being thus guided by the axial blades 32 of the diffuser 14. To its radially inner end, the downstream flange 24 can be connected to one or more annular rings downstream here, two concentric ferrules 44 and 46. As for the upstream annular flange 22, it is provided with an upstream annular ferrule 48. In the embodiment shown, this upstream annular ferrule 48 is located towards the radially inner end of the flange 22 and is connected to it by welding. The upstream collar 48 is equipped at its free end with a fastening flange 50. At the location of this fastening flange 50, are fixed together by bolting (reference 51 fig.1), the radial diffuser 12, a flange Intermediate 52 so-called CoHP (very massive and protected from the primary vein and which therefore slowly heats) and a cover 54 of wheel 17.
    [0013] However, the high temperatures encountered during operation lead to a high level of stress on the solders at the junction of the two flanges 22, 24, on the side of both the inlet (radially inner side, towards the zone 18) and the gas outlet of the blades 26. It is in particular in order to mitigate the risk of cracks in the solders resulting therefrom, or even consequences even more damaging, that the choice of fixing by ductile soldering of the blades 26 3024887 8 flanges upstream 22 and downstream 24 (or at least one of them) was retained. Two examples of alloys for such a solder are briefly presented below: - as described in EP 0104623, it is possible to use a solder alloy comprising between 0.25 and 5% of a reactive metal selected from the group consisting of titanium, vanadium, zirconium and mixtures thereof, between 25 and 85% by weight of a precious metal selected from the group consisting of gold, palladium and mixtures thereof, between 15 and 70 % By weight of copper as the third metal, optionally between 2 and 15% by weight of chromium as the fourth metal, and incidental impurities, or, as described in EP 0185954, use of ductile solder sheets quenched rapidly before a microcrystalline structure based on an alloy composed essentially of 6.5 to 8% by weight of titanium, up to 44% by weight of silver, the balance being copper. And it is for the mechanical quality of this flange (s) / blade attachment that, as illustrated in FIG. 2 and following for the upstream side of these blades 26, at least one of the upstream and downstream ends of said blades defines local excrescences 260 on the blades, these protrusions passing through the openings 34 and extending opposite side of the flanges or. As for the requirement to ensure optimized mastery of the vein height (H) parallel to the axis 1, with blades 26 and flange (s) 22 and / or 24 clad together at least one of these upstream and downstream sides of said blades, it is satisfied by providing that the ends of the blades passing through the openings 34 extend beyond these openings and the opposite face of the flange (s) and that these ends of blades will be retained against their withdrawal out of the openings by the mechanical assembly means 56.
    [0014] Figures 3 and following schematize several solutions concerning this mechanical assembly, via the means 56.
    [0015] In these figures, the assembly means 56 comprise tabs 57 engaged in either orifices 59 (FIGS. 6-8), grooves 61 (FIGS. 4,5) or notches 63 (FIGS. 9-10) formed. through the ends of the blades.
    [0016] In these figures, it can be seen that the orifices 59, grooves 61 and notches 63 are formed flush with the upstream surface 220 of the upstream flange 22 in such a way as to axially press together the flange (s) and blades, it being specified that it is preferably the same downstream side (downstream surface of the downstream flange), then concerning the relative position between the orifices, grooves and notches concerned and the downstream surface 240 of the downstream flange 24. For a favorable range and practical handling, it is recommended, in the solutions of FIGS. 3 to 8, that the tabs 57 are engaged transversely, and here perpendicularly, to the direction in which the ends of the blades 26 pass through the openings 34. Here again, what is made on one side (upstream or downstream) is preferably provided on both sides. In the solutions of FIGS. 9-11, the tabs 57 are biased in the notches 63. Indeed, in this case, the tabs, which are curved, for example in L, belong to a ring 570 along which said legs are distributed, circumferentially. The ring 570, which is closed on itself, is coaxial with the two upstream and downstream flanges 22, 24. Around the ring 570, all the tabs are bent in the same direction (see FIG. 11). And these tabs project from the ring parallel to the axis 1.
    [0017] All the more from the view of the figures, it will be understood that, on the considered side, the engagement of the hook of one of the tabs 57 in one of the notches 63 will imply that of the other tabs in the other circumferential notches. This will simplify and secure the implementation.
    [0018] It will also be possible to use together the two aforementioned categories of solutions, and in particular the ring 570 with hooks for the 3024887 10 blades located (the most) near the inner circumference 221,241 of the upstream flasks and / or or downstream 22, 24, and the solution of the orifices 59 or grooves 61, for the others. Thus, we will combine the best efficiency, practicality and safety.
    [0019] It is understood that the shapes of the orifices 59, grooves 61 and notches 63 and those of the legs 57 will be matched, the latter must engage without significant play, since it is a question of tightly locking the blades and flange (s). ), in axial prestressing. 4 and 5, a form of slat tab or plate, 572, 10 allows, with a groove 61 correspondingly elongate, parallel to the relevant surface of the flange against which the tab supports, to have to engage only one leg per blade, per side, with a good compromise between a limited weakening of the blade and an extended contact blade / leg. Figures 6-8, the tabs are shown as pins 574 engaged side by side in the orifices 59 fig.8). In the preferred example, there are, for a local outgrowth 260, two pins in two orifices 59 located side by side along the length of the outgrowth. 6, the pins 574 are two individual pins each engaged, for this group, in one of the two orifices 59 of the outgrowth.
    [0020] Figure 7 shows the same orifices, but with pins joined at one end by a bar 576 which secures them together. This can facilitate the engagement of the pieces, the bar allowing a joint action here on the two pieces. For overall strength, it is recommended that the material of the legs and blades be the same. By such an exclusively mechanical blade / flange assembly, it will therefore be easily possible to constrain, and even pre-constrain from the original assembly, the flange (s) 22,24 axially, by distributing the stress on many areas of the flange (see Figure 2) so over a large area, the combination of all or part of the technological solutions presented in this respect with the ductile solder solution 3024887 11 blade tip and at the mounting tabs to ensure sealing, in addition. In addition, brazing blade and flange on one side of the flange and engage the tab in its hole, its groove or notch, on the other side of the same flange, avoids interfering the two solutions that remain complementary, preferably . By way of just complementary use, it is also worthwhile to associate such a radial diffuser 12 with the aforementioned axial diffuser 14, or even to apply all or part of this technique of mechanical assembly in prestressing and of ductile soldering to blades 32 and ferrule (s) 28, 30 of the axial diffuser.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. Radial diffuser (12) for supplying air to a combustion chamber in a turbomachine, the radial diffuser comprising two annular flanges (22, 24) connected by blades (26) which are attached to at least one said flanges by brazing alloys, characterized in that the brazing alloys (33) are ductile.
    [0002]
    2. Radial diffuser according to claim 1, wherein the or each annular flange (22, 24) to which the blades (26) are fixed comprises openings (34) which at least one of the ends of the blades (26) passes through and where the ductile brazing alloys are located.
    [0003]
    3. radial diffuser according to claim 2 wherein the ends of the blades passing through the openings (34) define local growths (260) on the blades.
    [0004]
    4. Radial diffuser according to claim 2 or 3, wherein the ends of the blades (26) passing through the openings (34) extend beyond the openings and the opposite face of the or each annular flange (22, 24). ) to which are fixed the blades (26), and these blade ends are retained against their removal from the openings by means (56) of mechanical assembly.
    [0005]
    5. Radial diffuser according to one of claims 1 to 4, wherein only one of the two annular flanges (22, 24) is fixed to the blades (26) by the ductile brazing alloys, the other annular flange (22). 24) and the blades (26) being integral.
    [0006]
    6. radial diffuser according to claim 4 or claims 4 and 5, wherein the mechanical assembly means comprise lugs (57) engaged in orifices (59), grooves (61) or notches (63) formed through the ends of the blades.
    [0007]
    7. Radial diffuser according to claim 6, wherein the tabs (57) are engaged transversely to the direction in which the ends 3024887 13 of the blades pass through the openings (34), or the tabs are engaged obliquely in the notches (63). .
    [0008]
    8. A radial diffuser according to claim 6 or 7, wherein the tabs (57) are curved, for example L-shaped, and belong to a ring (570) which is coaxial with the annular flanges (22, 24) and along which said legs are distributed.
    [0009]
    9. Radial diffuser according to claim 6 or 7, wherein the tabs are at least some of: pions (574) individually engaged side by side, in groups, in the orifices (59), pions ( 574) joined by a bar (576) and individually engaged side by side in the orifices (59), and - slats (572) each engaged in one of the grooves (61).
    [0010]
    10. Diffuser assembly (10) for supplying air to a combustion chamber in a turbomachine, this assembly comprising a radial diffuser (12) and an axial diffuser (14) arranged at the outlet of the radial diffuser, characterized in that the radial diffuser is in accordance with that of any of claims 1 to 9.
    [0011]
    11. Turbomachine, such as a turbojet or turboprop aircraft, characterized in that it comprises a radial diffuser (12) according to one of claims 1 to 9 or a diffuser assembly (10) according to claim 10.
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3024887A1|2016-02-19|RADIAL DIFFUSER WITH DUCTILE FASTENING
    EP3390783B1|2019-10-02|Turbine shroud assembly and corresponding turbine
    WO2017103411A2|2017-06-22|Turbine ring assembly, elastically retained in a cold-state
    FR3036435A1|2016-11-25|TURBINE RING ASSEMBLY
    EP3433471B1|2020-01-29|Turbine shroud seal assembly with specific support in cold conditions
    FR2920328A1|2009-03-06|WELDING DISPENSER BLADE FOR STEAM TURBINE AND BONDED ASSEMBLY ASSEMBLIES.
    WO2010026181A1|2010-03-11|Method for making a circular revolution thermomechanical part comprising a carrier substrate containing titanium coated with steel or a superalloy, and titanium fire-resistant compressor casing for a turbine engine obtained by said method
    FR3056637A1|2018-03-30|TURBINE RING ASSEMBLY WITH COLD SETTING
    EP2795068B1|2021-07-14|Turbomachine compressor guide vanes assembly
    FR3034129A1|2016-09-30|MOBILE TURBINE AUB WITH IMPROVED DESIGN FOR AN AIRCRAFT TURBOMACHINE
    FR3080146A1|2019-10-18|CMC DISPENSER WITH EFFORT REPEAT
    EP2326845B1|2017-05-17|Compressor casing resistant to titanium fire, high pressure compressor including such a casing, and aircraft engine including such a compressor
    FR3005693A1|2014-11-21|DOUBLE-FLOW AIRCRAFT TURBOMACHINE COMPRISING AN INTER-VEIN VIOLINE WITH SIMPLIFIED HOLD
    FR2965843A1|2012-04-13|ROTOR FOR TURBOMACHINE
    FR2953250A1|2011-06-03|Rotor for low pressure turbine of turbo machine i.e. twin-shaft gas turbine engine, has air fixture comprising holes formed in distributed manner in ferrules of downstream disk to supply air from central opening to slide connections
    FR3017928B1|2019-07-26|TURBOMACHINE WITH EXTERNAL FLANGE OF "SANDWICH" COMBUSTION CHAMBER
    FR2963060A1|2012-01-27|STEAM DIVIDER ASSEMBLY FOR STEAM TURBOMACHINE AND PROCESS
    FR2950116A1|2011-03-18|Rectifier stage for use in high pressure compressor of e.g. turbojet engine of aircraft, has fixation unit fixing blade tip in mortise of outer shell, where fixation unit is in form of seal made of vibration damping material
    EP2031255B1|2015-12-23|Vane, collar and assembly for synchronising ring stage of a compressor, turbomachine comprising such a compressor and method of assembly by welding between a collar and a vane.
    WO2020065199A1|2020-04-02|Assembly for a turbomachine turbine and associated turbomachine
    WO2020224891A1|2020-11-12|Turbine ring assembly mounted on a cross-member
    FR3107725A1|2021-09-03|Assembly for an aircraft turbomachine stator, with reinforced sealing between an outer shell and a bladed stator ring surrounded by this shell
    FR3098246A1|2021-01-08|Turbomachine turbine with CMC distributor with load recovery
    WO2019141918A1|2019-07-25|Turbomachine ring
    FR3098849A1|2021-01-22|Improved aircraft module housing
    同族专利:
    公开号 | 公开日
    FR3024887B1|2018-12-07|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20050158173A1|2004-01-15|2005-07-21|Honeywell International Inc.|Performance and durability improvement in compressor structure design|
    EP1882821A1|2006-07-19|2008-01-30|Snecma|Nozzle-synchronising ring assembly for a turbomachine|
    FR2960603A1|2010-05-27|2011-12-02|Turbomeca|Radial diffuser for turboshaft engine e.g. turbojet of airplane, has slots whose shape and positioning are complementary to that of projecting portions such that projecting portions are embedded into slots|
    FR2987570A1|2012-03-02|2013-09-06|Snecma|METHOD FOR ASSEMBLING TWO METAL PIECES BY BRAZING|CN108691807A|2017-04-10|2018-10-23|清华大学|Aero-engine, centrifugal compressor and its diffuser structure|
    CN109281871A|2018-10-22|2019-01-29|沈阳透平机械股份有限公司|Space division casing inlet dwell guide-ring structure|
    CN111520362A|2020-04-28|2020-08-11|中国航发湖南动力机械研究所|Diffuser, centrifugal compressor and assembling process of diffuser|
    US11098730B2|2019-04-12|2021-08-24|Rolls-Royce Corporation|Deswirler assembly for a centrifugal compressor|
    US11187243B2|2015-10-08|2021-11-30|Rolls-Royce Deutschland Ltd & Co Kg|Diffusor for a radial compressor, radial compressor and turbo engine with radial compressor|
    法律状态:
    2015-08-11| PLFP| Fee payment|Year of fee payment: 2 |
    2016-02-19| PLSC| Search report ready|Effective date: 20160219 |
    2016-08-04| PLFP| Fee payment|Year of fee payment: 3 |
    2017-05-15| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-07-20| PLFP| Fee payment|Year of fee payment: 5 |
    2019-07-22| PLFP| Fee payment|Year of fee payment: 6 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 7 |
    2021-07-22| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1457848A|FR3024887B1|2014-08-15|2014-08-15|RADIAL DIFFUSER WITH DUCTILE FASTENING|
    FR1457848|2014-08-15|FR1457848A| FR3024887B1|2014-08-15|2014-08-15|RADIAL DIFFUSER WITH DUCTILE FASTENING|
    [返回顶部]