EP2376790B1 - Aube a calage variable pour etage de redresseur, comprenant une plateforme interne non circulaire - Google Patents

Aube a calage variable pour etage de redresseur, comprenant une plateforme interne non circulaire Download PDF

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Publication number
EP2376790B1
EP2376790B1 EP10700112.5A EP10700112A EP2376790B1 EP 2376790 B1 EP2376790 B1 EP 2376790B1 EP 10700112 A EP10700112 A EP 10700112A EP 2376790 B1 EP2376790 B1 EP 2376790B1
Authority
EP
European Patent Office
Prior art keywords
vane
radially inner
circle
platform
inner platform
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
EP10700112.5A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2376790A1 (fr
Inventor
Aude Abadie
Claude Robert Louis Lejars
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 Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP2376790A1 publication Critical patent/EP2376790A1/fr
Application granted granted Critical
Publication of EP2376790B1 publication Critical patent/EP2376790B1/fr
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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
    • F04D29/56—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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making

Definitions

  • the present invention relates generally to the field of stages of variable-pitch vane straighteners, these stages being provided for equipping turbine engine modules, of the compressor or turbine type.
  • Such a rectifier stage is known from EP 0 384 706 .
  • the invention is preferably applicable to aircraft turbomachines, for example of the turbojet or turboprop type.
  • the compressor 1 comprises, in a conventional manner, a plurality of rectifier stages 2a, 2b, 2c, and moving wheels (not shown). These elements, centered on the axis 4 of the turbomachine, are provided alternately in the axial direction, and intended to be traversed by a main air flow 6 flowing through the high pressure compressor.
  • Each stage of rectifier 2a, 2b, 2c comprises a plurality of blades 8, called variable pitch.
  • the pin 12 is connected to a system 14 for controlling the incidence of the blade 8, which system is mounted on the outer casing 10.
  • the system 14 is capable of controlling all the blades of its associated stator stage at the same time.
  • the blade 8 also has a foot, also usually comprising a radially internal platform 13 extending by a centering pin 16.
  • This pin 16 with axis identical to that of the pin 12 and corresponding to the axis 20 of the dawn around which this blade can be pivoted to be wedged in incidence, is inserted into a rectifier ring 22.
  • the latter generally made from several annular ring sectors, has in fact a plurality of orifices 24 distributed circumferentially, each housing a bushing 26 for receiving a centering pin 16.
  • these orifices 24 open respectively in other holes 27 housing platforms 13.
  • the rectifier ring 22 participates in the construction of the inner surface delimiting the main vein crossed by the airflow 6.
  • Each bushing 26 comprises a collar 28 inserted into one of the orifices 24 of the ring, this collar defining a housing 30 of centering, in which the pin 16 of a blade is inserted.
  • the pin 16 is coated with a member 32, preferably secured to the latter, whose function is to promote sliding in the collar 28.
  • the sleeve 26 comprises a base 34 integral with the collar, and disposed radially inwardly therefrom. The base 34 of each bushing rests in a circumferential groove 36 of the straightener ring 22, in order to ensure, in a known manner, a locking in rotation of this bushing.
  • each base 34 is delimited by two opposite faces in the circumferential direction 40, and two opposite faces in the axial direction 50, referenced 46 and 48.
  • the two faces 46, 48, said circumferential faces, are substantially flat and respectively facing two edges delimiting the groove 36, as shown on the figure 2 .
  • each bushing 26, along its axis 20, relative to the ring 22 is stopped by the consumption of the functional clearances initially provided between the circumferential faces 46, 48 and the edges of the groove 36. Once the contact established between the faces 46, 48 of the base 34 and these groove edges, the relative rotation of the base is stopped, while the relative rotation of the blade 8 relative to its sleeve 26 and the ring 22 can continue, to obtain the desired setting.
  • this assembly 60 for rectifier stage comprising the ring 22, the sockets 26 and the blades 8, is widely used in the embodiments of the prior art, it nevertheless has a significant disadvantage, residing in the high wear of the parts. in the presence.
  • there is an extremely rapid wear of the groove edges permanently impacted by the bases 34 this wear having the consequence of increasing in a similar proportion the amplitude of rotation of the bushes at each change of bearing timing, and thus also causing wear of other parts of the ring, such as those facing the flanges 28, resulting in widening by wear of the orifice 24.
  • each blade 8 undergoes a spill caused by the resultant aerodynamic forces acting on it.
  • This spill aerodynamic whose amplitude is greater than the aforementioned wear of the housing orifices 24 is large, has the consequence of creating friction between the radially inner platform 13 and its corresponding housing hole 27, practiced in the ring 22.
  • the invention therefore aims to at least partially overcome the disadvantages mentioned above, relating to the achievements of the prior art.
  • the invention firstly relates to a variable-pitch blade for a turbomachine module rectifier stage, comprising a blade part on either side of which are provided a radially inner platform and a radially outer platform, and also having a first centering pin extending radially outwardly from said radially outer platform, and a second centering pin extending radially towards the interior from said radially inner platform, said first and second centering pins defining a common axis of blade rotation, and said blade portion, which has a first surface forming an extrados and a second surface forming an intrados, separating said platform radially internal in a first portion arranged on the side of the first blade surface and a second portion arranged on the side of the second blade surface.
  • said first part of the radially inner platform in view taken in the direction of the axis of blade rotation, has an outer contour superimposed on a circle, at a distance and within which there is at least a portion of the outer contour of said second portion of the radially inner platform.
  • the invention therefore provides, in an original way, to break with the usual circular section shape for the radially inner platform of the blade.
  • the second part of the platform namely that which is the most subject to friction in its housing hole due to the aerodynamic discharge of the blade, is no longer circular, but has a peripheral shrinkage of material.
  • This removal makes it possible to spread it locally from the housing orifice of the ring in which this platform is intended to be housed, in order to reduce friction with this orifice.
  • the ring being less stressed in friction by the radially internal platforms that it supports, its life is advantageously increased.
  • the level of stress in the dawn remains the same as that for the new condition, and the life of the dawn is no longer impacted.
  • the portion of the contour of the radially inner platform, which deviates from said circle, extends over an angular sector between 100 and 140 °, centered on the center of said circle.
  • the portion of the contour of the radially inner platform, which deviates from said circle is at a maximum radial distance from said circle between a value corresponding to 7% of the diameter of the circle, and a value corresponding to 1% of the diameter of this circle.
  • the subject of the invention is also a set for a rectifier stage comprising a plurality of variable-pitch vanes such as the one described above, said assembly comprising a rectifier ring having, in association with each of said vanes, a housing orifice of the radially inner platform of the blade, opening at a main vein delimiting inner surface defined by the ring, and a housing hole of a centering sleeve of the blade in which is inserted said second centering pin so that taken in the direction of the axis of rotation of blade, said housing hole of the radially inner platform has an inner contour superimposed on a concentric circle and of diameter greater than said circle on which is superimposed the outer contour of said first portion of the radially inner platform.
  • each radially inner platform also forms a portion of said interior main vein delineation surface.
  • each centering sleeve comprises on the one hand a flange inserted in said socket receiving hole provided on the ring and defining a housing of the second centering pin, and on the other hand a base integral with said collar, said bushings, each extending along a bushing axis, succeeding each other in a circumferential direction of said ring.
  • each centering sleeve is housed in a circumferential groove of the ring, delimited by two songs opposite and spaced from each other in an axial direction of the ring.
  • the invention also relates to a variable-pitch vane straightener stage, for a turbomachine module, comprising an assembly as described above.
  • the invention furthermore relates to a turbomachine module comprising at least one rectifier stage as described above.
  • the module may be a compressor, preferably a high pressure compressor, or a turbine.
  • the invention relates to a turbomachine comprising at least one module as described above.
  • the subject of the invention is also a process for manufacturing a variable-pitch vane for a turbomachine module rectifier stage, such as that described above, in which said radially internal platform is obtained from a circular section shape, machined on its periphery so as to obtain said second part of this platform.
  • the blade according to the invention can be obtained by any other method, without departing from the scope of the invention.
  • the radially inner platform can be manufactured to adopt directly its final shape, for example by casting, without passing through an intermediate shape of circular section.
  • This first embodiment is intended to replace the assembly 60 of the prior art described above, and therefore designed to be arranged within any of the stages of rectifier 2a, 2b, 2c of the high pressure compressor of the figure 1 .
  • the assembly has, in section along the line II-II of the figure 4 , a shape identical or similar to that of the set 60 of the figure 2 .
  • the elements bearing identical reference numerals correspond to identical or similar elements.
  • the assembly 160 comprises a rectifier ring 22 identical to that described for the assembly 60 of the prior art.
  • the housing orifices 24, 27 regularly distributed in the circumferential or tangential direction 40, with the orifices 27 opening at a main vein delimiting inner surface 66 formed by the ring 22, and the orifices 24 opening at the circumferential groove (not visible on the figure 4 ) delimited by the two groove edges opposite and spaced from each other in the axial direction 50.
  • This ring is obviously centered on the axis of the turbomachine.
  • the assembly 160 is also equipped with a plurality of blade root receiving bushings (not shown), of the type shown in FIG. figure 2 , and provided in a number identical to that of the blades of the rectifier stage, namely several tens.
  • the assembly 160 finally comprises a plurality of vanes 8 with variable pitch, each cooperating with a pair of orifices 24, 27 and a sleeve housed in the orifice 24.
  • each blade 8 comprises a blade portion 43 on either side of which are disposed a radially inner platform 13 and a radially outer platform 11, and also having a first centering pin 12 extending radially towards the outside the platform 11, and a second centering pin (not visible on the figure 4 ) extending radially inwards from the platform 13, these first and second centering pins defining a common axis of blade rotation 20.
  • the blade portion 43 has a first surface forming an extrados 64 and a second surface opposite the first, forming a lower surface 62.
  • the base of this blade portion 43 separates the radially inner platform 13 into a first one. 13a portion arranged on the side of the upper surface 64, and a second portion 13b arranged on the side of the lower surface 62, as is best seen on the figure 5 .
  • the first and second parts 13a, 13b are delimited by the extension of the skeleton 70 of the base of the blade.
  • the delimitation is always effected by the intrados 62 and the extrados 64, since the trailing edge of the blade extends well beyond the platform 13. Because of this extension of the blade 43 beyond the platform, the orifice 27 has a slight chamfer 72 at its portion may be covered by this blade.
  • the upper surface of the portions 13a and 13b of the inner platform 13 also constitutes a portion of the main vein delimiting inner surface 66, which is preferably inclined with respect to the axial direction, and which, in general, deviates from the motor shaft downstream.
  • At least one portion Cb1 of the outer contour Cb of the second portion 13b of the platform 13 is arranged at a distance and within said circle C1.
  • the part Cb1 of the contour which is arranged inside the circle C1 corresponds only to a portion of this contour referenced Cb, the other part Cb2 being in turn superimposed on the circle C1 .
  • the part Cb2 may be that lying in the continuity of the two ends of the contour of the portion Ca, while the portion Cb1 may extend over an angular sector 74, for example of the order of 120 °, centered on the center 20 of the circle C1.
  • the portion Cb1 of the contour Cb may take the form of an arc of a circle centered on a center 76 offset from the center 20 of the circle C1.
  • the platform 13 that results from the geometric definition above, therefore has a general shape comparable to a cylindrical shape of circular section having a peripheral withdrawal of material at a portion of its second portion 13b, so that this portion is more away from the orifice 27 than are the other portions of this platform 13.
  • the housing hole 27 of the radially inner platform 13 has an inner contour C 'superimposed on a concentric circle C2 and diameter greater than the circle C1 mentioned above. Consequently, in the idle state, the first clearance separating the contour C 'and the contour portions Ca, Cb2 is substantially constant, for example of the order of 0.5 mm, and smaller than the second evolutionary clearance j Separating the contour C 'from the contour part Cb1.
  • This second game "j" also referenced on the figure 7 is, moreover, substantially identical to the first set near the two junctions with the contour Cb2, then progressively increases as it gets closer to the central portion of the contour portion Cb1, where it reaches its maximum, for example of the order of 1.75 mm.
  • the portion Cb1 of the contour Cb which deviates from the circle C1, to be at a maximum radial distance from this circle between a value corresponding to 7% of the diameter of the circle C1, and a value corresponding to 1% of the diameter of this circle C1. It is noted that the radial distance must naturally be understood as the distance between the circle C1 and the contour Cb1 in a straight line passing through the center 20 of the circle C1.
  • the blade 8 undergoes a spill caused by the resultant aerodynamic forces exerted on it, which has the effect of bringing the contour Cb1 of the orifice 27, without causing harmful friction on the ring 22.
  • the lateral surface of the platform 13, defining the contours Ca, Cb, is cylindrical with axis 20, as well as abstraction made of the chamfer 72, the surface Lateral of the housing orifice 27, defining the contour C ', is also cylindrical with axis 20.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP10700112.5A 2009-01-09 2010-01-08 Aube a calage variable pour etage de redresseur, comprenant une plateforme interne non circulaire Active EP2376790B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0950104A FR2941018B1 (fr) 2009-01-09 2009-01-09 Aube a calage variable pour etage de redresseur, comprenant une plateforme interne non circulaire
PCT/EP2010/050128 WO2010079204A1 (fr) 2009-01-09 2010-01-08 Aube a calage variable pour etage de redresseur, comprenant une plateforme interne non circulaire

Publications (2)

Publication Number Publication Date
EP2376790A1 EP2376790A1 (fr) 2011-10-19
EP2376790B1 true EP2376790B1 (fr) 2018-03-07

Family

ID=40833530

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10700112.5A Active EP2376790B1 (fr) 2009-01-09 2010-01-08 Aube a calage variable pour etage de redresseur, comprenant une plateforme interne non circulaire

Country Status (8)

Country Link
US (1) US8721269B2 (zh)
EP (1) EP2376790B1 (zh)
JP (1) JP5596703B2 (zh)
CN (1) CN102272458B (zh)
CA (1) CA2748830C (zh)
FR (1) FR2941018B1 (zh)
RU (1) RU2511811C2 (zh)
WO (1) WO2010079204A1 (zh)

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Publication number Priority date Publication date Assignee Title
FR2992376B1 (fr) * 2012-06-25 2016-03-04 Snecma Soufflante a calage variable par rotation differentielle des disques de soufflante
US20140140822A1 (en) * 2012-11-16 2014-05-22 General Electric Company Contoured Stator Shroud
DE102013222980A1 (de) 2013-11-12 2015-06-11 MTU Aero Engines AG Leitschaufel für eine Strömungsmaschine mit einer Dichtungsvorrichtung, Leitrad sowie Strömungsmaschine
FR3014152B1 (fr) * 2013-11-29 2015-12-25 Snecma Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine et procede d'assemblage d'un tel dispositif
EP3009604B1 (en) * 2014-09-19 2018-08-08 United Technologies Corporation Radially fastened fixed-variable vane system
RU2580249C1 (ru) * 2015-03-17 2016-04-10 Открытое акционерное общество "Авиадвигатель" Статор компрессора газотурбинного двигателя
EP3128132B1 (de) * 2015-08-03 2019-03-27 MTU Aero Engines GmbH Turbomaschinen-leitschaufelringelement
EP3176384B1 (de) * 2015-12-04 2023-07-12 MTU Aero Engines AG Innenring, zugehöriger innenringsektor, leitschaufelkranz und strömungsmaschine
JP6639275B2 (ja) * 2016-03-10 2020-02-05 株式会社東芝 水力機械のガイドベーン及び水力機械
DE102016204291A1 (de) * 2016-03-16 2017-09-21 MTU Aero Engines AG Leitschaufelteller mit einem angefasten und einem zylindrischen Randbereich
DE102016207212A1 (de) 2016-04-28 2017-11-02 MTU Aero Engines AG Leitschaufelkranz für eine Strömungsmaschine
DE102017212161A1 (de) * 2017-07-17 2019-01-17 MTU Aero Engines AG Verschleissschutzblech für die lagerung von verstellbaren leitschaufeln
FR3079553B1 (fr) 2018-03-30 2020-03-13 Safran Aircraft Engines Ensemble pour turbomachine
DE102018213983A1 (de) * 2018-08-20 2020-02-20 MTU Aero Engines AG Verstellbare Leitschaufelanordnung, Leitschaufel, Dichtungsträger und Turbomaschine
FR3108369B1 (fr) 2020-03-18 2022-10-28 Safran Aircraft Engines Redresseur pour turbomachine d’aeronef, comprenant un limitateur de pivotement d’aube a angle de calage variable
US11572798B2 (en) * 2020-11-27 2023-02-07 Pratt & Whitney Canada Corp. Variable guide vane for gas turbine engine
US20240360790A1 (en) * 2023-04-28 2024-10-31 Pratt & Whitney Canada Corp. Retainer and method for disassembling an aircraft engine

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DE2835349C2 (de) * 1978-08-11 1979-12-20 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Verstelleitgitter für hochbelastete Verdichter, insbesondere von Gasturbinentriebwerken
US4950129A (en) * 1989-02-21 1990-08-21 General Electric Company Variable inlet guide vanes for an axial flow compressor
US6283705B1 (en) * 1999-02-26 2001-09-04 Allison Advanced Development Company Variable vane with winglet
RU2186257C2 (ru) * 2000-10-03 2002-07-27 Открытое акционерное общество "Авиадвигатель" Статор компрессора газотурбинного двигателя
US7360990B2 (en) * 2004-10-13 2008-04-22 General Electric Company Methods and apparatus for assembling gas turbine engines
GB0504588D0 (en) 2005-03-05 2005-04-13 Rolls Royce Plc Pivot ring
FR2885182B1 (fr) 2005-04-28 2010-11-26 Snecma Moteurs Aube de stator a calage variable, procede de reparation d'une aube
DE102006052003A1 (de) 2006-11-03 2008-05-08 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit verstellbaren Statorschaufeln
US8123471B2 (en) * 2009-03-11 2012-02-28 General Electric Company Variable stator vane contoured button

Also Published As

Publication number Publication date
CN102272458A (zh) 2011-12-07
RU2511811C2 (ru) 2014-04-10
RU2011133198A (ru) 2013-02-20
EP2376790A1 (fr) 2011-10-19
CN102272458B (zh) 2014-04-09
US8721269B2 (en) 2014-05-13
US20110293406A1 (en) 2011-12-01
JP5596703B2 (ja) 2014-09-24
JP2012514712A (ja) 2012-06-28
CA2748830A1 (fr) 2010-07-15
FR2941018B1 (fr) 2011-02-11
WO2010079204A1 (fr) 2010-07-15
FR2941018A1 (fr) 2010-07-16
CA2748830C (fr) 2016-05-24

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