• 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 cooling device (21) extending circumferentially around a turbomachine casing, such as for example a turbine casing, comprising at least one cooling module (30a, 30b, 30c) comprising a support of tubes (31, 32) having at least one sheet, preferably a radially inner sheet (31) and a radially outer sheet (32) fixed relative to each other, the tube support (31, 32) defining at least two housings (34a) spaced axially from each other, each housing (34a) receiving a tube (23) and a sleeve (38) mounted around each tube (23), each tube (23) s extending circumferentially around the casing, each cooling module (30a, 30b, 30c) comprising first fixing means able to fixably hold its tube support (31, 32) relative to the casing, the fixing means comprising at least one spacer (41) having a radially inner end for come to bear against the housing and a radially outer end bearing on the or one of the tubes of the tube support (31, 32).
    公开号:FR3077097A1
    申请号:FR1850473
    申请日:2018-01-22
    公开日:2019-07-26
    发明作者:Jean-Marc Marcel Beauquin Nicolas
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Cooling device for a turbine of a turbomachine
    FIELD [001] The present invention relates to a cooling device for a turbine of a turbomachine, such as for example an airplane turbojet, in particular a turbofan.
    BACKGROUND [002] FIG. 1 represents a turbomachine 1 with double flow and with double body. The axis of the turbomachine is referenced X and corresponds to the axis of rotation of the rotating parts. In what follows, the axial and radial terms are defined with respect to the X axis.
    The turbomachine 1 comprises, from upstream to downstream in the gas flow direction, a fan 2, a low pressure compressor 3, a high pressure compressor 4, a combustion chamber 5, a high turbine pressure 6 and a low pressure turbine 7.
    The air from the fan 2 is divided into a primary flow 8 flowing in a primary annular vein 9, and a secondary flow 10 flowing in a secondary annular vein 11 surrounding the primary annular vein 10. [ The low pressure compressor 3, the high pressure compressor 4, the combustion chamber 5, the high pressure turbine 6 and the low pressure turbine 7 are formed in the primary stream 9.
    The rotor of the high pressure turbine 6 and the rotor of the high pressure compressor 4 are coupled in rotation by means of a first shaft 12 so as to form a high pressure body.
    The rotor of the low pressure turbine 7 and the rotor of the low pressure compressor 3 are coupled in rotation by means of a second shaft 13 so as to form a low pressure body, the fan 2 being able to be connected directly to the rotor of the low pressure compressor 3 or else via an epicyclic gear train for example.
    As is best seen in Figure 2, the low-pressure turbine 7 has in particular different successive stages comprising movable wheels 14 and fixed parts. The movable wheel comprises a disc 15 at the level of which blades are mounted 16. The ends of the blades 16 are surrounded by a fixed ring 17 of abradable material, said ring 17 being fixed on the casing 18 of the turbine. Distributors 19 are located downstream of the movable wheels 14. The distributors 19 and the rings 17 are mounted on the casing by means of flanges or hooks 20 extending from the radially internal surface of the casing 18.
    In order to guarantee a high efficiency of the turbomachine, it is necessary to limit the air flow which does not pass through the movable wheels 14 of the different stages, that is to say to limit the leaks between the radially outer ends of the vanes 16 and the ring 17 of abradable material. For this, it is necessary to control the clearance at this interface, this clearance being strongly dependent on the temperature of the casing 18, and in particular of the zones of said casing 18 comprising the hooks or flanges 20 supporting the ring 17.
    The primary air flow from the combustion chamber 5 has a very high temperature and heats the parts located downstream, such as the fixed and mobile parts of the turbine 6, 7.
    [011] In order to control the aforementioned play and to avoid any premature degradation of the different fixed and mobile parts of the turbine, it is necessary to provide efficient cooling means which can be easily integrated into the environment of the turbomachine.
    Patent application FR 3 021 700, in the name of the Applicant, discloses a cooling device 21 of a casing 18 of a low pressure turbine 7, visible in FIG. 3, comprising manifold boxes 22, each manifold box 22 forming an axially extending channel.
    The device 21 further comprises tubes 23 extending circumferentially on either side of the manifolds 22. Said tubes 23, also called ramps, are formed by curved pipes of circular section, each tube 23 s extending circumferentially around the housing for example at an angle of about 90 °.
    [014] Each tube 23 has an air inlet opening into the channel of the corresponding manifold housing 22 and a closed distal end. Each tube 23 further comprises a cylindrical wall provided with air ejection orifices facing the casing 18, so that cooling air can penetrate into the manifolds 22 and then into the tubes 23 before opening out by the orifices facing the casing 18, so as to cool it. We speak in particular of impact cooling since the air comes to impact the housing 18.
    All the tubes 23 are held together on the casing 18 by means of fixing means 24, at different places on the circumference of the casing 18. The fixing means 24 each comprise a radially internal plate and a plate radially external. The plates are fixed to each other and to the casing 18 by means of screws. In particular, the radially internal plate is held in contact with the radially external surface of the casing 18.
    [016] Such a structure needs to be improved to more effectively support the axial expansion of the casing. Indeed, in operation, the heating of the casing causes an axial and circumferential expansion of the housing. All the tubes of the above-mentioned cooling device are mounted together on the casing. Furthermore, the axial expansion of the sheets is not identical to the axial expansion of the housing, which can generate significant mechanical stresses and premature wear between the means for fixing the sheets and the housing, at the level of the tubes and / or at the areas of attachment of the tubes to the manifolds.
    SUMMARY OF THE INVENTION [017] The aim of the invention is in particular to provide a simple, effective and economical solution to these problems.
    To this end, it proposes a cooling device extending circumferentially around a turbomachine casing, such as for example a turbine casing, comprising at least one cooling module comprising a tube support having at least a sheet, preferably a radially internal sheet and a radially external sheet fixed with respect to each other, the tube support delimiting at least two housings spaced apart axially from each other, each housing receiving a tube and a bushing mounted around each tube, each tube extending circumferentially around the casing, each cooling module comprising first fixing means capable of fixedly holding its tube support relative to the casing, the fixing means comprising at least one spacer comprising a radially internal end intended to come into abutment against the casing and a radially external end coming in a ppui on one or one of the sheets of the tube support.
    [019] This support can be direct or indirect. In the case where the supports are indirect, that is to say are carried out by means of an additional element.
    The axial and radial terms are defined with respect to the axis around which the tube extends circumferentially, which can be globally coincident with the axis of the casing.
    [021] In this way, the spacer is able to maintain at a determined value the radial distance between the sheets and the housing, and therefore also the radial distance between the tubes mounted in the housing of the sheets and the housing. This distance is also called the air gap. The distance between the tubes and the housing can thus be controlled regardless of the expansion of the housing, so that the cooling of the housing is also controlled. Furthermore, contact with the tubes on the casing and therefore premature wear of the tubes is avoided.
    [022] In particular, the planned arrangement of the spacers also makes it possible to limit the heat exchanges between the casing and the tubes, in particular to maintain a low temperature of the cooling air.
    The distance between the tubes and the casing is for example between 2 and 10 mm.
    Each module can have between 2 and 5 tubes.
    [025] The spacer can be considered to be non-deformable, in particular in the radial direction. It is not, for example, formed by a sheet, which is flexible or deformable. In the case where at least one of the abovementioned supports of the spacer on the radially internal sheet and on the casing is indirect, that is to say is produced by means of an additional element, then the additional element is also undeformable.
    [026] The circumferential sliding of the tubes in the sockets makes it possible to compensate for the circumferential expansion of the casing.
    [027] Furthermore, the fact that the tubes are grouped into different modules fixed independently of each other on the casing makes it possible to adapt to the effects of axial expansion of the casing while retaining the axial positions of the tubes with respect to the zones of the casing to be cooled, in particular with respect to the radially internal flanges or hooks of the casing used for example for mounting the distributors or abradable rings of the turbine.
    [028] As is known per se, the tubes may include air ejection orifices directed towards the casing, that is to say opening radially inwards. The holes can be evenly distributed over the entire circumference and can form one or more rows of holes per tube.
    The first fastening means may include a screw or a rivet extending in the spacer, the spacer being tubular and surrounding said screw or said rivet.
    At least one cooling module comprises second fixing means axially spaced from the first fixing means, the second fixing means being able to fix the sheets of the module fixedly relative to each other and intended to fix said sheets to the housing. [031] The first fixing means and the second fixing means can be located axially on either side of all the tubes of the same module. Fixing means can also be provided axially between the tubes of the same module.
    The second fixing means may comprise a spacer comprising a radially internal end intended to come into abutment against the casing and a radially external end coming to bear on the or one of the sheets of the tube support.
    The second fixing means may comprise a connecting plate fixed to the support of the cooling module tubes and intended to be fixed to a radial annular flange of the housing.
    [034] The second fixing means are then devoid of spacer. Indeed, the connecting sheet does not form a spacer per se because, unlike the spacer, it cannot be considered to be non-deformable or almost non-deformable, especially in the radial direction.
    The first and / or second fastening means may comprise at least one screw or a rivet engaged in an oblong hole in the sheets, the radially outer end of the screw or the rivet comprising a shoulder, an elastic member being mounted between said shoulder and the tube support.
    [036] The shoulder may be formed by an enlarged head of the screw or the rivet, or by a nut screwed onto a thread of the screw.
    [037] The oblong hole allows the displacement of the fastening means relative to the sheets, in the event of axial expansion of the casing. The elastic member makes it possible to keep the radially external sheet metal in abutment on the radially internal sheet metal, so as to maintain the sockets in the corresponding housings of the sheets. The radially internal and external sheets are in fact not welded to each other.
    [038] The elastic member can be a spring, such as for example a helical compression spring. The elastic member can also be an elastic washer, such as for example a Belleville washer.
    [039] The first and / or second fixing means may include a screw or a rivet engaged in holes in the tube support of the cooling module, one of the screws or one of the rivets being engaged in an oblong hole , the other screw or rivet being engaged without play in a circular hole.
    The term "without play" refers to the absence of an oblong shape of the hole. Of course, there can be a slight mounting clearance between the screw or the rivet and the holes in the module sheets.
    [041] The first and / or second fixing means may comprise a screw or a rivet engaged in oblong holes in the support of the tubes of the cooling module.
    [042] This makes it possible to compensate for significant expansion of the casing and in particular to avoid the appearance of cracks or cracks at the level of the connection between the tubes and the corresponding manifold housing.
    [043] The radially inner sheet and / or the radially outer sheet of the tube support can form housings and the tube support comprises at least one stiffener extending axially between the housings of the sheets.
    [044] Each sheet may include a stiffener. Each stiffener can be formed by a sheet extending radially and axially, welded to the corresponding radially internal or external sheet.
    At least one socket can extend circumferentially on either side of a housing for the tube support of a cooling module.
    [046] In this way, it avoids any contact of the tubes on the sheets, in order to prevent any premature wear of the tubes, in particular when the assembly is subjected to vibrations.
    [047] The sleeve can be fixed by stamping on the sheets. The sleeve can be made of silica.
    [048] The invention also relates to an assembly comprising an annular casing of a turbomachine, for example an annular casing of a turbine, characterized in that it may comprise a cooling device of the aforementioned type, fixed to said casing and surrounding said casing, the fixing means ensuring the fixing of the sheets to the casing, the radially internal end of the spacer of said first and / or second fixing means coming to bear against the radially external surface of the casing.
    [049] The casing may include cylindrical portions and frustoconical portions.
    The invention also relates to an assembly for a turbine, comprising an annular casing and a cooling device of the aforementioned type.
    [051] The invention further relates to a turbofan engine, comprising a fan 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 compressor, a combustion chamber and a turbine comprising a turbine casing,
    - a secondary stream in which flows a secondary stream distinct from the primary stream, characterized in that the turbine comprises a cooling device of the aforementioned type, located radially outside the turbine casing.
    [052] 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 view in axial section of a turbofan engine of the prior art,
    FIG. 2 is a view in axial section of a part of the turbojet engine of the prior art, in particular illustrating the low pressure turbine,
    FIG. 3 is a perspective view of a cooling device of the prior art,
    FIG. 4 is a perspective view of part of a cooling device according to an embodiment of the invention,
    FIG. 5 is a top view of part of the cooling device according to the invention,
    FIG. 6 is a view in axial section of a part of the cooling device according to the invention,
    - Figures 7 and 8 are detailed views in axial section of a part of the cooling device, illustrating two alternative embodiments of the invention.
    DETAILED DESCRIPTION [053] Figures 4 to 6 illustrate a part of a cooling device 21 mounted on a casing 18 of a low pressure turbine 7 of an aircraft turbomachine 1, according to an embodiment of the invention.
    [054] The casing 18 is of annular shape and has, from upstream to downstream, an upstream radial annular flange 24, a first cylindrical part 25, a first frustoconical part 26, a second frustoconical part 27, a second cylindrical part 28 and a downstream radial annular flange 29. The flanges 24, 29 allow the turbine casing 18 to be connected to other casings of the turbomachine 1.
    [055] The cooling device 21 comprises three modules 30a, 30b, 30c, respectively an upstream module 30a, a middle module 30b and a downstream module 30c. The terms upstream, downstream, axial and radial are defined below with respect to the axis of the housing 18.
    [056] Each module 30a, 30b, 30c comprises a radially internal sheet metal 31 and a radially external sheet metal 32. Each sheet metal 31,32 comprises at least one axially planar central part 33, two planar axial end parts 34, and two portions housing 34a of semi-cylindrical shape for example, formed between the middle part 33 and the end parts 34. The planar parts 33, 34 extend in a plane tangent to the circumferential direction. The housing portions 34a are axially spaced from one another. The housing portions 34a of the radially internal sheet 31 are located axially opposite the housing portions 34a of the radially external sheet 32, so as to form two housings of rounded or cylindrical shape, axially offset from one another for each module 30a, 30b, 30c.
    [057] Each sheet 31, 32 has a hole 35, 36 (Figure 5) at each end portion 34 of the sheet 31, 32. The holes 35, 36 of the radially internal sheet 31 are located axially opposite holes 35, 36 of the radially outer sheet 32.
    [058] Each sheet 31, 32 comprises a stiffener 37 extending axially between the abovementioned housing portions 34a. In particular, the radially internal sheet 31 has a stiffener 37 in the form of a sheet extending radially inward from the middle portion 33 of the corresponding sheet 31. The radially external sheet 32 has a stiffener 37 having the form of a sheet extending radially outward from the middle part 33 of the corresponding sheet 32.
    [059] The sheets 31, 32 may have a thickness of between 0.5 and 5 mm.
    [060] A socket 38 is mounted in each housing of each module 30a, 30b, 30c. Each socket 38 extends circumferentially beyond the sheets 31, 32, on either side of said sheets 31, 32. The sockets 38 can be made of silica. Each socket 38 is surrounded by the housing portions 34a and is fixed to at least one of the sheets, by matting, that is to say by local deformation of the material. The sheets 31, 32 thus form flanges at the level of said housing portions 34a, surrounding the sockets 38 and the tubes 23.
    [061] Tubes 23 are slidably mounted inside the sockets 38. The tubes 23 extend circumferentially and are parallel to each other.
    [062] As is known per se, the tubes 23 are formed by curved pipes of circular section, each tube 23 extending for example at an angle of about 90 °.
    [063] Each tube 23 has an air inlet opening into the channel of a corresponding collecting box 22 and a closed distal end. Each tube 23 further comprises a cylindrical wall provided with air ejection orifices facing the casing 18, so that cooling air can penetrate into the manifolds 22 and then into the tubes 23 before opening out by the orifices facing the casing 18, so as to cool it. The tubes 23 are in particular situated axially opposite the zones of the casing comprising the flanges or hooks 20 used for mounting the distributors 19 or the abradable rings 17.
    [064] We will first describe the middle module 30b in the following.
    [065] The sheets 31, 32 of the middle module 30b are fixed to the casing 18 by upstream fixing means and downstream fixing means each comprising a fixing screw 39, a nut 40 and a tubular spacer 41.
    [066] Each screw 39 has an enlarged head 42 (FIG. 7) intended to bear on a radially internal surface 43 of the casing 18, an enlarged holding part 44 and a radially external threaded end 45, cooperating with the nut 40 coming from resting on the radially external sheet 32, by means of a washer 45, 46. Each screw 39 is engaged in the corresponding holes 35, 36 of the radially internal sheet 31 and of the radially external sheet 32.
    [067] Each spacer 41 surrounds part of the screw 39 and is located between the external surface of the casing 18 and the radially internal sheet 31. Thus, as is better visible in FIG. 7, the radially internal end of the spacer 41 comes to bear on the external surface of the casing 18 (here on the frusto-conical part 27 of the casing 18) and the radially external end of the spacer 41 comes to bear on the radially internal sheet 31. The spacers 41 are for example made of steel.
    [068] The enlarged zones 44 are mounted slightly in force in the spacers 41 so as to hold the screws 39 in position relative to the casing 18 during assembly of the cooling device 21.
    [069] As a variant, as illustrated in FIG. 8, the enlarged holding part 44 can be replaced by an elastic ring 47 engaged in a groove of the screw 39 and coming elastically to bear on the internal surface of the sleeve 41 so ensuring the function of holding the screw 39 relative to the casing 18.
    [070] A flat washer 45 is mounted between the nut 40 of the upstream fixing means and the radially external sheet 32. The holes 35 of the sheets 31, 32 allowing the passage of the screw 39 of the upstream fixing means are of circular shape . The screw 39 is mounted without play or almost without play in said holes 35. Obviously, a mounting play can be provided.
    [071] An elastically deformable washer 46, such as for example a Belleville washer, is interposed between the nut 40 of the downstream fixing means and the radially external sheet 32. The holes 36 of the sheets 31,32 allowing the passage of the screw 39 of the downstream fixing means are oblong, so as to compensate for any axial expansion of the casing 18. The elastically deformable washer 46 makes it possible to maintain the radially external sheet 32 on the radially internal sheet 31, so as to enclose and maintain the sockets 38 and the tubes 23 between the sheets 31, 32, while allowing the axial displacement of the screw 39 and the corresponding nut 40 relative to the radially internal and external sheets 31,32.
    [072] We will now describe the upstream module 30a. This differs from the middle module 30b in that the sheets 31, 32 have an oblique part 48 between the upstream end parts 34 and the upstream housing portions 34a. The holes 35 of the downstream end portions 34 are circular and the holes 36 of the upstream end portions 34 are oblong.
    [073] The upstream end parts 34 of the sheets 31, 32 are fixed to the upstream flange 24 of the casing 18 by means of a bent connecting sheet 49. The connecting plate 49 comprises a part extending axially 50, pressed against the upstream end part 34 of the radially internal sheet 31, and a part 51 extending radially, fixed to the upstream flange 24 by any suitable means.
    [074] The upstream fixing means do not have a spacer 41. In particular, the upstream fixing means comprise a screw 39 engaged in the corresponding oblong holes 36 and a nut 40 making it possible to fix the radially internal and external sheets 31 together, 32 and the axial part 50 of the connecting sheet 49. Such an assembly allows axial movement of the connecting sheet 49 relative to the radially internal and external sheets 31, 32 of the upstream module 30a.
    [075] The downstream fixing means comprise a spacer 41 located between the radially internal sheet metal 31 and the casing 18 and a flat washer 45 located between the corresponding nut 40 and the radially external sheet metal 32. The downstream fixing means of the upstream module 30a are located axially opposite the upstream fixing means of the middle module 30b. There is therefore a circumferential offset, preferably slight, between the sheets 31, 32 and the means for fixing the upstream module 30a relative to the sheets 31, 32 and the means for fixing the middle module 30b.
    [076] We will now describe the downstream module 30c. This differs from the middle module 30b in that the sheets 31, 32 have an oblique part 48 between the downstream end parts 34 and the downstream housing portions 34a. The holes 36 of the downstream end portions 34 are oblong and the holes 36 of the upstream end portions 34 are oblong.
    [077] The downstream end portions 34 of the sheets 31, 32 are fixed to the downstream flange 29 of the casing 18 by means of a bent connecting sheet 49. The connecting sheet 49 comprises a part 50 extending axially, pressed against the downstream end part 34 of the radially internal sheet 31, and a part 51 extending radially, fixed to the downstream flange 29 by any suitable means.
    [078] The downstream fixing means do not have a spacer 41. In particular, the downstream fixing means comprise a screw 39 engaged in the corresponding oblong holes 36 and a nut 40 making it possible to fix the radially internal and external sheets 31 together, 32 and the axial part 50 of the connecting sheet 49. Such an assembly allows an axial displacement of the connecting sheet 49 relative to the radially internal and external sheets 31, 32 of the downstream module 30c.
    [079] The upstream fixing means comprise a spacer 41 located between the radially internal sheet 31 and the casing 18 and an elastically deformable washer 46 located between the corresponding nut 40 and the radially external sheet 32, so as to allow axial movement between the corresponding screw 39 and the sheets 31, 32 of the downstream module 30c. The upstream fixing means of the downstream module 30c are located axially opposite the downstream fixing means of the middle module 30b. There is therefore a circumferential offset between the sheets 31, 32 and the means for fixing the downstream module 30c with respect to the sheets 31, 32 and the means for fixing the middle module 30b. Such a shift makes it possible in particular to facilitate the positioning of the tube supports relative to one another around the casing.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. Cooling device (21) extending circumferentially around a casing (18) of a turbomachine (1), such as for example a casing (18) of a turbine (7), comprising at least one cooling module ( 30a, 30b, 30c) comprising a tube support (31, 32) having at least one sheet, preferably a radially internal sheet (31) and a radially external sheet (32) fixed relative to each other, the tube support (31, 32) delimiting at least two housings (34a) axially spaced from one another, each housing (34a) receiving a tube (23) and a socket (38) mounted around each tube ( 23), each tube (23) extending circumferentially around the casing (18), each cooling module (30a, 30b, 30c) comprising first fixing means capable of holding its tube support fixedly (31, 32) by relative to the casing (18), the fixing means comprising at least one spacer (41) having a radial end internal ent intended to come into abutment against the casing (18) and a radially external end coming to bear on the or one of the sheets of the tube support (31, 32).
    [2" id="c-fr-0002]
    2. Cooling device (21) according to claim 1, characterized in that the first fixing means comprise a screw (39) or a rivet extending in the spacer (41), the spacer (41) being tubular and surrounding said screw (39) or said rivet.
    [3" id="c-fr-0003]
    3. Cooling device (21) according to claim 1 or 2, characterized in that at least one cooling module (30b) comprises second fixing means axially spaced from the first fixing means, the second fixing means being suitable fixedly holding the tube support (31, 32) of the cooling module (30a, 30b, 30c) fixed relative to the casing (18).
    [4" id="c-fr-0004]
    4. Cooling device (21) according to claim 3, characterized in that the second fixing means comprise a spacer (41) having a radially internal end intended to come into abutment against the casing (18) and a radially external end coming from resting on one or one of the sheets of the tube support (31, 32).
    [5" id="c-fr-0005]
    5. Cooling device (21) according to claim 3, characterized in that the second fixing means comprise a connecting plate (49) fixed to the tube support (31, 32) of the cooling module (30a, 30b) and intended to be fixed to a radial annular flange (24, 29) of the casing (18).
    [6" id="c-fr-0006]
    6. Cooling device (21) according to one of claims 3 to 5, characterized in that the first and / or the second fixing means comprise at least one screw (39) or a rivet engaged in an oblong hole (36 ) sheets (31, 32), the radially outer end of the screw (29) or of the rivet comprising a shoulder (40), an elastic member (46) being mounted between said shoulder (40) and the tube support ( 31, 32).
    [7" id="c-fr-0007]
    7. Cooling device (21) according to any one of claims 3 to 6, characterized in that the first and / or the second fixing means each comprise a screw (39) or a rivet engaged in holes (35) of the tube support (31, 32) of the cooling module (30a, 30b), one of the screws (39) or one of the rivets being engaged in an oblong hole (36), the other screw (39) or rivet being engaged without play in a circular hole (35).
    [8" id="c-fr-0008]
    8. Cooling device (21) according to any one of claims 3 to 6, characterized in that the first and / or the second fixing means each comprise a screw (39) or a rivet engaged in oblong holes (36 ) of the tube support (31, 32) of the cooling module (30c).
    [9" id="c-fr-0009]
    9. Cooling device (21) according to one of claims 1 to 8, characterized in that the radially inner sheet (31) and / or the radially outer sheet (32) of the tube support (31, 32) form the housings (34a) and the tube support (31, 32) comprises at least one stiffener (37) extending axially between the housings (34a).
    [10" id="c-fr-0010]
    10. Cooling device (21) according to one of claims 1 to 9, characterized in that at least one socket (38) can extend circumferentially on either side of a housing (34a) of the tube support. (31,32) of a cooling module (30a, 30b, 30c).
    5
    [0011]
    11. An assembly comprising an annular casing (18) of a turbomachine (1), for example an annular casing (18) of a turbine (7), characterized in that it comprises a cooling device (21) according to one of claims 1 to 10, fixed to said casing (18) and surrounding said casing (18), the fixing means ensuring the fixing of the sheets (31, 32) to the casing (18), 10 the radially internal end of the spacer (41 ) of said first and / or second fixing means coming to bear against the radially external surface of the casing (18).
    类似技术:
    公开号 | 公开日 | 专利标题
    EP1705340B1|2013-12-25|Connector between a cooling air plenum and a stator vane in a turbomachine
    EP2096266B1|2011-08-31|Nozzle-synchronising ring assembly for a turbomachine
    EP2917519B1|2018-08-15|Air exhaust tube holder in a turbomachine
    EP1873385B1|2009-08-12|Exhaust cone for channeling a gas stream downstream of a turbine
    EP2917518B1|2017-03-01|Air exhaust tube holder in a turbomachine
    FR3018548A1|2015-09-18|TURBOREACTOR CONDUIT OF DISCHARGE
    FR3077097A1|2019-07-26|COOLING DEVICE FOR TURBINE OF A TURBOMACHINE
    EP3775498B1|2022-02-09|Cooling device for a turbine of a turbine engine
    EP3775501B1|2022-02-16|Cooling device for a turbine of a turbomachine
    FR3082227A1|2019-12-13|PILOT COOLING DEVICE FOR A TURBINE OF A TURBOMACHINE
    FR3099798A1|2021-02-12|Set for a turbomachine turbine
    EP3710679B1|2022-02-09|Device for holding a radial centripetal air sampling member
    FR3099801A1|2021-02-12|Set for a turbomachine turbine
    FR3099799A1|2021-02-12|Set for a turbomachine turbine
    WO2010116051A2|2010-10-14|Turbine engine with an annular combustion chamber
    FR3089544A1|2020-06-12|COOLING DEVICE FOR A TURBOMACHINE HOUSING
    FR3082912A1|2019-12-27|FLUIDIC CONNECTION DEVICE FOR AN AIR CIRCUIT OF AN AIRCRAFT ENGINE
    FR3097271A1|2020-12-18|Device for cooling a casing of a turbomachine
    WO2020016533A1|2020-01-23|Assembly for a turbomachine
    FR3094398A1|2020-10-02|TURBOMACHINE ROTOR SET
    FR3068732A1|2019-01-11|COOLING DEVICE
    FR3040077A1|2017-02-17|TURBOMACHINE, SUCH AS A TURBO AIRBORNE OR TURBOPROPULSER
    同族专利:
    公开号 | 公开日
    US20190226357A1|2019-07-25|
    GB201900764D0|2019-03-06|
    GB201900782D0|2019-03-06|
    FR3077097B1|2020-08-07|
    GB2571826A|2019-09-11|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1473499A1|2003-05-02|2004-11-03|Hellermann Tyton GmbH|Holding device for elongated articles|
    EP2573277A1|2010-05-17|2013-03-27|Volvo Construction Equipment AB|Fixing device of hydraulic pipe of construction machine|
    FR3021700A1|2014-05-27|2015-12-04|Snecma|DEVICE FOR MAINTAINING A COOLING TUBE FOR A TURBOJET CARTRIDGE|
    WO2017032952A1|2015-08-27|2017-03-02|Safran Aircraft Engines|Device for attaching manifolds for cooling the casing of a turbine-engine turbine by air jets|
    DE102005011131B4|2005-03-10|2007-07-26|Airbus Deutschland Gmbh|Mounting system for guiding and fixing one or more pipes or similarly shaped bodies|
    US9341074B2|2012-07-25|2016-05-17|General Electric Company|Active clearance control manifold system|
    FR2995022B1|2012-09-04|2017-11-24|Snecma|DEVICE FOR FASTENING A COOLING SYSTEM FOR AN AIRCRAFT TURBOKIN BOX|
    US10320173B2|2017-03-28|2019-06-11|Atkore Steel Components, Inc.|Conduit support assembly|GB2584882A|2019-06-19|2020-12-23|Airbus Operations Ltd|Pipe support|
    US20210245684A1|2020-02-06|2021-08-12|Rosemount Aerospace Inc.|Adapter clip|
    法律状态:
    2018-12-18| PLFP| Fee payment|Year of fee payment: 2 |
    2019-07-26| PLSC| Publication of the preliminary search report|Effective date: 20190726 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 3 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 4 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1850473|2018-01-22|
    FR1850473A|FR3077097B1|2018-01-22|2018-01-22|COOLING DEVICE FOR A TURBINE OF A TURBOMACHINE|FR1850473A| FR3077097B1|2018-01-22|2018-01-22|COOLING DEVICE FOR A TURBINE OF A TURBOMACHINE|
    GBGB1900764.0A| GB201900764D0|2018-01-22|2019-01-18|Cooling device for a turbine of a turbomachine|
    GB1900782.2A| GB2571826A|2018-01-22|2019-01-21|Cooling device for a turbine of a turbomachine|
    US16/253,842| US20190226357A1|2018-01-22|2019-01-22|Cooling device for a turbine of a turbomachine|
    [返回顶部]