• 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 sealing in a gas turbine engine. Passages (52) for a gaseous barrier fluid are provided through a rotor portion, as are means for blowing the gaseous fluid. The passages open, through a wiper (41) or, in the vicinity of this wiper, through a rotor portion provided with the wiper, so that blown gaseous fluid can be present in a zone (55) located radially between a coating (46) of abradable material and the wiper (41) or said portion thereof.
    公开号:FR3067405A1
    申请号:FR1755263
    申请日:2017-06-13
    公开日:2018-12-14
    发明作者:Cyrille TELMAN；Frederic Claude Cyrille Evain Gael；Arnaud Fabien Lambert Olivier；Charles Jean Verdiere Mathieu
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    In a gas turbomachine for an aircraft, such as a turboprop or an airplane turbojet, the present invention relates to the control of certain seals with respect to the gases in circulation.
    In such a turbomachine, it is common for a low pressure compressor and a high pressure compressor to be provided, each driven by a rotation shaft and connected by an intermediate casing defining an annular flow stream of a primary air flow circulating globally. axially from the low pressure compressor (LP) to the high pressure compressor (HP).
    Traditionally, these turbomachines comprise a fixed part (or stator) and a rotating part (or rotor). The part considered to be rotatable is mounted to rotate about an axis of rotation, with respect to the part considered to be fixed, the parts respectively fixed and rotating being locally provided with complementary sealing means with respect to gaseous fluids circulating in the turbomachine. .
    In an aircraft turbine or compressor, a rotor part thus in particular comprises rotating blades, also called rotary blades, provided at the radially external end with wipers. These wipers cooperate with blocks of abradable material defining radially internal coatings of a fixed outer wall of the turbomachine to which the blocks are circumferentially fixed, as complementary sealing means for the wipers.
    In addition to the free ends of rotary blades, gas tightness is also typically achieved at the location of radially internal feet of fixed blades which can be provided with the abradable blocks of abovementioned material, to then define sealing means, radially internal, again complementary to wipers, typically wipers of an intermediate sealing ring and / or at least one intermediate ferrule carrying inter-stage seals and interposed between an upstream disc and an axially successive downstream disc rotor.
    These two examples therefore provide a seal between fixed and rotating parts respectively via structures comprising a fixed part made of solid material or a honeycomb structure and wipers on the rotating part. This is the case in FR3027341 where a labyrinth shell carries wipers coming into contact with abradable tracks of an abradable carrier ring in order to impede the passage of air at the foot of the fixed vanes. Like the labyrinth shell, the abradable ring is made of 3D woven CMC. This is a constraint, even if mastering the quality of these seals is always essential in order to be able to ensure the expected performance of the turbomachine and limit the thermal stresses.
    It is therefore for this purpose and if necessary in order to avoid the abovementioned drawbacks, that a gas turbomachine comprising a sealing device is proposed here (or, on a gas turbomachine, a sealing device) between a rotor part and a stator part of the turbomachine having a longitudinal axis (X), the sealing device comprising:
    - at least one coating of abradable material fixed with the stator part,
    - at least one wiper with which a portion of the rotor part is provided and which is adapted to cooperate with said coating of abradable material, for sealing, characterized in that there are further provided:
    - through the rotor part, gaseous fluid passages, and
    means for blowing this gaseous fluid into said passages, which passages open out, through the wiper or, near said (at least one) wiper, through said portion provided with the wiper, so that said blown gaseous fluid can lead into an area radially between:
    - the coating of abradable material, and
    - the wiper or said area provided with the wiper.
    In this application:
    - axial has the direction parallel to the axis (X) of rotation about which the so-called rotating blades of the turbomachine in question are rotatably mounted,
    - radial has the direction perpendicular to the X axis,
    - circumferential has the meaning extending around the X axis,
    - exterior and interior (or exterior and interior) have respectively radially exterior and radially interior direction with respect to the axis X; and
    - léchette will often be translated into English: "rubbing strip (seal)" or "labyrinth seal lip".
    The above solution must allow, at least in part:
    - limit the loss of engine performance and the increase in temperatures when the radial clearances in front of the wipers are open, and / or
    - to keep, if desired, the current wiper configurations, in particular the solutions with straight or inclined wipers, and / or
    - to intervene directly on the leakage gas flow, by countering its diffusion, via the planned blowing, and / or
    - to favor a pressure delta towards the abradable (higher pressure in the radial zone between (base of the) wiper and abradable), and thus make a barrier to the leakage gas, generator of loss of tightness,
    - to avoid difficulties in precisely controlling the radial clearances in front of the wipers, depending on the operating conditions of the turbomachine.
    As mentioned above, a first practical mounting situation may arise if:
    - The stator part comprises distributor vanes provided with external platforms and internal platforms, the latter being connected radially inside to feet to which is (are) fixed (s) said (s) coating (s) ) in abradable matter,
    - the rotor part includes:
    - vanes that can rotate around said longitudinal axis (X), and - an intermediate sealing ring and / or at least one ferrule, having said portion provided with several said wipers and interposed (e) between an upstream disc and a axially successive downstream rotor disc on which said vanes are mounted by their feet, and
    - Said passages pass through the intermediate sealing ring and / or said at least one ferrule.
    Thus, by using air, for example from the compressor, which can be used to cool the disc bottoms where the cells for mounting the movable vanes on these discs are located, we will in particular be able to create said barrier to leakage gas, without alter the cooling of the alveoli.
    More generally, provision is also made for the means for blowing, in said passages, of the gaseous barrier fluid to comprise at least one air supply circuit (hereinafter B) coming from a compressor of the turbomachine. .
    Concerning the origin of this blown air, and although it is therefore appreciated, in certain turbomachinery, to use air taken from the upstream high pressure compressor, HP, to cool parts located in a warmer environment, and in particular the HP turbine blade, the bores of the discs, etc. purge air could for example be extracted from a downstream compressor stage, or extracted and mixed from several compressor stages .
    As for the gas flow which is to be countered via the barrier flow, it may further be provided that, axially between the external and / or internal platforms of the distributor vanes and those of the (so-called rotating) vanes of the rotor part, a leakage gas flow (ci5 after flow V) can pass through slots adapted to allow such flow:
    - outside a gas flow stream from the turbomachine in which the distributor vanes and said vanes of the rotor part extend,
    - up to said zones located radially between the wipers and the coverings of abradable material, so that said leaky gas flow can meet there the gaseous fluid coming from said passages.
    Thus, in particular without altering the cooling provided by the leakage gas flow, therefore by vein air, it will be possible to prevent this leakage gas from passing, at the location of the wipers, from an upstream stage to a stage downstream of the relevant part of the turbomachine.
    In another case, provision is also made to cover a second practical mounting situation which may arise if:
    the stator part comprises ring sectors fixed (hooked) 15 circumferentially with an external casing and to which several said abradable coatings are fixed,
    the rotor part comprises vanes which can rotate around said longitudinal axis (X) and having said portion provided with several said wipers, at a radially outer end, and if
    - Said passages pass through at least some of the blades.
    In this case, while potentially being able to use the air for cooling the disc bottoms, we will then be able in particular to create said barrier to the leakage gas, not only without altering the cooling of the discs and blade roots, but by cooling to passing the blades of the movable blades, which will therefore be locally hollow.
    To get as close as possible to the meeting zones between the flows of leakage air and of blown air creating said barrier, it is also proposed that said passages for this blown air pass through said at least one wiper.
    One could however in certain cases fear having to carry out a drilling of the wiper (s). These are sensitive places, mechanically and thermally.
    A complement or an alternative thus offers:
    the turbomachine comprises, radially opposite said at least one coating of abradable material, at least two wipers, and
    - that in the direction of said zone where the blown gaseous fluid must open to create the expected anti-leakage barrier, said passages provided for this purpose pass between said at least two wipers, said portion of sealing ring, and / or ferrule, intermediate provided with these wipers.
    We can thus secure the realization of the passages, or even work more precisely their shape and arrangement, and / or benefit in addition from the chamber which actually exists in the space present between said at least two wipers then respectively upstream and downstream.
    A favorable pressurization of this chamber can be expected.
    The first and second practical situations may or may not be combined.
    Above was mentioned an interest in having worked on the shape of the blowing passages of the gaseous fluid. In this regard, it may be advantageous for said passages to extend in the direction of said zone by diverging.
    Indeed, it will then promote an enlarged outlet of the gas flow aimed at the creation of a kind of barrier gas curtain, a situation that the rotation of the wiper support parts must promote. Thus, a kind of dynamic seal will be established.
    Same beneficial effect expected if said passages are arranged and / or shaped so that the flow of gaseous fluid blown by such adjacent passages overlap, when the turbomachine is operating. Indeed, this arrangement will further promote the sealing of the barrier gas curtain thanks to a partial covering of jets.
    It is also advisable, for such a still favored effect, that said passages:
    - are located axially (axis X) opposite said at least one coating of abradable material, and / or
    - that they are either radial, or made so as to extend upstream, in the direction of said coating.
    The technology which has just been presented must allow, from the implementation of its principle, to have an engine performance less dependent on the opening of the radial clearances, while keeping the possibility of coming to machine the abradable when the game closes.
    This technology can be applied to all parts with a wiper (s) on the low pressure turbine, namely the moving discs and rings but also the moving blades.
    It is therefore a characteristic here mentioned that the above-mentioned rotor and stator parts belong to a low pressure turbine of the turbomachine located axially downstream of a high pressure turbine of this turbomachine.
    Other advantages and characteristics of the invention will appear on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which:
    FIG. 1 diagrammatically shows a conventional aircraft turbomachine, in vertical half-section along a median plane containing its horizontal axis X of rotation,
    FIG. 2 shows diagrammatically, in the same half-section, a portion of the low pressure turbine of the turbomachine of FIG. 1,
    - Figure 3 shows schematically, in vertical section transverse to the X axis, an outer zone showing a part of a moving blade of a turbine stage opposite a sealing sector provided with an abradable mounted in a casing exterior, still according to the prior art,
    - Figure 4 is the same view as Figure 3, but with a passage for barrier air, according to the invention, arranged between two wipers, with an alternative or complementary possibility (marked in broken lines) of at least one passage for barrier air through at least one wiper, in accordance with another exemplary embodiment of the invention,
    FIG. 5 is a side view of a movable blade, here hollow, also provided with such a passage,
    - Figures 6 and 7 schematize two alternative embodiments of the invention, again in vertical cross section, when the passages are provided on disc ferrules or movable ring,
    FIG. 8 shows, in the same section, an example of a barrier fluid circuit in the schematic turbine,
    FIG. 9 repeats FIG. 1 and shows an example of sampling and supplying air so that this air can serve as barrier air, and,
    - Figure 10 shows this air barrier emerging from a series of aforementioned passages.
    As shown schematically in FIG. 1, a double-flow reactor or turbomachine 1 for an aircraft comprises at least one annular casing 2 of an external fan within which various components of the turbomachine are arranged.
    At the entrance to the outer annular casing 2, considering the direction of air movement (opposite to the direction of advancement of the aircraft, i.e. from left to right in the figure; see arrows), find blades of a blower 3 coupled to a rotary shaft 4. Next, connected to the shaft 4 which extends around the axis X of rotation of the turbomachine, there are different axial compression stages, typically a compressor low pressure 5a followed by a high pressure compressor 5b; then are arranged various other elements of the engine including stages of axial turbine (s), typically a high pressure turbine 6 followed by a low pressure turbine 16.
    The air enters upstream (AM) in the outer annular casing 2 of the blower where it is entrained by the blades of the blower 3. To ensure propulsion, most of it flows downstream (AV) in the vein secondary 11 delimited radially between a part of the outer annular casing 2 and a more inner motor casing 7. Another part of the air is sucked into a primary stream 13 by the low pressure compressor 5a and directed downstream in the turbine stages via other components of the engine. Stiffening arms 10 also connect the external annular casing 2 and the motor casing 7.
    Each compressor, such as the low pressure compressor 5a, comprises a rotating part, or rotary part, and a fixed part secured to the motor casing 7. More particularly, the compressor comprises alternating blades 8 belonging to rotor wheels, coupled to the shaft 4, and therefore rotary, and rectifiers 9 (or stators) coupled to the fixed part of the compressor in order to straighten the air.
    In the example, the low-pressure turbine 16 partly shown in FIG. 2 comprises rows of rotating or rotor blades, 18, 20, 22 (blades 8) and rows of fixed blades 24, 25, 26 (rectifiers 9).
    The fixed vanes 24, 25, 26 are, at their radially external ends, mounted by means not shown on an external casing 440 and the rotating vanes 18, 20, 22 are mounted at their radially internal ends on discs 28, 30, 32 of the rotor. Each disc comprises an upstream annular ferrule 36a and a downstream annular ferrule 36b used for fixing the discs to each other and to a drive cone 34 connected to the shaft 4 of the turbomachine, to rotate with it, as well as to the fixing of annular flanges retaining the feet 81 of blades on the discs. The feet of the blades are shaped to cooperate with axial grooves provided in the rotor discs. Each rotating blade extends along an axis perpendicular to the axis X of the rotor on which the blade is mounted.
    Two axially successive discs, such as 28.30, of rotor are secured to each other, via the above-mentioned upstream and downstream annular ferrules, by bolts 33. An inter-stage seal 37 can be carried by one of these ferrules 36a, 36b or by an intermediate sealing ring 35, which can also be maintained by the bolts 33 and located at the outer periphery of the corresponding upstream shell 36a. As a portion of the rotor part concerned, this seal may include radial annular extensions or wipers 41 cooperating with an abradable coating 46, so as to define a labyrinth seal.
    Generally, the rotor blades are arranged and can rotate, around the X axis, between an outer annular limit and an inner annular limit which can be essentially defined respectively by external platforms 44b and internal 45b, respectively, of which are provided with rotating vanes and fixed rectifiers. At least one coating 46 of abradable material is fixed to each radially internal leg 43 of the inner platform 45a of the fixed, or stator, vane of the corresponding distributor. The covering 46 can be produced in sectors and be of honeycomb structure.
    Externally, at least one such covering 46 is also indirectly attached to the fixed external casing 440. Fasteners 49a can make it possible to fix the linings 46 on ring sectors 48 hooked circumferentially on the external casing 440. A part 490 of these fasteners is located radially outside and adjacent to the platforms 44a (see FIG. 4).
    As shown in FIGS. 3 and 4, towards the external platforms 44b, as a portion of the rotor part concerned, the rotary vanes 8 all include wipers 41. These wipers 41 cooperate by friction with the coating (s) 46 of the outer casing 440 fixed to ensure the sealing at the top of the rotary blades concerned, that is to say limiting the parasitic air flows between the tops of the rotary blades and the coating (s) 46.
    Via such a sealing device 50 formed with the coatings 46 associated with the wipers 41, it will therefore be possible, during the operation of the turbomachine, to allow the stator, by abrading, to adapt to the shape of the wipers rubbing against him by their tops.
    However, as explained above, the seal is a function of the radial distance (L, FIG. 3) between the fixed part, here the linings 46, and the rotating part, here the wipers 40.
    Note that the forms of coating (s) 46 and wiper (s) 40/41 could be other, for example a radially stepped coating and / or one (s) inclined wiper (s).
    An objective of the invention is:
    - limit the importance of having to precisely control this distance, and / or
    - to propose a solution that complements the current control of sealing.
    It is therefore proposed that, in addition, on the turbomachine, and as shown diagrammatically in FIGS. 4-7 and 9:
    - through the rotor part considered, such 8,35,36a, 36b, 37, passages 52 of gaseous fluid, and
    - means 54 for blowing the gaseous fluid into said passages 52.
    The passages 52 lead to:
    - through the wiper (s), 41, considered, or,
    - Close to this or these wipers 41, then through the rotor portion, such as 35a, 36 and / or 35 and / or 44b concerned.
    Thus, blown gaseous fluid B will be able to open into a zone 55 located radially between:
    the coating 46 of abradable material, and
    - The wiper or wipers 41 considered or said portion which is provided with it.
    The part of the turbomachine concerned will favorably be the low pressure turbine 16.
    The means 54 for blowing, in the passages 52, the gaseous fluid (flow B; FIGS. 4-8) therefore provided to make a barrier to the leakage V of a vein air, as also shown diagrammatically in FIG. 2, can come from the HP compressor 5b, via circuits 56 for removing or supplying air (see FIG. 9), as is already used to cool the discs, such as
    28,30,32 (the circuits shown diagrammatically 56, which can be circuits of the “LTP cooling” or “air cooling / low pressure cooling” type - in French) and / or “Bore cooling” or “air de bore cooling / bore cooling ”- in French - are in fact internal to the turbomachine). The supplied air is therefore used here to pressurize the aforementioned zone 55 where said barrier air opens.
    For the barrier air B to pass in the intended direction (towards the zone 55 considered), it will be necessary to adjust the flow rate of the air coming, in the example, from the circuits 56, in order to establish a higher pressure in zone 55 than in its environment, such as just upstream; see spaces 58 figures 4-7.
    As (part at least) of the circuits 56 for drawing or supplying air B, provision may also be made for using tube (s) for supplying cooling air flow to low temperature (so-called LTCA tubes) which, in an already known manner, often supplies relatively fresh air to a section of the turbine 16 from a section of the compressor 5b (see WO2014175969).
    Among the zones concerned by such an air blowing, there will therefore typically be, as shown diagrammatically in FIGS. 4-5, those situated at the outer periphery of the rotor blades 8.
    In this case, we are therefore in the situation:
    - where the stator part concerned comprises the ring sectors 48 to which several said abradable coatings 46 are fixed,
    - And where the rotor part comprises the vanes 8, said portion 44b (platform) is provided with several said wipers 41, at a radially outer end.
    To facilitate access, for the barrier air, to zone 55, the passages 52 can then pass through at least some of the blades 8. Thus, these blades will be hollow, at least locally; portion 80 in FIG. 4 or 5, where another passage 59, in the base 81 and the inner platform of the blade, allows the air coming from the air supply circuit 56 to reach the hollow blade 83.
    Another case of areas affected by such air blowing, those located on the inner periphery of stator blades, as shown schematically in Figures 6-7.
    In this case, we are therefore in the situation:
    - where the stator part comprises distributor vanes 9, at the internal feet 43 of which are fixed several said coatings 46 of abradable material,
    - and where the rotor part comprises:
    - Said vanes 8 mounted to rotate about the X axis, and - several said wipers 41 provided on the intermediate ring 35 and / or on one of the disc ferrules 36a, 36b, interposed (e) between said discs upstream and downstream axially successive, such as 28.30, on which said vanes 8 are mounted, by their feet, and a portion of which is therefore provided with these wipers 41.
    The passages 52 then pass through the intermediate sealing ring 35 (FIG. 7) and / or said at least one disc ferrule 36a, 36b (FIG. 6).
    As can be seen in FIGS. 4-7, axially between at least some of the outer platforms 44a and inner 45a of the distributor vanes 9 and those 44b, 45b of the rotor vanes 8, the leakage gas flow V occurs via one or more slots 61 and / or 63 adapted to allow such a flow V:
    - outside the stream 13 of the turbomachine in which the distributor and rotor vanes extend, 9.8,
    - towards space 58 located, axially:
    - between the upstream disc (AM) considered, as 28 Figures 6-7, and the internal feet 43 of the distributor vanes 9 located downstream, and / or - between a part of the fasteners 49a of the linings 46 (part 490) and the external platforms 44b with their wipers (FIG. 4).
    The zones 58 and 55 being communicating, a leakage gas flow will thus reach the said zones 55 located opposite the distributor vanes 9, so that said leakage gas flow V there meets the barrier gas fluid B coming from the passages 52 and be blocked in its path. We therefore stop the leakage flow.
    To make the through passages 52, it will be possible to pass through the wipers 41 as shown in FIGS. 3 and 6. With two wipers, upstream and downstream, it will be possible to have a double barrier to the flow of leakage. But wipers are fragile structures and are subject to strong constraints.
    We may therefore prefer:
    - provide, radially opposite a said coating 46 of abradable material, at least two annular wipers 41, as in FIG. 4 or 7, and
    - that in the direction of said zone 55 and between these at least two wipers, the passages 52 pass through:
    - The intermediate sealing ring 35 and / or said at least one ferrule 36a, 36b (Figure 7), - and / or the external platform 44b concerned (Figure 4).
    To optimize the solution presented here, it may be sought that the passages 52, typically made by drilling, are fairly easily fabricable and that the jets 65 of fluid B emerging from such adjacent passages are superimposed, in operation, that is to say -to say when the turbomachine 1 is operating and therefore in particular that the rotor blades 8 rotate around the axis X. FIG. 10 shows schematically such dynamic sealing. One advantage is that it imposes less manufacturing constraints.
    Another solution with the same advantages, and which can therefore complement the previous one, provides that said passages 52 extend in the direction of zone 55 while diverging. They could be tapered holes. This is illustrated in FIG. 6 and can be assumed in FIG. 10, taking into account the frustoconical shape of the jets 65. In another case, as in FIG. 5 or 7, the through holes 52 are cylindrical with a constant circular section.
    In the structural portion concerned, the passages 52 will typically be formed circumferentially, around the axis X, along a row (Figures 4,5,7) or two axially adjacent rows (Figure 6).
    They will be radial (Z axis), but could in particular follow the orientation of the wipers (see wipers inclined upstream in Figure 7). Thus, it is advisable that the perforations, or passages 52, which must be opposite the abradable 46 considered, are either radial or made in the opposite direction of the movement of the hot air, so in a way to extend upstream, as in Figure 7, in order to blow the flow B upstream.
    As is apparent from the above and as shown diagrammatically in FIG. 4 for one of the cases, it will be possible to dissociate or associate at will, in front of a zone 55, at least one passage 52 through a wiper 41 and at least one passage 52:
    - through a platform 44b,
    - And / or through an intermediate sealing ring 35 or a ferrule 36a.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Gas turbomachine comprising a sealing device between a rotor part and a stator part of the turbomachine having a longitudinal axis (X), the sealing device comprising:
    - at least one coating (46) of abradable material fixed with the stator part (9,43; 440),
    - at least one wiper (40,41) which is provided with a portion of the rotor part (8; 35,37) and which is adapted to cooperate with said coating (46) of abradable material, for sealing, characterized in what it further includes:
    - through the rotor part (8; 35,37), gaseous fluid passages (52), and
    - Means (54) for blowing this gaseous fluid into said passages (52), which passages open out, through the wiper (40,41) or, near said wiper (40,41), through said portion provided of the wiper (40,41), so that said blown gaseous fluid can open into a zone (55) located radially between:
    - the coating (46) of abradable material, and
    - The wiper (40,41) or said portion (35,36a, 36b, 44b) which is provided therewith.
    [2" id="c-fr-0002]
    2. A gas turbomachine according to claim 1, in which:
    - the stator part (9,43; 440) comprises distributor vanes (9) provided with internal platforms (45a) connected radially inside to feet (43) to which is (are) fixed (s) the (s) ) said coating (s) (46) of abradable material,
    - the rotor part (8; 35,37) comprises:
    - vanes (8) which can rotate around said longitudinal axis (X), and - an intermediate sealing ring (35) and / or a ferrule (36a, 36b), having said portion provided with at least one wiper (40,41) and interposed (e) between an upstream disk (28) and an axially successive downstream disk (30) of rotor on which said blades (8) are mounted by their feet (81), and
    - Said passages pass through the intermediate sealing ring (35) and / or said ferrule (36a, 36b).
    [3" id="c-fr-0003]
    3. Gas turbomachine according to claim 1, in which:
    the stator part (9,43; 440) comprises ring sectors (48) to which several said abradable coatings (46) are fixed,
    - the rotor part (8; 35,37) comprises vanes (18,20,22) which can rotate around said longitudinal axis (X) and having said portion provided with several said wipers (40,41), at a radially outer end , and
    - Said passages (52) pass through at least some of the blades (18,20,22).
    [4" id="c-fr-0004]
    4. Gas turbomachine according to any one of the preceding claims, in which the means for blowing the gaseous fluid (54) into said passages (52) comprise at least one circuit (56) for supplying air (B) from a compressor (5b) of the turbomachine.
    [5" id="c-fr-0005]
    5. Gas turbomachine according to any one of the preceding claims, in which said passages (52) pass through at least one wiper (40,41).
    [6" id="c-fr-0006]
    6. Gas turbomachine according to claim 2 alone or in combination with any one of claims 3 to 5,
    - which comprises, radially opposite said at least one coating (46) of abradable material, at least two wipers (40,41) and
    - in which, in the direction of said zone, said passages pass, between said at least two wipers (40,41), said portion provided with wipers (40,41) of the intermediate sealing ring (35) and / or of said at least one ferrule (36a, 36b).
    [7" id="c-fr-0007]
    7. Gas turbomachine according to any one of the preceding claims, in which said passages (52) extend in the direction of said zone (55) while diverging.
    [8" id="c-fr-0008]
    8. Gas turbomachine according to any one of the preceding claims, in which said passages (52) are arranged and / or shaped so that the flows of gaseous fluid blown by adjacent passages (52) overlap, when the turbomachine works.
    [9" id="c-fr-0009]
    9. Gas turbine engine according to any one of the preceding claims, in which the passages (52) which are located axially opposite said at least one coating (46) of abradable material, are either radial or produced so as to extend upstream, in the direction of said at least one covering (46).
    [10" id="c-fr-0010]
    10. Gas turbomachine according to any one of the preceding claims, in which said rotor and stator part belong to a low pressure turbine (16) of the turbomachine located axially downstream of a high pressure turbine (6) of the turbomachine.
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    FR3009336A1|2015-02-06|ROTARY TURBOMACHINE ASSEMBLY WITH A VIROLE LABYRINTHE CMC
    同族专利:
    公开号 | 公开日
    US20180355742A1|2018-12-13|
    FR3067405B1|2020-08-14|
    US11208909B2|2021-12-28|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4820116A|1987-09-18|1989-04-11|United Technologies Corporation|Turbine cooling for gas turbine engine|
    US20140086743A1|2012-09-26|2014-03-27|Alstom Technology Ltd|Method and cooling system for cooling blades of at least one blade row in a rotary flow machine|
    US20160186666A1|2014-09-12|2016-06-30|United Technologies Corporation|Method and assembly for reducing secondary heat in a gas turbine engine|
    EP3112694A1|2015-07-01|2017-01-04|Techspace Aero S.A.|Perforated drum of an axial turbine-engine compressor|
    US4142824A|1977-09-02|1979-03-06|General Electric Company|Tip cooling for turbine blades|
    US4422648A|1982-06-17|1983-12-27|United Technologies Corporation|Ceramic faced outer air seal for gas turbine engines|
    US4589823A|1984-04-27|1986-05-20|General Electric Company|Rotor blade tip|
    US5660523A|1992-02-03|1997-08-26|General Electric Company|Turbine blade squealer tip peripheral end wall with cooling passage arrangement|
    US5733102A|1996-12-17|1998-03-31|General Electric Company|Slot cooled blade tip|
    US6224336B1|1999-06-09|2001-05-01|General Electric Company|Triple tip-rib airfoil|
    US6527514B2|2001-06-11|2003-03-04|Alstom Ltd|Turbine blade with rub tolerant cooling construction|
    GB2413160B|2004-04-17|2006-08-09|Rolls Royce Plc|Turbine rotor blades|
    US8113779B1|2008-09-12|2012-02-14|Florida Turbine Technologies, Inc.|Turbine blade with tip rail cooling and sealing|
    US20130078084A1|2011-09-23|2013-03-28|United Technologies Corporation|Airfoil air seal assembly|
    EP3348803B1|2013-03-13|2019-09-11|United Technologies Corporation|Engine mid-turbine frame transfer tube for low pressure turbine case cooling|
    US9856739B2|2013-09-18|2018-01-02|Honeywell International Inc.|Turbine blades with tip portions having converging cooling holes|
    FR3027341B1|2014-10-15|2020-10-23|Snecma|ROTARY ASSEMBLY FOR TURBOMACHINE INCLUDING A SELF-PROPORTED ROTOR CRANKSET|
    US20160222813A1|2015-01-29|2016-08-04|United Technologies Corporation|Abradable Seal Material|US10544699B2|2017-12-19|2020-01-28|Rolls-Royce Corporation|System and method for minimizing the turbine blade to vane platform overlap gap|
    US10533610B1|2018-05-01|2020-01-14|Florida Turbine Technologies, Inc.|Gas turbine engine fan stage with bearing cooling|
    FR3099786B1|2019-08-07|2021-07-30|Safran Helicopter Engines|MOBILE DAWN FOR ONE WHEEL OF A TURBOMACHINE|
    法律状态:
    2018-12-14| PLSC| Publication of the preliminary search report|Effective date: 20181214 |
    2019-05-22| PLFP| Fee payment|Year of fee payment: 3 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 4 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1755263|2017-06-13|
    FR1755263A|FR3067405B1|2017-06-13|2017-06-13|TURBOMACHINE AND PROCESS FOR SEALING BY AIR BLOWING|FR1755263A| FR3067405B1|2017-06-13|2017-06-13|TURBOMACHINE AND PROCESS FOR SEALING BY AIR BLOWING|
    US16/005,911| US11208909B2|2017-06-13|2018-06-12|Turbine engine and air-blowing sealing method|
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