• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a combustion chamber for a turbomachine, such as an airplane turbojet or turboprop engine, comprising an inner annular shroud (12) and an outer annular shroud (14) connected at their upstream ends by an annular wall of chamber base (48), said chamber having baffles (50) mounted downstream of the annular bottom wall (48). Injectors (19) are mounted in sleeves (44), at least one of which comprises a radial annular flange (66) which is arranged to slide radially between the chamber bottom (48) and the deflector (50) and which is axially locked. between the chamber bottom (48) and the deflector (50).
    公开号:FR3026827A1
    申请号:FR1459362
    申请日:2014-10-01
    公开日:2016-04-08
    发明作者:Romain Nicolas Lunel；Thomas Olivier Marie Noel；Matthieu Francois Rullaud
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a combustion chamber in a turbomachine, and a turbomachine equipped with a combustion chamber.
    [0002] In a known manner, an annular combustion chamber comprises two inner and outer coaxial annular shrouds, connected to each other at their upstream ends by an annular so-called bottom wall having injector head passage openings. Each injector is engaged in a centering sleeve which is movable radially in support means integral with the chamber bottom. In the current technique, the sleeve carries at its downstream end an annular flange extending radially outward and slidably mounted in an annular groove formed in support means integral with the annular wall of the chamber bottom. The annular groove allows a radial and circumferential displacement of the sleeve housing the injector to compensate for manufacturing tolerances that can lead to misalignment of the injector with the fuel injection axis between the inner and outer rings of the combustion chamber. It also makes it possible to compensate for differential expansions in operation between the injector and the chamber. The annular groove of radial displacement of the sleeve is defined by means of retaining axially upstream and downstream of the radial annular collar. In practice, the axially downstream retaining means 25 are formed by a downstream radial annular wall of an annular sheath fixed on the annular chamber bottom, the radial annular wall being connected to a cylindrical flange extending towards the upstream and on which is fixed by welding or brazing a washer attached to the cylindrical rim and defining with the radial annular wall the aforementioned groove.
    [0003] This washer is thus fixed releasably on the sheath. In the case where it is necessary to disassemble the injector and the sleeve, it is necessary to desolder or remove the braze of the washer, which is a delicate operation because the sleeve which is fixed on the annular wall of chamber floor should not be damaged. Furthermore, it has been found breaks welding seams, which is not permissible, and does not ensure a perfect mechanical integrity of the fuel injection systems. The invention aims in particular to provide a simple, effective and economical solution to the problems of the prior art described above. For this purpose, it proposes a combustion chamber for a turbomachine, such as a turbojet or an airplane turboprop, comprising an inner annular shell and an outer annular shell 15 connected at their upstream ends by an annular wall of the bottom of the chamber. , said chamber comprising baffles mounted downstream of the annular bottom wall of the chamber, injectors being mounted in sleeves, at least one of which comprises a radial annular flange arranged to slide radially between the chamber bottom and the deflector and axially locked between the chamber floor and the deflector. The invention makes it possible to eliminate the fixing sleeve of each injector and thus to reduce the mass of the combustion chamber. According to the invention, the axial spacing between the baffle and the annular chamber bottom wall serves to accommodate the flange of the sleeve which can slide there radially freely, which also reduces the axial size of the combustion chamber. using said spacing that was not used in the prior art. According to another characteristic of the invention, the combustion chamber comprises first means for rotating the sleeve on the deflector and second means for rotating the deflector against the chamber bottom. The anti-rotation of the sleeve relative to the axis of the injector is thus achieved by means of the deflector itself locked in rotation on the annular wall of the chamber bottom. In one embodiment of the invention, the collar carries at least one radially outwardly projecting member arranged axially between the annular chamber bottom and the deflector for axial locking of the sleeve on the chamber bottom and the deflector. Preferably, the first rotational abutment means comprise a radial groove formed on the upstream face of the deflector and in which said member is engaged. According to another characteristic of the invention, the baffle comprises a central annular wall of axis that of the injector and extending axially upstream and passing through a passage opening of an injector of the annular bottom wall. chamber, said annular wall of the baffle comprising a mounting slot axially sliding the flange into said groove of the baffle. Advantageously, the second rotational abutment means comprise a lug formed on the inner peripheral edge of said opening of the chamber bottom and projecting radially inwards in said notch. According to yet another characteristic of the invention, a ring is screwed onto the outer periphery of the central annular wall and applied on the periphery of the upstream face of the opening of the chamber bottom. This assembly ensures an axial locking of the deflector on the annular wall of the chamber bottom. The ring may be welded to the annular wall of the baffle to prevent unscrewing during operation of the ring. The sleeve may comprise two members each forming a tab extending radially outwardly, preferably diametrically opposite to each other. The annular bottom wall of the chamber and the baffle advantageously comprise ventilation air passage bores.
    [0004] Preferably, the annular collar comprises an annular row of orifices whose axes open towards a radial annular rim of the sleeve which is arranged downstream. The orifices of the collar make it possible to cool the radial annular flange efficiently because of the orientation of the axes of the orifices perpendicular to the radial flange and the reduced distance between the flange and the radial annular flange. The invention also relates to a turbomachine, such as a turbojet engine or a turboprop engine, comprising a combustion chamber as above. The invention will be better understood and other details, advantages and characteristics of the invention will become apparent on reading the following description given by way of nonlimiting example, with reference to the appended drawings, in which: FIG. schematic view in axial section of the upstream portion of a combustion chamber according to the prior art; Figure 2 is a schematic axial sectional view of the upstream portion of a combustion chamber according to the invention; Figure 3 is a diagrammatic perspective view from upstream in section along a passing plane containing the axis of an injector and the axis of the combustion chamber; Figure 4 is a schematic perspective view from upstream of an injection device in a combustion chamber according to the invention; Figure 5 is a schematic perspective view of a deflector 25 alone; Figure 6 is a schematic perspective view of a centering sleeve of an injector and an associated deflector; Figure 7 is a schematic perspective view similar to Figure 4 without the clamping ring; Referring first to FIG. 1 which represents the upstream portion of a turbomachine combustion chamber 10 according to the known technique comprising two inner and outer annular rings 12 extending around the axis 16 of the combustion chamber 10 and fixed at their upstream ends on an annular bottom wall of the chamber 18 extending between the walls of internal revolution 12 and external 14 and traversed by fuel injectors 19 axis 21. The annular chamber bottom 18 comprises a radial annular wall 20 connected at its radially outer periphery to an outer cylindrical rim 22 extending upstream and fixed on the upstream end of the outer shell 14. The radial annular wall 20 of the chamber bottom 18 is connected to its radially inner periphery with an internal cylindrical rim 26 extending upstream and fixed on the upstream end of the inner shell 12. The radial annular wall of the chamber bottom 18 includes nd a plurality of openings each aligned with an opening of a deflector 28 arranged downstream of the radial annular wall 20 of the chamber bottom 18.
    [0005] The deflectors 28 are intended to protect the chamber bottom 18 of the flame formed downstream between the inner and outer shells 12 and 14. Each injector 19 is engaged axially in freely radially displaceable centering means in support means 32 secured to the annular chamber bottom 18.
    [0006] The support means 32 of each injector 19 comprise a sheath formed of a radial annular wall 34 fixed around the passage opening of the injector 19 and on the upstream face of the radial annular wall 20 of the chamber floor 18. The radial annular wall 34 is connected at its radially outer end to a cylindrical rim 36 extending upstream. In the prior art (Figure 1), for each injection system, a washer 38 is fixed by welding or brazing its radially outer periphery on the upstream end of the cylindrical rim 36 of the sleeve.
    [0007] In the known art, the centering means of each injector 19 comprise a cylindrical portion 40 traversed axially by the head of the injector 19 and connected downstream to an annular flange 42 extending radially outwardly and mounted with radial sliding in the annular groove delimited upstream by the washer 38 and downstream by the radial annular wall 34. The bottom of the groove is delimited externally by the cylindrical rim 36. As explained in the foregoing, the weld beads that hold the washers 38 can be weakened and are thus liable to break in operation, which impacts the injection of fuel between the walls of internal revolution 12 and external 14.
    [0008] According to the invention described with reference to FIGS. 3 to 7, each injector is engaged in a sleeve 44 which is engaged in radial sliding between the radial annular wall 46 of the chamber bottom 48 and the deflector 50 and which is also locked axially towards the end of the chamber. upstream by the radial annular wall 46 of the chamber bottom 48 and axially downstream by the deflector 50. Each deflector 50 has a generally angular sector shape and comprises a central cylindrical annular wall 52 extending upstream, an inner peripheral edge 54 and an outer peripheral edge 56 connected by radial lateral edges 58 (FIG. 4).
    [0009] The deflectors 50 are disposed circumferentially adjacent to form a radial annular ring thermally protecting the annular bottom wall of the chamber 48. The central annular wall 52 of each deflector 50 comprises on its outer surface a thread for receiving by screwing a ring 60 as shown in Figures 3 and 4. The inner and outer peripheral edges 54, 56 respectively comprise downwardly extending flanges, parallel to the inner and outer rings 12, 14 and spaced from them a non-zero distance.
    [0010] The central annular wall 52 of each baffle 50 comprises two radial notches 62 diametrically opposite one another and opening at the upstream end of the central annular wall 52. Each notch 62 opens downstream in a radial groove 64 formed on the upstream face of the sector of the deflector 50. As shown in Figure 5, each groove 64 is open at its radially inner and outer ends. Each sleeve 44 comprises an upstream upstream frustoconical wall 76 flaring connected at its downstream end to a cylindrical wall 78 which is itself connected at its downstream end to an annularly radially inward convexly curved wall 80 whose end downstream is extended by a radial annular flange 82 arranged downstream of a radial annular flange 66 which carries two members or rectangular tabs elongate radially from its peripheral edge. The annular flange 66 is thus arranged substantially downstream of the sleeve 44 and extends annularly around the curved wall 80. The annular flange 66 and the radial annular flange 82 are internally connected to the same cylindrical wall 84. Advantageously, the collar 66 comprises holes 86 or orifices (FIG. 3). These bores 86 are preferably arranged to form an annular row. The axes of the bores are parallel to the axis 21 of the injector and are directed towards the radial annular flange 82. Thus, the air flowing from upstream to downstream in the bores 86 impacts perpendicularly the annular rim 82 which allows to cool it well. In addition, the arrangement of the annular flange 66 between the chamber bottom 48 and a deflector 50 makes it possible to reduce the axial distance (along the axis of the injector) between each piercing 86 and the annular flange 82 with respect to the prior art, thereby limiting the dispersions of the airflow and increasing the cooling of the radial flange 82 exposed to the combustion flame. As shown in FIG. 6, the sleeve 44 is engaged from upstream so that the tabs 68 slide in the notches 62 and each fit into a groove 64 of the deflector 50.
    [0011] Each groove 64 thus forms first means for rotating the sleeve 44 on the deflector 50. The inner peripheral edge of the opening of the radial annular wall 46 of the chamber bottom 48 which is aligned with the opening of the deflector 50 comprises a lug 70 projecting radially inwards. As can be seen in FIG. 7, the lug 70 is arranged in the notch 62 and forms second abutment means intended to block the rotation of the deflector 50 on the radial annular wall 46 of the chamber bottom 48. Thus, the sleeve 44 is locked in rotation about the axis 21 of the injector 19 via the deflector 50 itself locked in rotation on the chamber bottom 48. The assembly is carried out by inserting from the downstream formed assembly the deflector 50 and the sleeve 44 in the opening of the chamber bottom 48. Thereafter the ring 60 is screwed from the upstream to the outer periphery of the central annular wall 52 of the deflector 50 so as to be applied on the upstream face of the radial annular wall 46 of the chamber bottom 48. One or more weld seams are made at the contact zone between the ring 60 and the central annular wall 52 of the deflector 50 so as to prevent loosening by ring operation 60. According to the invention, the sleeve 44 is guided in radial direction by means of the radial tabs 68 which slide in the grooves 64 of the deflector 50. The tabs 68 of the sleeve 44 provide an axial locking of the sleeve 44 between the radial annular wall 46 of the chamber bottom 48 and the deflector 50. The invention eliminates the sheath of the prior art and reduces the axial size of the upstream portion of the combustion chamber. In the embodiment of the invention shown in Figures 2 to 4 and 7, the inner peripheral rims 72 and outer 74 of the chamber bottom 48 are oriented downstream and not upstream. It will be understood, however, that these peripheral inner rims 72 and outer 74 may also be directed upstream without this affecting the definition of the invention. Although not shown in the figures, the radial annular wall 46 of the chamber bottom 48 and the deflector 50 may comprise ventilation air passages.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. Combustion chamber for a turbomachine, such as a turbojet engine or an airplane turboprop, comprising an inner annular shroud (12) and an outer annular shroud (14) connected at their upstream ends by an annular bottom wall of a chamber (48). ), said chamber comprising baffles (50) mounted downstream of the annular chamber bottom wall (48), injectors (19) being mounted in sleeves (44) of which at least one (44) comprises a radial annular flange (66) arranged radially sliding between the chamber bottom (48) and the baffle (50) and axially locked between the chamber bottom (48) and the deflector (50).
    [0002]
    2. Combustion chamber according to claim 1, wherein there are provided first means (64) for rotating the sleeve on the deflector (50) and second means (62) for rotating the deflector (50) on the bedroom floor (48).
    [0003]
    3. Combustion chamber according to claim 1 or 2, wherein the flange (66) carries at least one member (68) projecting radially outwardly and arranged axially between the annular chamber bottom (48) and the deflector. (50) for axial locking of the sleeve (44) on the chamber floor (48) and the baffle (50).
    [0004]
    The combustion chamber according to claim 2 or claim 3 when dependent on claim 2, wherein the first rotational abutment means comprises a radial groove (64) formed on the upstream face of the deflector (50) and wherein said member is engaged.
    [0005]
    5. Chamber according to claim 4, wherein the baffle (50) comprises a central annular wall (52) of axis that of the injector and extending axially upstream and passing through a passage opening 30 of a injector (19) of the annular chamber bottom wall (48), said annular wall of the deflector (50) comprising a notch (62) axially slidably disassembling the collar (66) into said (64) groove of the deflector ( 50).
    [0006]
    The combustor of claim 5, wherein the second rotational abutment means comprises a lug (70) formed on the inner peripheral edge of said chamber bottom opening and projecting radially inwardly. in said notch (62).
    [0007]
    Combustion chamber according to claim 5 or 6, wherein a ring (60) is screwed onto the outer periphery of the central annular wall (52) and applied on the periphery of the upstream face of the opening of the bottom wall. bedroom (48).
    [0008]
    8. Combustion chamber according to one of claims 3 to 7, wherein the sleeve comprises two members (68) each forming a tab extending radially outwardly, preferably diametrically opposite to each other. 15
    [0009]
    9. Combustion chamber according to one of claims 1 to 8, wherein the annular chamber bottom wall (48) and the baffle (50) comprise ventilation air passage bores.
    [0010]
    10. Combustion chamber according to one of the preceding claims, characterized in that the annular collar (66) comprises an annular row 20 of orifices (86) whose axes open towards a radial annular flange (82) of the sleeve which is arranged downstream.
    [0011]
    11. Turbomachine, such as a turbojet or turboprop, characterized in that it comprises a combustion chamber according to one of claims 1 to 9. 25
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    引用文献:
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    法律状态:
    2015-10-09| PLFP| Fee payment|Year of fee payment: 2 |
    2016-04-08| PLSC| Search report ready|Effective date: 20160408 |
    2016-10-03| PLFP| Fee payment|Year of fee payment: 3 |
    2017-09-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-23| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170707 |
    2018-09-19| PLFP| Fee payment|Year of fee payment: 5 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 7 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1459362|2014-10-01|
    FR1459362A|FR3026827B1|2014-10-01|2014-10-01|TURBOMACHINE COMBUSTION CHAMBER|FR1459362A| FR3026827B1|2014-10-01|2014-10-01|TURBOMACHINE COMBUSTION CHAMBER|
    EP15785163.5A| EP3201531B1|2014-10-01|2015-09-29|Turbomachine combustion chamber|
    PCT/FR2015/052588| WO2016051067A1|2014-10-01|2015-09-29|Turbomachine combustion chamber|
    US15/516,070| US10488049B2|2014-10-01|2015-09-29|Turbomachine combustion chamber|
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