• 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 turbomachine comprising an annular combustion chamber (110) formed of two annular inner coaxial annular walls (112) and outer (114) with respect to the axis (130) of the turbomachine, arranged one to one of the other and connected at their upstream ends by an annular chamber bottom wall (118) which is attached to an outer casing (138) surrounding the outer annular shell (114), the downstream ends of the inner ring ferrules ( 112) and outer (114) being connected to flanges secured to an inner housing (128) and to the outer housing (138), respectively. According to the invention, the upstream end of at least one of the inner (112) and outer (114) shrouds is centered by radial abutment on the annular chamber bottom wall (118) and cooperates by axially sliding sealing with this one.
    公开号:FR3020865A1
    申请号:FR1454216
    申请日:2014-05-12
    公开日:2015-11-13
    发明作者:Romain Nicolas Lunel；Denis Jean Maurice Sandelis
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a turbomachine comprising an annular combustion chamber, the turbomachine may be a turbojet or an airplane turboprop.
    [0002] FIG. 1 represents an annular combustion chamber according to the known technique. This combustion chamber 10, of axis 11, comprises two annular inner and outer coaxial annular ferrules 14, fixed by bolting 16 at their upstream ends to a very rigid annular bottom wall of chamber 18. It also comprises an upstream annular shroud fixed by the bolts 16 to the chamber bottom 18 and intended to direct the flow of air entering or bypassing the combustion chamber 10. The bottom wall of the chamber 18 and the shroud 20 comprise openings 22, 24 allowing the entry of air into the chamber and the insertion of the heads of the injectors 26 diffusing fuel in the combustion chamber 10. The downstream end of the inner annular shell 12 is connected to a annular flange 26 for fixing on an inner casing 28 arranged radially inside the inner annular shell 26 with respect to the axis 30 of the turbomachine. The inner annular flange 26 also comprises at its radially inner end a radial annular wall 32 fixed by bolting on a corresponding radial annular wall 34 of the inner casing 28. Similarly, the downstream end of the outer annular shell 14 is connected to an annular flange. The radially outer end of the outer flange 36 comprises a radial annular wall 40 bolted to a corresponding radial annular wall 42 of the outer casing 38. As shown in FIG. 1, the outer casing 38 also comprises a plurality of bosses 44 distributed circumferentially around the axis of the turbomachine and each allowing the attachment of a fuel injector 26 whose arm 46 passes through the boss 44, the downstream end of the injector or head 48 of the injector housed in an opening 22 of the shroud 20 facing axially an opening e 24 of the chamber bottom 18 for the injection of fuel into the combustion chamber 10. To achieve the ignition of the injected fuel, one or more candles 50 are carried by the outer casing 38 and the cross member and the outer annular shell 14 so that the radially inner end of the spark plug 50 is flush with the inner face of the outer shell 14. Such a combustion chamber is currently commonly used since it allows a good axial alignment of the chamber outlet 10 relative to the distributor of the high pressure turbine (not shown) arranged at the outlet of the combustion chamber 10. In this way, it is possible to limit the leakage of hot gas leaving the combustion chamber.
    [0003] However, the lack of attachment of the upstream end of the chamber 10 leads to a cantilever positioning thereof that can lead to operation, due to vibrations and high temperatures in the chamber, to non-elastic deformations ( 12) and outer annular ferrules 14 which can generate significant initiations of cracks. The formation of cracks on the inner and outer ring rings 12 and 12 can spread rapidly due to the presence of the perforations they present for the supply of dilution air in particular. In addition, the positioning of the heads 48 of the injectors 26 relative to the openings of the chamber bottom 18 is difficult to achieve due to the aforementioned deformations in operation and mounting cantilever. Thus, in FR2686683 of the applicant, it has been proposed to fix the chamber bottom to the outer casing by means of threaded rods passing through the casing, the upstream ends of the inner and outer ring ferrules being fixed to the chamber bottom and the downstream ends being fixed by bolting on inner and outer casings. If this arrangement ensures a good relative positioning of the injectors, it leads however to a hyperstatic assembly of the combustion chamber, which is not desirable since it leads to an increase in stress on the inner and outer ring ferrules.
    [0004] In addition, the replacement of the downstream fasteners of the inner and outer ring ferrules by simple supports on the inner and outer casings, respectively, is not desirable since this would no longer make it possible to guarantee the correct axial positioning of the outlet of the chamber by compared to the distributor of the high pressure turbine and increase the hot gas leaks. The invention aims in particular to provide a simple, economical and effective solution to these problems, to avoid at least partly the aforementioned drawbacks. For this purpose, it proposes a turbomachine comprising an annular combustion chamber formed of two inner and outer coaxial annular shroud walls with respect to the axis of the turbomachine, arranged one inside the other and connected to their upstream ends by an annular wall of the chamber bottom which is fixed to an outer casing surrounding the outer annular shell, the downstream ends of the inner and outer annular shells being connected to flanges fixed to an inner casing and to the outer casing, respectively, characterized in that the upstream end of at least one of the inner and outer shrouds is centered by radial abutment on the annular bottom wall of the chamber and cooperates by axial sliding with sealing therewith.
    [0005] According to the invention, the upstream end of the chamber and the downstream end of the chamber are thus fixed to the inner and outer casings of the chamber, which allows easy positioning of the injector heads with respect to the openings in the bottom of the chamber. chamber and a good positioning of the chamber outlet relative to a high pressure distributor of a high pressure turbine arranged immediately downstream of the combustion chamber. The addition of a sliding connection between the bottom wall of the chamber and at least one of the upstream ends of the inner and outer annular shell allows to channel the deformations in the direction of elongation. According to another characteristic of the invention, the upstream end of the inner ferrule and the upstream end of the outer annular ferrule are centered on the annular chamber bottom wall and each cooperate by axial sliding sealing therewith. Preferably, the annular wall of the chamber bottom comprises two inner and outer annular flanges extending substantially axially, the upstream end of the outer shell being centered on the outer annular flange by bearing radially inwards on the outer annular flange, the upstream end of the inner shell being centered on the inner annular flange by bearing radially outwardly on the inner annular flange.
    [0006] The outer casing may include orifices for fixing rod passages on the outer annular flange of the chamber bottom. The combustion chamber may also comprise a fairing extending upstream from the chamber bottom and having internal and external annular flanges secured by bolting members to the inner and outer annular flanges, respectively, of the annular chamber bottom. . Preferably, the upstream edges of the inner and outer annular shrouds each comprise notches traversed by said fixing rods on the outer annular flange of the chamber bottom and said bolting members of the shroud on the chamber bottom. In a practical embodiment of the invention, it comprises at least four rods regularly distributed around the axis of the combustion chamber. The invention will be better understood and other details, advantages and features of the invention will become apparent on reading the following description given by way of non-limiting example, with reference to the appended drawings, in which: FIG. a schematic view in axial section of a combustion chamber according to the prior art and already described; Figure 2 is a schematic axial sectional view of a combustion chamber according to the invention; Figure 3 is a schematic sectional view of the upstream end of the combustion chamber of Figure 2 and in an axial section plane passing through fasteners of the upstream end of the combustion chamber; Figure 4 is a schematic view from above of the cooperation between the outer annular shell and the annular wall of the chamber bottom; Figure 5 is a schematic developed view of the upstream end of the outer annular shell.
    [0007] Referring now to Figure 2 which shows a combustion chamber 100 according to the invention. In the embodiment shown, the combustion chamber is of the convergent type, that is to say that its hot gas ejection axis 111 converges downstream towards the axis 130 of the turbomachine. The description made with reference to FIG. 1 showing a divergent combustion chamber applies to FIG. 2. The similar elements are incremented by one hundred and will not necessarily be described again. The downstream end of the inner annular shroud 112 is connected to an inner annular flange 126 having internally a radial annular wall 132 fixed by bolting on a corresponding radial annular wall 134 of an inner casing 128. Similarly, the downstream end of the outer annular shroud 114 is connected to an outer annular flange 136 having externally a radial annular wall 140 fixed by bolting on a radial annular wall 142 of the downstream end of the outer casing 138 surrounding the combustion chamber 100.
    [0008] As shown in FIG. 2, the chamber bottom 118 includes two coaxial inner and outer annular grooves 152 extending substantially axially. According to the invention, the upstream end of the outer annular shell 114 is centered on the outer annular flange 154 by a support radially inwardly thereon. Similarly, the upstream end of the inner annular shell 112 is centered on the inner annular flange 152 by a radially outwardly pressing thereon. The assembly according to the invention allows an axial sliding relative to sealing between the upstream ends of the outer annular ferrules 112 and 10 outer 114 and the inner annular flanges 152 and outer 154, respectively, of the annular wall of the chamber bottom 118. To achieve the attachment of the upstream end of the combustion chamber, the outer casing 138 comprises bosses 156 regularly distributed on the outer face of the outer casing 138. These bosses 156 each comprise an orifice whose axis is aligned radially with the axis of an opening of a tubular boss 158 formed on the outer face of the outer annular flange 154 of the annular bottom wall of chamber 118. A fixing rod 160 is engaged from outside the outer casing 138 in each opening of the boss 156 of the outer casing 138 and includes a radially inner end threaded on a corresponding thread of the inner surface of the tubular boss 158. Figure 160 comprises externally a flat head 162 abutting the boss 156 of the outer casing 138 during screwing. As also shown in FIG. 5, the upstream edge of the outer annular shell 114 includes notches 164 (recesses or hollow portions) in which the tubular bosses 158 of the outer annular flange 154 of the chamber bottom 118 are housed. the outer annular shroud 114 may have a sufficient axial distance from radial contact with the outer annular flange 154 of the chamber bottom to ensure a good sliding sealing and this irrespective of the relative axial displacement of the parts therebetween.
    [0009] The inner annular shroud 112 may also include notches in which are engaged the fixing bolts 116 of the inner annular flange 152 of the chamber bottom to the inner annular flange 166 of the shroud 122.
    [0010] Similarly, the outer ring 114 may also include notches 164 for passage of the fixing bolts 116 of the outer annular flange 154 of the chamber bottom to the outer annular flange 168 of the fairing 122. In this case, the bolting 116 of the outer annular flange 154 of the chamber bottom 118 and the fixing rods 160 form an annular row and the outer annular shell 114 comprises as many notches 164 in addition, with respect to the inner annular shell 112, there are tubular bosses 158 for the fixation of the fixing rods 160.15
    权利要求:
    Claims (7)
    [0001]
    REVENDICATIONS1. Turbomachine comprising an annular combustion chamber (110) formed by two inner coaxial (112) and outer (114) annular shroud walls with respect to the axis (130) of the turbomachine, arranged one inside the other and connected at their upstream ends by an annular chamber bottom wall (118) which is attached to an outer casing (138) surrounding the outer annular shell (114), the downstream ends of the inner (112) and outer ( 114) being connected to flanges fixed to an inner casing (128) and to the outer casing (138), respectively, characterized in that the upstream end of at least one of the inner (112) and outer (114) ferrules ) is centered by radial support on the annular bottom wall of the chamber (118) and cooperates by axial sliding with sealing therewith.
    [0002]
    2. A turbomachine according to claim 1, wherein the upstream end of the inner shell (112) and the upstream end of the outer annular shell (114) are centered on the annular chamber bottom wall (118) and cooperate each by axial sliding with sealing therewith.
    [0003]
    3. A turbomachine according to claim 2, wherein the annular chamber bottom wall (118) comprises two inner (152) and outer (154) annular flanges extending substantially axially, the upstream end of the outer shell (114). being centered on the outer annular flange (154) by bearing radially inwardly on the outer annular flange (154), the upstream end of the inner shroud (112) being centered on the inner annular flange (152) by radially bearing outwardly on the inner annular flange (152).
    [0004]
    The turbomachine according to claim 3, wherein the outer casing (138) includes pin hole openings (160) for attachment to the outer annular flange (154) of the chamber bottom (118).
    [0005]
    The turbomachine according to claim 3 or 4, wherein the combustion chamber (110) comprises a fairing (122) extending upstream from the chamber bottom (118) and having internal annular flanges (166) and external (168) secured by bolting members on the inner (152) and outer (154) annular flanges, respectively, of the annular chamber bottom (118).
    [0006]
    6. A turbomachine according to claim 5, wherein the upstream edges of the annular inner ring (112) and outer (114) each comprise notches (164) traversed by said rods (160) for attachment to the outer annular flange (154) of the chamber base (118) and said fairing bolting members (122) on the chamber bottom (118).
    [0007]
    7. A turbomachine according to claim 5 or 6, wherein it comprises at least four rods (160) evenly distributed around the axis (130) of the combustion chamber.
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    同族专利:
    公开号 | 公开日
    GB201507946D0|2015-06-24|
    GB2528356B|2018-12-19|
    US20160084501A1|2016-03-24|
    US10151485B2|2018-12-11|
    GB2528356A|2016-01-20|
    FR3020865B1|2016-05-20|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB2011546A|1977-12-24|1979-07-11|Rolls Royce|Gas turbine combustion chamber|
    FR2686683A1|1992-01-28|1993-07-30|Snecma|TURBOMACHINE WITH REMOVABLE COMBUSTION CHAMBER.|
    EP0584906A2|1992-06-12|1994-03-02|General Electric Company|Film cooling starter geometry for combustor liners|WO2020229781A1|2019-05-14|2020-11-19|Safran Aircraft Engines|Gas turbomachine with combustion chamber attachment|
    FR3107107A1|2020-02-07|2021-08-13|Safran Aircraft Engines|TURBOMACHINE COMBUSTION CHAMBER|FR1538394A|1967-06-28|1968-09-06|Snecma|Improvements to thermal machines including an annular combustion chamber|
    GB2135440B|1983-02-19|1986-06-25|Rolls Royce|Mounting combustion chambers|
    US4686823A|1986-04-28|1987-08-18|United Technologies Corporation|Sliding joint for an annular combustor|
    US5916142A|1996-10-21|1999-06-29|General Electric Company|Self-aligning swirler with ball joint|
    US7637110B2|2005-11-30|2009-12-29|General Electric Company|Methods and apparatuses for assembling a gas turbine engine|
    FR2897145B1|2006-02-08|2013-01-18|Snecma|ANNULAR COMBUSTION CHAMBER FOR TURBOMACHINE WITH ALTERNATE FIXINGS.|
    FR2920524B1|2007-08-30|2013-11-01|Snecma|TURBOMACHINE WITH ANNULAR COMBUSTION CHAMBER|
    FR2927949B1|2008-02-27|2010-03-26|Snecma|TURBOMACHINE DIFFUSER COMPRISING SCREWED ANNULAR SAILS|
    FR2930628B1|2008-04-24|2010-04-30|Snecma|ANNULAR COMBUSTION CHAMBER FOR TURBOMACHINE|
    US9046272B2|2008-12-31|2015-06-02|Rolls-Royce Corporation|Combustion liner assembly having a mount stake coupled to an upstream support|
    FR2944090B1|2009-04-07|2015-04-03|Snecma|TURBOMACHINE WITH ANNULAR COMBUSTION CHAMBER|
    US8893382B2|2011-09-30|2014-11-25|General Electric Company|Combustion system and method of assembling the same|
    US8839627B2|2012-01-31|2014-09-23|United Technologies Corporation|Annular combustor|
    US9612017B2|2014-06-05|2017-04-04|Rolls-Royce North American Technologies, Inc.|Combustor with tiled liner|
    US11149646B2|2015-09-02|2021-10-19|General Electric Company|Piston ring assembly for a turbine engine|US10100675B2|2014-12-09|2018-10-16|United Technologies Corporation|Outer diffuser case for a gas turbine engine|
    GB2558566B|2017-01-05|2019-11-13|Rolls Royce Plc|A combustion chamber arrangement|
    US10393381B2|2017-01-27|2019-08-27|General Electric Company|Unitary flow path structure|
    US10371383B2|2017-01-27|2019-08-06|General Electric Company|Unitary flow path structure|
    US10253643B2|2017-02-07|2019-04-09|General Electric Company|Airfoil fluid curtain to mitigate or prevent flow path leakage|
    US10378373B2|2017-02-23|2019-08-13|General Electric Company|Flow path assembly with airfoils inserted through flow path boundary|
    FR3107106A1|2020-02-11|2021-08-13|Safran Aircraft Engines|Assembly INCLUDING a crankcase and a combustion chamber, and turbomachine thus equipped|
    法律状态:
    2015-05-12| PLFP| Fee payment|Year of fee payment: 2 |
    2015-11-13| PLSC| Search report ready|Effective date: 20151113 |
    2016-05-13| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-26| 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 |
    2018-04-23| PLFP| Fee payment|Year of fee payment: 5 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 7 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1454216A|FR3020865B1|2014-05-12|2014-05-12|ANNULAR CHAMBER OF COMBUSTION|FR1454216A| FR3020865B1|2014-05-12|2014-05-12|ANNULAR CHAMBER OF COMBUSTION|
    US14/708,699| US10151485B2|2014-05-12|2015-05-11|Annular combustion chamber|
    GB1507946.0A| GB2528356B|2014-05-12|2015-05-11|An annular combustion chamber in a turbine engine|
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