• 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 casing (1) for a turbomachine, comprising: - a hub (2), - an outer ring (3), and - clevises (11) projecting from the outer ring (3), for fixing the housing (1), characterized in that it comprises at least one stiffener (10) extending between pairs of yokes (11) facing one another.
    公开号:FR3016660A1
    申请号:FR1450579
    申请日:2014-01-23
    公开日:2015-07-24
    发明作者:Sousa Mario Cesar De；Benoit Argemiro Matthieu Debray；Paul Moreau；Frederic Noel
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] Field of the Invention The invention relates to a turbomachine casing, in particular a turbomachine exhaust casing.
    [0002] Presentation of the Prior Art The exhaust casing is a structural part of a turbomachine conventionally arranged at the outlet of a turbine, before the ejection nozzle. The housing includes a hub, an outer shell and a plurality of structural arms circumferentially disposed between the hub and the outer shell. In order to fix the exhaust casing to a support of the turbomachine, it is known from the patent application FR 2975131, to provide attachment points named clevises projecting on the outer shell, whose ears extend radially and which have bores for receiving fixing rods 103 (Figure 1). The tensile and compressive forces induced by the connecting rods on the yokes induce moments of deflection which can damage the ferrule as well as the arms of the crankcase.
    [0003] This results from the misalignment between the bores of the yokes and the neutral fiber of the ferrule. FR 2975131 proposes to create a vacuum in the ferrule to bring the bores of the yokes with the neutral fiber of the ferrule. However, this solution is less effective if the shell has a thin thickness, which is desirable to reduce the mass of the housing. Another solution, illustrated in Figure 1, is to create bosses 100 to lower the yokes 101 and bring them closer to the neutral fiber of the ferrule. However, these bosses have a negative aerodynamic impact on the flow in the vein, which is increased when the structural arms are short.
    [0004] In addition, in the solutions of the prior art, it is difficult to machine the screeds, because they are arranged close to the outer shell, which implies that the machining tools encounter obstacles.
    [0005] Presentation of the invention In order to overcome the drawbacks of the prior art, the invention proposes a turbomachine casing, comprising a hub, an outer shell, and clevises projecting from the outer shell, for fixing the casing, characterized in that it comprises at least one stiffener extending between pairs of yokes facing one another. The invention is advantageously completed by the following features, taken alone or in any of their technically possible combination: the ends of the stiffener are integral with the yokes; the ends of the stiffener are fixed to the yokes by means of fixing elements; the stiffener has a central portion, and side arms projecting from the central portion; the stiffener has a general shape of H; the lateral arms have a larger section in their center than at their ends; the lateral arms have a smaller section in their center than at their ends; the side arms have a section of substantially constant width; said housing is a turbomachine exhaust casing and comprises a plurality of structural arms circumferentially disposed between the hub and the outer shell, the yokes being arranged in the extension of the structural arms.
    [0006] The invention also relates to a turbomachine comprising a casing as described above, connecting rods fixed on the one hand to the yokes of the casing by means of fixing elements, and on the other hand to a support of the turbomachine, the stiffener being configured to take up forces applied by the fasteners on the housing.
    [0007] DESCRIPTION OF THE FIGURES Other features and advantages of the invention will become apparent from the following description, which is purely illustrative and nonlimiting, and should be read with reference to the accompanying drawings, in which: FIG. 1 is a representation of FIG. an exhaust casing according to the prior art, comprising bosses in the space between the hub and the outer shell; - Figure 2 is a representation of a housing according to one embodiment of the invention; - Figure 3 is a representation of pairs of yokes projecting on the shell, and a stiffener separate from the yokes; - Figure 4 shows a connection between the stiffener and the yokes by a fastener, according to the embodiment of Figure 3; - Figure 5 is a representation of an embodiment in which the stiffener is integral with the yokes; Figure 6 is a representation of a possible embodiment for the shape of the stiffener; Figure 7 is a side view of the embodiment of Figure 6; - Figure 8 is a representation of another possible embodiment for the shape of the stiffener; Figure 9 is a side view of the embodiment of Figure 8; Figure 10 is a representation of another possible embodiment for the shape of the stiffener; Figure 11 is a side view of the embodiment of Figure 10; - Figure 12 is a representation of a housing connected to a turbomachine support by fasteners; - Figure 13 is a representation of an area upstream of bosses in a housing according to the prior art.
    [0008] DETAILED DESCRIPTION FIG. 2 shows an embodiment of a turbomachine casing 1 according to the invention. This is for example a turbomachine exhaust casing.
    [0009] The casing 1 comprises a hub 2 and an outer shell 3. The outer shell 3 is for example of generally cylindrical shape of revolution, or polygonal. It has a fixing flange 35 comprising a plurality of holes, for attachment to another housing. In the case of an exhaust casing, the casing 1 further comprises a plurality of structural arms 14. The latter, which may in particular be radial or tangential, are circumferentially arranged and connect the hub 2 and the outer shell 3. By radial means the radial axis of the turbomachine, which extends radially with respect to the longitudinal axis of the turbomachine, the longitudinal axis being the axis of flow of the primary flow of the turbomachine, upstream in downstream. Tangential arm means an arm arranged substantially tangentially relative to the hub 2, that is to say with a pronounced inclination relative to a purely radial arm.
    [0010] The spaces between the structural arms 14 define exhaust openings in which the flow of the turbomachine (vein) flows. The casing 1 further comprises clevises 11 projecting from the outer shell 3, for fastening the casing, and in particular, for receiving fastening elements 8, themselves connected to connecting rods 9 (FIG. 12) of FIG. fixing the casing 1 to a support 32 (FIG. 12) of the turbomachine.
    [0011] The yokes 11 have lugs 30 oriented radially with respect to the outer shell 3. The lugs 30 have bores 31 for receiving the fastening elements 8, such as for example axes. An end 33 (FIG. 12) of the fixing rods 9 is received and fixed (for example by means of the fastening elements 8) between a pair of clevises 11 facing each other, the other end 34 (Figure 12) being fixed to the support 32 of the turbomachine. The housing 1 further comprises at least one stiffener 10 extending between pairs of yokes 11 facing one another.
    [0012] According to one possible embodiment, the yokes 11 are arranged in pairs facing each other, and side by side. In the case of an exhaust casing 1 comprising a plurality of structural arms 14 arranged circumferentially between the hub 2 and the outer shell 3, the yokes 11 are advantageously arranged in the radial extension of the arms 14 structural. The stiffener 10 extends between two pairs of yokes 11, each pair comprising two yokes facing one another. In the example illustrated in FIG. 2, the housing 1 comprises six screeds on the circumference of the outer shell 3 and three stiffeners 10, each stiffener 10 extending between two adjacent pairs of screeds 11. This number and this arrangement are not however not limiting. The stiffener 10 extends in the main direction of the fixing rods 9, so as to take up the forces applied by the fixing rods 9 on the casing 1. This makes it possible to prevent the application of bending moments on the casing 1 In this case, the stiffeners 10 extend mainly in a direction substantially tangential to the outer shell 3. The ends 12 of the stiffener 10 are in turn aligned with the bores 31 of the yokes 11 opposite.
    [0013] In Figure 12, there is shown an exhaust casing 1 attached to a support 32 of a turbomachine. As can be seen, the fixing rods 9 are fixed on the one hand to the yokes 11 of the casing 1 and on the other hand to the support 32. Given the attachment of the casing 1, the buckling stress of the structural arms 14 is relatively low, but this attachment induces significant moments of sagging on the shell 3 and the top of the arms 14, which are taken up by the stiffeners 10. According to one embodiment, the ends 12 of the stiffener 10 are integral with the yokes 11. The stiffener 10 can be obtained by various manufacturing processes, for example by stamping, forging or foundry and secured to the yokes 11 by casting or welding. In this case, the forces imposed by the fixing rods 9 are taken up by the yokes 11 reinforced by the stiffeners 10 by means of the fastening elements 8, which avoids the mechanical stresses of the shell 3, and, where appropriate, where appropriate, structural arms 14. According to one possible example, the casing 1 comprises several independent sectors, derived from foundries, the joining of which makes it possible to obtain the casing 1. Each sector comprises a portion of an arm, a portion of ferrule, and, where appropriate, one or more pairs of projecting copings. According to this example, a stiffener portion 10 is secured to each pair of yokes 11 of each sector, from manufacture. When assembling the sectors of the casing 1, the stiffener portions 10 are then secured, for example by welding. In practice, a central portion is generally attached and welded to the stiffener portions integral with each pair of clevises of each sector, to facilitate the manufacture and alignment of the stiffener portions 10 therebetween. According to another embodiment, the stiffener 10 is attached and fixed on the pairs of yokes 11. The yokes 11 and the stiffener 10 are therefore 30 in this case two separate parts.
    [0014] For this purpose, the ends 12 of the stiffener 10 are fixed to the yokes 11 by means of the fixing elements 8, such as pins, which are common to the stiffeners 10 and the rods 9. In this embodiment, the forces applied by the fixing elements 8 are distributed between the yokes 11 and the stiffeners 10. The invention simplifies the manufacture of the housing. Indeed, in the prior art, the yokes 11 have a low radial position, close to the outer shell 3, which makes the development of the foundry mold at the level of the pits, the machining of the yokes, and, in particular, the passage of tools for the manufacture of bores screeds, because of the proximity of the outer shell 3. Thanks to the invention, the yokes 11 can be projecting on the outer shell 3, and it is no longer necessary to align the yokes 11 with the neutral fiber of the ferrule. The stiffeners 10, possibly in cooperation with the yokes 11, allow the bending moment induced by the misalignment of the bores 31 of the yokes 11 to be resumed with the neutral fiber of the shell 3. Consequently, the access to the yokes 11 is improved, and the machining of the yokes 11 is simplified. The shape of the stiffener 10 is designed to meet different demands. It is advantageous that the stiffener 10 can be manufactured at reduced cost and have a reduced mass, while ensuring the required mechanical strength. In particular, the stiffener 10 is designed to have a buckling behavior, at best equal to, better than that of the ferrule 3, to preserve it in extreme stresses. As illustrated in FIGS. 5 to 11, the stiffener 10 may in particular have: a central portion 18 and lateral arms 19 projecting from the central portion 18 and whose ends are connected (by joining or by pieces fixing) to screeds 11.
    [0015] The lateral arms 19 generally extend beyond the central portion 18 in a direction tangential to the shell 3. The stiffener 10 may in particular have a general shape of H in plan view.
    [0016] In the example of Figures 6 and 7, the side arms 19 have a section 25 less wide in their center than at their ends. Thus, the arms 19 are refined from their ends connected to the yokes 11 towards their center connected to the central portion 18 of the stiffener 10. In addition, the central section of the side arms 19 has, in these figures, a concave external profile. In the example of Figures 8 and 9, the side arms 19 have a wider section in their center than at their ends. Thus, the arms 19 are refined from their center connected to the central portion 18 of the stiffener 10 towards their ends connected to the yokes 11.
    [0017] In addition, the central section of the lateral arms 19 has, in these figures, a convex external profile. In the example of Figures 10 and 11, the side arms 19 have a section 26 of substantially constant width. These embodiments are only examples, and other forms are conceivable in order to optimize the dimensioning in mechanical strength and the rationalization of the mode of industrialization. The prior art described a casing with punctures, which are removed by the subject of the invention. Removing these impediments to flow flow improves the performance of the turbomachine. In addition, the manufacture of the housing is improved. The screeds, which are remote from the outer circumference of the shell 3, can be machined in a simple and effective manner, the machining tools do not encounter obstacles to their passage.
    [0018] Moreover, the invention makes it possible to increase the service life of crankcase zones. In the prior art, the zone upstream of the pits is in life limit. The elimination of the empoages makes it possible to overcome this limitation. Indeed, the zone 29 (FIG. 13) located in the prior art upstream (depending on the direction of flow of the flow in the casing) of the pockets 100, on the outer circumference of the hub 3, which has a limited lifetime , no longer exists thanks to the invention, due to the suppression of the punctures. Finally, the costs are reduced, and the mass balance is satisfactory compared to the solutions of the prior art.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Turbomachine casing (1), comprising: a hub (2), an outer shell (3), and clevises (11) projecting from the outer shell (3), for fixing the casing (1), characterized in that it comprises at least one stiffener (10) extending between pairs of yokes (11) facing one another.
    [0002]
    2. Carter (1) according to claim 1, wherein the ends (12) of the stiffener (10) are integral with the yokes (11).
    [0003]
    3. Housing (1) according to claim 1, wherein the ends (12) of the stiffener (10) are fixed to the yokes (11) via elements (8) for fixing.
    [0004]
    4. Carter (1) according to one of claims 1 to 3, wherein the stiffener (10) has: a portion (18) central, and arms (19) extending laterally projecting from the portion (18) Central.
    [0005]
    The housing (1) according to claim 4, wherein the stiffener (10) has a general shape of H.
    [0006]
    6. Carter (1) according to one of claims 4 or 5, wherein the arms (19) side have a section (25) wider at their center than at their ends.
    [0007]
    7. Carter (1) according to one of claims 4 or 5, wherein the arms (19) side have a section (25) narrower in their center at their ends.
    [0008]
    8. Carter (1) according to one of claims 4 or 5, wherein the arms (19) side have a section (26) of substantially constant width.
    [0009]
    9. Carter (1) according to one of claims 1 to 8, said housing (1) being a turbomachine exhaust casing and comprising a plurality of structural arms (14) arranged circumferentially between the hub (2). and the shell (3) outer, the yokes (11) being arranged in the extension of the arms (14) structural.
    [0010]
    10. Turbomachine comprising: 15 a housing (1) according to one of claims 1 to 9, connecting rods (9) fixed on the one hand to the yokes (11) of the housing (1) via elements (8) for fixing, and secondly to a support (32) of the turbomachine, the stiffener (10) being configured to take up forces applied by the connecting rods (9) for fixing on the housing (1). 25
    类似技术:
    公开号 | 公开日 | 专利标题
    WO2015110749A1|2015-07-30|Turbomachine casing comprising a cavity-free shroud and yokes reinforced by stiffeners
    EP2058476B1|2013-08-07|Connection of radial struts to a circular casing by interleaving inserts
    FR2906008A1|2008-03-21|SMOOTH CHEST AND ORBITAL JUNCTION DEVICE
    WO2011036386A1|2011-03-31|Aircraft assembly including an element for attaching an engine and related aircraft
    FR2950323A1|2011-03-25|AIRCRAFT ENGINE HANDLING MACHINE, AN ASSEMBLY COMPRISING THIS MAT AND ASSOCIATED AIRCRAFT
    EP3027854B1|2017-09-27|Turbine engine casing and manufacturing method
    EP3781793A2|2021-02-24|Load-bearing cmc nozzle diaphragm
    WO2019202249A2|2019-10-24|Distributor made of cmc, with stress relief provided by a sealed clamp
    FR2997896A1|2014-05-16|BICYCLE WHEEL WHEEL
    EP2821595A1|2015-01-07|Stator blade section with mixed fixation for an axial turbomachine
    EP1548233B1|2006-08-02|Fastening device for stator blades and compressor stator stage comprising such a fastening device
    FR2940359A1|2010-06-25|Exhaust casing for turbine engine of engine assembly of aircraft, has structural unit passed through exterior shell in manner to locally authorize relative displacement of unit between integrated assembly and shell
    FR2946712A1|2010-12-17|ROD FOR AERONAUTICAL CONSTRUCTION AND METHOD FOR MANUFACTURING SUCH ROD
    EP2058477B1|2013-08-07|Connection of radial struts to a circular casing by pins and spacers
    EP3084140B1|2018-03-14|Guide arm for elements having an elongated shape, in particular for a turbomachine
    FR3051831A1|2017-12-01|TURBOMACHINE EXHAUST CASE AND METHOD FOR MANUFACTURING THE SAME
    FR2942638A1|2010-09-03|Angular sector for rectifier in compressor of e.g. turbojet engine, of airplane, has angular locking flange arranged coaxially around outer shell and including shoulder that is radially supported against outer shell
    EP2930308B1|2021-07-28|Faceted axial turbomachine housing
    FR2970897A1|2012-08-03|Fibrous structure for manufacturing composite part such as shaft of turboengine and turbojet of airplane, comprises matrix reinforced by fibrous structure, which has main part and edge including end part and intermediate part
    EP2435686A1|2012-04-04|Part for attaching together the mobile portion of a deployable divergent nozzle of a propulsive unit and a mechanism for deploying said mobile portion
    FR3029238A1|2016-06-03|TURBOMACHINE ASSEMBLY COMPRISING RADIANT ARMS CONNECTED WITH CIRCULAR PIECE
    FR2648638A1|1990-12-21|IMPROVEMENTS IN TRANSMISSIONS OF VEHICLES EQUIPPED WITH ELECTRIC RETARDERS
    FR3068383B1|2019-08-09|CONNECTION OF RADIAL ARMS TO A CIRCULAR VIROLE BY ILLUMINATION OF REPORTED PARTS
    EP3734101A1|2020-11-04|Engagement device for friction clutch disc and friction clutch disc including such a device
    CA2786988C|2017-11-14|Turbine engine air blower
    同族专利:
    公开号 | 公开日
    GB2538897A|2016-11-30|
    US20170030222A1|2017-02-02|
    US10371009B2|2019-08-06|
    GB201614257D0|2016-11-09|
    GB2538897B|2020-11-04|
    FR3016660B1|2018-10-05|
    WO2015110749A1|2015-07-30|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2102187A1|1970-08-11|1972-04-07|Secretaire Etat Royaume|
    WO2008121047A1|2007-03-30|2008-10-09|Volvo Aero Corporation|A gas turbine engine component, a turbojet engine provided therewith, and an aircraft provided therewith|
    WO2012150418A1|2011-05-04|2012-11-08|Snecma|Exhaust case for a turbomachine with a flexible hub|WO2017187093A1|2016-04-27|2017-11-02|Safran Aircraft Engines|Air flow rectification assembly and turbomachine comprising an assembly of this type|
    FR3056251A1|2016-09-21|2018-03-23|Safran Aircraft Engines|REINFORCED EXHAUST CASE AND METHOD OF MANUFACTURE|
    US11280204B2|2016-04-27|2022-03-22|Safran Aircraft Engines|Air flow straightening assembly and turbomachine including such an assembly|US5452575A|1993-09-07|1995-09-26|General Electric Company|Aircraft gas turbine engine thrust mount|
    FR2975131B1|2011-05-09|2015-12-25|Snecma|SUSPENSION OF THE COLD FLOW CHANNEL OF A TURBOJET ENGINE BY CONNECTING RODS AND RADIAL CHAPELS ON THE EXHAUST CASING|US10100677B2|2016-09-27|2018-10-16|General Electric Company|Fixture for restraining a turbine wheel|
    US10024164B2|2016-09-27|2018-07-17|General Electric Company|Fixture for restraining a turbine wheel|
    FR3110138A1|2020-05-14|2021-11-19|Airbus Operations |Assembly comprising two rods and an intermediate stiffener, aircraft engine attachment comprising such an assembly|
    法律状态:
    2016-01-11| PLFP| Fee payment|Year of fee payment: 3 |
    2017-01-03| PLFP| Fee payment|Year of fee payment: 4 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 5 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 7 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 8 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1450579A|FR3016660B1|2014-01-23|2014-01-23|TURBOMACHINE HOUSING WITHOUT PUNCHES AND WITH REINFORCED REINFORCED CHAPELS|
    FR1450579|2014-01-23|FR1450579A| FR3016660B1|2014-01-23|2014-01-23|TURBOMACHINE HOUSING WITHOUT PUNCHES AND WITH REINFORCED REINFORCED CHAPELS|
    PCT/FR2015/050133| WO2015110749A1|2014-01-23|2015-01-20|Turbomachine casing comprising a cavity-free shroud and yokes reinforced by stiffeners|
    US15/113,543| US10371009B2|2014-01-23|2015-01-20|Turbomachine casing comprising a cavity-free shroud and yokes reinforced by stiffeners|
    GB1614257.2A| GB2538897B|2014-01-23|2015-01-20|Turbomachine casing comprising a cavity-free shroud and yokes reinforced by stiffeners|
    [返回顶部]