EP3553322A1 - Einheit für ein axiales turbotriebwerk mit einem zweiteiligen aussenring - Google Patents

Einheit für ein axiales turbotriebwerk mit einem zweiteiligen aussenring Download PDF

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Publication number
EP3553322A1
EP3553322A1 EP19166505.8A EP19166505A EP3553322A1 EP 3553322 A1 EP3553322 A1 EP 3553322A1 EP 19166505 A EP19166505 A EP 19166505A EP 3553322 A1 EP3553322 A1 EP 3553322A1
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EP
European Patent Office
Prior art keywords
sections
orifices
section
assembly according
flanges
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
EP19166505.8A
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English (en)
French (fr)
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EP3553322B1 (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
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Publication of EP3553322A1 publication Critical patent/EP3553322A1/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
    • 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
    • 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
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters
    • 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

Definitions

  • the invention relates to the field of axial turbomachines and more particularly aircraft turbojets. More specifically, the invention relates to the construction of an outer ring of a compressor provided with variable-pitch stator vanes. The invention also relates to a compressor provided with such a ferrule, the assembly method of such a compressor and a blade for such a compressor.
  • the document FR 2 565 297 A1 discloses a gas turbine compressor stator.
  • the stator vanes are orientable about their axis by means of a connecting rod which is screwed to each blade head.
  • Housings are provided on the ferrule to receive the heads of the blades with a socket and a flange that closes the housing to enclose the blade heads in their homes.
  • the bushing and the heads of the vanes are recessed to cooperate with a bolt to maintain radially the blade in its housing.
  • the object of the invention is to solve at least one of the problems posed by the prior art.
  • the invention also aims to provide a simpler and more compact design, allowing easier assembly of blades with variable orientation.
  • the invention also aims to propose a lightweight, economical, reliable solution, easy to produce, convenient maintenance, and easy inspection.
  • the subject of the invention is an assembly according to claim 1 and an assembly method according to claim 12.
  • the half-orifices and the flanges of the sections are arranged to allow the assembling of the sections to one another via the flanges, the half-orifices of the sections being brought into view to form cylindrical orifices when the two sections are assembled.
  • the invention also relates to a method of assembling an assembly as described above, the method comprising the following steps: the assembly of an operating rod at the head of each blade, or the one-piece manufacture a connecting rod with dawn; the introduction of blade journals in the half-orifices of one of the sections, preferably the downstream section; the introduction of the other sections, thus enclosing the trunnions in the orifices thus formed; fixing, preferably by screwing, the flanges of the two sections together.
  • the method comprises a step of fixing the synchronization ring of the connecting rods, preferably on the downstream section, and preferably before mounting the blades.
  • the method comprises a step of connecting the connecting rods to the synchronizing ring takes place before the sections are positioned vis-à-vis one another.
  • the ring can be attached to the connecting rods after assembly of the two sections.
  • each object of the invention is also applicable to the other objects of the invention.
  • Each object of the invention is combinable with the other objects, and the objects of the invention are also combinable with the embodiments of the description, which in addition are combinable with each other, according to all possible technical combinations, unless otherwise not explicitly mentioned.
  • the invention proposes a specific geometry that allows to assemble the blades with variable orientation without the need to mount each of the rods once the dawn mounted.
  • the design proposed in the present invention generates substantial savings in mounting time.
  • this design allows the mounting of a one-piece synchronization ring (a 360 ° ring) more compact.
  • the terms “internal” and “external” 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.
  • a commonly designated fan or blower inlet fan 16 is coupled to the rotor 12 via a gear train 13, and generates a flow of air which splits into a primary stream 18 passing through the various aforementioned levels of the turbomachine, and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the turbine outlet.
  • the secondary flow can be accelerated so as to generate a thrust reaction necessary for the flight of an aircraft.
  • the primary 18 and secondary 20 streams are coaxial annular flows and fitted into one another.
  • the figure 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 .
  • the flow can be transonic.
  • the compressor may be a low-pressure compressor 4.
  • the rotor 12 comprises several rows of rotor vanes 24, in this case three. It may be a bladed monobloc drum, or include dovetail blades.
  • the low-pressure compressor 4 comprises a plurality of rectifiers, in this case four, which each contain a row of stator vanes 26. Some stator vanes may be adjustable in orientation, also called variable pitch vanes.
  • the rectifiers are associated with the fan 16 or a row of rotor blades to straighten the air flow, so as to convert the speed of the flow pressure, including static pressure.
  • a defrosting spout 22 can be mounted on a housing that supports a row of stator inlet vanes 28.
  • the stator vanes 26 extend essentially radially from an outer shell 30 to internal rings 32.
  • the vanes 26 may be attached to the outer shell 30 by means of pins.
  • the ferrule 30 defines an inner surface 29 which guides the flow of gas. According to the invention, the ferrule 30 is composed of several axial sections.
  • the blades 26 comprise a cylindrical pin 34 which is received in a radial orifice of the outer ring 30.
  • a connecting rod 36 integral with the pin and pivoting about the axis of the pin 34 makes it possible to maneuver the pivoting of the blade.
  • Actuating means 40 of the connecting rod 36 are schematically shown and will be described later.
  • the Figures 3 and 4 illustrate a known example of connection between the head of a blade 26 and the outer shell 30.
  • the blade 26 comprises a blade 42 having a leading edge 44 and a trailing edge 46.
  • the head of the blade 26 can include a shoulder 48 for centering and positioning the blade 26 in the ferrule 30 and a groove for receiving a seal.
  • the connecting rod 36 for actuating the pivoting of the blade is fixed by a nut 50 on a threaded portion 52 of the head of the blade.
  • a centering chamfer 54 may be provided at the end of the journal 34.
  • the head of the dawn is received at the right of an extra thickness of the ferrule 30, which may be in the form of a boss 33.
  • the connecting rod 36 comprises a conical orifice 60 corresponding to the chamfer 54, a body 62 and a tab 64.
  • the orifice 60 may comprise a groove 66 to receive a key and thus rotate the blade 26 and the rod 36.
  • the rod 36 also comprises a hole 68 to be connected to an actuating member (described in figure 10 ).
  • the outer shell 30 has an orifice receiving the pin 34. The pin 34 is inserted into the hole from the bottom (in the direction of the figure 3 ), then the connecting rod 36 is screwed to the thread 52.
  • FIGS. 5 to 7 show a first embodiment of the connection between the blade 26 and the outer shell 30 according to the invention
  • the figure 5 shows a partial top view of the assembly according to the invention.
  • Each of the sections comprises a tubular wall 131, 231 defining an inner guide surface 129, 229 and an annular series of half-orifices 132, 232, formed in half-bosses 133, 233.
  • the two half-orifices 132, 232 form the orifice 31 which receives the head of the dawn.
  • the two sections 130, 230 are assembled via screwed elements which maintain two flanges 134, 234 adjacent together.
  • the flanges 134, 234 may extend from a boss to the circumferentially adjacent boss.
  • the figure 5 represents only one orifice.
  • the figure 6 is a section in the plane VI: VI defined on the figure 5 .
  • the shell comprises two adjacent axial sections 130, 230.
  • Each of the two sections comprises a tubular wall 131, 231 and an annular row of half-orifices 132, 232 formed in the bosses 133, 233.
  • the rod 36 of this first embodiment is welded to the head of the blade. This is done before mounting the dawn in the shell.
  • the pin 34 can be positioned in a half-orifice 132, 232 of one of the sections despite the size of the rod which is greater than the diameter of the orifice 31, then the other section is fixed to grip the pin 34 in the orifice 31.
  • the rod 36 may have a shape similar to that of the figure 4 , potentially without keyway, become unnecessary due to welding.
  • the figure 7 shows a view according to plane VII: VII defined on the figure 5 .
  • This view shows the assembly of the two flanges 134, 234 by means of a bolt 35.
  • the flanges 134, 234 have through holes 135, 235 for assembling the ferrule sections by screwed elements 35.
  • Back plan on the figure 7 we distinguish bosses 133, 233.
  • the figure 8 shows another embodiment.
  • the connecting rod 36 is here not welded to the pin 34 but the entire blade (blade, pin, connecting rod) is monobloc, made in one piece.
  • the connecting rod can be forged or molded with the rest of the dawn. The functional surfaces (trunnion, extrados / intrados) are then machined.
  • it is the two-part design of the orifice of the ferrule which makes it possible to provide such a one-piece blade with its connecting rod.
  • the figure 9 is a partial isometric view of the ferrule 30.
  • the bosses 133, 233 and flanges 134, 234 and their assembly holes (only the holes 235 of the downstream portion 230 are visible).
  • the flanges can completely connect each of the bosses 133, 233 to the adjacent boss.
  • the upstream section 130 comprises a flange 136 which makes it possible to connect the shell to the nozzle of the compressor.
  • the downstream section 230 comprises a bearing surface, preferably cylindrical 237 for guiding the pads of the synchronizing ring 72 (see figure 10 ).
  • the flanges 134, 234 rise above the tubular wall 131, 231 of a height equivalent to that of the bosses 133, 233. Alternatively, their respective elevations may differ.
  • the sections may have axial centering pins, particularly at the flanges.
  • axial pins provided in one or more of the flanges 134 can enter corresponding axial orifices in one or more of the flanges 234.
  • the figure 10 represents a section of the compressor.
  • the ferrule composed of the two sections 130, 230 is fixed to the support housing of the defrosting spout which carries the stator inlet vanes 28 via the upstream flange 136.
  • a downstream flange 236 may be provided on the downstream section.
  • the actuating mechanism 40 of the pivoting blade comprises a pin 70 which is received in a distal orifice of the rod 36 (equivalent to the orifice 68 of the connecting rod of the figure 4 ).
  • the pin 70 passes through a synchronizing ring 72 and ends with a shoe 74.
  • the pad 74 rests on a cylindrical surface 237 of the downstream section.
  • the cylindrical surface 237 ends upstream by a projection which limits the movement of the pad 74 axially.
  • the projection and the cylindrical surface 237 form a seat for the shoe 74.
  • the synchronizing ring 72 cooperates with as many pins 70 as rods 36 distributed annularly.
  • the ring 72 can be pivotally actuated about the axis 14 by appropriate means such as for example a toothed wheel co-operating with a rack provided on the ring 72.
  • the pivoting of the ring 72 causes a corresponding displacement of the pins 70 along the surface 237 and they thus rotate the rod 36 and the blade 26 about the axis 38.
  • the general shape of the downstream section allows the mounting of the synchronizing ring and pins.
  • the flange 236 has an outer diameter which is substantially smaller than the inner diameter of the ring 72, thus allowing the pins with their pads to be inserted into the ring before the ring and pin assembly is slid axially towards the ring. upstream to be mounted on the downstream section.
  • the journals 34 of the vanes are inserted into the half-orifices 232, then the upstream section is brought to enclose the journals 34 in the orifices 31 thus formed.
  • the flanges 134, 234 are then aimed at each other.
  • the actuating pins 70 carried by the synchronizing ring 72 can be assembled to the connecting rods 36.
  • the fixing of the pins 70 to the rods 36 can take place before the upstream section 130 is positioned in contact with the downstream section 230.
  • the ring 72 can be inserted around the downstream section 230 before the vanes 26 are brought into the half-orifices 232.
  • the embodiment described here has two sections 130 and 230 but one or more additional sections may be provided and assembled in the same way, each of the sections having an annular row of half-holes facing the half-orifices of the adjacent section to forming orifices receiving blade heads which may or may not be of variable orientation.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP19166505.8A 2018-04-10 2019-04-01 Einheit für ein axiales turbotriebwerk mit einem zweiteiligen aussenring Active EP3553322B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
BE2018/5242A BE1026199B1 (fr) 2018-04-10 2018-04-10 Virole exterieure en deux parties

Publications (2)

Publication Number Publication Date
EP3553322A1 true EP3553322A1 (de) 2019-10-16
EP3553322B1 EP3553322B1 (de) 2023-05-31

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EP19166505.8A Active EP3553322B1 (de) 2018-04-10 2019-04-01 Einheit für ein axiales turbotriebwerk mit einem zweiteiligen aussenring

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US (1) US20190309650A1 (de)
EP (1) EP3553322B1 (de)
BE (1) BE1026199B1 (de)

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3314654A (en) 1965-07-30 1967-04-18 Gen Electric Variable area turbine nozzle for axial flow gas turbine engines
US3558237A (en) 1969-06-25 1971-01-26 Gen Motors Corp Variable turbine nozzles
FR2565297A1 (fr) 1984-06-04 1985-12-06 Gen Electric Moyens de retenue d'aubes fixes
FR2644525A1 (fr) * 1989-03-15 1990-09-21 Snecma Systeme de retention d'aubes de stator a calage variable
US5380152A (en) * 1992-11-03 1995-01-10 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Adjustable guide vane for turbines, compressors, or the like
EP2006495A1 (de) 2007-06-20 2008-12-24 ABB Turbo Systems AG Positionsregelung für Vordrall-Leitvorrichtung
US20120076658A1 (en) * 2010-09-28 2012-03-29 General Electric Company Attachment stud for a variable vane assembly of a turbine compressor
US20160341068A1 (en) 2014-10-13 2016-11-24 United Technologies Corporation Fixed-variable vane with potting in gap
EP3290657A1 (de) * 2016-08-30 2018-03-07 Safran Aero Boosters SA Stator mit verstellbaren schaufeln für den kompressor eines axialen gasturbinenmotors

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE1026411B1 (fr) * 2018-06-21 2020-01-30 Safran Aero Boosters Sa Virole extérieure de turbomachine

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3314654A (en) 1965-07-30 1967-04-18 Gen Electric Variable area turbine nozzle for axial flow gas turbine engines
US3558237A (en) 1969-06-25 1971-01-26 Gen Motors Corp Variable turbine nozzles
FR2565297A1 (fr) 1984-06-04 1985-12-06 Gen Electric Moyens de retenue d'aubes fixes
FR2644525A1 (fr) * 1989-03-15 1990-09-21 Snecma Systeme de retention d'aubes de stator a calage variable
US5380152A (en) * 1992-11-03 1995-01-10 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Adjustable guide vane for turbines, compressors, or the like
EP2006495A1 (de) 2007-06-20 2008-12-24 ABB Turbo Systems AG Positionsregelung für Vordrall-Leitvorrichtung
US20120076658A1 (en) * 2010-09-28 2012-03-29 General Electric Company Attachment stud for a variable vane assembly of a turbine compressor
US20160341068A1 (en) 2014-10-13 2016-11-24 United Technologies Corporation Fixed-variable vane with potting in gap
EP3290657A1 (de) * 2016-08-30 2018-03-07 Safran Aero Boosters SA Stator mit verstellbaren schaufeln für den kompressor eines axialen gasturbinenmotors

Also Published As

Publication number Publication date
BE1026199A1 (fr) 2019-11-05
BE1026199B1 (fr) 2019-11-12
EP3553322B1 (de) 2023-05-31
US20190309650A1 (en) 2019-10-10

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