EP3290656A1 - Innenring und ausrichtbare leitschaufel eines kompressors eines axialen turbotriebwerks und herstellungsverfahren - Google Patents

Innenring und ausrichtbare leitschaufel eines kompressors eines axialen turbotriebwerks und herstellungsverfahren Download PDF

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Publication number
EP3290656A1
EP3290656A1 EP17186472.1A EP17186472A EP3290656A1 EP 3290656 A1 EP3290656 A1 EP 3290656A1 EP 17186472 A EP17186472 A EP 17186472A EP 3290656 A1 EP3290656 A1 EP 3290656A1
Authority
EP
European Patent Office
Prior art keywords
bearing
assembly
ferrule
turbomachine
pocket
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP17186472.1A
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English (en)
French (fr)
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EP3290656B1 (de
Inventor
Morgan Vyvey
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
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
Publication of EP3290656A1 publication Critical patent/EP3290656A1/de
Application granted granted Critical
Publication of EP3290656B1 publication Critical patent/EP3290656B1/de
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Classifications

    • 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
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/056—Bearings
    • 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
    • F04D29/08—Sealings
    • F04D29/083—Sealings especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/10—Stators
    • F05B2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2240/50—Bearings
    • 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
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the invention relates to the field of steerable blades axial turbomachine. More specifically, the invention relates to the pivot connection between an inner shell and a steerable rotor blade. The invention also relates to an axial turbomachine, in particular an aircraft turbojet engine or an aircraft turboprop engine.
  • vanes can equip a stator housing turbojet compressor.
  • Such vanes may pivot during engine operation. Their arched blades tilt relative to the primary flow through which they adapt their action according to engine speed and flight conditions. The operating range and efficiency are thus extended.
  • the inner shell which is suspended from the steerable vanes can be split into two axial parts. These two parts can be assembled to enclose the rotating bearings around the inner journals of the steerable vanes.
  • the document FR 3,009,335 A1 discloses a rectifier blade guide device with a variable turbine engine timing angle.
  • the device comprises a casing from which radially a row of adjustable vanes.
  • An inner ferrule is attached to these adjustable vanes.
  • the inner ferrule is suspended from the adjustable vanes by means of cylindrical bushings shod around the internal trunnions of the adjustable vanes.
  • the assembly of the inner ferrule is carried out by axial approximation of its axial portions, while enclosing the cylindrical bushings.
  • this assembly operation is complex as the temporary retention of the sleeves in a ferrule portion is unstable.
  • the object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the invention aims to improve the maintenance of a bearing articulating a steerable blade relative to a ferrule. The invention also aims to provide a simple solution, resistant, lightweight, economical, reliable, easy to produce, convenient maintenance, waterproof, and easy inspection.
  • the subject of the invention is an assembly for an axial turbomachine stator, in particular for a turbomachine compressor, the assembly comprising: a shell, optionally an inner shell, which is divided axially into two parts; a pocket formed in the shell; a bearing disposed in the pocket; and a steerable blade pivotally mounted in the bearing about a pivot axis; remarkable in that the shell comprises an axial separation interface parts which is axially offset from the pivot axis of the steerable blade.
  • the bearing ensures a seal between the steerable blade and the inner shell, optionally the bearing completely fills the pocket.
  • the separation interface defines axially the bearing, one of the parts possibly comprising a flat circular surface in contact with the bearing.
  • the assembly comprises an outer monoblock shell to which the steerable blade is mounted.
  • the bearing is longer axially than broad depending on the circumference, and / or wider than radially thick.
  • the bag comprises a sealed bottom, possibly in contact with the bearing.
  • the bearing comprises two generally parallel lateral faces, said faces possibly extending over most of the axial length of said bearing.
  • the bag is predominantly or totally formed in one of the parts, possibly in the upstream part.
  • the downstream part comprises an annular seal, possibly with an abradable material, which is separated axially and / or radially from the bearing.
  • the bearing comprises an outer face with a flat and circular surface.
  • the bearing comprises a through hole and axially eccentric.
  • the bearing comprises rotational locking means, in particular a planar face cooperating with a pocket partition.
  • the bearing comprises a portion in radial excess partially forming the outer surface of the ferrule.
  • the steerable blade comprises a disk with a contour, the extra-thick portion axially separating said disk from one of the parts.
  • the bearing comprises a semicircular axial portion.
  • the blade comprises an external pin and / or an internal pin cooperating with the bearing.
  • the journal in particular the journal, is remote from the axial separation interface.
  • the axial separation interface is a plane, and / or circularly and axially cut the ferrule.
  • the bearing surrounds the inner pin and / or is in one piece.
  • the bearing completely fills the pocket between the blade and the ferrule.
  • At least one or each part of the ferrule is in one piece.
  • the inner ring or one of the parts has a general profile of revolution which is longer, or at least twice as long, or at least three times longer axially than radially thick.
  • the pivot axis of the steerable blade is inside one of the parts, and / or at a distance axially from the other of the two parts.
  • the pivot axis of the steerable blade is inside the annular envelope of one of the parts, and / or at an axial distance from the annular envelope of the other of the two parts.
  • the sealed bottom marries the bearing over its entire axial length.
  • the depth of the pocket increases upstream, particularly at the level of the extra thickness of the bearing.
  • At least one of the parts comprises axial partition walls of the pockets.
  • the invention also relates to an assembly for axial turbomachine stator, the assembly comprising: a ferrule which is divided axially into two parts via an axial separation interface; a pocket formed in the shell; a bearing disposed in the pocket; and a steerable blade pivotally mounted in the bearing about a pivot axis; remarkable in that the pocket comprises a sealed bottom, possibly in contact with the bearing.
  • the invention also relates to an assembly for axial turbomachine stator, the assembly comprising: a ferrule which is divided axially into two parts via an axial separation interface and which comprises an annular surface for guiding an annular flow of the turbomachine; a formed pocket in the ferrule; a bearing disposed in the pocket; and a steerable blade pivotally mounted in the bearing about a pivot axis; remarkable in that the bearing comprises a portion in radial excess partially forming the guide surface of the ferrule.
  • the invention also relates to a turbomachine comprising a stator assembly, characterized in that the assembly is in accordance with the invention, preferably the turbomachine comprises an intermediate casing with an internal hub.
  • the intermediate casing comprises a downstream face; the assembly being mounted on said downstream face.
  • one of the parts of the ferrule is in contact with the inner hub, and / or one of the parts of the ferrule is axially spaced from the inner hub.
  • the subject of the invention is also a method of assembling an assembly for a turbomachine stator, the assembly comprising an outer ferrule, an inner ferrule with a pocket occupied by a rotating bearing in connection with an orientable blade, the inner ferrule being axially split into a first portion and a second portion, the method comprising the steps of: (b) placing a first ferrule portion; (c) radial introduction of the steerable blade into a support; (d) radial engagement of the bearing within the steerable blade; remarkable in that the bearing comprises an axial guide face, and in that the method further comprises a step (e) mounting the second portion by sliding against the axial guide face of the bearing; the assembly being optionally in accordance with the invention.
  • the bearing slides radially against the first part, in particular against the downstream part.
  • step (b) during step (b) implementation of a first part, said part cooperates with a sealing device of the rotor of the turbomachine.
  • each object of the invention is also applicable to the other objects of the invention.
  • each object of the invention is combinable with other objects.
  • the Objects of the invention are also combinable with the embodiments of the description, which in addition are combinable with each other.
  • the invention optimizes the maintenance of the bearings due to their asymmetry which has repercussions on the parts of the shell. Staggering the interface between the parts also makes it possible to offer more space for use of a temporary socket holding tool. In addition, the outline of the bearings allows them to better gain their place in the pockets. The stator is more economical to produce.
  • the configuration of the ferrule parts like the filling character of the bearings; increases the sealing and therefore the efficiency of the turbomachine.
  • the closed form of the bottom of the pockets further increases the seal, while increasing the rigidity of the corresponding part.
  • inner and outer refer to a positioning relative to the axis of rotation of an axial turbomachine.
  • the axial direction corresponds to the direction along the axis of rotation of the turbomachine.
  • the radial direction is perpendicular to the axis of rotation. Upstream and downstream are in reference to the main flow direction of the flow in the turbomachine.
  • the figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine.
  • the turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator vanes. The rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until it reaches the combustion chamber 8.
  • An inlet fan commonly referred to as a fan, or blower, 16 is coupled to the rotor 12 and generates a flow of air which splits into a primary flow 18 passing through the various levels mentioned above of the turbomachine, and a secondary flow 19 passing through a annular duct (partially shown) by generating a thrust useful to the propulsion of an aircraft.
  • the figure 2 is a sectional view of a compressor portion of an axial turbomachine such as that of the figure 1 .
  • the compressor may be a low-pressure compressor 4.
  • the compressor comprises a stator 20 with an integral outer shell 22 which can form the outer casing of the compressor.
  • the outer shell 22 is in one piece. It describes a closed loop. It has a continuity of circular material and / or a circular homogeneity. It can be monobloc along its entire length. It can include a portion of matter.
  • the rotor 12 may comprise several rows of rotor blades 24, for example two or three or more rows of rotor (only one visible). Despite the rotation of the rotor 12, the inclination in the space of the ropes of the rotor blades 24 remains invariant with respect to the axis of rotation 14.
  • the rotor blades 24 can form a one-piece disc; that is to say that they are indissociable from their support rim 25. Such an arrangement is also known by the term "blisk”.
  • the compressor 4 comprises several rectifiers, for example at least two, or at least three or at least four rectifiers.
  • Each rectifier comprises an annular row of stator vanes 26. These vanes are stator in the sense that they are mounted on the stator 20 and therefore remain in contact with the latter.
  • the rectifiers are associated with the fan or with a row of rotor vanes 24 to straighten their air flows, so as to convert the speed of the flow into static pressure.
  • the stator vanes 26 comprise pilot-driven stator vanes 26. These orientable vanes 26 extend radially inwardly of the outer ferrule 22 and describe an annular array. These steerable vanes 26 are also called variable-pitch vanes, or according to the acronym "VSV” for "Variable Stator Vane”. Their particularity is that they can pivot on themselves, so that the inclination of their ropes can vary with respect to the axis of rotation 14 of the compressor 4, and during its operation.
  • the steerable vanes 26 can pivot relative to the flow 18, so that they cover more or less fluid vein with their blades. They may further intercept the primary stream 18. The circumferential width they occupy may vary. Their leading edge and their trailing edge can move toward or away from the blades of the same row. Being more or less inclined relative to the general direction of flow, they deviate more or less the primary flow 18 to modulate the flow recovery they provide. Thus, the turbomachine and the compressor can follow different yield curves during operation.
  • the stator vanes may comprise other annular rows of blades 28; these other blades being optionally fixed orientation or controlled orientation.
  • the stator 20 of the compressor 4 comprises an inner ferrule 30 suspended at the inner ends of the steerable vanes 26, but retaining the pivoting nature of the steerable vanes 26.
  • the inner ferrule 30 is equipped with rotating bearings 32 which are mounted around internal journals 34 of the steerable vanes 26. Radially opposite, the steerable vanes 26 have external journals 36 engaged in orifices 38, possibly formed through bosses 40.
  • the pins (34; 36) can form cylindrical rods, and can be integral with their blade.
  • the steerable blade control system is well known to those skilled in the art and will not be detailed further.
  • the stator 20 comprises an intermediate casing 42, forming part of the bearing structure of the turbomachine.
  • This intermediate casing 42 may receive a separation spout (not shown).
  • the intermediate casing 42 may comprise an outer portion 44, casing arms 46 forming supports passing through the primary stream 18, and an inner hub 48 which can join the inner shell 30.
  • the outer shell 22 may comprise an annular wall 50 and an upstream flange 52 fixed to the outer portion 44 of the intermediate casing 42.
  • the wall 50 may be integral. It may extend axially along the blades 26 and optionally other vanes.
  • the inner surface 56 of the outer shell 22 has an internal diameter which decreases downstream and which matches the outer ends of the rotor blades 24. This configuration therefore requires placing the rotor blades 24 in the external ferrule 22 before mounting the steerable vanes 26 and their inner ferrule 30. The opposite would not be physically possible because of the one-piece nature of the outer ferrule 22.
  • the inner ferrule 30 is split. It is divided axially into an upstream portion 60 and a downstream portion 62. These portions may each form a closed loop. At least one or each portion (60; 62) is integral, i.e. present (s) a continuity of circular material. Alternatively, one of them is angularly segmented. However, a one-piece configuration improves the rigidity and retention of the inner shell 30 via the internal pins 34, which form pivot links; a mechanical connection with a single degree of freedom.
  • the figure 3 sketch a plan view of the inner ferrule 30 of the figure 2 the bearings are not shown for the sake of clarity.
  • the axis of rotation 14 is drawn.
  • the upstream portion 60 and the downstream portion 62 are shown from the outside.
  • the upstream portion 60 has an annular row of pockets 64, four of which are shown.
  • the pockets 64 each have a bottom 66 closed to seal against the downstream portion 62. They can end against the axial separation interface 68 of the axial portions (60; 62).
  • the axial separation interface 68 may be a plane perpendicular to the axis of rotation 14, or be substantially conical.
  • the pockets 66 have forms of the letter "U" returned, the bearings being of complementary shape to that of these pockets 64. These pockets 64 are separated by bulkheads 69.
  • the figure 4 illustrates the bearing 32 in an isometric view, the bearing may correspond to the bearing shown in relation to the figures 2 and 3 .
  • the bearing 32 is monobloc. It has a hemicylindrical upstream portion, and a rectangular downstream portion having lateral faces 70 of axial guidance. These faces 70 may be parallel.
  • An orifice 72 for receiving the inner pin of the steerable blade is at the interface of the portions.
  • a disk-shaped flat surface 74 surrounds the orifice 72.
  • the bearing has a radial excess thickness 76, which is in elevation relative to the plane surface 74. The extra thickness 76 can join an axial end of the bearing, for example its downstream facet 78 plane which allows blocking in rotation against the downstream part of the ferrule.
  • the figure 5 corresponds to an enlargement of a zone delimited in figure 2 .
  • the section of the inner ring 30 at the level of an orientable blade 26 and its bearing 32 coincides with the pivot axis 80 of the internal pin 34.
  • the pivot axis 80 is remote from the axial interface 68 between the portions (60; 62). This makes it possible to better maintain the bearing 32 in one of the parts; in this case in the upstream part 60.
  • the remote aspect can be measured in the material of the ferrule 30.
  • the extra thickness 76 is flush with the outside of the ferrule 30.
  • the excess thickness 76 may partially form the outer surface 82 of the inner ferrule 30; outer surface 82 which delimits and guide the primary flow 18 in the turbomachine.
  • This extra thickness 76 makes it possible to fill a space of the ferrule 30 while accommodating its compactness.
  • the profile of the inner shell may have a length greater than or equal to twice its radial thickness.
  • the excess thickness 76 can form a separation between the downstream portion 62 and the platinum disk 84 of the steerable blade 26. In particular, it can slide against the cylindrical contour of the disk 84.
  • the rotor 12 cooperates sealingly with the downstream part 62, possibly at an abradable seal 86.
  • the bearing 32 does not overlap the annular seal 86 since the interface 68 separates them.
  • the figure 6 is a diagram of a method of assembling a turbomachine.
  • the entities of the turbomachine can correspond to those described in connection with the Figures 1 to 5 .
  • the first portion in place is in contact with the rotor, for example around and / or in contact with a rotor seal.
  • This seal can be a game of wipers.
  • the seal may center the downstream portion relative to the rotor.
  • the other part can be free of joint.
  • step (d) engagement 106 the bearing slides radially against the first part, in particular against the downstream part, and is shod around the inner pin of the steerable blade.
  • step (e) mounting 108 the upstream portion is translated axially while being guided by the guide faces. Since the bearings can rotate relative to the journals, they rotate so as to be in their pocket, which simplifies the approach of the upstream part.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP17186472.1A 2016-08-30 2017-08-16 Innenring und ausrichtbare leitschaufel eines kompressors eines axialen turbotriebwerks und herstellungsverfahren Active EP3290656B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
BE2016/5663A BE1024524B1 (fr) 2016-08-30 2016-08-30 Virole interne et aube orientable de compresseur de turbomachine axiale

Publications (2)

Publication Number Publication Date
EP3290656A1 true EP3290656A1 (de) 2018-03-07
EP3290656B1 EP3290656B1 (de) 2021-09-29

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP17186472.1A Active EP3290656B1 (de) 2016-08-30 2017-08-16 Innenring und ausrichtbare leitschaufel eines kompressors eines axialen turbotriebwerks und herstellungsverfahren

Country Status (5)

Country Link
US (1) US11512713B2 (de)
EP (1) EP3290656B1 (de)
CN (1) CN107795525B (de)
BE (1) BE1024524B1 (de)
CA (1) CA2976930A1 (de)

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Publication number Priority date Publication date Assignee Title
BE1024605B1 (fr) * 2016-09-27 2018-04-26 Safran Aero Boosters S.A. Carter avec bras aspirant pour turbomachine axiale
US11028709B2 (en) * 2018-09-18 2021-06-08 General Electric Company Airfoil shroud assembly using tenon with externally threaded stud and nut
WO2020202174A1 (en) * 2019-04-01 2020-10-08 Dasari Dileep Systems and methods for increasing the efficiency of axial ducted fans
CN110617117B (zh) * 2019-08-02 2022-04-08 中国航发贵阳发动机设计研究所 一种涡轮导向器喉道面积调节方法
DE102021129534A1 (de) 2021-11-12 2023-05-17 MTU Aero Engines AG Leitschaufelanordnung einer Strömungsmaschine und Verfahren zur Montage einer Leitschaufelanordnung

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GB749577A (en) * 1952-07-10 1956-05-30 Havilland Engine Co Ltd Improvements in or relating to blade ring assemblies for axial flow compressors or turbines
EP0298894A1 (de) * 1987-07-08 1989-01-11 United Technologies Corporation Kompressor mit geteiltem Gehäuse
US4834613A (en) * 1988-02-26 1989-05-30 United Technologies Corporation Radially constrained variable vane shroud
FR2824593A1 (fr) * 2001-05-10 2002-11-15 Snecma Moteurs Agencement de support de pivots d'aubes de stator a deux parties d'anneau liees par un element interne
EP1967718A2 (de) * 2007-03-06 2008-09-10 United Technologies Corporation Deckband für eine verstellbare Leitschaufelanordnung einer Turbomaschine
US20120082545A1 (en) * 2010-09-30 2012-04-05 Brian Peck Seal arrangement for variable vane
FR3009335A1 (fr) 2013-07-30 2015-02-06 Snecma Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine

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US5639212A (en) * 1996-03-29 1997-06-17 General Electric Company Cavity sealed compressor
DE102006024085B4 (de) * 2006-05-23 2020-04-16 MTU Aero Engines AG Turboverdichter in Axialbauweise
US8500394B2 (en) * 2008-02-20 2013-08-06 United Technologies Corporation Single channel inner diameter shroud with lightweight inner core
JP5747703B2 (ja) * 2011-07-13 2015-07-15 株式会社Ihi ターボ圧縮機
US9932988B2 (en) * 2013-02-15 2018-04-03 United Technologies Corporation Bushing arranged between a body and a shaft, and connected to the shaft
JP5736443B1 (ja) * 2013-12-19 2015-06-17 川崎重工業株式会社 可変静翼機構

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB749577A (en) * 1952-07-10 1956-05-30 Havilland Engine Co Ltd Improvements in or relating to blade ring assemblies for axial flow compressors or turbines
EP0298894A1 (de) * 1987-07-08 1989-01-11 United Technologies Corporation Kompressor mit geteiltem Gehäuse
US4834613A (en) * 1988-02-26 1989-05-30 United Technologies Corporation Radially constrained variable vane shroud
FR2824593A1 (fr) * 2001-05-10 2002-11-15 Snecma Moteurs Agencement de support de pivots d'aubes de stator a deux parties d'anneau liees par un element interne
EP1967718A2 (de) * 2007-03-06 2008-09-10 United Technologies Corporation Deckband für eine verstellbare Leitschaufelanordnung einer Turbomaschine
US20120082545A1 (en) * 2010-09-30 2012-04-05 Brian Peck Seal arrangement for variable vane
EP2622178A2 (de) * 2010-09-30 2013-08-07 Rolls-Royce North American Technologies, Inc. Dichtungsanordnung für eine verstellbare leitschaufel
FR3009335A1 (fr) 2013-07-30 2015-02-06 Snecma Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine

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Publication number Publication date
CA2976930A1 (en) 2018-02-28
EP3290656B1 (de) 2021-09-29
BE1024524B1 (fr) 2018-03-26
US11512713B2 (en) 2022-11-29
CN107795525A (zh) 2018-03-13
CN107795525B (zh) 2022-01-04
BE1024524A1 (fr) 2018-03-23
US20180058471A1 (en) 2018-03-01

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