EP3591178B1 - Abdichtungsmodul für turbomaschine - Google Patents

Abdichtungsmodul für turbomaschine Download PDF

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Publication number
EP3591178B1
EP3591178B1 EP19183350.8A EP19183350A EP3591178B1 EP 3591178 B1 EP3591178 B1 EP 3591178B1 EP 19183350 A EP19183350 A EP 19183350A EP 3591178 B1 EP3591178 B1 EP 3591178B1
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EP
European Patent Office
Prior art keywords
hook
ring
deflector
circumferential
sector
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EP19183350.8A
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English (en)
French (fr)
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EP3591178A1 (de
Inventor
Simon Nicolas Morliere
Nicolas Jean-Marc Marcel Beauquin
Renaud James MARTET
Vincent François Georges MILLIER
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals

Definitions

  • the present invention relates to a turbomachine module, which can be a turbine or form part of a turbine for example.
  • the state of the art includes in particular the documents US201404452 , FR-A1-3 914 350 and WO-A1-2016/024060 .
  • a turbomachine turbine comprises one or more stages each comprising a distributor formed of an annular row of fixed blades carried by a casing of the turbine, and a bladed wheel generally rotatably mounted downstream of the distributor.
  • the wheel is surrounded by a sealing ring which is divided into sectors and formed by sectors which are arranged circumferentially end to end and which are attached to the casing of the turbine.
  • Each ring sector generally comprises a circumferentially oriented body which carries an abradable coating attached to the internal surface of the body.
  • This coating is for example of the honeycomb type and is intended to wear by friction on the external wipers of the blades of the impeller, to form a labyrinth seal and minimize the radial clearances between the impeller and the ring sectors.
  • Each ring sector includes, at its upstream and downstream ends, attachment means on the casing.
  • Each ring sector can comprise at its upstream end a circumferential hook which defines an annular groove in which is engaged, on the one hand, an annular rail of the casing, and on the other hand, a downstream hooking spoiler of the distributor located upstream.
  • the hook of the ring has in section a general U or C shape and comprises two coaxial circumferential walls, respectively internal and external, connected together by a central bottom wall.
  • the distributor's downstream hooking spoiler has a circumferential orientation and is held tight radially against the casing rail by means of the upstream circumferential hook of the ring, the circumferential walls of which extend inside the distributor spoiler and outside the housing rail respectively. This makes it possible to participate in the radial maintenance of the distributor vis-à-vis the housing.
  • annular foil for protecting the casing rail, in particular against wear and high temperatures.
  • This foil can be sectorized and then comprises an annular row of foil sectors arranged circumferentially end to end. It has a generally U-shaped or C-shaped section and comprises two coaxial circumferential walls, respectively internal and external, connected together by a central bottom wall.
  • the foil sectors are made of sheet metal and make it possible to avoid direct contact between the hooks of the ring sectors and the casing rail, which on the one hand protects the latter against wear by friction and on the other part of protecting it thermally from the ring which can be very hot in operation due to its proximity to the combustion gases flowing in the turbine stream.
  • the longitudinal edges of the circumferential ends of two adjacent sectors of the foil face each other and are separated from each other by a circumferential clearance.
  • the circumferential clearances between the foil sectors can be offset circumferentially with respect to the circumferential clearances between the ring sectors, and in particular with respect to the circumferential clearances between the hooks of the ring sectors at the level of which there is no it is not possible to mount tabs of the type aforementioned for reasons of space in particular. Hot gases can thus pass through the circumferential clearances between the hooks of the ring sectors and impact the foil sectors, which will heat the casing rail by conduction, and therefore risks reducing its service life.
  • the document WO-A1-2016/024060 proposes to shift each shim circumferentially with respect to the associated hook so as to better protect the casing rail because the gases which would be likely to pass between the edges of the circumferential ends of the ring sectors are blocked by the shim sectors (due to their circumferential offset vis-à-vis the ring sectors) and do not reach the casing rail.
  • this solution does not make it possible to protect the casing from inter-sector leaks which take place at the level of the median bottom walls of the hooks of the ring.
  • the document FR-A1-3 914 350 proposes to circumferentially offset the body of the ring sector, with respect to its hook and its abradable coating.
  • this solution is applicable only in the case where the body of the ring sector covers its hook, which is not always the case when an optimization of the integration is desired.
  • This solution also leads to inter-sector leaks at the hooks of the ring sectors
  • the gases in the stream which are liable to heat and damage the casing escape from the stream by passing through an axial clearance between the outer periphery of the wheel and the outer periphery of the distributor located upstream of the wheel.
  • These gases cross this clearance by passing radially from the inside outwards and enter an annular space delimited, upstream, by the downstream hooking spoiler of the distributor, and downstream, by a wiper sealing upstream of the wheel.
  • This annular space is therefore the place where leak gas circulates, which is likely to pass through the inter-sector clearances and reach the casing.
  • the object of the present invention is in particular to provide a simple, effective and economical solution to this need by improving in particular the thermal protection of the casing rail in the aforementioned case.
  • the present invention thus proposes a sealing module for a turbomachine, in particular for an aircraft, this sealing module extending around an axis and comprising a distributor fixed to a casing and comprising at least one blade connected to a platform external, the external platform comprising a spoiler for attachment to the casing, the turbine module further comprising a bladed wheel rotatably mounted inside the casing and surrounded by a sealing ring attached to this casing, this ring being sectorized and comprising an annular row of ring sectors arranged so that the circumferential end edges of two adjacent sectors face each other, each ring sector comprising a body carrying an abradable coating configured to cooperating with at least one wiper carried by the wheel and a hook which extends circumferentially by being located upstream of said abradable coating and which is configured to cooperate with an accr ochage of the casing, this hook having in section a general C shape, the opening of which is oriented axially upstream and intended to receive said rail.
  • each ring sector further comprises a deflector which is arranged upstream of said coating and which extends radially inwards and upstream with respect to the axis so that its end radially internal extends around a downstream end of the external platform of the distributor.
  • each hook has a circumferential extent identical to that of said deflector, and the circumferential ends of said hook are offset in the circumferential direction from the circumferential ends of said deflector.
  • the deflector is thus intended to be located in the aforementioned annular space, between the outer periphery of the wheel and that of the distributor located upstream, and makes it possible to limit the circulation of gas in this space.
  • it makes it possible to limit the circulation of leak gases at the upstream hook of each ring sector and therefore to reduce the risk of these gases passing into the inter-sector clearances at their hooks.
  • the crankcase is thus better protected and has an optimized lifespan.
  • the offset of the ends is advantageous because the gases which are capable of passing radially from the inside outwards through the circumferential clearances between the circumferential ends of the deflectors, are blocked by the hooks which extend opposite these clearances, and the gases which are capable of passing radially from the inside to the outside through the circumferential clearances between the circumferential ends of the hooks are blocked by the deflector sectors which extend opposite these clearances.
  • each deflector has a circumferential extent identical to that of said body and of said covering, and the circumferential ends of said deflector are substantially aligned axially with those of said body and of said covering, said body comprises at its circumferential ends slots for housing inter-sector sealing tabs, and said deflector comprises at its circumferential ends notches aligned axially with these slots so that upstream axial ends of at least some of said sealing tabs penetrate into these notches; the tabs thus extend as close as possible to the hook, which optimizes inter-sector sealing.
  • the present invention also relates to a turbomachine, comprising at least one sealing module as described above.
  • FIG. 1 represents a turbine 10, here low-pressure, of a turbomachine such as a turbojet or an aircraft turboprop, this turbine comprising several stages (only one of which is shown here) each comprising a distributor 12 formed of a row ring of fixed blades carried by a casing 14 of the turbine, and a blade wheel 16 mounted downstream of the distributor 12 and rotating around an axis (not visible) in a ring 18 attached to the casing 14.
  • a turbine 10 here low-pressure
  • this turbine comprising several stages (only one of which is shown here) each comprising a distributor 12 formed of a row ring of fixed blades carried by a casing 14 of the turbine, and a blade wheel 16 mounted downstream of the distributor 12 and rotating around an axis (not visible) in a ring 18 attached to the casing 14.
  • the ring 18 is divided into sectors and formed of several sectors which are carried circumferentially end to end by the casing 14 of the turbine.
  • Each ring sector 18 comprises a body 20 which extends circumferentially and a coating 22 of abradable material fixed by brazing and/or welding on the radially internal surface of the body 20, this coating 22 being of the honeycomb type and being intended to wear by friction on external wipers 24 of the blades of the impeller 16 to minimize the radial clearances between the impeller and the ring sectors 18.
  • the wipers 24 are formed projecting from an outer platform 16a of the impeller 16, the outer platform 16a being connected to a blade of the paddle wheel.
  • Each ring sector 18 comprises at its upstream end a hook 32 with a C or U section which extends circumferentially and whose opening opens upstream, this hook 32 being engaged axially from downstream on a spoiler of attachment 34 oriented downstream of the distributor 12 which extends circumferentially upstream of the ring sectors 18, on the one hand, and on a cylindrical rail 36 of the housing 14 on which this distributor is hung, on the other hand .
  • the spoiler 34 has a general L-shape and projects from a platform 12a of the distributor 12, to which are connected at least one blade of the distributor.
  • each ring sector 18 comprises two walls 38 and 40 extending circumferentially and upstream, each wall, respectively radially outer and radially inner, are interconnected at their downstream ends by a median bottom wall 42 substantially radial, and which extend respectively radially outside and inside the rail 36, the internal wall 40 radially maintaining the spoiler 34 of the distributor against the rail 36.
  • the circumferential maintenance of the distributor 12 is ensured by means of an anti-rotation pin 44 which is carried by the housing 14 and is engaged in a notch of the distributor 12. Its axial maintenance downstream is ensured by a ring ring 46 split which is mounted in an annular groove 48 of the rail 36, which opens radially inwards.
  • the spoiler 34 of the distributor 12 is in axial support downstream on the ring 46 which is held radially in the groove of the casing rail by the internal wall 40, which extends radially inside the ring 46.
  • the axial stop function of the rod 46 can be ensured directly by the casing rail 36.
  • the downstream ends of the ring sectors 18 are clamped radially on a cylindrical rail 30 of the casing by the distributor located downstream of the ring sectors.
  • the ring sectors 18 bear radially outwards on a radially inner cylindrical face of the rail 30 of the casing, and inwards on a radially outer cylindrical face of a cylindrical rim 28 of the downstream distributor.
  • the downstream ends of the ring sectors 18 are also tightened axially via lugs on the cylindrical rail 30.
  • annular foil 50 which is sectorized and comprises an annular row of foil sectors arranged circumferentially end to end. It has a general C or U shape in section and comprises two coaxial annular walls, respectively internal 52 and external 54, connected together by a median bottom wall 56.
  • the foil 50 is mounted on the casing rail 36 and on the spoiler 34 of the distributor 12 so that the internal walls 52 of the foil sectors 50 are interposed between the internal walls 40 of the hooks 32 of the ring sectors 18, one hand, and the spoiler 34 of the distributor 12 and the annular ring 46, on the other hand, that the outer walls 54 of the foil sectors are interposed between the outer walls 38 of the hooks 32 of the ring sectors and the casing rail 36, and that the bottom walls 56 of the foil sectors are interposed between the bottom walls 42 of the hooks of the ring sectors and the casing rail 36.
  • the foil sectors 50 are made of sheet metal and make it possible to avoid direct contact between the hooks 32 of the ring sectors 18 and the casing rail 36, which makes it possible on the one hand to protect the latter against wear by friction. and on the other hand to protect it thermally from the ring which can be very hot in operation due to its proximity to the combustion gases flowing in the turbine stream.
  • the longitudinal edges of the circumferential ends of the ring sectors include slots for mounting tabs 58.
  • the tabs 58 each have a generally elongated and planar shape and each include a longitudinal edge engaged in a slot in the edge of a ring sector and an opposite longitudinal edge engaged in a slot in the edge facing an adjacent ring sector.
  • the figure 1 shows a first sealing ring technology 18 in which the body 20 and the hook 32 are formed in one piece.
  • the picture 2 shows a second sealing ring 18 technology in which the body 20 and the hook 32 are formed as assembled parts.
  • the references used in the picture 2 are the same as those of the figure 1 insofar as they designate the same elements.
  • the second technology covers the case where the hook 32 is fixed under the body, just upstream of the covering 22 (as is the case in the application FR-A1-3 914 350 ), as well as the case where the hook 32 is fixed upstream of the body, as is the case in the example shown.
  • each distributor 12 is separated by an axial clearance J of the outer periphery of the adjacent wheel 16, which may be traversed by leakage gases.
  • the cooperation of the wipers 24 with the abradable coating 22 limits the passage of these leakage gases from upstream to downstream between the wheel 16 and the ring 18.
  • the leakage gases then circulate in the annular space E extending radially between the external platforms 12a, 16a of the distributor 12 and of the wheel 16, and axially between the downstream spoiler 34 of the distributor 12 and the upstream wiper 24a of the wheel 16.
  • the tongues 58 limit the passage of gases from the space E radially outwards, at the level of the circumferential clearances between the bodies 20 of the ring sectors. However, as is best seen at the figure 3 , circumferential clearances are always present between the hooks 32 and gas can pass from the space E radially outwards, in particular between the median bottom walls 42 of the hooks 32 (arrow F).
  • each ring sector further comprises a deflector 60 which is arranged upstream of the coating 22 and which extends radially inwards with respect to the aforementioned axis so that its radially inner end extends around the downstream end of the outer platform 12a of the distributor 12.
  • the deflector 60 is formed by a part independent of the hook 32 and of the body 20, and which is inserted axially between the hook 32 located upstream, and the body 20 and the coating 22 located downstream.
  • the deflector 60 can be formed by an annular sheet metal sector.
  • the deflector 60 here has a curved general orientation and a general V-shape. It thus comprises a radially outer portion 60a extending in a plane substantially perpendicular to the aforementioned axis, and a radially inner portion 60b which is tapered.
  • Portion 60a is inserted between bottom median wall 42 of hook 32 and the upstream ends of body 20 and coating 22.
  • Portion 60b extends from downstream to upstream, radially inward. Its internal periphery defines a diameter D which is smaller than the smallest internal diameters D1, D2 of the hook 32 and of the coating 22. This internal periphery surrounds here with a small radial clearance the end of the external platform 12a of the distributor 12 ( figure 4 ).
  • the deflector 60 has a circumferential extent around the axis which is identical to that of the body 20 and the cover 22.
  • the circumferential ends of the deflector 60 are substantially aligned axially with those of the body 20 and the cover 22, as can be seen at the figure 5 .
  • the deflector 60 comprises at its circumferential ends notches 62 aligned axially with the slots 64 for housing tabs 58 for inter-sector sealing. These notches 62 are designed to be able to be crossed by the tongues 58. Each notch 62 has a height (or radial dimension) at least equal to the height (or radial dimension of the slots 64 for housing the tongues), and a width (or dimension circumferential) at least equal to the circumferential dimension between the bottoms of the two slots 64 opposite the housing of the tabs.
  • each circumferential end of a ring sector can comprise two slots 64 for housing two tabs 58, which have different lengths and extend one above the another in the radial direction.
  • the upstream ends of the slots 64 meet at the upstream end of each edge and both communicate with the notch 62, so that the two tongues 58 of each edge are likely to pass through the notch 62 ( figure 4 and 5 ).
  • the edge of each circumferential end of a ring sector could carry only one tab 58.
  • Each hook 32 has a circumferential extent identical to that of the deflector 60, and the circumferential ends of the hook 32 are offset in the direction circumferential of the circumferential ends of the deflector ( figure 5 ).
  • Each hook 32 thus comprises a circumferential end part 32a which protrudes with respect to the circumferential ends of the other parts of the ring sector, and another circumferential end part 32b which is recessed with respect to the circumferential ends of the other parts of the ring sector ( figure 5 ).
  • each ring sector comprising the projecting end portion 32a
  • the tabs 58 bear axially on this end portion (the bearing zone Z is visible in figures 6 and 7 ).
  • the tongues 58 bear axially not on this end portion 32b but on the end portion 32a of the sector of adjacent ring.
  • the deflector 60 extends into the space E located between the hook 32 and the end 12 of the external platform 12a of the distributor and divides it into two parts respectively upstream and downstream. Its shape requires the leak gases passing through the clearance J to flow downstream in the direction of the labyrinth seal defined by the wipers 24. There is therefore less risk of leakage gas circulating at the level of the hooks 32 of the ring sectors.
  • the inter-sector clearances at the level of these hooks are also sealed due to the circumferential offset between the hooks 32 and the deflectors 60.
  • the invention thus makes it possible to effectively protect the casing 14 and to improve its service life and also avoid leaks from the stream to the casing which improves the performance of the turbomachine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (6)

  1. Abdichtungsmodul für Turbomaschine, insbesondere Flugzeug, wobei sich dieses Abdichtungsmodul um eine Achse erstreckt und einen Verteiler (12) umfasst, der an einem Gehäuse (14) festgemacht ist, wobei der Verteiler (12) mindestens ein mit einer äußeren Plattform (12a) verbundenes Blatt aufweist, wobei die äußere Plattform (12a) einen Spoiler (34) zum Festmachen am Gehäuse (14) umfasst, wobei das Abdichtungsmodul weiter ein drehbar montiertes Rad (16) mit Schaufeln innerhalb des Gehäuses (14) umfasst und das von einem Abdichtungsring (18) umgeben ist, der an diesem Gehäuse (14) befestigt ist, wobei dieser Abdichtungsring (18) untergliedert ist und eine ringförmige Reihe von Ringsektoren umfasst, die derart angeordnet sind, dass Umfangsendränder von zwei angrenzenden Sektoren einander zugewandt sind, wobei jeder Ringsektor einen Körper (20) umfasst, der eine abschleifbare Auskleidung (22) trägt, die konfiguriert ist, um mindestens mit einer Lasche (24), die von dem Rad (16) getragen wird, und einem Greifer (32) zusammenzuwirken, der sich in Umfangsrichtung erstreckt, indem er sich stromaufwärts der abschleifbaren Auskleidung (22) befindet und der konfiguriert ist, um mit einer Schiene (36) zum Befestigen des Gehäuses (14) zusammenzuwirken, wobei dieser Greifer (32) im Querschnitt eine allgemeine C-förmige Form aufweist, deren Öffnung axial stromaufwärtig ausgerichtet ist und zum Aufnehmen der Schiene (36) vorgesehen ist, wobei jeder Ringsektor weiter einen Deflektor (60) umfasst, der stromaufwärts der Auskleidung angeordnet und der sich radial nach innen und stromaufwärtig in Bezug auf die Achse derart erstreckt, dass sich sein radial inneres Ende um ein stromabwärtiges Ende der äußeren Plattform (12a) des Verteilers (12) erstreckt, wobei jeder Greifer (32) eine Umfangserstreckung aufweist, die identisch ist zu jener der Deflektors (60), wobei die Umfangsenden des Greifers (32) in Umfangsrichtung von den Umfangsenden des Deflektors (60) versetzt sind, wobei jeder Deflektor (60) eine Umfangserstreckung aufweist, die identisch ist zu jener des Körpers (20) und der Auskleidung (22), dadurch gekennzeichnet, dass die Umfangsenden des Deflektors (60) im Wesentlichen mit jenen des Körpers (20) und der Auskleidung (22) axial ausgerichtet sind, und dadurch, dass der Körper (20) an seinen Umfangsenden intersektorielle Schlitze zur Unterbringung von intersektoriellen Abdichtungslaschen (58) umfasst, und dadurch, dass der Deflektor (60) an seinen Umfangsenden Einkerbungen (62) umfasst, die derart axial mit diesen Schlitzen ausgerichtet sind, dass stromaufwärtige axiale Enden mindestens einiger der Abdichtungslaschen in die Einkerbungen (62) eindringen.
  2. Abdichtungsmodul nach dem vorstehenden Anspruch, wobei der Deflektor (60) einen ringförmigen Blechsektor umfasst, der axial einerseits zwischen dem Greifer (32) und andererseits der Auskleidung (22) und/oder dem Körper (20) eingeschoben ist.
  3. Abdichtungsmodul nach dem vorstehenden Anspruch, wobei der Blechsektor eine allgemeine V-förmige Form aufweist, bei der ein radial äußerer Abschnitt (62a) sich radial erstreckt und bei der ein radial innerer Abschnitt (62b) kegelstumpfförmig ist und sich von stromabwärts nach stromaufwärts radial nach innen erstreckt.
  4. Abdichtungsmodul nach dem vorstehenden Anspruch, wobei der Greifer (32) eine mittlere Bodenwand (42) umfasst, die zwei radial innere (40) bzw. äußere (38) Wände verbindet, die sich in Umfangsrichtung erstrecken, wobei der radial äußere Abschnitt des Blechsektors axial zwischen der Bodenwand des Greifers (32) und der Auskleidung (22) und/oder dem Körper (20) eingeschoben ist.
  5. Abdichtungsmodul nach einem der vorstehenden Ansprüche, wobei jeder Ringsektor an einem seiner Umfangsenden mindestens eine Abdichtungslasche (58), deren stromaufwärtiges axiales Ende eine Einkerbung (62) des Deflektors (60) durchquert und axial auf einem Greifer (32) dieses Ringsektors aufliegt, und am anderen seiner Umfangsenden mindestens eine Abdichtungslasche umfasst, deren stromaufwärtiges axiales Ende eine Einkerbung (62) des Deflektors durchquert und axial auf einem Greifer eines benachbarten Ringsektors aufliegt.
  6. Turbomaschine, umfassend mindestens ein Abdichtungsmodul nach einem der vorstehenden Ansprüche.
EP19183350.8A 2018-07-03 2019-06-28 Abdichtungsmodul für turbomaschine Active EP3591178B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1856139A FR3083563B1 (fr) 2018-07-03 2018-07-03 Module d'etancheite de turbomachine d'aeronef

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EP3591178A1 EP3591178A1 (de) 2020-01-08
EP3591178B1 true EP3591178B1 (de) 2022-08-10

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US (1) US11035244B2 (de)
EP (1) EP3591178B1 (de)
CN (1) CN110685753B (de)
FR (1) FR3083563B1 (de)

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FR3100838B1 (fr) * 2019-09-13 2021-10-01 Safran Aircraft Engines Anneau d’etancheite de turbomachine
FR3108935B1 (fr) * 2020-04-02 2022-03-04 Safran Aircraft Engines Dispositif de distribution d’huile d’un palier a roulement de turbomachine d’aeronef
FR3111382B1 (fr) * 2020-06-11 2022-12-23 Safran Aircraft Engines Ensemble annulaire pour turbine de turbomachine
FR3114841B1 (fr) * 2020-10-05 2023-06-30 Safran Aircraft Engines Ensemble annulaire pour turbine de turbomachine
FR3114840B1 (fr) * 2020-10-05 2022-11-11 Safran Aircraft Engines Ensemble annulaire pour turbine de turbomachine
FR3122692A1 (fr) * 2021-05-07 2022-11-11 Safran Aircraft Engines Pièce annulaire d’étanchéité pour aubes mobiles de turbine de turbomachine
FR3140112A1 (fr) * 2022-09-22 2024-03-29 Safran Aircraft Engines Amélioration de l’étanchéité dans une turbine de turbomachine

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US20140044528A1 (en) * 2012-08-07 2014-02-13 United Technologies Corporation Blade outer air seal having anti-rotation feature

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EP3591178A1 (de) 2020-01-08
US20200011194A1 (en) 2020-01-09
CN110685753B (zh) 2023-04-28
FR3083563B1 (fr) 2020-07-24
US11035244B2 (en) 2021-06-15
FR3083563A1 (fr) 2020-01-10
CN110685753A (zh) 2020-01-14

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