EP3553322B1 - Einheit für ein axiales turbotriebwerk mit einem zweiteiligen aussenring - Google Patents

Einheit für ein axiales turbotriebwerk mit einem zweiteiligen aussenring Download PDF

Info

Publication number
EP3553322B1
EP3553322B1 EP19166505.8A EP19166505A EP3553322B1 EP 3553322 B1 EP3553322 B1 EP 3553322B1 EP 19166505 A EP19166505 A EP 19166505A EP 3553322 B1 EP3553322 B1 EP 3553322B1
Authority
EP
European Patent Office
Prior art keywords
orifices
sections
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.)
Active
Application number
EP19166505.8A
Other languages
English (en)
French (fr)
Other versions
EP3553322A1 (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
Original Assignee
Safran Aero Boosters SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Safran Aero Boosters SA filed Critical Safran Aero Boosters SA
Publication of EP3553322A1 publication Critical patent/EP3553322A1/de
Application granted granted Critical
Publication of EP3553322B1 publication Critical patent/EP3553322B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • 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
    • 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
    • F04D29/40—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 shroud of a compressor fitted with variable-pitch stator vanes. The invention also relates to a compressor fitted with such a shroud, to the method of assembling such a compressor and to a blade for such a compressor.
  • the document FR 2 565 297 A1 describes a gas turbine compressor stator.
  • the stator vanes can be oriented around their axis by means of a connecting rod which is screwed to each vane tip.
  • Housings are provided on the shroud to receive the blade heads with a sleeve and a flange closes the housings to enclose the blade heads in their housings.
  • the sleeve and the heads of the blades are hollowed out to cooperate with a bolt in order to hold the blade radially in its housing.
  • the object of the invention is to solve at least one of the problems posed by the prior art.
  • Another object of the invention is to propose a simpler and more compact design, allowing easier mounting of variable orientation vanes.
  • the invention also aims to provide a lightweight solution, economical, reliable, easy to produce, easy to maintain, and easy to inspect.
  • 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 assembly of the sections to each other via the flanges, the half-orifices of the sections being placed opposite each other to form cylindrical orifices when the two sections are assembled.
  • the invention also relates to a method for 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 of a connecting rod with dawn; the introduction of the journals of the blades into the half-orifices of one of the sections, preferably the downstream section; the positioning of the other of the sections, thus enclosing the journals 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 the assembly of the blades.
  • the method comprises a step of connecting the connecting rods to the synchronization ring takes place before the sections are positioned facing one another.
  • the ring can be fixed to the connecting rods after the assembly of the two sections.
  • the invention proposes a specific geometry which makes it possible to assemble the vanes with variable orientation without requiring the mounting of each of the connecting rods once the vane has been fitted.
  • the design proposed in the present invention generates substantial savings in assembly time.
  • this design allows the mounting of a more compact one-piece synchronization ring (a 360° ring).
  • the terms “internal” and “external” refer to 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 refer to the main flow direction of the stream in the turbomachine.
  • FIG. 1 schematically represents an axial turbomachine.
  • the turbojet engine 2 comprises a first compression level, called low-pressure compressor 4, a second compression level, called high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power of 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 blades. The rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to gradually compress the latter until it enters the combustion chamber 8.
  • An inlet fan commonly referred to as a fan or blower 16 is coupled to the rotor 12 via a gear train 13, and generates an air flow which is divided into a primary flow 18 crossing the various aforementioned levels of the turbomachine, and into 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 streams fitted into one another.
  • FIG. 1 There picture 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 .
  • the flow can be transonic there.
  • the compressor may be a low-pressure compressor 4.
  • the rotor 12 comprises several rows of rotor blades 24, in this case three. It can be a bladed one-piece drum, or include blades fixed by dovetail.
  • the low-pressure compressor 4 comprises several rectifiers, in this case four, which each contain a row of stator vanes 26. Certain stator vanes are of adjustable orientation, also called variable-pitch vanes.
  • the rectifiers are associated with the fan 16 or with a row of rotor blades to straighten the air flow, so as to convert the speed of the flow into pressure, in particular into static pressure.
  • a de-icing nozzle 22 may be mounted on a housing which supports a row of inlet stator vanes 28.
  • Stator vanes 26 extend substantially radially from outer shroud 30 to inner rings 32. Vanes 26 can be attached to outer shroud 30 using pins.
  • the shroud 30 defines an internal surface 29 which guides the flow of gas. According to the invention, the shroud 30 is composed of several axial sections.
  • the blades 26 comprise a cylindrical trunnion 34 which is received in a radial orifice of the outer shroud 30.
  • Actuating means 40 of the connecting rod 36 are shown schematically and will be described later.
  • THE figures 3 and 4 illustrate a known example of a connection between the tip of a blade 26 and the outer shroud 30.
  • the blade 26 comprises a blade 42 having a leading edge 44 and a trailing edge 46.
  • the tip of the blade 26 can include a shoulder 48 for centering and positioning the vane 26 in the shroud 30 as well as a groove to receive a seal.
  • the connecting rod 36 for operating 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 pin 34.
  • the head of the blade is received in line with an extra thickness of the shroud 30, which can be in the form of a boss 33.
  • Connecting rod 36 comprises a conical orifice 60 corresponding to chamfer 54, a body 62 and a lug 64.
  • the orifice 60 may comprise a groove 66 to receive a key and thus make the blade 26 and the connecting rod 36 integral in rotation.
  • the connecting rod 36 also comprises a hole 68 to be connected to an actuating member (described in figure 10 ).
  • the outer shroud 30 has an orifice receiving the journal 34. The journal 34 is inserted into the orifice from below (in the direction of the picture 3 ), then connecting rod 36 is screwed to thread 52.
  • THE figures 5 to 7 show a first embodiment of the connection between the blade 26 and the outer shroud 30 according to the invention
  • FIG. 5 shows a partial top view of the assembly according to the invention.
  • FIG. 5 references the directions VI and VII whose cross-sectional views are illustrated in figures 6 and 7 respectively.
  • Each of the sections comprises a tubular wall 131, 231 defining an internal 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 blade.
  • the two sections 130, 230 are assembled via screwed elements which hold two adjacent flanges 134, 234 together.
  • the flanges 134, 234 extend from one boss to the neighboring boss circumferentially.
  • There figure 5 represents only one orifice.
  • the shroud 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 connecting rod 36 of this first embodiment is welded to the head of the blade. This is done before the assembly of the blade in the shell.
  • the journal 34 can be positioned in a half-orifice 132, 232 of one of the sections despite the dimension of the connecting rod which is greater than the diameter of the orifice. 31, then the other section is fixed to enclose pin 34 in hole 31.
  • the connecting rod 36 may have a shape similar to that of the figure 4 , potentially without keyway, become unnecessary due to welding.
  • FIG 7 shows a view according to the VII:VII plane 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 allowing the assembly of the ferrule sections by screwed elements 35.
  • Back -map on the figure 7 we distinguish the bosses 133, 233.
  • FIG 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 one piece, made in one piece.
  • the connecting rod can be forged or cast with the rest of the blade. 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.
  • FIG 9 represents a partial isometric view of the ferrule 30. It shows in particular some of the bosses 133, 233 as well as the flanges 134, 234 and their assembly holes (only the holes 235 of the downstream section 230 are visible).
  • the flanges completely connect each of the bosses 133, 233 to the neighboring boss.
  • the upstream section 130 comprises a flange 136 which makes it possible to connect the shroud to the nozzle of the compressor.
  • the downstream section 230 comprises a cylindrical bearing surface 237 to guide the pads of the synchronization ring 72 (see figure 10 ).
  • the flanges 134, 234 rise above the tubular wall 131, 231 by a height equivalent to that of the bosses 133, 233. Alternatively, their respective elevations may differ.
  • the sections may have axial centering pins, in particular at the level of the flanges.
  • axial pins provided in one or more of the flanges 134 can penetrate into corresponding axial orifices in one or more of the flanges 234.
  • FIG. 10 represents a section of the compressor.
  • the shroud made up of the two sections 130, 230 is fixed to the support casing of the de-icing nozzle which carries the inlet stator vanes 28 via the upstream flange 136.
  • a downstream flange 236 can be provided on the downstream section.
  • the mechanism 40 for actuating the pivoting of the blade comprises a pin 70 which is received in a distal orifice of the connecting rod 36 (equivalent to the orifice 68 of the connecting rod of the figure 4 ).
  • the pin 70 passes through a synchronization ring 72 and ends in a pad 74.
  • the pad 74 rests on a cylindrical surface 237 of the downstream section.
  • the cylindrical surface 237 ends upstream with 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 synchronization ring 72 cooperates with as many pins 70 as connecting rods 36 distributed annularly.
  • the ring 72 can be actuated in pivoting around the axis 14 by appropriate means such as for example a toothed wheel cooperating 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 these thus make the connecting rod 36 and the blade 26 pivot around the axis 38.
  • the downstream section allows the assembly of the synchronization ring and the pins.
  • the flange 236 has an outer diameter which is substantially smaller than the inner diameter of the ring 72, thereby allowing the pegs with their pads to be inserted into the ring before the ring and peg assembly is slid axially upstream to be mounted on the downstream section.
  • the trunnions 34 of the blades are inserted into the half-orifices 232, then the upstream section is brought to enclose the trunnions 34 in the orifices 31 thus formed.
  • the flanges 134, 234 are then screwed together.
  • the actuating pins 70 carried by the synchronization ring 72 can be assembled to the connecting rods 36.
  • the fixing of the pins 70 to the connecting 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 blades 26 are brought into the half-orifices 232.
  • the embodiment described here has two sections 130 and 230 but one or more additional sections can be provided and assembled in the same way, each of the sections having an annular row of half-orifices facing the half-orifices of the adjacent section to forming orifices receiving blade tips which may or may not have variable orientation.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (12)

  1. Baugruppe für ein axiales Turbinentriebwerk (2), insbesondere für Flugzeug-Turbinentriebwerke, das Folgendes umfasst:
    - eine ringförmige Reihe von Schaufeln (26), die jeweils eine Schaufel (42) und einen radialen Kopf (34, 48, 54) umfassen, der eine zylindrische Nabe (34) enthält, wobei die Schaufeln (26) um die Nabenachse (38) schwenkbar sind;
    - ein Stellglied (40) zum Schwenken der Schaufeln (26), das einen Steuerring (72) und Antriebsstange (36) umfasst, die den Steuerring (72) mit jeder der Schaufeln verbinden;
    - einen äußeren Ring (30), der eine rohrförmige Wand (131, 231) umfasst und eine ringförmige Reihe von radialen Bohrungen (31) aufweist, in die die Enden (34, 48, 54) der Schaufeln (26) eintreten, wobei der äußere Ring (30) einen axialen Abschnitt (130) des äußeren Rings, der als stromaufwärtiger Abschnitt bezeichnet wird, und einen axialen Abschnitt (230) des äußeren Rings, der als stromabwärtiger Abschnitt bezeichnet wird, umfasst;
    jeder der Abschnitte (130, 230) eine Innenfläche (129, 229) zur Führung des Gasstroms aus der Turbomaschine umfasst, wobei die beiden Abschnitte (130, 230) axial benachbart sind,
    jeder der Abschnitte (130, 230) umfasst:
    - eine ringförmige Reihe von radialen, vorzugsweise halbzylindrischen Halbbohrungen (132, 232); und
    - mindestens einen Flansch (134, 234), der zwischen zwei in Umfangsrichtung benachbarten Halbbohrungen (132, 232) angeordnet ist;
    wobei die Halbbohrungen (132, 232) so angeordnet sind, dass jede der Halbbohrungen (132, 232) eines Abschnitts (130, 230) axial und in Umfangsrichtung mit einer Halbbohrung (132, 232) des anderen Abschnitts (230, 130) ausgerichtet werden kann, um die ringförmige Reihe von Bohrungen (31) zu bilden, wobei der Flansch oder die Flansche (134, 234) des einen Abschnitts (130, 230) so angeordnet sind, dass er/sie axial und in Umfangsrichtung mit dem Flansch oder den Flanschen (134, 234) des anderen Abschnitts (230, 130) ausgerichtet sind;
    die Abschnitte (130, 230) mit einer ringförmigen Reihe von radialen Vertiefungen oder Nuten (133, 233) versehen sind, in die die Halbrundungen (132, 232) eintreten,
    die radialen Nuten oder Vorsprünge (133, 233) sind zu zweit am Umfang durch Flansche (134, 234) verbunden,
    einer der Abschnitte (130, 230), insbesondere der stromabwärtige Abschnitt (230), eine Aussparung für das Stellglied (40) zur Ausrichtung der Schaufeln (26) aufweist, wobei die Aussparung eine zylindrische Außenfläche (237) umfasst, dadurch gekennzeichnet, dass der Kopf (34, 48, 54) jeder der Schaufeln (26) einen radial äußeren Teil (36, 62, 64) auf der der Schaufel (42) gegenüberliegenden Seite der Nabe (34) aufweist, wobei sich der radial äußere Teil (36, 62, 64) in Umfangsrichtung und/oder axial um eine Abmessung erstreckt, die größer ist als der Durchmesser der zugehörigen Bohrung (31), und
    der Abschnitt (130, 230), der das Gehäuse umschließt, auf der den Halbbohrungen (132, 232) gegenüberliegenden axialen Seite des Gehäuses nur Abschnitte mit einem Durchmesser aufweist, der kleiner als der Durchmesser der zylindrischen Oberfläche (237) des Gehäuses ist.
  2. Baugruppe nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass jeder Umfangsabstand zwischen zwei benachbarten Halbbohrungen (132, 232) einen der Flansche (134, 234) umfasst.
  3. Baugruppe nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass sich die Flansche (134, 234) vollständig in Umfangsrichtung von einer Halbbohrung (132, 232) zur benachbarten Halbbohrung (132, 232) erstrecken.
  4. Eine Baugruppe nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Flansche (134, 234) jeweils mit zwei Bohrungen (135, 235) versehen sind, in die ein Befestigungsstift (35) zum Verbinden der Abschnitte (130, 230) eintritt, wobei sich die Bohrungen (135, 235) an einer Umfangsposition befinden, die weniger als ein Viertel der Umfangslänge eines Flansches (134, 234) neben jeder der Halbbohrungen (132, 232) beträgt.
  5. Baugruppe nach dem vorhergehenden Anspruch, dadurch gekennzeichnet, dass die Flansche (133, 233) eine halbkonische Außenfläche und eine halbzylindrische Innenfläche haben, die die Halbbohrung (132, 232) bilden.
  6. Baugruppe nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der stromaufwärts gelegene Abschnitt (130) an seinem den Halbbohrungen (132) gegenüberliegenden axialen Ende einen Flansch (136) aufweist, der dazu dient, den Abschnitt (130) mit einem Gebläseträgergehäuse oder einer Abtropfdüse (22) zu verbinden.
  7. Baugruppe nach einem der vorhergehenden Ansprüche, mit einem dritten Abschnitt, der mit dem stromaufwärts oder stromabwärts gelegenen Abschnitt (130, 230) verbunden ist und mit diesem eine weitere ringförmige Reihe von Bohrungen bildet, in die eine weitere ringförmige Reihe von Statorschaufeln eintritt.
  8. Baugruppe nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der Ring (72) mit Auflagen (74) versehen ist, die eine zylindrische Oberfläche (237) eines der Abschnitte (130, 230) radial berühren.
  9. Baugruppe nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Flansche (134, 234) den Ring (72) radial überlappen und von diesem axial beabstandet sind.
  10. Verfahren zum Zusammenbau einer Baugruppe nach einem der Ansprüche 1 bis 9, wobei das Verfahren die folgenden Schritte umfasst:
    - Montage einer Antriebsstange (36) an den Kopf (34, 48, 54) jeder Schaufel (26) oder Fertigung der Antriebsstange (36) mit der Schaufel (26) in einem Stück;
    - Einsetzen der Naben (34) der Schaufeln (26) in die Halbbohrungen (232) eines der Abschnitte, vorzugsweise des stromabwärts gelegenen Abschnitts (230);
    - Einsetzen des anderen Abschnitts (130), wodurch die Naben (34) in den so gebildeten Bohrungen (31) verschlossen werden;
    - Befestigen, vorzugsweise durch Verschrauben (35, 135, 235), der Flansche (134, 234) der beiden Abschnitte (130, 230) aneinander.
  11. Verfahren nach Anspruch 10, dadurch gekennzeichnet, dass es einen Schritt der Befestigung des Rings (72) umfasst, der die Flansche (36) synchronisiert, vorzugsweise auf dem stromabwärts gelegenen Abschnitt (230) und vorzugsweise vor der Montage der Schaufeln (26).
  12. Verfahren nach einem der Ansprüche 10 oder 11, gekennzeichnet durch einen Schritt des Verbindens der Flansche (36) mit dem Synchronisierungsring (72), bevor die Abschnitte (130, 230) einander gegenüber positioniert werden.
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 EP3553322A1 (de) 2019-10-16
EP3553322B1 true EP3553322B1 (de) 2023-05-31

Family

ID=62067309

Family Applications (1)

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

Country Status (3)

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

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019243484A1 (fr) * 2018-06-21 2019-12-26 Safran Aero Boosters Sa Virole extérieure de turbomachine

Family Cites Families (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
US4585390A (en) 1984-06-04 1986-04-29 General Electric Company Vane retaining means
FR2644525B1 (fr) * 1989-03-15 1991-05-24 Snecma Systeme de retention d'aubes de stator a calage variable
DE4237031C1 (de) * 1992-11-03 1994-02-10 Mtu Muenchen Gmbh Verstellbare Leitschaufel
EP2006495A1 (de) * 2007-06-20 2008-12-24 ABB Turbo Systems AG Positionsregelung für Vordrall-Leitvorrichtung
US8668444B2 (en) * 2010-09-28 2014-03-11 General Electric Company Attachment stud for a variable vane assembly of a turbine compressor
EP3009607A1 (de) * 2014-10-13 2016-04-20 United Technologies Corporation Fest-verstellbare schaufel mit vergussspalt
BE1024523B1 (fr) * 2016-08-30 2018-03-29 Safran Aero Boosters S.A. Stator a aubes ajustables pour compresseur de turbomachine axiale

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019243484A1 (fr) * 2018-06-21 2019-12-26 Safran Aero Boosters Sa Virole extérieure de turbomachine

Also Published As

Publication number Publication date
BE1026199A1 (fr) 2019-11-05
BE1026199B1 (fr) 2019-11-12
US20190309650A1 (en) 2019-10-10
EP3553322A1 (de) 2019-10-16

Similar Documents

Publication Publication Date Title
EP2075413B1 (de) Vorrichtung zur Versteifung eines Stators einer Strömungsmaschine und deren Anwendung in Luftfahrzeugmotoren
EP2795068B1 (de) Leitschaufelanordnung eines turbomaschinenverdichters
BE1026411B1 (fr) Virole extérieure de turbomachine
WO2023118686A1 (fr) Module de turbomachine equipe d'aubes a calage variable et d'une virole annulaire d'interface
FR3071868B1 (fr) Bras pour carter de turbomachine comprenant un corps et une piece amovible
EP4185767A1 (de) Turbinenmotormodul mit propeller- und leitschaufeln mit haltevorrichtung und zugehöriger turbinenmotor
EP3690192B1 (de) Rotor für einen kompressor einer axialen turbomachine
EP3553322B1 (de) Einheit für ein axiales turbotriebwerk mit einem zweiteiligen aussenring
EP3973146B1 (de) Abnehmbarer stift an einer turbomaschinendüse
EP4143421A1 (de) Gehäuse mit zwischenflussglättung mit monoblockstrukturarm
EP3751102B1 (de) Rotor für den kompressor einer rotationsmaschine und zugehöriges fertigungsverfahren
EP3290657B1 (de) Stator mit verstellbaren schaufeln fürden kompressor eines axialen gasturbinenmotors
EP4077880A1 (de) Modul für turbomaschine
EP3715638B1 (de) Hybridrotor mit einem aussenmantel, der an der ringgförmigen verbundwand anliegt
EP4034752B1 (de) Anordnung für einen turbinenmotor
BE1025131A1 (fr) Arbre de transmission à double cannelure pour turbomachine
BE1026460B1 (fr) Carter structural pour turbomachine axiale
EP4222355A1 (de) Turbomaschinenmodul mit einem propeller und versetzten leitschaufeln
EP4222052A1 (de) Turbinenmotormodul mit einem propeller und von zwei gehäusen getragenen leitschaufeln und zugehöriger turbinenmotor
FR3109796A1 (fr) Carter intermediaire de redressement avec bras structural rapporte

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20200409

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20210913

REG Reference to a national code

Ref document number: 602019029443

Country of ref document: DE

Ref country code: DE

Ref legal event code: R079

Free format text: PREVIOUS MAIN CLASS: F04D0029560000

Ipc: F01D0009040000

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20230210

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 25/24 20060101ALI20230127BHEP

Ipc: F04D 29/64 20060101ALI20230127BHEP

Ipc: F04D 29/56 20060101ALI20230127BHEP

Ipc: F01D 17/16 20060101ALI20230127BHEP

Ipc: F01D 9/04 20060101AFI20230127BHEP

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602019029443

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1571026

Country of ref document: AT

Kind code of ref document: T

Effective date: 20230615

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20230531

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1571026

Country of ref document: AT

Kind code of ref document: T

Effective date: 20230531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230831

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230930

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230901

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231002

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602019029443

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20240321

Year of fee payment: 6

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230531

26N No opposition filed

Effective date: 20240301