EP2495399B1 - Segmentierter Stator-Außenring zum Kompensieren von Rotorverschiebungen gegenüber dem Stator - Google Patents

Segmentierter Stator-Außenring zum Kompensieren von Rotorverschiebungen gegenüber dem Stator Download PDF

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Publication number
EP2495399B1
EP2495399B1 EP11156828.3A EP11156828A EP2495399B1 EP 2495399 B1 EP2495399 B1 EP 2495399B1 EP 11156828 A EP11156828 A EP 11156828A EP 2495399 B1 EP2495399 B1 EP 2495399B1
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EP
European Patent Office
Prior art keywords
housing
rotor
segments
accordance
shell
Prior art date
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Active
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EP11156828.3A
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English (en)
French (fr)
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EP2495399A1 (de
Inventor
Jean-François Cortequisse
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Safran Aero Boosters SA
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Safran Aero Boosters SA
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Filing date
Publication date
Application filed by Safran Aero Boosters SA filed Critical Safran Aero Boosters SA
Priority to EP11156828.3A priority Critical patent/EP2495399B1/de
Priority to CA2769815A priority patent/CA2769815C/en
Priority to US13/407,948 priority patent/US8939712B2/en
Priority to RU2012107669A priority patent/RU2620883C2/ru
Priority to CN201210142291.9A priority patent/CN102654141B/zh
Publication of EP2495399A1 publication Critical patent/EP2495399A1/de
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Publication of EP2495399B1 publication Critical patent/EP2495399B1/de
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Classifications

    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/312—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being parallel to each other
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Definitions

  • the invention relates to a housing for wrapping the ends of a row of blades of a rotor, the housing being provided with a sealing device between the blade tips and the housing. More specifically, the invention relates to such a casing for an axial turbomachine compressor. The invention also relates to an axial turbomachine compressor comprising such a housing.
  • the document US Patent 6,406,256 B1 discloses a rotating sealing device between a rotor and an axial turbomachine stator. More specifically, this teaching addresses the problem of compensating for variation of play between the blade tips and an outer shell under operating conditions covering a wide temperature range, that is to say typically for the turbine part of the turbomachine.
  • the sealing device comprises a segmented outer shroud disposed around the ends of the rotor blades. Each segment is held at the wall of the stator housing via fingers which are inclined in an opposite manner and cooperating with corresponding grooves in the housing wall. In case of increase of the temperature of the different segments, these will expand and lengthen slightly. This lengthening will have the effect of moving the fingers away.
  • the game between a row of rotor blades and its outer shell can vary in particular as a function of the speed of rotation and also as a function of a misalignment related to the operating loads (gyroscopic pairs related to a change in attitude of the turbomachine), as well as to the ingestion of foreign matter (as example of birds).
  • a misalignment between the rotor and the stator will change the mechanical play between the blade tips and the ferrule to the point that they will come into contact with the ferrule on a certain sector and the game will increase considerably on the opposite sector.
  • the patent document US 2008/0159850 A1 discloses a rotating sealing device between the rotor and the stator of the turbine part of an axial turbomachine.
  • This teaching relates to the problem of high temperatures at the ferrule and the need for cooling the ferrule.
  • the proposed solution consists essentially of a quick fixing device, facilitating the assembly and disassembly of the ferrule. More specifically, it consists in providing a segmented ferrule wherein each segment is provided with a circumferential rib with a dovetail section and directed radially outwardly of the stator. This rib cooperates with a groove of approximately corresponding section of the stator housing wall.
  • a spring may be optionally disposed in the casing wall so as to exert a force on the segments, this force being directed essentially radially towards the center of rotation of the rotor.
  • the aim of this spring is to apply a contact force between the groove surfaces and the corresponding surfaces of the dovetail section rib to ensure a certain seal.
  • Seals may also be disposed laterally of the rib, between the surface of the segments which is opposed to the inner surface of the shell and the inner surface of the housing wall. These seals are made of solid material because of the high temperatures at which a turbine works.
  • the advantage of this solution is that the different constituent segments of the shell can be easily replaced by a simple translational movement relative to the housing wall. Unlike what figure 3 of this document might suggest, the constituent segments of the ferrule are not suitable for move radially and even less to compensate for any misalignment or variation of play whatsoever.
  • the document patent FR 2,636,373 A1 relates to the problem of differential thermal expansion in a gas turbine, and more specifically to the compensation of variation of clearance between the ends of the rotor blades and the corresponding ferrule.
  • the proposed solution consists of a unitary closed ring-shaped ferrule mounted on a rotor housing via a series of pneumatic bellows compensators. Compressed air is fed into the compensators in order to exert radial forces on the ferrule and thus to control the radial clearance between the ends of the blades and the ferrule.
  • This solution although technically interesting and potentially powerful, is limited to compensate the game evenly over the entire circumference. It is therefore not suitable to compensate for variations in play in case of misalignment between the rotor and the stator.
  • it requires a device for controlling the air pressure, which makes its implementation quite expensive and likely to experience failures.
  • the patent document US 5456576 A discloses a turbomachine casing according to the preamble of claim 1.
  • the patent document DE 10 2008 007 321 A1 also discloses a turbomachine casing, comprising an annular groove in which is maintained a ring of material abradable by means of springs. The groove has a shape enveloping the ring so as to ensure its retention.
  • one of the sources of irreversible opening of the games is the misalignment of the axis of the rotor relative to that of the stator, closing the games on one side and opening the opposite.
  • At least two sources of misalignment are reversible and temporally limited during the mission: it is the misalignment related to the loads of maneuvers (gyroscopic couples related to a variation of attitude of the turbomachine) and that related to the foreign body ingestion (example: birds).
  • the misalignment related to the loads of maneuvers (gyroscopic couples related to a variation of attitude of the turbomachine) and that related to the foreign body ingestion (example: birds).
  • a slight misalignment can appear during the life of the turbomachine. It is caused by an unbalance related to the punctual deterioration, accidental or not of the rotor.
  • a friable wear material thickness (abradable) is irreversibly removed, which leads to an opening of irreversible play and therefore to the equally irreversible reduction of the efficiency of the turbomachine
  • the misalignment of the axis of the rotor relative to that of the stator causes the release of particles constituting the abradable in the primary vein can cause engine damage (including by causing the closure of holes ventilation in the turbine)
  • the object of the invention is to provide a sealing device between a rotor and an axial turbomachine stator that overcomes at least one of the aforementioned problems. More particularly, the invention aims to provide a sealing device between a rotor and an axial turbomachine stator compatible with misalignments between the rotor and the stator. More particularly, the invention aims to provide a solution to the aforementioned problems for an axial turbomachine compressor.
  • the invention relates to a casing for wrapping the ends of a row of blades of an axial turbomachine compressor rotor, comprising: a structural wall; a segmented ferrule for surrounding the row of blades and supported by the wall, the inner surface of the ferrule segments including a friable coating in case of friction with the ends of the blades; remarkable in that it further comprises elastic means disposed between the wall and the segments of the shell so as to allow said segments to move radially in the event of contact with the ends of the rotor blades, particularly in case misalignment of the axis of rotation of the rotor relative to the axis of the housing, the elastic means comprising a plurality of elastic members each having a first end secured by adhesion to the wall and a second end secured by adhesion to a segment of the ferrule.
  • the elastic means support the segments. These are exclusively maintained by the elastic means.
  • the radial movement of the segments can be limited to the vanes by mechanical retaining means.
  • the elastic means comprise one or more elements of deformable material (s) elastically, the elasticity of said element (s) being mainly based on the elasticity of the material (s), the or the materials being preferably elastomer.
  • the elastic means comprise a plurality of circumferentially and / or axially distributed elastic elements.
  • the elastic elements are spaced from each other so as to be able to deform freely.
  • the first ends and / or the second ends are preferably fixed by diffusion and / or gluing.
  • the wall has an internal groove in which the elastic means are at least partially housed.
  • the segments of the ferrule each have ends in a circumferential direction of the ferrule which are bevelled.
  • the contiguous ends of the segments are preferably engaged one to the other and bevelled so that a radial movement of a segment in the direction of an approximation of the casing caused by contact with the blades of the rotor leads to end engagement a similar movement of the next segment in the direction of rotation of the rotor.
  • the ends of the segments have a generally inclined profile between 30 ° and 60 ° relative to a tangent, said profile being preferably straight.
  • the ends in a circumferential direction of each segment of the ferrule are inclined in the same direction.
  • the invention also relates to an axial turbomachine compressor, comprising: a rotor provided with at least one row of vanes; a stator with a casing enclosing the rotor; remarkable in that the housing is in accordance with the invention.
  • a mechanical clearance is provided between the ends of the blades and the ferrule in normal operation when the axis of rotation of the rotor is aligned with the axis of the rotor.
  • the invention has the advantage of allowing radial displacement of the segments and hence compensation in case of misalignment between the rotor and the stator, especially in case of change of attitude of the aircraft or in case of ingestion of a foreign object.
  • the state of the art identified focuses on the thermal problems associated with the turbines and does not address in any case the misalignment problem. The latter can be sudden and then disappear, as for example during a change of attitude.
  • the proposed solution by the segmentation of the ferrule and the maintenance of these segments by elastic means, allows the shell to conform to a misalignment and then return to an initial circular shape centered.
  • blocks made of elastomeric materials has the advantage of the intrinsic damping component of the elastomer.
  • the figure 1 is a diagrammatic sectional view of an axial turbomachine with a double flow, of the airplane engine type, the low-pressure compressor and / or the high-pressure compressor may be equipped with one or more sealing devices according to the invention.
  • the figure 2 is a partial sectional view of the low-pressure compressor of the turbomachine of the figure 2 , the low-pressure compressor being equipped with sealing devices according to the invention.
  • the figure 3 is a sectional view of one of the compressor sealing devices of the figure 2 .
  • the figure 4 is a detail view of an elastic element of the figure 3 this elastic element ensuring the connection between the ferrule and the housing.
  • the figure 5 is a view of the elastic element of the figure 4 in a compressed state.
  • the figure 6 is a sectional view of a compressor sector of the figure 2 , illustrating the sealing device according to the invention.
  • the figure 7 is a sectional view of a sealing device constituting an alternative to that of the figure 3 .
  • the term “external” for the ferrule refers instead to the generally annular fluid vein, “outer ferrule” denoting a ferrule on the side of the outer or outer limit of the vein fluid and “inner ferrule” designating a ferrule on the side of the inner or inner limit of the fluid vein.
  • the axial turbomachine 2 illustrated in FIG. figure 1 is a jet engine type double jet engine for aircraft. It comprises, from upstream to downstream, a low-pressure compressor 4, a high-pressure compressor 6, a combustion chamber 8 and a turbine 10.
  • the low-pressure and high-pressure compressors are not subjected to the high temperatures to which they are subjected. the turbine is subjected. It is therefore possible to use lower melting point materials for the realization of different elements of these compressors.
  • the low-pressure compressor 4 of the figure 1 is illustrated at the figure 2 .
  • the rotor 20 carrying several rows of so-called rotor blades 24, the stator formed of a housing 12 and a wall 16 defining the secondary air flow.
  • the housing 12 supports a series of fixed vanes 26 called statoric.
  • Each circumferential row of stator vanes form a rectifier stage.
  • Each circumferential row of stator vanes form with a circumferential row of rotor blades a compression stage whose role is to increase the pressure of the fluid, in this case air, passing therethrough.
  • An outer shell 22 is disposed facing the outer ends of each row of rotor blades 24 to provide a seal with possibility of contact.
  • the figure 3 is a sectional view of a crankcase section provided with a housing with a sealing device according to the invention.
  • the housing wall 12 has a groove-like housing 32 on its inner surface.
  • This housing contains a series of elastically deformable elements 30 fixed to the surface of the bottom of the groove and fixed to the shell 22. The latter is at least partially housed in the groove. It is maintained and connected to the casing exclusively by the elastically deformable elements 30.
  • the ferrule is constituted by a series of segments 22 distinct so as to be able to move independently in case of misalignment between the rotor and the stator.
  • the elastically deformable elements 30 provide an elastic connection between these segments and the housing so that in case of contact of the inner surface of the shell by the ends of the blades, the segments of the shell subject to this contact can move closer to the the groove of the housing by deformation of the elastically deformable elements 30 under the force of contact blades.
  • FIGS. Figures 4 and 5 The effect of the deformation of the elements 30 is illustrated in FIGS. Figures 4 and 5 .
  • an element 30 can be observed in its normal state where the outer surface of the ferrule segment 22 is at a distance e from the bottom surface of the groove of the housing 12. This distance e corresponds to the height of the element 30.
  • the same element 30 is in a deformed state under the effect of a force generated by the blade tip contact with the inner surface of the ferrule segment 22.
  • the element 30 has a barrel shape with a shorter height e ', corresponding to the new distance between the outer surface of the ferrule segment 22 and the inner surface of the bottom of the groove of the housing 12.
  • the elastically deformable elements 30 are preferably made of elastomeric material. They are preferably glued to the housing and to the shell, respectively. They can also be linked by broadcast. The elastically deformable elements are preferably made of elastically deformable material per se, conferring exclusively their elastic deformability.
  • the elastically deformable elements may also be mechanically deformable elements whose elastic deformability is based on the combination of an elastically deformable material and a particular geometry, such as for example springs.
  • the ferrule segments are preferably connected to the housing by several elastically deformable elements arranged axially.
  • the figure 6 is a sectional view of a portion of the compressor housing of the figure 2 .
  • the bevels are inclined so that the radial displacement of a first segment in the direction of an approximation of the housing leads with it a second segment following it directly in the direction of rotation of the rotor by engagement of the beveled face of the end of the first segment with the beveled face of the contiguous end of the second segment.
  • the inner surface of the ferrule at the junctions thus remains essentially continuous.
  • the ferrule although having at rest a circular shape can thus be deformed by conforming to the misalignment between the rotor and the stator.
  • the beveled ends of the segments are preferably generally planar. They may, however, take various forms capable of ensuring engagement of the segments as described above, namely ensuring a continuity of the inner surface of the shell at the junctions between the segments when the rotating rotor exerts pressure on certain segments. .
  • the ends may for example have a stair-shaped profile in a plane perpendicular to the axis of rotation of the machine.
  • the elastically deformable elements 30 are arranged in a pointwise manner and at a distance from each other in several circumferential rows. The fact of arranging them at a distance from one another axially and / or circumferentially allows the various elements to deform freely and independently. Such an arrangement therefore does not ensure sealing between a point of the fluid stream passing through the compressor which is upstream of the blade row and another point of the fluid stream which is downstream. A minimum clearance between the upstream and downstream edges, respectively, of the ferrule and the edges corresponding to slot 32 (see figure 3 ) is provided to ensure an acceptable seal.
  • a seal 34 is fixed for example by gluing on the edges of the housing 32 corresponding to the upstream and downstream edges of the ferrule 22.
  • these joints can also provide a damping function of the movement of the different segments of the ferrule. the ferrule.
  • the shell has on its inner surface a coating of friable material able to disintegrate during frictional contact with the blades of the rotor.
  • coatings are said to be “abradable” coatings and well known to those skilled in the art.
  • the capacity of the ferrule to move and to comply in particular with a misalignment between the rotor and the stator makes it possible to provide an optionally thinner and / or harder coating.
  • the use of harder materials releases little or no particles likely to damage the engine during the contacts between the "abradable" and the wheel head.
  • the sealing device which is the subject of this document is not required to ensure complete sealing, especially in view of the presence of a mechanical clearance between the ends of the blades and the inner surface of the shell.

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Claims (12)

  1. Gehäuse für die Umhüllung der Enden einer Reihe von Leitschaufeln eines Rotors eines Kompressors einer axialen Turbomaschine, mit:
    einer strukturellen Wandung (12);
    einem segmentierten Außenring (22), der dazu bestimmt ist, um die Reihe von Leitschaufeln zu umgeben und von der Wandung getragen wird, wobei die innere Oberfläche der Segmente des Außenrings eine Beschichtung aufweist, die im Falle der Reibung mit den Enden der Leitschaufeln spröde ist;
    elastischen Mitteln (30), die in der Weise zwischen der Wandung (12) und den Segmenten (22) des Außenrings angeordnet sind, dass sich die genannten Segmente im Falle des Kontakts mit den Enden der Leitschaufeln (24) des Rotors verschieben können, insbesondere im Falle einer Verschiebung der Rotationsachse des Rotors im Verhältnis zur Achse des Gehäuses;
    dadurch gekennzeichnet, dass
    die elastischen Mittel (30) eine Vielzahl von elastischen Elementen beinhalten, die jeweils ein erstes Ende besitzen, das mittels Adhäsion an der Wandung fixiert ist und ein zweites Ende, das mittels Adhäsion an einem Segment des Außenrings fixiert ist.
  2. Gehäuse nach Anspruch 1, dadurch gekennzeichnet, dass die elastischen Mittel (30) die Segmente (22) tragen.
  3. Gehäuse nach einem der Ansprüche 1 und 2, dadurch gekennzeichnet, dass die elastischen Mittel (30) ein oder mehrere Elemente aus elastisch verformbarem Material oder elastisch verformbaren Materialien beinhalten, wobei die Elastizität des genannten Elements oder der genannten Elemente vorwiegend auf der Elastizität des Materials oder der Materialien basiert, wobei das Material oder die Materialien vorzugsweise Elastomer ist/sind.
  4. Gehäuse nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die elastischen Mittel (30) eine Vielzahl von elastischen Elementen beinhalten, die kreisförmig und/oder axial verteilt sind
  5. Gehäuse nach Anspruch 4, dadurch gekennzeichnet, dass die elastischen Mittel (30) in der Weise voneinander entfernt sind, dass sie sich frei verformen können.
  6. Gehäuse nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die ersten Enden und/oder die zweiten Enden mittels Diffusion und/oder Verklebung fixiert werden.
  7. Gehäuse nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass die Wandung (12) eine innere Auskehlung beinhaltet, in der die elastischen Mittel (30) mindestens teilweise untergebracht sind.
  8. Gehäuse nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass die Segmente (22) des Außenrings jeweils Enden in einer kreisförmigen Richtung des Außenrings aufweisen, die abgeschrägt sind.
  9. Gehäuse nach Anspruch 8, dadurch gekennzeichnet, dass die Enden der Segmente ein Profil aufweisen, das im Verhältnis zur Tangente zwischen 30° und 60° geneigt ist, wobei das genannte Profil vorzugsweise gerade ist.
  10. Gehäuse nach einem der Ansprüche 8 und 9, dadurch gekennzeichnet, dass die Enden in einer kreisförmigen Richtung jedes Segments des Außenrings in der gleichen Richtung geneigt sind.
  11. Kompressor einer axialen Turbomaschine, mit:
    einem Rotor (20), der mit mindestens einer Reihe von Leitschaufeln (24) ausgestattet ist;
    einem Stator mit einem Gehäuse (12), das den Rotor umschließt;
    dadurch gekennzeichnet, dass
    das Gehäuse einem der Ansprüche 1 bis 10 entspricht.
  12. Kompressor einer axialen Turbomaschine nach Anspruch 11, dadurch gekennzeichnet, dass im Normalbetrieb ein mechanisches Spiel zwischen den Enden der Leitschaufeln (24) und dem Außenring (22) vorgesehen ist, wenn die Rotationsachse des Rotors mit der Achse des Rotors ausgerichtet ist.
EP11156828.3A 2011-03-03 2011-03-03 Segmentierter Stator-Außenring zum Kompensieren von Rotorverschiebungen gegenüber dem Stator Active EP2495399B1 (de)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP11156828.3A EP2495399B1 (de) 2011-03-03 2011-03-03 Segmentierter Stator-Außenring zum Kompensieren von Rotorverschiebungen gegenüber dem Stator
CA2769815A CA2769815C (en) 2011-03-03 2012-02-28 External segmented shell capable of correcting for rotor misalignment in relation to the stator
US13/407,948 US8939712B2 (en) 2011-03-03 2012-02-29 External segmented shell capable of correcting for rotor misalignment in relation to the stator
RU2012107669A RU2620883C2 (ru) 2011-03-03 2012-03-01 Внешняя сегментированная оболочка, выполненная с возможностью корректирования смещения ротора по отношению к статору
CN201210142291.9A CN102654141B (zh) 2011-03-03 2012-03-05 用于覆盖轴向涡轮机压缩机转子叶片排的端部的外罩

Applications Claiming Priority (1)

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EP11156828.3A EP2495399B1 (de) 2011-03-03 2011-03-03 Segmentierter Stator-Außenring zum Kompensieren von Rotorverschiebungen gegenüber dem Stator

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EP2495399A1 EP2495399A1 (de) 2012-09-05
EP2495399B1 true EP2495399B1 (de) 2016-11-23

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EP11156828.3A Active EP2495399B1 (de) 2011-03-03 2011-03-03 Segmentierter Stator-Außenring zum Kompensieren von Rotorverschiebungen gegenüber dem Stator

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US (1) US8939712B2 (de)
EP (1) EP2495399B1 (de)
CN (1) CN102654141B (de)
CA (1) CA2769815C (de)
RU (1) RU2620883C2 (de)

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FR3025261B1 (fr) * 2014-09-03 2020-02-21 Safran Helicopter Engines Ensemble rotatif muni d'un dispositif de calage
BE1022471B1 (fr) 2014-10-10 2016-04-15 Techspace Aero S.A. Carter externe de compresseur de turbomachine axiale avec joint d'etancheite
FR3036436B1 (fr) * 2015-05-22 2020-01-24 Safran Ceramics Ensemble d'anneau de turbine avec maintien par brides
GB2539217B (en) 2015-06-09 2020-02-12 Rolls Royce Plc Fan casing assembly
EP3196413B1 (de) * 2016-01-19 2018-11-14 MTU Aero Engines GmbH Turbomaschinenstufe
RU2650013C2 (ru) * 2016-02-17 2018-04-06 Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева" Лабиринтное уплотнение-демпфер газовой турбины
CN109923284B (zh) * 2016-11-22 2022-11-11 苏尔寿管理有限公司 包括例如迷宫密封件的上游非接触式部分和下游吊环的轴密封件
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RU2704056C2 (ru) * 2017-06-07 2019-10-23 федеральное государственное автономное образовательное учреждение высшего образования "Самарский национальный исследовательский университет имени академика С.П. Королёва" Турбина двухконтурного газотурбинного двигателя с активным тепловым регулированием радиального зазора в турбине, способ активного теплового регулирования радиального зазора в турбине двухконтурного газотурбинного двигателя
CN112319845A (zh) * 2020-08-04 2021-02-05 杨海成 用于飞机壁板精度自修正的变形监测方法及系统
CN114542512A (zh) * 2022-02-23 2022-05-27 中国航发沈阳发动机研究所 一种处理机匣结构及具有其的压气机

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RU2012107669A (ru) 2013-09-10
RU2620883C2 (ru) 2017-05-30
CN102654141A (zh) 2012-09-05
US20120224953A1 (en) 2012-09-06
US8939712B2 (en) 2015-01-27
CA2769815C (en) 2017-11-28
EP2495399A1 (de) 2012-09-05
CA2769815A1 (en) 2012-09-03

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