• 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 comprising a bottom wall (16), at least one mixing bowl (22) intended to promote the mixing of air and fuel, mounted in an opening in the bottom wall ( 16), at least one annular deflector (23) mounted axially downstream of the bottom wall (16), with respect to the direction of gas circulation within the combustion chamber, around said opening, the deflector (23) coming in one piece with the mixing bowl (22) so as to form a one-piece assembly (30), characterized in that said assembly (30) comprises at least one channel intended for the flow of cooling air, said channel comprising a air inlet located upstream from the bottom wall (16) and an air outlet located downstream from the bottom wall (16), said air outlet being located radially opposite the deflector (23).
    公开号:FR3082284A1
    申请号:FR1854962
    申请日:2018-06-07
    公开日:2019-12-13
    发明作者:Yoann Guezel Yvan；Xavier Chapelle Francois；Nicolas Lunel Romain
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    COMBUSTION CHAMBER FOR A TURBOMACHINE
    FIELD [001] The present invention relates to a combustion chamber for a turbomachine, such as for example a turbojet or an airplane turboprop.
    BACKGROUND [002] FIG. 1 represents a turbomachine 1 of the prior art, in particular a turbofan engine.
    The air or gas flow flowing through the turbomachine 1 is directed from upstream to downstream, that is to say from left to right in Figure 1. [004] The turbomachine , of axis X, conventionally comprises a fan 2 downstream of which extends:
    a primary stream in which a primary stream flows, said primary stream passing in particular, in the direction of flow of the primary stream, a low-pressure compressor 3, a high-pressure compressor 4, a combustion chamber 5, a high-pressure turbine 6 and a low-pressure turbine 7, the primary stream being delimited externally at the level of the turbine by a casing 8,
    - a secondary vein referenced 9, in which a secondary flow distinct from the primary flow flows.
    The secondary stream 9 is surrounded by a nacelle 10 forming a fairing for the turbomachine 1.
    FIG. 2 represents the combustion chamber 5 of the turbomachine 1 of FIG. 1. The combustion chamber 5 is annular and comprises a radially internal annular ferrule 11 and a radially external annular ferrule 12, said ferrules 11,12 being coaxial and of axis X. The ferrules 11, 12 conventionally comprise holes 13 allowing the passage of said primary air and holes 14 allowing the passage of said dilution air.
    Fairings 15 are mounted on the upstream ends of the ferrules 11,12.
    The ferrules 11,12 are connected at their upstream end by an annular wall at the bottom of the chamber 16 equipped with air and fuel injection systems 17, regularly distributed around the axis X and housed partly in the volume delimited by the fairings 15.
    As best seen in Figure 3, each air and fuel injection system 17 includes a fuel injection rod 18, a socket 19 mounted around the end or nose 20 of the rod , an annular air intake or injection device 21, a mixing bowl or spray bowl 22 and a deflector 23. The air injection device 21 and the bowl 22 may be formed in one piece or on the contrary be formed of two distinct parts.
    In the following description, the terms axial, radial and circumferential are defined with respect to an axis Y called injection, corresponding to the axis of the sleeve and the device.
    The device 21 here forms two air injection tendrils 21a, 21b, also known as "swirlers", in English. The tendrils 21a, 21b are separated from each other by an annular wall 26 which extends radially inwards to form an internal annular deflection wall 27, also called a venturi, having an internal profile of convergent then divergent shape. , from upstream to downstream.
    Each spin 21 a, 21 b conventionally comprises an annular row of inclined fins so as to rotate the air flow and thus improve the atomization or vaporization of the fuel jet coming from the nose 20 of the fuel injection pipe 18. In particular, part of this fuel flows in liquid form on the internal surface of the venturi 27 and is sheared by swirling air at the downstream end of the venturi (shown schematically in the form arrows in Figure 3).
    The fuel vaporization and the air and fuel mixture continue, downstream of the tendrils 21a, 21b, in the bowl 22 and then in the upstream part of the combustion chamber 5, where the premixing of air and fuel from the bowl 22 is further mixed with air from the primary holes 13 and the dilution holes 14.
    The device 21 is mounted in the deflector 23, itself partially mounted in an opening in the chamber bottom 16. The deflector 23 has an annular part extending radially 24 around the opening and located downstream from the bottom chamber 16 so as to form a thermal barrier to prevent premature degradation of the chamber bottom.
    The deflector comprises in particular a cylindrical part 25 fixed by brazing to the edge of the opening of the chamber bottom 16, the radial annular part 24 extending from the downstream end of the cylindrical part 25.
    The deflector 23 is subjected to significant thermal stresses in operation, which can generate cracks or cracks at the level of the brazing zone with the chamber bottom 16 and / or at the base of the radial annular part 24 , that is to say at the level of the connection between the cylindrical part 25 and the radial annular part 24.
    [017] Furthermore, the structure of the air injection system 17 is relatively complex and has a large axial size, in particular at the level of the attachment between the deflector 23 and the bowl 22.
    SUMMARY OF THE INVENTION The aim of the invention is in particular to provide a simple, effective and economical solution to these problems.
    To this end, the invention relates to a combustion chamber for a turbomachine comprising a bottom wall, at least one mixing bowl intended to promote the mixing of air and fuel, mounted in an opening in the bottom wall , at least one annular deflector mounted axially downstream of the bottom wall, with respect to the direction of gas flow within the combustion chamber, around said opening, the deflector coming from the material with the mixing bowl so as to form a one-piece assembly, characterized in that said assembly comprises at least one channel intended for the cooling air flow, said channel comprising an air inlet situated upstream of the bottom wall and an air outlet situated in downstream of the bottom wall, said air outlet being located radially opposite the deflector.
    [020] As indicated above, the terms axial, radial and circumferential are defined relative to the axis of the opening, which is globally coincident with the axis of the above-mentioned assembly.
    [021] The fact of making the deflector and the mixing bowl in one piece makes it possible to reduce the axial size of the assembly. The mixing bowl is also called the spray bowl or pre-mix bowl. As is known per se, the bowl may have a frustoconical annular wall which widens downstream.
    [022] Furthermore, the formation of a channel opening facing the deflector improves its cooling and also allows the zone of the assembly in which the channel is formed to be cooled. We therefore reduce the risk of cracks and cracks appearing in these areas.
    [023] Said assembly may include a cylindrical fixing part, fixed to the chamber bottom and mounted radially inside the opening, the deflector comprising a radially internal base part connected to said fixing part, the channel being formed. in the cylindrical fixing part, the air outlet of the channel being located radially opposite the base of the deflector.
    The air from the channel then comes to impact more specifically the base of the deflector, which is one of the zones in which the appearance of cracks or cracks has been observed in the prior art. The risks of degradation in this area are therefore specifically reduced.
    [025] The combustion chamber may comprise at least one air intake tendril capable of generating a rotary air flow, located upstream of the mixing bowl.
    [026] As indicated above, such a spin makes it possible to atomize or vaporize the fuel, so as to produce a homogeneous premix of air and fuel.
    [027] The fixing part can extend axially upstream from the radially external periphery of the mixing bowl, the deflector extending radially outwards from the radially external periphery of the mixing bowl.
    [028] The radially outer periphery of the deflector may include a flange extending downstream, located near said corresponding ferrule and offset radially from said ferrule.
    [029] In this way, the cooling air opening into the space provided axially between the chamber bottom and the radial annular part of the deflector can open into the combustion chamber through the spaces provided between the edges of the deflectors and the ferrules. concerned. This cooling air opening into the chamber then forms films of air that lick, cool and protect the corresponding ferrules.
    [030] The assembly may include a plurality of channels intended for the flow of cooling air, regularly distributed around the circumference.
    [031] The section of each channel can be substantially constant from the upstream end of said channel to the downstream end of said channel.
    [032] The section of each channel can decrease axially from upstream to downstream.
    Such a characteristic makes it possible to increase the speed of the flow of cooling air impacting the deflector at the outlet of the channel, which can make it possible to improve the cooling of the zone concerned of the deflector.
    The at least one channel intended for the cooling air flow can be delimited by a radially internal surface and a radially external surface, in the form of a portion of cylinders or of portions of cones, said radially internal surfaces and external being coaxial.
    [035] Two adjacent channels can be separated circumferentially by a connection wall, said connection wall comprising an upstream end and a downstream end, said upstream end being rounded.
    The cylindrical fixing part of the assembly can be fixed by brazing or welding to a cylindrical part of the bottom wall, formed at the radially outer periphery of the opening.
    [037] The cylindrical part of the bottom wall may include an upstream shoulder, the upstream end of the cylindrical part of the assembly being able to come into abutment on said shoulder. The upstream end of the cylindrical part of the assembly can be fixed by brazing or welding to said shoulder.
    [038] The assembly can be made of a superalloy based on nickel and / or cobalt. The assembly can be produced by an additive manufacturing process, for example by selective melting or by selective sintering of powder, using an electron beam or a laser beam.
    [039] The invention also relates to a turbomachine comprising a combustion chamber of the aforementioned type.
    The invention will be better understood and other details, characteristics and advantages of the invention will appear on reading the following description given by way of nonlimiting example with reference to the accompanying drawings.
    BRIEF DESCRIPTION OF THE FIGURES FIG. 1 is a schematic view in axial section of a turbomachine of the prior art;
    Figure 2 is an axial sectional view illustrating a combustion chamber of the turbomachine of Figure 1;
    Figure 3 is a schematic view of an injection system fitted to the combustion chamber of Figure 2;
    Figure 4 is an axial sectional view of a portion of a combustion chamber according to an embodiment of the invention;
    Figure 5 is a perspective view illustrating a portion of the chamber bottom and a portion of the assembly including forming the deflector and the mixing bowl, according to the invention;
    Figure 6 is a detail view of Figure 4;
    FIG. 7 is a detailed view of FIG. 5.
    DETAILED DESCRIPTION [041] A combustion chamber 5 according to one embodiment is illustrated in FIGS. 4 to 7. This comprises a radially internal annular ferrule 11 and a radially external annular ferrule 12, relative to the axis X of the turbomachine, said ferrules 11,12 being coaxial.
    [042] Annular fairings 15 are mounted at the upstream ends of the ferrules 11, 12 and delimit an annular volume.
    [043] The ferrules 11,12 are connected at their upstream end by a radial annular wall at the bottom of the chamber 16. The bottom of the chamber 16 has openings of axis Y, regularly distributed over the circumference. In particular, the edge of each opening is delimited by a cylindrical fixing part 28. The cylindrical part 28 has a shoulder 29 at its upstream end (FIG. 6).
    [044] An assembly 30 forming both a mixing bowl 22 and a deflector 23 ensuring the protection of the chamber bottom 16, is mounted and fixed in each opening of the chamber bottom 16.
    [045] An air intake or injection device 21 is mounted upstream of the assembly 30.
    [046] The device 21 is annular with a Y axis and comprises, from upstream to downstream, a part 31 used for mounting a bushing 19, an upstream tendon for air intake or injection 21 a and a downstream tendon for air intake or air injection 21b.
    [047] The upstream part 31 of the device 21 comprises a cylindrical part 32 and a radial part 33, a washer 34 being fixed in the cylindrical part
    32. The washer 34 is axially offset from the radial part 33 so as to form a groove for mounting a collar 34a of the sleeve 19. The sleeve 19 further comprises a frustoconical part 35 surrounding the nose 20 of a cane 18 fuel injection. Fuel injection is carried out along the Y axis.
    The tendrils 21a, 21b are separated from each other by an annular wall 26 which extends radially inwards to form an internal annular deflection wall 27, also called a venturi, having an internal profile of shape. convergent then divergent, from upstream to downstream. [049] Each spin 21 a, 21 b conventionally comprises an annular row of inclined fins so as to rotate the air flow and thus improve the atomization or vaporization of the jet of fuel coming from the nose 20 of the fuel injection rod 18. In particular, part of this fuel flows in liquid form on the internal surface of the venturi 27 and is sheared by the swirling air at the downstream end of the venturi 27.
    [050] The bowl 22 is formed by a frustoconical annular wall widening towards the downstream. Said frustoconical wall has holes 36 (Figures 4 and 5) allowing the passage of cooling air from the internal volume delimited by the fairings 15 to the combustion chamber 5.
    [051] The deflector 23 is formed at the level of the radially external downstream periphery of the bowl 22. In particular the deflector 23 comprises a cylindrical axial part 25 extending upstream from the external periphery of the bowl 22 and a part 24 s 'extending radially outward from the downstream end of the cylindrical part 25. The peripheries of the radial part 24 are extended by flanges 37 extending upstream and radially spaced from the corresponding ferrules.
    [052] The cylindrical part 25 of the assembly 30 is mounted in the cylindrical part 28 of the bottom wall 16. The upstream end of the cylindrical part 25 of the assembly 30 comes into axial abutment on the shoulder 29. The cylindrical part 25 of the assembly 30 is fixed by brazing or welding to the cylindrical part 28 of the chamber bottom 16, in particular at the level of the corresponding cylindrical surfaces 38 (FIG. 6), or even also at the level of the annular radial surface forming shoulder 29.
    [053] Channels 39 are formed in the cylindrical axial part 25 of the deflector 23, the channels 39 being regularly distributed over the circumference. The channels 39 are separated two by two by axially extending connecting walls 40 (FIG. 7). Each channel 39 is delimited by a radially internal surface 41, a radially external surface 42 and by the surfaces of the two corresponding adjacent connection walls 40.
    [054] The radially internal and external surfaces 41,42 are coaxial and cylindrical, for example.
    [055] The upstream end 43 of each connecting wall 40 can be rounded so as to facilitate the introduction of cooling air into the channels 39, by limiting the pressure losses. The term rounded may designate a complex shape having a rounded portion, for example having a triangular end whose apex is rounded.
    [056] The downstream end of each channel 39 opens opposite the part of the radially internal base 44 of the radial part of the deflector 23 (FIG.
    6), that is to say at the level of the connection zone 44 between the radial part 24 of the deflector 23 and the downstream end of the axial part 25. This connection zone 44 may have a connection fillet.
    [057] Each channel 39 may have a section whose radial and / or circumferential dimension is between 15 and 35 mm.
    [058] The assembly 30 can be made of a superalloy based on nickel and / or cobalt. The assembly 30 can be produced by an additive manufacturing process, for example by selective melting or by selective sintering of powder, using an electron beam or a laser beam.
    [059] In operation, the cooling air from the high pressure compressor enters the channels 39 and impacts the base 44 of the radial part 24 of the deflector 23 then circulates in the space 45 formed axially between said radial part 24 and the chamber bottom 16 before opening 5 into the combustion chamber 5 through the space 46 (FIG. 4) formed between the flanges 37 and the ferrules 11, 12.
    This cooling air effectively cools the axial part 25 of the assembly 30 as well as the base 44 of the radial part 24, which are the most critical zones in terms of thermal stresses. This avoids the appearance of cracks or cracks so as to increase the life of the assembly 30.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Combustion chamber (5) for a turbomachine comprising a bottom wall (16), at least one mixing bowl (22) intended to promote the mixing of air and fuel, mounted in an opening in the bottom wall ( 16), at least one annular deflector (23) mounted axially downstream of the bottom wall (16), relative to the direction of circulation of the gases within the combustion chamber (5), around said opening, * the deflector (23) made in one piece with the mixing bowl (22) so as to form a one-piece assembly (30), characterized in that said assembly (30) comprises at least one channel intended for the flow of cooling air, said channel (39) comprising an air inlet located upstream from the bottom wall (16) and an air outlet located downstream from the bottom wall (16), said air outlet being located radially opposite of the deflector (23).
    [2" id="c-fr-0002]
    2. Combustion chamber (5) according to claim 1, characterized in that said assembly (30) comprises a cylindrical fixing part (25), fixed to the chamber bottom (16) and mounted radially inside the opening, the deflector (23) comprising a radially internal base part (44) connected to said fixing part (25), the channel (39) being formed in the cylindrical fixing part (25), the air outlet of the channel (39) being located radially opposite the base (44) of the deflector (23).
    [3" id="c-fr-0003]
    3. Combustion chamber (5) according to claim 1 or 2, characterized in that it comprises at least one twist (21a, 21b) of air intake capable of generating a rotary air flow, located upstream from the mixing bowl (22).
    [4" id="c-fr-0004]
    4. Combustion chamber (5) according to claim 2 or 3, characterized in that the fixing part (25) extends axially upstream from the radially external periphery of the mixing bowl (22), the deflector (23 ) extending radially (24) outward from the radially outer periphery of the mixing bowl (22).
    [5" id="c-fr-0005]
    5. Combustion chamber (5) according to one of claims 1 to
    4, characterized in that the assembly (30) comprises a plurality of channels (39) intended for the flow of cooling air, regularly distributed over the circumference.
    [6" id="c-fr-0006]
    6. Combustion chamber (5) according to one of claims 1 to
    5, characterized in that the section of each channel (39) is substantially constant from the upstream end of said channel (39) to the downstream end of said channel (39).
    [7" id="c-fr-0007]
    7. Combustion chamber (5) according to one of claims 1 to 5, characterized in that the section of each channel (39) decreases axially from upstream to downstream.
    [8" id="c-fr-0008]
    8. Combustion chamber (5) according to one of claims 1 to 7, characterized in that the at least one channel (39) intended for the flow of cooling air is delimited by a radially internal surface (41 ) and a radially external surface (42), in the form of a portion of cylinders or of cone portions, said radially internal and external surfaces (41, 42) being coaxial.
    [9" id="c-fr-0009]
    9. Combustion chamber (5) according to claim 5 and according to one of claims 1 to 4, 6 or 7, characterized in that two adjacent channels (39) are circumferentially separated by a connecting wall (40), said connecting wall (40) having an upstream end (43) and a downstream end, said upstream end (43) being rounded.
    [10" id="c-fr-0010]
    10. Combustion chamber (5) according to one of claims 1 to 9, characterized in that the cylindrical fixing part (25) of the assembly (30) is fixed by brazing or welding to a cylindrical part (28) of the bottom wall (16), formed at the radially inner periphery of the opening.
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    同族专利:
    公开号 | 公开日
    US11242994B2|2022-02-08|
    EP3578884A1|2019-12-11|
    US20190376689A1|2019-12-12|
    CN110578934A|2019-12-17|
    FR3082284B1|2020-12-11|
    EP3578884B1|2020-08-05|
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    法律状态:
    2019-05-21| PLFP| Fee payment|Year of fee payment: 2 |
    2019-12-13| PLSC| Publication of the preliminary search report|Effective date: 20191213 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 3 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1854962|2018-06-07|
    FR1854962A|FR3082284B1|2018-06-07|2018-06-07|COMBUSTION CHAMBER FOR A TURBOMACHINE|FR1854962A| FR3082284B1|2018-06-07|2018-06-07|COMBUSTION CHAMBER FOR A TURBOMACHINE|
    EP19178425.5A| EP3578884B1|2018-06-07|2019-06-05|Combustion chamber for a turbomachine|
    US16/433,078| US11242994B2|2018-06-07|2019-06-06|Combustion chamber for a turbomachine|
    CN201910495293.8A| CN110578934A|2018-06-07|2019-06-10|Combustion chamber for a turbomachine|
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