• 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:
    A turbine ring assembly comprising ring sectors (10) forming a turbine ring (1) and a ring support structure (3), each ring sector (10) having, in accordance with a plane of section defined by an axial direction (DA) and a radial direction (DR) of the turbine ring (1), an annular base portion (12) with, in the radial direction (DR), an inner face (12a) defining the inner face of the turbine ring (1) and an outer face (12b) from which project a first and a second attachment lugs (14, 16), the support structure of ring (3) having a central ring (31) from which project first and second radial tabs between which are held the first and second attachment tabs (14, 16) of each ring sector (10). The first radial flange comprises a one-piece annular flange (35) removably attached to the central ring (31) of the ring support structure (3).
    公开号:FR3055148A1
    申请号:FR1657827
    申请日:2016-08-19
    公开日:2018-02-23
    发明作者:Nicolas Paul TABLEAU；Sebastien Serge Francis CONGRATEL；Clement Jean Pierre DUFFAU；Lucien Henri Jacques QUENNEHEN
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    © Publication number: 3,055,148 (to be used only for reproduction orders) (© National registration number: 16 57827 ® FRENCH REPUBLIC
    NATIONAL INSTITUTE OF INDUSTRIAL PROPERTY
    COURBEVOIE © Int Cl 8 : F 01 D 25/24 (2017.01), F 01 D 11/08, 11/18, 9/04
    A1 PATENT APPLICATION
    ©) Date of filing: 19.08.16. © Applicant (s): SAFRAN AIRCRAFT ENGINES (© Priority: Simplified joint stock company - FR. @ Inventor (s): TABLE NICOLAS PAUL, CONGRA- TEL SEBASTIEN SERGE FRANCIS, DUFFAU CLE- (43) Date of public availability of the MENT JEAN PIERRE and QUENNEHEN LUCIEN HENRI request: 23.02.18 Bulletin 18/08. JACQUES. ©) List of documents cited in the report preliminary research: Refer to end of present booklet (© References to other national documents ® Holder (s): SAFRAN AIRCRAFT ENGINES Company related: by simplified actions. ©) Extension request (s): © Agent (s): CABINET BEAU DE LOMENIE.
    (04) TURBINE RING ASSEMBLY.
    FR 3 055 148 - A1 _ A turbine ring assembly comprising ring sectors (10) forming a turbine ring (1) and a ring support structure (3), each ring sector (10 ) having, according to a cutting plane defined by an axial direction (D A ) and a radial direction (D R ) of the turbine ring (1), an annular base portion (12) with, in the radial direction ( D R ), an internal face (12a) defining the internal face of the turbine ring (1) and an external face (12b) from which project first and second hooking lugs (14 , 16), the ring support structure (3) comprising a central ring (31) from which project first and second radial tabs projecting between which the first and second hooking tabs are held ( 14, 16) of each ring sector (10).
    The first radial tab comprises an annular flange (35) in a single piece removably attached to the central ring (31) of the ring support structure (3).
    Invention background
    A turbine ring assembly includes a plurality of ring sectors of ceramic matrix composite material and a ring support structure.
    The field of application of the invention is in particular that of aeronautical gas turbine engines. The invention is however applicable to other turbomachinery, for example industrial turbines.
    In the case of entirely metallic turbine ring assemblies, it is necessary to cool all the elements of the assembly and in particular the turbine ring which is subjected to the hottest flows. This cooling has a significant impact on engine performance since the cooling flow used is taken from the main flow of the engine. In addition, the use of metal for the turbine ring limits the possibilities of increasing the temperature at the turbine, which would however improve the performance of aeronautical engines.
    In order to try to solve these problems, it has been envisaged to produce turbine ring sectors in ceramic matrix composite material (CMC) in order to dispense with the use of a metallic material.
    CMC materials have good mechanical properties making them suitable for constituting structural elements and advantageously retain these properties at high temperatures. The use of CMC materials has advantageously made it possible to reduce the cooling flow to be imposed during operation and therefore to increase the performance of the turbomachines. In addition, the use of CMC materials advantageously makes it possible to reduce the mass of the turbomachines and to reduce the effect of hot expansion encountered with metal parts.
    However, the existing solutions proposed can implement an assembly of a CMC ring sector with metal attachment parts of a ring support structure, these attachment parts being subjected to the hot flow. Consequently, these metal attachment parts undergo hot expansion, which can lead to mechanical stressing of the ring sectors in CMC and to embrittlement of the latter.
    The documents FR 2 540 939, GB 2 480 766, EP 1 350 927, US 2014/0271145, US 2012/082540 and FR 2 955 898 which disclose turbine ring assemblies are also known.
    There is a need to improve the existing turbine ring assemblies and their mounting, and in particular the existing turbine ring assemblies using a CMC material in order to reduce the intensity of the mechanical stresses to which the ring sectors in CMCs are subject to the operation of the turbine.
    Subject and summary of the invention
    The invention aims to propose a set of turbine rings allowing the maintenance of each ring sector in a deterministic manner, that is to say so as to control its position and prevent it from vibrating. on the one hand, while allowing the ring sector, and by extension to the ring, to deform under the effects of temperature rises and pressure variations, and this in particular independently of the metal parts at the interface, and , on the other hand, while improving the seal between the non-vein sector and the vein sector and simplifying handling and reducing their number for mounting the ring assembly.
    An object of the invention provides a turbine ring assembly comprising a plurality of ring sectors forming a turbine ring and a ring support structure, each ring sector having, according to a cutting plane defined by an axial direction and a radial direction of the turbine ring, an annular base portion with, in the radial direction of the turbine ring, an internal face defining the internal face of the turbine ring and an external face to from which protrude first and second hooking lugs, the ring support structure comprising a central ring from which protrude first and second radial lugs between which are held the first and second attachment tabs of each ring sector.
    According to a general characteristic of the object, the first radial tab comprises a single-piece annular flange fixed removably to the central crown of the ring support structure, the annular flange having a first free end, a second end coupled to the central ring of the ring support structure, and at least one hanging hook projecting from the second end of the annular flange and cooperating with at least one housing included in the central ring of the ring structure ring support to hold the annular flange in position.
    In a particular embodiment, the ring sectors can be made of a ceramic matrix composite material.
    The removable nature of the annular flange makes it possible to have axial access to the cavity of the turbine ring. This makes it possible to assemble the ring sectors together outside of the ring support structure and then to axially slide the assembly thus assembled into the cavity of the ring support structure until it comes in support against the second radial tab, before fixing the annular flange on the central ring of the ring support structure.
    During the operation of fixing the turbine ring to the support structure of the ring, it is possible to use a tool comprising a cylinder or a ring on which the ring sectors are supported or suction cups during their crown assembly.
    Having a one-piece annular flange, that is to say describing the entire ring over 360 °, makes it possible, in relation to a sectored annular flange, to limit the passage of the air flow between the non-vein sector and the vein sector, insofar as all inter-sector leaks are eliminated, and therefore to control the seal.
    The solution defined above for the ring assembly thus makes it possible to maintain each ring sector in a deterministic manner, that is to say to control its position and prevent it from vibrating, while improving sealing between the non-vein sector and the vein sector, simplifying handling and reducing their number for mounting the ring assembly, and allowing the ring to deform under the effects of temperature and pressure especially independently of the metallic parts at the interface.
    According to a first aspect of the turbine ring assembly, the annular flange comprises a first portion extending from the first end and a second portion extending between the first portion and the second end, the first portion comprising a first and a second separate legs, the first leg being in abutment against the first hooking leg and the second leg being distant from the first leg in the axial direction, the second leg being upstream of the first leg relative to the direction of flow air to pass through the turbine ring assembly.
    The second leg of the removable annular flange is dedicated to the resumption of the effort of the high pressure distributor, also noted DHP. This annular flange allows this effort to be taken up, on the one hand, by deforming, and, on the other hand, by passing this effort towards the casing line which is more mechanically robust.
    Indeed, leaving a space between the first leg and the second leg of the flange makes it possible to deflect the force received by the second leg, upstream of the first leg, and to have it pass directly to the central crown of the support structure. ring via the second portion of the flange, without impacting the second leg of the flange. Since the second flange tab does not undergo any force, the turbine ring is thus preserved from this axial force.
    According to a second aspect of the turbine ring assembly, the annular flange comprises a first and a second hook hooks projecting from the second end of the annular flange in the axial direction of the turbine ring and being distant in the radial direction of the turbine ring, the central ring of the ring support structure comprising two hooking housings cooperating with the first and second hooks for hooking the annular flange to maintain the annular flange in position in the radial direction of the turbine ring.
    The attachment to the central ring of the removable annular flange makes it possible to maximize the contact surface between the central ring of the ring support structure and the annular flange, which limits possible air leaks between the two parts.
    According to a third aspect of the turbine ring assembly, the first and second hooks for hooking the annular flange have two distinct axial positions in the axial direction of the turbine ring.
    Moving the hooks axially away from one another makes it possible to limit the tilting of the annular flange and thus to optimize the transfer of the forces taken up by the second tab of the annular flange.
    According to a fourth aspect of the turbine ring assembly, the ring assembly comprises, for each ring sector, at least three pins to radially maintain the ring sector in position, the first and second legs d attachment of each ring sector each comprising a first end integral with the external face of the annular base, a second free end, at least three ears for receiving said at least three pins, at least two ears projecting from the second end of one of the first or second lugs in the radial direction of the turbine ring and at least one ear projecting from the second end of the other lug in the radial direction of the turbine ring, each receiving lug comprising a hole for receiving a pin.
    The ears made projecting radially from the free ends of the first and second hooking lugs make it possible to offset the holding zone of the hooking lugs relative to the support zones comprised between the two ends of the hooking lugs and intended to produce a tight contact, on the one hand, with the removable annular flange, and, on the other hand, with the second radial tab.
    According to a fifth aspect of the turbine ring assembly, the second portion of the annular flange has holes for receiving a pin, and the second leg of the ring support structure comprises an annular flange having a first portion pressing against the second attachment tab, a second portion thinned relative to the first portion, and a third portion positioned between the first and the second portion and comprising orifices for receiving a pin.
    Separating the receiving area of the pins and the support areas of the latching lugs of the ring against the annular flange, on the one hand, and against the annular flange, on the other hand, makes it possible to optimize the sealing. reducing cuts in the support area.
    According to a sixth aspect of the turbine ring assembly, each ring sector can comprise rectilinear bearing surfaces mounted on the faces of the first and second hooking lugs in contact respectively with the second annular flange and the first annular flange.
    The rectilinear supports make it possible to have controlled sealing zones. More specifically, having supports on radial planes makes it possible to overcome the effects of de-cambering in the turbine ring. This alignment of the contact zones on parallel rectilinear planes indeed makes it possible to maintain sealing lines in the event of the ring toppling and to keep the same contact zones both cold and hot.
    In operation, the ring sectors tilt around an axis corresponding to the normal to the plane formed between the axial direction and the radial direction of the turbine ring. In the case of a curvilinear support, as in the prior art, the lugs of the ring sectors are in contact with the ring support structure at only one or two points while, in the present invention, the supports the legs of each ring sector allow support on an entire line, which improves the seal between the ring sectors and the ring support structure.
    In a variant, for each ring sector, the faces of the second annular flange and of the first annular flange in contact respectively with the first and second hooking lugs comprise rectilinear bearing surfaces.
    According to a seventh aspect of the turbine ring assembly, each rectilinear bearing surface may include a groove hollowed out over the entire length of the bearing surface and a seal inserted into the groove to improve sealing.
    Another object of the invention provides a turbomachine comprising a turbine ring assembly as defined above.
    Brief description of the drawings.
    The invention will be better understood on reading the following, for information but not limitation, with reference to the accompanying drawings in which:
    - Figure 1 is a schematic perspective view of an embodiment of a turbine ring assembly according to the invention;
    - Figure 2 is a schematic exploded perspective view of the turbine ring assembly of Figure 1;
    - Figures 3 and 5 are respectively a partial and total schematic perspective view of the removable annular flange of the turbine ring assembly of Figure 1;
    - Figure 4 is a schematic sectional view of the turbine ring assembly of Figure 1.
    Detailed description of embodiments
    Figure 1 shows a high pressure turbine ring assembly comprising a turbine ring 1 made of ceramic matrix composite material (CMC) and a metal ring support structure
    3. The turbine ring 1 surrounds a set of rotating blades (not shown). The turbine ring 1 is formed from a plurality of ring sectors 10, FIG. 1 being a view in radial section. The arrow D A indicates the axial direction of the turbine ring 1 while the arrow Dr indicates the radial direction of the turbine ring 1. For reasons of simplification of presentation, FIG. 1 is a partial view of the turbine ring 1 which is actually a complete ring.
    As illustrated in FIG. 2 which presents a schematic exploded perspective view of the turbine ring assembly of FIG. 1, each ring sector 10 has, according to a plane defined by the axial directions D A and radial directions Dr, a section substantially in the shape of the Greek letter π inverted. The section in fact comprises an annular base 12 and radial lugs for hooking upstream and downstream, respectively 14 and 16. The terms upstream and downstream are used here with reference to the direction of flow of the gas flow in the turbine represented by the arrow F in FIG. 1. The legs of the ring sector 10 could have another shape, the section of the ring sector having a shape other than π, such as for example a shape in k.
    The annular base 12 comprises, in the radial direction Dr of the ring 1, an internal face 12a and an external face 12b opposite one another. The internal face 12a of the annular base 12 is coated with a layer 13 of abradable material forming a thermal and environmental barrier and defines a flow stream for gas flow in the turbine.
    The upstream and downstream radial lugs 14 and 16 extend in projection, in the direction Dr, from the external face 12b of the annular base 12 at a distance from the upstream and downstream ends 121 and 122 of the annular base 12 The upstream and downstream hooking radial lugs 14 and 16 extend over the entire width of the ring sector 10, that is to say over the entire arc of a circle described by the ring sector 10, or else over the entire circumferential length of the ring sector 10.
    As illustrated in FIGS. 1 and 2, the ring support structure 3 which is integral with a turbine casing 30 comprises a central ring 31, extending in the axial direction D A , and having an axis of revolution coincides with the axis of revolution of the turbine ring 1 when they are fixed together, as well as a removable annular flange 35 and an annular radial flange 36, the removable annular flange 35 being positioned upstream of the radial flange annular 36 which is therefore downstream of the removable annular flange 35.
    As illustrated in FIGS. 1 and 2, the annular radial flange 36 extends in the circumferential direction of the ring 1 and, in the radial direction Dr, from the central ring 31 towards the center of the ring 1. It comprises a first free end 361 and a second end 362 integral with the central crown 31. The annular radial flange 36 comprises a first portion 363, a second portion 364, and a third portion 365 between the first portion 363 and the second portion 364. The first portion 363 extends between the first end 361 and the third portion 365, and the second portion 364 extends between the third portion 365 and the second end 362. The first portion 363 of the annular radial flange 36 is in contact with the downstream radial latching leg 16. The second portion 364 is thinned relative to the first portion 363 and the third portion 365 so as to give a certain soup loosens the annular radial flange 36 and thus does not overly constrain the turbine ring 1 in CMC.
    As illustrated in Figures 1 and 2, as well as in Figure 3 which shows a partial schematic perspective view of the removable annular flange 35 of the turbine ring assembly 1 and in Figure 5 which shows a schematic view complete in perspective with the removable annular flange 35, the removable flange 35 comprises a first free end 351 and a second end 352 intended to be coupled to the central ring 31 of the annular support structure 3. The removable flange 35 further comprises a first portion 353 extending from the first end 351 and a second portion 354 extending between the first portion 353 and the second end 352. The first portion 353 comprises a first tab 33 and a second tab 34 distinct from the first tab 33 and distant from the latter in the axial direction D A , the second tab 34 being upstream of the first tab 33 relative to the direction of the air flow, designated by the arrow referenced by the letter F, intended to pass through the turbine ring assembly 1. When the ring assembly is mounted, the first tab 33 of the removable flange 35 is in abutment against the radial tab d upstream attachment 14 of each of the ring sectors 10 making up the turbine ring 1.
    The second tab 34 of the removable annular flange 35 is dedicated to the recovery of the force of the high pressure distributor (DHP) on the removable annular flange 35, on the one hand, by deforming, and, on the other hand, by transit this force towards the casing line which is more mechanically robust, that is to say towards the line of the ring support structure 3 as illustrated by the force arrows E presented in FIG. 4 which is a sectional view of the turbine ring assembly of FIG. 1 according to a plane comprising the axial direction D A of the turbine ring 1 and the radial direction Dr of the turbine ring 1.
    The first tab 33 and the second tab 34 of the removable annular flange 35 meet at the second portion 354 of the removable annular flange 35.
    To fix the removable annular flange 35 to the central ring 31 of the ring support structure 3, the second end 352 of the removable annular flange 35 comprises first and second hooks 60 and 61, and the central ring 31 comprises first and second corresponding housings 62 and 63.
    The first and second hooks 60 and 61 are arranged at two distinct positions in the radial direction Dr of the turbine ring 1 and at two distinct positions in the axial direction
    D a of the turbine ring 1. The associated housings 62 and 63 are produced in the central ring 31 in a corresponding manner to cooperate respectively with the first and the second hooking hooks 60 and to maintain the removable annular flange 35 with the rest of ring support structure 3.
    In the illustrated embodiment, the first and second hooking hooks 60 and 61 each have a distal portion 65, such as a tongue, projecting from a proximal portion 66. The distal portion 65 is shaped to insert into the corresponding housing and 63 and form with the proximal portion 66 a shoulder 67 against which the contour of each housing 62 and 63 comes to bear to prevent any tilting of the removable annular flange 35 in the radial direction Dr of the turbine ring 1 and in particular in the direction towards the center of the turbine ring 1.
    In the opposite direction, any tilt of the removable annular flange 35 is blocked by the proximal portion 66 and the distal portion 65 of the hooking hooks 60 and 61 having a surface in direct contact, in the radial direction Dr and in the direction opposite to the direction towards the center of the turbine ring 1, with the central ring 31 of the ring support structure 3.
    In the axial direction D A , the annular radial flange 36 of the ring support structure 3 is separated from the first leg 33 of the removable annular flange 35 by a distance corresponding to the spacing of the upstream radial hooking legs and downstream 14 and 16 so as to maintain the latter between the annular radial flange 36 and the first tab 33 of the removable annular flange 35.
    To keep the ring sectors 10, and therefore the turbine ring 1, in position with the ring support structure 3, the ring assembly comprises two first pins 19 cooperating with the upstream hooking lug 14 and the removable annular flange 35, and two second pins 20 cooperating with the downstream hooking lug 16 and the annular radial flange 36.
    For each corresponding ring sector 10, the second portion 354 of the removable annular flange 35 comprises two orifices 3540 for receiving the first two pins 19, and the third portion 365 of the annular radial flange 36 comprises two orifices 3650 configured to receive the two second pawns 20.
    For each ring sector 10, each of the upstream and downstream hooking radial lugs 14 and 16 comprises a first end, 141 and 161, integral with the external face 12b of the annular base 12 and a second end, 142 and 162, free. The second end 142 of the upstream radial lug 14 comprises two first ears 17 each comprising an orifice 170 configured to receive a first pin 19. Similarly, the second end 162 of the downstream radial lug 16 comprises two second ears 18 each comprising an orifice 180 configured to receive a second pin 20. The first and second ears 17 and 18 extend projecting in the radial direction Dr from the turbine ring 1 respectively from the second end 142 of the tab upstream radial attachment 14 and the second end 162 of the downstream radial attachment tab 16.
    The holes 170 and 180 can be circular or oblong. Preferably the set of orifices 170 and 180 comprises a portion of circular orifices and a portion of oblong orifices. The circular orifices allow the rings to be tangentially indexed and to prevent them from being able to move tangentially (in particular in the event of contact by the blade). The oblong holes make it possible to accommodate the differential expansions between the CMC and the metal. CMC has a much lower coefficient of expansion than that of metal. When hot, the lengths in the tangential direction of the ring sector and of the housing portion opposite will therefore be different. If there were only circular orifices, the metal casing would impose its displacements on the ring in CMC, which would be a source of very high mechanical stresses in the ring sector. Having oblong holes in the ring assembly allows the pin to slide in this hole and avoid the over-stress phenomenon mentioned above. Therefore, two drilling patterns can be imagined: a first drilling pattern, for a case with three ears, would include a oblong radial hole on a radial hooking tab and two oblong tangential holes on the other radial hooking tab , and a second drilling scheme, for a case with at least four ears, would include a circular orifice and an oblong orifice by radial lug for hooking facing each other. Other ancillary cases can also be envisaged.
    For each ring sector 10, the first two lugs 17 are positioned at two different angular positions relative to the axis of revolution of the turbine ring 1. Similarly, for each ring sector 10, the two seconds ears 18 are positioned at two different angular positions relative to the axis of revolution of the turbine ring 1.
    Each ring sector 10 further comprises rectilinear bearing surfaces 110 mounted on the faces of the upstream and downstream hooking radial tabs 14 and 16 in contact respectively with the first tab 33 of the removable annular flange 35 and the annular radial flange 36, that is to say on the upstream face 14a of the upstream radial latching lug 14 and on the downstream face 16b of the downstream latching lug 16. In a variant, the rectilinear supports could be mounted on the first tab 33 of the removable annular flange 35 and on the downstream annular radial flange 36.
    The rectilinear supports 110 make it possible to have controlled sealing zones. Indeed, the bearing surfaces 110 between the upstream radial hooking tab 14 and the first tab 33 of the removable annular flange 35, on the one hand, and between the downstream radial hooking tab 16 and the annular radial flange 36 are included in the same rectilinear plane.
    More precisely, having supports on radial planes makes it possible to overcome the effects of decambrage in the turbine ring 1.
    A method of producing a set of turbine rings corresponding to that shown in FIG. 1 will now be described.
    Each ring sector 10 described above is made of ceramic matrix composite material (CMC) by forming a fibrous preform having a shape close to that of the ring sector and densification of the ring sector by a ceramic matrix. .
    For the production of the fiber preform, it is possible to use ceramic fiber yarns, for example SiC fiber yarns such as those sold by the Japanese company Nippon Carbon under the name Hi-NicalonS, or carbon fiber yarns.
    The fibrous preform is advantageously produced by three-dimensional weaving, or multilayer weaving with the arrangement of unbinding zones making it possible to separate the parts of preform corresponding to the tabs 14 and 16 from the sectors 10.
    The weaving can be of the interlock type, as illustrated. Other three-dimensional or multi-layer weaving weaves can be used, for example multi-canvas or multi-satin weaves. Reference may be made to document WO 2006/136755.
    After weaving, the blank can be shaped to obtain a ring sector preform which is consolidated and densified by a ceramic matrix, densification being able to be carried out in particular by chemical gas infiltration (CVI) which is well known in oneself. In a variant, the textile preform can be hardened a little by CVI so that it is rigid enough to be handled, before making liquid silicon rise by capillary action in the textile to make densification (“Melt Infiltration”).
    A detailed example of manufacturing ring sectors in CMC is described in particular in document US 2012/0027572.
    The ring support structure 3 is made of a metallic material such as a Waspaloy® or inconel 718® or C263® alloy.
    The production of the turbine ring assembly continues with the mounting of the ring sectors 10 on the ring support structure
    3.
    For this, the ring sectors 10 are assembled together on an annular tool of the “spider” type comprising, for example, suction cups configured to each maintain a ring sector 10.
    Then the two second pins 20 are inserted into the two orifices 3650 provided in the third part 365 of the annular radial flange 36 of the ring support structure 3.
    The ring 1 is then mounted on the ring support structure 3 by inserting each second pin 20 into each of the orifices 180 of the second ears 18 of the downstream radial lugs 16 of each ring sector 10 making up the ring 1.
    We then place all the first pawns 19 in the holes
    3540 provided in the second part 354 of the removable annular flange 35.
    Then the removable annular flange 35 is fixed to the ring support structure 3 and to the ring 1. To fix the removable annular flange 35 to the ring support structure 3, the two hooks are inserted. 60 and 61 in the associated housings 62 and 63 until the shoulder 67 of each hook 60 and 61 abuts against the contour of the housing 62, 63. To keep the ring 1 in the radially position, the annular flange removable 35 is fixed to the ring by inserting each first pin 19 into each of the orifices 170 of the first ears 17 of the upstream radial lugs 14 of each ring sector 10 making up the ring 1.
    The ring 1 is thus held in an axial position by means of the removable annular flange 35 and of the annular radial flange 36 bearing respectively upstream and downstream on the support surfaces 110 rectilinear of the respectively upstream radial lugs 14 and downstream 16. When installing the removable annular flange 35, an axial prestress can be applied to the first tab 33 of the removable annular flange 35 and to the upstream radial lug 14 to overcome the effect of differential expansion between the CMC material of the ring 1 and the metal of the ring support structure 3. The removable annular flange 35 is held in axial stress by mechanical elements placed upstream as shown in dotted lines in FIG. 4.
    The ring 1 is held in position radially by means of the first and second pins 19 and 20 cooperating with the first and second ears 17 and 18 and the orifices 3540 and 3650 of the removable annular flange 35 and of the annular radial flange 36.
    The invention thus provides a turbine ring assembly allowing the maintenance of each ring sector in a deterministic manner while allowing, on the one hand, the ring sector, and by extension to the ring, deform under the effects of temperature rises and pressure variations, and this independently of the metal parts at the interface, and, on the other hand, while improving the seal between the non-vein sector and the vein sector and simplifying manipulations and reducing their number for mounting the ring assembly.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. A turbine ring assembly comprising a plurality of ring sectors (10) forming a turbine ring (1) and a ring support structure (3), each ring sector (10) having, according to a section plane defined by an axial direction (D A ) and a radial direction (Dr) of the turbine ring (1), an annular base portion (12) with, in the radial direction (D R ) of the turbine ring (1), an internal face (12a) defining the internal face of the turbine ring (1) and an external face (12b) from which project first and second legs d 'hooking (14, 16), the ring support structure (3) comprising a central ring (31) from which project first and second radial legs projecting between which the first and second legs are held attachment (14,16) of each ring sector (10), characterized in that the first radial tab comprises an annular flange (35) in a single piece removably attached to the central ring (31) of the ring support structure (3), the annular flange (35) having a free first end (351), a second end (352) coupled to the central ring (31) of the ring support structure (3), and at least one hooking hook (60, 61) projecting from the second end (352) of the annular flange (35) and cooperating with at least one housing (62, 63) included in the central ring (31) of the ring support structure (3) to maintain the annular flange (35) in position.
    [2" id="c-fr-0002]
    2. The assembly of claim 1, wherein the annular flange (35) comprises a first portion (353) extending from the first end (351) and a second portion (354) extending between the first portion (353) and the second end (352), the first portion (353) comprising first and second legs (33, 34) distinct, the first leg (33) being in abutment against the first hooking leg (14) and the second leg (34) being distant from the first leg (33) in the axial direction (D A ), the second leg (34) being upstream of the first leg (33) relative to the direction of an air flow ( F) intended to pass through the turbine ring assembly (1).
    [3" id="c-fr-0003]
    3. Assembly according to one of claims 1 or 2, wherein the annular flange (35) comprises a first and a second hooking hooks (60,61) projecting from the second end (352) of the flange annular (35) in the axial direction (D A ) of the turbine ring (1) and being spaced in the radial direction (Dr) of the turbine ring (1), the central crown (31) of the structure ring support (3) comprising two attachment housings (62, 63) cooperating with the first and second attachment hooks (60, 61) of the annular flange (35) to maintain the annular flange (35) in position in the radial direction (Dr) of the turbine ring (1).
    [4" id="c-fr-0004]
    4. The assembly of claim 3, wherein the first and second hooks (60, 61) of the annular flange (35) have two distinct axial positions in the axial direction (D a ) of the turbine ring (1 ).
    [5" id="c-fr-0005]
    5. Assembly according to one of claims 1 to 4, comprising, for each ring sector (10), at least three pins (19, 20) for radially maintaining the ring sector (10) in position, the first and second attachment tabs (14,16) of each ring sector (10) each comprising a first end (141, 161) integral with the external face (12b) of the annular base (12), a second end ( 142, 162) free, at least three ears (17, 18) for receiving said at least three pins (19, 20), at least two ears (17) of said at least three ears projecting from the second end ( 142, 162) of one of the first or second hooking lugs (14, 16) in the radial direction (Dr) of the turbine ring (1) and at least one ear (18) of said at least three ears s extending from the second end (162, 142) projecting from the other hooking lug (16, 14) in the radial direction (Dr) of the turbine ring (1), each ear of reception (17, 18) comprising an orifice (170,180) for receiving one of the pins (19, 20).
    [6" id="c-fr-0006]
    6. The assembly of claim 5, wherein the second portion (354) of the annular flange (35) has holes (3540) for receiving one of the pins (19), and the second leg of the support structure ring (3) comprises an annular flange (36) comprising a first portion (363) bearing against the second attachment tab (16), a second portion (364) thinned relative to the first portion (363), and a third portion (365) positioned between the first and the second portion (363 and 364) and comprising orifices (3650) for receiving one of the pins (20).
    [7" id="c-fr-0007]
    7. Assembly according to one of claims 1 to 6, in which each ring sector (10) comprises rectilinear bearing surfaces (110) mounted on the faces of the first and second attachment tabs (14, 16) in contact respectively with the second radial tab and the annular flange (33).
    [8" id="c-fr-0008]
    8. Assembly according to one of claims 1 to 6, wherein, for each ring sector (10), the faces of the second radial tab and the annular flange (33) in contact with the first and second legs respectively. hooking (14, 16) comprise rectilinear bearing surfaces (110).
    [9" id="c-fr-0009]
    9. Assembly according to one of claims 7 or 8, in which each rectilinear bearing surface (110) may comprise a groove hollowed out over the entire length of the bearing surface (110) and a seal inserted in the groove for improve sealing.
    [10" id="c-fr-0010]
    10. Turbomachine comprising a turbine ring assembly (1) according to any one of claims 1 to 9.
    1/4
    2/4
    CO
    3/4
    I
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3055147A1|2018-02-23|TURBINE RING ASSEMBLY
    FR3055148A1|2018-02-23|TURBINE RING ASSEMBLY
    EP3390783B1|2019-10-02|Turbine shroud assembly and corresponding turbine
    EP3596314B1|2021-04-28|Turbine shroud seal assembly
    EP3390782B1|2019-11-27|Turbine ring assembly, elastically retained in a cold-state
    EP3596315B1|2021-07-28|Seal shroud assembly
    FR3055146A1|2018-02-23|TURBINE RING ASSEMBLY
    FR3064023B1|2019-09-13|TURBINE RING ASSEMBLY
    EP3433471B1|2020-01-29|Turbine shroud seal assembly with specific support in cold conditions
    FR3056632A1|2018-03-30|TURBINE RING ASSEMBLY COMPRISING A COOLING AIR DISTRIBUTION ELEMENT
    FR3061929A1|2018-07-20|TURBOMACHINE TURBINE COMPRISING A DISPENSING STAGE OF CERAMIC MATRIX COMPOSITE MATERIAL
    FR3056637A1|2018-03-30|TURBINE RING ASSEMBLY WITH COLD SETTING
    EP3737837A1|2020-11-18|Turbine shroud assembly
    FR3056636A1|2018-03-30|TURBINE RING ASSEMBLY WITHOUT COLD MOUNTING SET
    EP3568574B1|2020-11-25|Turbine ring assembly
    EP3870807A1|2021-09-01|Turbine ring assembly with curved rectilinear seatings
    EP3899208A2|2021-10-27|Turbine ring assembly
    EP3908738A1|2021-11-17|Method for assembling and disassembling a turbine ring assembly
    FR3106152A1|2021-07-16|Turbine ring assembly with indexed flanges
    同族专利:
    公开号 | 公开日
    US20180051590A1|2018-02-22|
    US10598045B2|2020-03-24|
    FR3055148B1|2020-06-05|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20070077141A1|2005-10-04|2007-04-05|Siemens Power Generation, Inc.|Ring seal system with reduced cooling requirements|
    US20160177759A1|2013-08-06|2016-06-23|General Electric Company|Mounting apparatus for low-ductility turbine nozzle|
    WO2015191174A1|2014-06-12|2015-12-17|General Electric Company|Multi-piece shroud hanger assembly|
    EP2960440A1|2014-06-27|2015-12-30|Rolls-Royce Corporation|Segmented turbine shroud and method of making a turbine shroud|
    FR2540939B1|1983-02-10|1985-03-22|Snecma|
    US5188506A|1991-08-28|1993-02-23|General Electric Company|Apparatus and method for preventing leakage of cooling air in a shroud assembly of a gas turbine engine|
    US5738490A|1996-05-20|1998-04-14|Pratt & Whitney Canada, Inc.|Gas turbine engine shroud seals|
    US6733235B2|2002-03-28|2004-05-11|General Electric Company|Shroud segment and assembly for a turbine engine|
    US6758653B2|2002-09-09|2004-07-06|Siemens Westinghouse Power Corporation|Ceramic matrix composite component for a gas turbine engine|
    US7494317B2|2005-06-23|2009-02-24|Siemens Energy, Inc.|Ring seal attachment system|
    FR2887601B1|2005-06-24|2007-10-05|Snecma Moteurs Sa|MECHANICAL PIECE AND METHOD FOR MANUFACTURING SUCH A PART|
    US7374395B2|2005-07-19|2008-05-20|Pratt & Whitney Canada Corp.|Turbine shroud segment feather seal located in radial shroud legs|
    ES2398727T3|2009-03-09|2013-03-21|Snecma|Turbine ring set|
    JP4634528B1|2010-01-26|2011-02-23|三菱重工業株式会社|Split ring cooling structure and gas turbine|
    FR2955898B1|2010-02-02|2012-10-26|Snecma|UPPER SEALING OF A CMC RING IN A TURBOMACHINE TURBINE|
    US8740552B2|2010-05-28|2014-06-03|General Electric Company|Low-ductility turbine shroud and mounting apparatus|
    US8905709B2|2010-09-30|2014-12-09|General Electric Company|Low-ductility open channel turbine shroud|
    US8790067B2|2011-04-27|2014-07-29|United Technologies Corporation|Blade clearance control using high-CTE and low-CTE ring members|
    US9726043B2|2011-12-15|2017-08-08|General Electric Company|Mounting apparatus for low-ductility turbine shroud|
    US9188062B2|2012-08-30|2015-11-17|Mitsubishi Hitachi Power Systems, Ltd.|Gas turbine|
    WO2014158286A1|2013-03-12|2014-10-02|Thomas David J|Turbine blade track assembly|
    EP3025042A4|2013-07-23|2016-08-17|United Technologies Corp|Radial position control of case support structure with splined connection|
    EP2963250B1|2014-06-30|2019-08-07|Rolls-Royce Corporation|Coating for isolating metallic components from composite components|
    EP3034803A1|2014-12-16|2016-06-22|Rolls-Royce Corporation|Hanger system for a turbine engine component|
    FR3033825B1|2015-03-16|2018-09-07|Safran Aircraft Engines|TURBINE RING ASSEMBLY OF CERAMIC MATRIX COMPOSITE MATERIAL|
    EP3088679A1|2015-04-30|2016-11-02|Rolls-Royce Corporation|Seal for a gas turbine engine assembly|
    US10385712B2|2015-05-22|2019-08-20|United Technologies Corporation|Support assembly for a gas turbine engine|
    FR3036432B1|2015-05-22|2019-04-19|Safran Ceramics|TURBINE RING ASSEMBLY WITH AXIAL RETENTION|
    US10458263B2|2015-10-12|2019-10-29|Rolls-Royce North American Technologies Inc.|Turbine shroud with sealing features|
    US10436071B2|2016-04-15|2019-10-08|United Technologies Corporation|Blade outer air seal having retention snap ring|
    FR3055147B1|2016-08-19|2020-05-29|Safran Aircraft Engines|TURBINE RING ASSEMBLY|
    FR3056632B1|2016-09-27|2020-06-05|Safran Aircraft Engines|TURBINE RING ASSEMBLY INCLUDING A COOLING AIR DISTRIBUTION ELEMENT|
    US10577977B2|2017-02-22|2020-03-03|Rolls-Royce Corporation|Turbine shroud with biased retaining ring|
    FR3072720B1|2017-10-23|2019-09-27|Safran Aircraft Engines|CARTRIDGE FOR TURBOMACHINE COMPRISING A CENTRAL PORTION PROJECTED IN RELATION TO TWO SIDE PORTIONS IN A JUNCTION REGION|FR3056637B1|2016-09-27|2018-10-19|Safran Aircraft Engines|TURBINE RING ASSEMBLY WITH COLD SETTING|
    FR3064024B1|2017-03-16|2019-09-13|Safran Aircraft Engines|TURBINE RING ASSEMBLY|
    US11085316B2|2018-08-22|2021-08-10|Raytheon Technologies Corporation|Blade outer air seal formed of laminate and having radial support hooks|
    US10858949B2|2018-09-12|2020-12-08|Rolls-Royce Corporation|Multi-piece carrier assembly for mounting ceramic matrix composite seal segments|
    US10815810B2|2019-01-10|2020-10-27|Raytheon Technologies Corporation|BOAS assemblies with axial support pins|
    US11047250B2|2019-04-05|2021-06-29|Raytheon Technologies Corporation|CMC BOAS transverse hook arrangement|
    CN110374698B|2019-07-15|2022-02-22|中国航发沈阳发动机研究所|Bearing ring assembly and double-layer casing structure with same|
    US11047245B2|2019-08-12|2021-06-29|Raytheon Technologies Corporation|CMC component attachment pin|
    法律状态:
    2017-05-17| PLFP| Fee payment|Year of fee payment: 2 |
    2018-02-23| PLSC| Search report ready|Effective date: 20180223 |
    2018-07-20| PLFP| Fee payment|Year of fee payment: 3 |
    2019-07-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 5 |
    2021-07-22| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1657827A|FR3055148B1|2016-08-19|2016-08-19|TURBINE RING ASSEMBLY|
    FR1657827|2016-08-19|FR1657827A| FR3055148B1|2016-08-19|2016-08-19|TURBINE RING ASSEMBLY|
    US15/680,924| US10598045B2|2016-08-19|2017-08-18|Turbine ring assembly|
    [返回顶部]