• 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 an exhaust casing (10) of a turbomachine for an aircraft which extends along an axis and which comprises a central hub (20), an annular outer shell (30) and arms (40) which connect the central hub (20) to the outer shell (30), at least one yoke (50) for fixing the exhaust housing (10) to the turbomachine being located on the outer shell (30) and forms at least one ear (51) extending in a plane perpendicular to the axis and projecting outwardly from said outer shell (30), characterized in that the outer shell (30) comprises ribs (60) which form an extra thickness constant of said outer ferrule (30), which are located on either side of said at least one lug (51) of said at least one yoke (50), and which are aligned with said at least one lug (51) .
    公开号:FR3056251A1
    申请号:FR1658862
    申请日:2016-09-21
    公开日:2018-03-23
    发明作者:Benoit Argemiro Matthieu Debray；Jeremie Sylvain Bonnaudet；Gregory Ghosarossian-Prillieux；Nicolas Rene Bruno Michelidakis；Guillaume Sevi
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    GENERAL TECHNICAL AREA
    The present invention relates to an exhaust casing for a turbomachine for an aircraft.
    More specifically, it relates to a reinforced exhaust casing in order to increase the resistance of said exhaust casing to mechanical stresses, and in particular to buckling.
    The present invention also relates to a method of manufacturing such a reinforced exhaust casing.
    The present invention also relates to a turbomachine for an aircraft comprising such a reinforced exhaust casing.
    STATE OF THE ART
    A turbomachine has a main direction extending along a longitudinal axis, and typically comprises, from upstream to downstream in the direction of gas flow, a fan, a low pressure compressor, a high pressure compressor, a combustion chamber , a high pressure turbine, a low pressure turbine, and an exhaust casing (or "TRF" according to the aeronautical term, TRF being the acronym of the well known English term "Rear Frame Turbine") located directly at the outlet of said low pressure turbine.
    The exhaust casing includes:
    - a hub, of annular shape, which is centered on the axis of the turbomachine,
    - an outer ferrule, coaxial with the hub, which forms a ring of diameter greater than the hub, and
    - arms, or cuffs, connecting the hub and the outer shell.
    The space formed between the hub and the outer shell forms a flow channel for the primary stream at the outlet of the low pressure turbine.
    In order to fix the exhaust casing to a support of the turbomachine, yokes projecting from the outer shroud which form attachment points are provided on the outer wall of said outer shroud. These yokes have ears which extend radially outwards from the outer shell and which have bores for the reception of connecting rods.
    The new generations of turbomachines tend to increase the diameter of the exhaust casing, and in particular of the outer shell. Thus, for example, the fixing flange located on the contour of the outer shell, for fixing the exhaust casing with the low pressure turbine, may have a diameter greater than 2000 mm for new generation exhaust casings.
    Such an increase in the diameter of the outer shell tends to weaken the resistance of said outer shell to buckling. This weakness in buckling notably impacts the resistance of the ferrule to very heavy loads which may arise during an incident, in particular the loss of a fan blade (or “PAF” for “Loss of Dawn Fan”, according to the well-known aeronautical term). ).
    Reinforced exhaust casings of the type of the exhaust casing 1 are known for a turbomachine illustrated in FIG. 1. The exhaust casing 1 comprises a hub 2 connected to a ferrule 3 by arms 4. The reinforcement of the casing d exhaust 1 is provided by a stiffener 5 fixed at each of its two ends to a yoke 6, so as to connect two adjacent yokes 6 together. The stiffener 5 is fixed by a flange disposed in a bore formed in each of the yokes 6.
    Such a casing has, for example, already been proposed in the document FR. 3,016,660.
    However, it does not sufficiently increase the buckling resistance of the exhaust casing 1, and in particular of the shell 3, while keeping the mass of the exhaust casing 1 as low as possible.
    OVERVIEW OF THE INVENTION
    A general object of the invention is to propose a solution making it possible to increase the buckling resistance of an exhaust casing of a turbomachine, without increasing the mass of said exhaust casing.
    Another object of the invention is to propose a solution making it possible to reduce the mass of an exhaust casing of a turbomachine while maintaining the same buckling resistance.
    An object of the invention can also be to propose a solution making it possible to increase the buckling resistance of an exhaust casing of a turbomachine, by increasing the mass of said exhaust casing to a limited extent.
    More particularly, according to a first aspect, the invention provides an exhaust casing of a turbomachine for an aircraft, said exhaust casing extending along an axis and comprising a central hub, an annular external ferrule and arms which connect the central hub to the outer shell, at least one yoke for fixing the exhaust casing to the turbomachine being located on the outer shell and forming at least one ear extending in a plane perpendicular to the axis and projecting outwardly of said outer shell, the outer shell further comprising ribs which are located on either side of said at least one ear of said at least one yoke, and which are aligned with said at least one ear.
    The exhaust casing can also include the following characteristics alone, or in all technically possible combinations:
    - Two yokes are formed on the outer ferrule, the ribs formed on said outer ferrule comprising a central rib connecting together the ears of said two yokes, and two outer ribs connected to a single ear;
    - The arms each include a top connected to the outer shell and a foot connected to the central means, and in which two ribs include an end which each stops opposite the top of an arm;
    - The arms comprise on the one hand a yoke arm located opposite a yoke, and on the other hand non-yoke arms forming the rest of said arms, said non-yoke arms comprising a first arm yoke and a second arm yoke which are both adjacent to said yoke arm, the end of the two ribs stopping respectively opposite the top of the first arm outside the yoke and facing the top of the second arm out of the yoke;
    - the outer shell includes:
    - A first zone corresponding to the ribs on which said outer shell has a first thickness;
    - A second zone extending from the top of the first non-yoke arm to the top of the second non-yoke arm by covering the top of the yoke arm, and on which said outer ferrule has a second thickness which is less than the first thickness;
    - A third zone extending over the rest of said outer shell and over which said outer shell has a third thickness which is less than the second thickness;
    - The at least one yoke comprises two parallel ears which are spaced from one another, and in which the outer shell comprises two rows of grooves located on either side of each of the two ears and which are parallel and spaced axially from each other;
    - The exhaust casing is an exhaust casing with tangential arms.
    According to a second aspect, the invention proposes a turbomachine for an aircraft comprising an exhaust casing according to the first aspect.
    According to a third aspect, the invention proposes a method for manufacturing an exhaust casing according to the first aspect comprising the following steps:
    assembling at least one first panel with second panels, said at least one first panel forming an annular portion along an axis of an external ferrule and comprising at least one yoke which forms at least one ear extending in a plane perpendicular to the the axis and projecting towards the outside of said at least one first panel, said at least one first panel further comprising ribs which are situated on either side of said at least one ear of said at least one yoke, and which are aligned with said at least one ear, the second panels each forming an annular portion along the axis of the outer shell.
    According to a fourth aspect, the invention proposes a method of manufacturing an exhaust casing according to the first aspect comprising the following steps:
    machining an outer wall of an annular external ferrule along an axis which comprises at least one yoke which forms at least one ear extending in a plane perpendicular to the axis and projecting towards the outside of said external ferrule, forming ribs on either side of said at least one ear of said at least one yoke, and which are aligned with said at least one ear.
    DESCRIPTION OF THE FIGURES
    Other characteristics, aims and advantages of the present invention will appear on reading the detailed description which follows, and with reference to the appended drawings, given by way of nonlimiting examples and in which:
    • Figure 1 shows a front view of a portion of an exhaust casing according to the prior art;
    • Figure 2 shows a half view of an exhaust casing according to a possible embodiment of the invention which is mounted in a turbomachine of an aircraft in which said exhaust casing comprises at least one yoke forming at minus two ears;
    • Figure 3 shows a perspective view of a portion of the exhaust casing according to a possible embodiment of the invention in which said exhaust casing comprises three yokes each forming two ears;
    • Figure 4 shows a detailed view of the embodiment illustrated in Figure 3 at the outer ribs located opposite a first arm outside the yoke;
    • Figure 5 shows a detailed view of the embodiment illustrated in Figure 3 at the level of central ribs;
    • Figure 6 shows a detailed view of the embodiment illustrated in Figure 3 at the outer ribs located opposite a second arm outside the yoke;
    • Figure 7 shows a section of the outer shell as illustrated in Figure 3 at the grooves formed at the ends of the ears of the yokes;
    • Figure 8 shows a method of manufacturing an exhaust casing according to a first possible implementation of the invention;
    • Figure 9 shows a method of manufacturing an exhaust casing according to a second possible implementation of the invention.
    DESCRIPTION OF ONE OR MORE EXAMPLES OF MODE OF
    PRODUCTION
    FIG. 2 shows an exhaust casing 10 fixed to a low pressure turbine 11 of a turbomachine for an aircraft. The exhaust casing 10 is a part extending along an axis Ω which is the axis of the turbomachine, the radial direction of the exhaust casing being perpendicular to the axis Ω.
    As shown in FIG. 2, the exhaust casing 10 comprises a central hub 20 which is an annular part centered on the axis Ω of the turbomachine, an external shroud 30 which is also an annular part centered on the axis Ω of the turbomachine, and arms 40 which connect the central hub 20 to the outer shell 30 while being distributed radially around the contour of the central hub 20.
    The central hub 20 comprises an internal wall 21 directed towards the interior of the central hub 20, and an external wall 22 directed towards the exterior of the central hub 20, as well as towards the external ferrule 30.
    The external shell comprises an internal wall 31 directed towards the interior of the external shell 30, as well as towards the central hub 20, and an external wall 32 directed towards the exterior of said external shell 30.
    The arms 40 include a foot 41 connected to the external wall 22 of the central hub, and apex 42 connected to the internal wall 31 of the external shell 30.
    As illustrated in FIGS. 2 to 7, at least one yoke 50 for fixing the exhaust casing 10 to the turbomachine is located on the external wall 32 of the external ferrule 30. In the example illustrated in FIG. 3 the ferrule external 30 includes three yokes 50, however said external ferrule can include a greater or lesser number of yokes 50. The external ferrule 30 can for example comprise a single yoke 50.
    The yokes 50 each form at least one lug 51 projecting radially outward from the outer shell 30 which includes a bore in order to fix the yokes 50 to the fastening elements of the turbomachine by connecting rods arranged in the bores. The ears 51 are fins of rounded shape located in a plane perpendicular to the axis Ω.
    In the embodiment shown in Figure 2, the yokes 50 are U-shaped parts and each include two parallel ears 51 which are axially spaced from one another. However, the yokes 50 can form a greater or lesser number of ears 51. For example the yokes 50 can form only one ear 51. The yokes 50 all include the same number of ears 51, and said ears 51 of the yokes 50 are aligned in the same plane (s) perpendicular to the axis Ω. Thus, as in the example illustrated in FIG. 2, when the yokes 50 form two ears 51, then the external ferrule 30 comprises two rows of ears 51 parallel and axially spaced from one another.
    The arms 40, which are visible in FIG. 3, comprise two categories of arms 40, on the one hand screed arms 40a situated radially opposite the screeds 50, and on the other hand non-screed arms 40b which correspond to the rest said arms 40. In other words, at the top 42 of the yoke arms 40a is located a yoke 50, while at the top 42 of the arms outside the yoke 40b there is no yoke 50. A reinforcement can be formed under the foot 41 yoke arms 40a on the central hub 20.
    The non-clevis arms 40b comprise a first non-clevis arm 43 and a second non-clevis arm 44 which are the two non-clevis arms 40b which are adjacent to the clevis arms 40a and which are located on either side of said clevis arms 40a . In the embodiment in which the outer shell 30 comprises only a single yoke 50, the first arm without yoke 43 and the second arm without yoke 44 are both adjacent to the same yoke arm 40a, the arms 40 only comprising a single yoke arm 40a.
    The external shell 30 comprises ribs 60 formed on the external wall 32 of said shell 30 which participate in increasing the buckling resistance of the exhaust casing 10, and in particular of the external shell 30.
    The ribs 60 are formed on either side of the ears 51 of each of the yokes 50, and are aligned with said ears 51 to which the ribs 60 are connected. The ribs 60 are formed in the extension of the ears 51. Thus, the ribs are located in the plane perpendicular to the corresponding axis Ω of said ears 51. A rib comprises a first end connected to one ear and a second end opposite to the first end.
    The ribs 60 each form, in the radial direction, a constant excess thickness of the outer shell 30 which extends the variable excess thickness of said outer shell 30 formed by each of the ears 51. The transition between the ears 51 and the ribs 60 is gradual in order to do not form edges at which the mechanical stresses are concentrated. The ribs 60 preferably have a width, in the axial direction, identical to the ears 51.
    The extra thicknesses created by the ribs 60, which join by the ears 51, form stiffeners of the outer shell 30 extending substantially transversely relative to the axis Ω. These stiffeners formed by the ribs 60 increase the resistance to bending of the outer shell at the level of the yokes 50, thereby increasing the resistance of the exhaust casing to buckling.
    Indeed, during the loss of a fan blade, the charges created by this loss of blade come from an imbalance of the low pressure shaft which is connected to said fan. These loads are therefore transmitted to the exhaust casing by the central hub 20 which is fixed to bearings which are themselves fixed to the low pressure shaft. The exhaust casing 10 being fixed to the turbomachine by the yokes 50, the mechanical stresses due to these loads are concentrated at the level of the yoke arms 40a and of the outer shell part 30 located near said yokes 50. The buckling of the exhaust casing is therefore caused by the bending of the outer shell 30 and the yoke arms
    40a when the mechanical stresses become too great.
    Thus, locally strengthening the thickness of the outer shell 30 at the level of the yokes 50 by forming the ribs 60 makes it possible to increase the buckling resistance of the exhaust casing while limiting the increase in the mass of said exhaust casing due local thickness increases of the outer shell 30.
    In addition, this solution is particularly advantageous when the exhaust casing 10 is an exhaust casing with tangential arms. An exhaust casing 10 with tangential arms is an exhaust casing 10 whose arms 40 are inclined with respect to a radial direction defined a straight line normal to the axis Ω. The arms 40 being inclined relative to the normal to the axis Ω, the buckling resistance of the exhaust casing 10 is lower.
    However, the invention also applies to an exhaust casing 10 whose arms 40 are radial, that is to say oriented along a straight line perpendicular to the axis Ω.
    In the embodiments in which the outer shell 30 comprises several yokes 50, therefore at least two yokes 50, the ribs 60 formed on the outer shell 30 comprise on the one hand central ribs 61 whose first and second ends connect to each other the ears 51 of two adjacent yokes 50, and on the other hand external ribs 62, the respective first end of which is connected to a single ear 51.
    By “connected to a single ear 51” it is understood that the outer ribs 62 are connected only to one ear 51 of the yoke 50, unlike the central ribs 61 connected to two ears 51, but that said outer ribs 62 can be connected to other elements located on the outer shell 30, such as for example duct fixing openings.
    The fact that the ears 51 of adjacent yokes 50 are connected by the central ribs 61 makes it possible to create a continuous stiffener, thus preventing the creation of zones of weakness between the yokes 50 due to a local stop of said stiffener created by the ribs 60.
    In the embodiment in which the outer shell 30 comprises a single yoke 50 comprising a single ear 51, the outer shell 30 comprises only two outer ribs 62 located on either side of said ear 51, the first ends of the two ribs 62 being connected to the ear 51.
    In the embodiment in which the outer shell 30 comprises only two yokes 50 each comprising a single ear 51, the outer shell 30 comprises a single central rib 61 connecting the two ears 51, as well as two outer ribs 62 connected to said ears to the opposite the central rib 61.
    In the embodiment in which the outer shell 30 comprises only three yokes 50 each comprising a single ear 51, the outer shell 30 comprises two central ribs 61 located on either side of the ear 51 of the yoke 50 located at the center of the three yokes 50, as well as two outer ribs 62 each connected to an ear 51 opposite the central ribs 61.
    According to an advantageous variant, the outer ribs 62 include their first end which is connected to an ear 51 and their second end which stops at the top 42 of an arm 40. The second end of the outer ribs 62 is therefore located opposite the apex 42 of an arm 40. This variant makes it possible to improve the buckling resistance of the exhaust casing 10 because the stiffener formed by the ribs 60 ends at each of its ends at the apex 42 of an arm 40, thus avoiding concentrating the mechanical stresses in a part of the outer shell 30 located between two arms 40 and therefore having a lower flexural strength.
    Preferably, the second end of the outer ribs 62 ends respectively at the apex 42 of the first arm outside of the yoke 43 and at the apex 42 of the second arm outside of the yoke 44. This characteristic is a good compromise for the length of the stiffener formed by the ribs 60 between the improvement in the flexural strength of the outer shell 30 and the increase in mass due to the formation of the ribs 60. In addition, it is advantageous for the stiffener formed on the contour of the outer shell 30 by the ribs 60 does not have too long a length because of the expansion of said outer shell 30 during operation of the turbomachine under the effect of heat. Indeed, the local excess thickness formed by the ribs 60 has a greater thermal inertia than the rest of the outer shell 30 which is finer, which can generate mechanical stresses negatively impacting the life of the exhaust casing 10 if the ribs 60 extend over too large a part of the contour of said external shell 30.
    The outer shell 30 may include a first zone A in which said external shell 30 has a first thickness, a second zone B in which said external shell 30 has a second thickness thinner than the first thickness, and a third zone C in which said outer shell 30 has a third thickness which is weaker than the second thickness.
    The first zone A corresponds to the ribs 60, which for example have a thickness of 15 mm in the radial direction. The second zone B extending from the top 42 of the first non-yoke arm 43 to the top 42 of the second non-yoke arm 44 by covering the top 42 of the yoke arms 40a. The second thickness can for example be 6mm. The second zone B makes it possible to further strengthen the resistance to bending of the external shell at the level of the yokes 50. The third zone C covers the remainder of the external shell 30 which does not correspond to the first zone A and to the second zone B. The third thickness may for example be 4 mm.
    According to a possible variant illustrated in FIGS. 3 to 7 in which the yokes 50 comprise several ears 51 which are parallel and axially spaced from one another, the outer shell 30 comprises several rows of ribs 60 which are parallel and axially spaced apart. Each row of grooves corresponds to a row of ears of the yokes 50. Thus, when the yokes 50 each comprise two ears 51, the outer shell 30 comprises two rows of ribs 60 parallel.
    In the variant in which the outer shell 30 comprises only a single yoke 50 which comprises several ears 51, said shell 30 comprises as many parallel rows of ribs 60 each comprising only two outer ribs 62 as the number of ears 51 that comprises the single yoke 50.
    The rows of ribs 60 may have a different thickness in the radial direction. Thus, for example, a first row of ribs 60 can have a thickness of 13 mm while a second row can have a thickness of 15 mm.
    For an exhaust casing 10 as illustrated in FIGS. 3 to 7, the outer ring 30 of which comprises three yokes 50 which each form two ears 51, the ribs 60 therefore comprising parallel rows each formed by two central ribs 61 and two outer ribs 62, an increase of about 10% in buckling resistance is obtained compared to an exhaust casing of the same diameter according to the state of the art, while reducing the mass by about 1%.
    The exhaust casing 10 can be obtained by welding several panels obtained by foundry which form portions of said exhaust casing 10, such as for example portions of the outer shell 30, said panels being assembled together to form said casing d exhaust 10.
    According to a first implementation of the invention, the exhaust casing 10 can be obtained by a manufacturing process as illustrated in FIG. 8 comprising the following steps:
    step 100: assembling at least a first panel with second panels, said at least one first panel forming an annular portion of the outer shell 30 and comprising at least one yoke 50 which forms at least one ear 51 projecting outwards from said at least one first panel, said at least one first panel further comprising ribs 60 which form a constant excess thickness of said at least one first panel, which are located on either side of said at least one ear 51 of said at least a yoke 50 in the extension of said at least one ear 51, and which are aligned with said at least one ear 51 of said at least one first panel, the second panels each forming an annular portion of the outer shell 30, so as to form the complete outer shell 30.
    The number of yokes 50 that comprises the outer shell 30 obtained by this variant of the manufacturing process is adapted with the number of first panels supplied. In addition, in order to, for example, form an outer shell with three adjacent yokes 50, three first panels are assembled together, for example by welding.
    In this variant of the manufacturing process, the ribs 60 can be formed by portions of ribs located on different panels, which once assembled, align in a same plane perpendicular to the axis Ω and then put one after the other different portions of ribs so as to constitute said ribs 60.
    According to a second implementation of the invention, the exhaust casing 10 can be obtained by a manufacturing process as illustrated in FIG. 9 comprising the following steps:
    step 200 to machine an outer wall 32 of an outer ferrule 30, said outer ferrule 30 comprising at least one yoke 50 forming at least one lug 51 which protrudes outward from said outer ferrule 30, forming ribs 60 and on the other side of said at least one ear 51, said ribs 60 forming a constant extra thickness of said external ferrule 30, and being aligned with said at least one ear 51.
    The ribs 60 are therefore formed in this embodiment by removal of material on the external surface 32 of the external shell 30. Before the machining step, the external shell 30 therefore comprises, at the level of the at least one yoke 50 , a transient thickness greater than the final thickness, so that the ribs 60 can be formed.
    In the embodiments presented above, the yokes 50 are grouped on the same area of the outer shell 30, thus forming a single area of attachment of the outer shell 30. However, according to a possible variant, the yokes 50 can insulated by being distributed over the contour of the outer shell 30. According to one possible example, the yokes 50 are equally distributed over the contour of the outer shell 30, for example by forming two diametrically opposite yokes 50 on the outer shell 30, or for example by forming three yokes 50 spaced at an angle of 120 °. However, other configurations for distributing the yokes 50 along the contour of the outer shell 30 are possible.
    In the variant according to which the yokes 50 are isolated, the ribs 60 formed on either side of said one or more ears 51 of the isolated yokes 50 only comprise external ribs 62.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. Exhaust casing (10) of a turbomachine for an aircraft, said exhaust casing (10) extending along an axis (Ω) and comprising a central hub (20), an annular external ferrule (30) and arms (40) which connect the central hub (20) to the outer shroud (30), at least one yoke (50) for fixing the exhaust casing (10) to the turbomachine being located on the outer shroud ( 30) and forming at least one lug (51) extending in a plane perpendicular to the axis (Ω) and projecting towards the outside of said external ferrule (30), characterized in that the external ferrule (30) comprises ribs (60) which are located on either side of said at least one ear (51) of said at least one yoke (50), and which are aligned with said at least one ear (51).
    [2" id="c-fr-0002]
    2. Exhaust casing (10) according to claim 1, in which two yokes are formed on the external ferrule (30), the ribs (60) formed on said external ferrule (30) comprising a central rib (61) connecting between they the ears of said two yokes, and two outer ribs (62) connected to a single ear (51).
    [3" id="c-fr-0003]
    3. Exhaust casing (10) according to claim 1 or 2, in which the arms (40) each comprise a top (42) connected to the outer shell (30) and a foot (41) connected to the central hub (20 ), and in which two ribs (60) comprise an end which each stops opposite the top of an arm (40).
    [4" id="c-fr-0004]
    4. Exhaust casing (10) according to claim 3, in which the arms (40) comprise on the one hand a yoke arm (40a) situated opposite a yoke (50), and on the other hand non-yoke arms (40b) forming the rest of said arms (40), said non-yoke arms (40b) comprising a first non-yoke arm (43) and a second non-yoke arm (44) which are both adjacent to said yoke arm (40a), the end of the two ribs (60) stopping respectively opposite the top (42) of the first arm outside the yoke (43) and facing the top (42) of the second arm out of the yoke (44).
    [5" id="c-fr-0005]
    5. Exhaust casing (10) according to claim 4, in which the outer shell (30) comprises:
    - A first zone (A) corresponding to the ribs (60) on which said outer shell (30) has a first thickness;
    - A second zone (B) extending from the top (42) of the first non-yoke arm (43) to the top (42) of the second non-yoke arm (44) by covering the top (42) of the yoke arm (40a) , and on which said outer shell (30) has a second thickness which is less than the first thickness;
    - A third zone (C) extending over the rest of said outer shell (30) and on which said outer shell (30) has a third thickness which is less than the second thickness.
    [6" id="c-fr-0006]
    6. Exhaust casing (10) according to any one of claims 1 to 5, in which the yoke (50) comprises two parallel ears (51) which are axially spaced from one another, and in which the outer shell (30) comprises two rows of grooves (60) located on either side of each of the two ears (51) and which are parallel and axially spaced from one another.
    [7" id="c-fr-0007]
    7. exhaust casing (10) according to any one of claims 1 to 6, wherein said exhaust casing (10) is an exhaust casing (10) with tangential arms (40).
    [8" id="c-fr-0008]
    8. Turbomachine for aircraft comprising an exhaust casing (10) according to any one of claims 1 to 7.
    [9" id="c-fr-0009]
    9. A method of manufacturing an exhaust casing (10) according to any one of claims 1 to 7 comprising the following steps:
    - (100) assembling at least a first panel with second panels, said at least one first panel forming an annular portion along an axis (Ω) of an external ferrule (30) and comprising at least one yoke (50) which forms at least one ear (51) extending in a plane perpendicular to the axis (Ω) and projecting outward from said at least one first panel, said at least one first panel further comprising ribs (60) which are located on either side of said at least one ear (51) of said at least one yoke (50), and which are aligned with said at least one ear (51),
    5 and the second panels each forming an annular portion along the axis (Ω) of the outer shell (30).
    [10" id="c-fr-0010]
    10. A method of manufacturing an exhaust casing (10) according to any one of claims 1 to 7 comprising the following steps:
    10 - (200) machining an outer wall (32) of an annular outer shell (30) along an axis (Ω) which comprises at least one yoke (50) which forms at least one ear (51) extending in a plane perpendicular to the axis (Ω) and projecting towards the outside of said external ferrule (30), forming ribs (60) on either side of said at least one ear (51) of said at least a screed,
    [11" id="c-fr-0011]
    15 and which are aligned with said at least one ear (51).
    305625
    1/7
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    同族专利:
    公开号 | 公开日
    FR3056251B1|2018-09-07|
    US10746056B2|2020-08-18|
    US20180080345A1|2018-03-22|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    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|
    EP2003293A1|2007-06-13|2008-12-17|Snecma|Turbomachine exhaust case|
    EP2251540A2|2009-05-15|2010-11-17|Pratt & Whitney Canada Corp.|Turbofan mounting system|
    WO2015004059A1|2013-07-09|2015-01-15|Snecma|Turbine engine casing having a cut-out flange|
    FR3016660A1|2014-01-23|2015-07-24|Snecma|TURBOMACHINE HOUSING WITHOUT PUNCHES AND WITH REINFORCED REINFORCED CHAPELS|
    FR2677953B1|1991-06-19|1993-09-10|Snecma|REAR SUSPENSION STRUCTURE OF A TURBOREACTOR.|
    FR2973339B1|2011-03-29|2014-08-22|Snecma|DEVICE FOR THE SUSPENSION OF A TURBOMACHINE TO AN AIRCRAFT|
    FR3015434B1|2013-12-23|2017-12-08|Snecma|TURBOMACHINE SUSPENSION|
    FR3039207B1|2015-07-21|2019-07-26|Safran Aircraft Engines|EXHAUST CASE OF A TURBOMACHINE WITH INCREASED LIFETIME|US10774685B2|2018-04-30|2020-09-15|Ratheon Technologies Corporation|Gas turbine engine exhaust component|
    US10822964B2|2018-11-13|2020-11-03|Raytheon Technologies Corporation|Blade outer air seal with non-linear response|
    US10934941B2|2018-11-19|2021-03-02|Raytheon Technologies Corporation|Air seal interface with AFT engagement features and active clearance control for a gas turbine engine|
    US10920618B2|2018-11-19|2021-02-16|Raytheon Technologies Corporation|Air seal interface with forward engagement features and active clearance control for a gas turbine engine|
    法律状态:
    2017-05-15| PLFP| Fee payment|Year of fee payment: 2 |
    2018-03-23| PLSC| Publication of the preliminary search report|Effective date: 20180323 |
    2018-08-22| PLFP| Fee payment|Year of fee payment: 3 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 4 |
    2020-08-19| PLFP| Fee payment|Year of fee payment: 5 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1658862A|FR3056251B1|2016-09-21|2016-09-21|REINFORCED EXHAUST CASE AND METHOD OF MANUFACTURE|FR1658862A| FR3056251B1|2016-09-21|2016-09-21|REINFORCED EXHAUST CASE AND METHOD OF MANUFACTURE|
    US15/710,026| US10746056B2|2016-09-21|2017-09-20|Reinforced exhaust casing and manufacturing method|
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