EP1331402B1 - Steuereinrichtung für Statorschaufel - Google Patents

Steuereinrichtung für Statorschaufel Download PDF

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Publication number
EP1331402B1
EP1331402B1 EP03290058A EP03290058A EP1331402B1 EP 1331402 B1 EP1331402 B1 EP 1331402B1 EP 03290058 A EP03290058 A EP 03290058A EP 03290058 A EP03290058 A EP 03290058A EP 1331402 B1 EP1331402 B1 EP 1331402B1
Authority
EP
European Patent Office
Prior art keywords
link
pivot
recess
clamping cap
vane
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.)
Expired - Lifetime
Application number
EP03290058A
Other languages
English (en)
French (fr)
Other versions
EP1331402A1 (de
Inventor
Michel Bouru
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 EP1331402A1 publication Critical patent/EP1331402A1/de
Application granted granted Critical
Publication of EP1331402B1 publication Critical patent/EP1331402B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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
    • 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
    • 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
    • Y10T403/00—Joints and connections
    • Y10T403/32—Articulated members
    • Y10T403/32008—Plural distinct articulation axes
    • Y10T403/32057—Angular and linear
    • Y10T403/32073—Pivot stud slidable in elongated opening
    • 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
    • Y10T403/00—Joints and connections
    • Y10T403/32—Articulated members
    • Y10T403/32114—Articulated members including static joint
    • Y10T403/32163—Articulate joint intermediate end joints
    • Y10T403/32172—Variable angle
    • 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
    • Y10T403/00—Joints and connections
    • Y10T403/50—Bridged by diverse connector
    • 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
    • Y10T403/00—Joints and connections
    • Y10T403/54—Flexible member is joint component

Definitions

  • the present invention relates to the control of blades variable pitch angle as defined in the preamble of claim 1.
  • Such a device is known from the document US-A-5,024,580 .
  • the present invention finds particular application in the field of aeronautics, in particular for controlling the angular positions of air inlet guide vanes in turbomachine compressors, such as aircraft turbomachines.
  • Known devices for controlling variable pitch vanes in a turbomachine usually comprise a control member in the form of a ring surrounding a casing of the turbomachine and a plurality of levers or links, each link having a first end connected to the turbine engine. control ring by a hinge and a second end mounted on the pivot of a respective blade.
  • the synchronized modification of the angular position of the blades is made by rotation of the ring around the axis of the turbomachine.
  • the connection between each link and the ring comprises at least one degree of freedom in rotation about an axis directed substantially radially relative to the ring.
  • the link being rigidly mounted on the pivot of the corresponding blade, the rotation of the ring induces other relative movements between the ring and the portion of the rod mounted on the pivot of the blade.
  • connection in the form of a ball or a similar part which, in addition to the rotation around a substantially radial axis relative to the ring, allows rotation about an axis having a substantially circumferential direction relative to the ring. It has also been proposed to provide a link providing an additional degree of freedom in translation in a substantially radial direction relative to the ring.
  • US 5,024,580 discloses a control device having an inverted V truncated vane pivot, a correspondingly shaped link and a clamping cap exerting a point contact on the link.
  • the present invention therefore aims to overcome such drawbacks by providing a control device using fastening means of the link which can maintain without play it on the pivot of the blade.
  • An object of the invention is also to eliminate the drive imprecision.
  • a blade control device variable pitch angle for turbomachine compressor rectifier comprising a rod, connecting means forming an articulation between a first end of the rod and a control ring, and means for fixing a second end of the rod on a pivot of a blade to be controlled, characterized in that it further comprises a radial recess formed in the pivot of the blade and intended to receive the second end of the link, the recess comprising at least one inclined plane edge with respect to a plane longitudinal median of the recess and cooperating with a corresponding inclined edge of the second end of the link, and a clamping cap applied on the second end of the rod and on which act the fastening means, the clamping cap having a surface planar inner surface providing a plane contact with the outer face of the second end of the rod on which is applied the clamping cap to maintain without play the second end of the rod on the pivot of the blade by contact between the inclined edges.
  • the second end of the rod is positioned without play on the pivot of the blade through the inclined planes made at the radial recess and the second end of the rod.
  • the immobilization of the second end of the rod on the pivot of the blade is obtained by the clamping cap, and its locking in rotation by the fastening means.
  • the precision of rotation drive between the rod and the pivot of the blade is improved.
  • a groove formed on the inner surface of the clamping cap and in which is partially engaged the second end of the rod advantageously provides an anti-rotation of the clamping cap relative to other parts.
  • the radial recess formed in the pivot of the blade advantageously has two flat inclined edges symmetrical with respect to a median longitudinal plane of the recess in order to obtain a symmetrical locking of the link on the pivot of the blade.
  • the two inclined plane edges may also be asymmetrical with respect to the median plane of the recess to provide a keying between a leading edge and a trailing edge of the rod.
  • FIG. 1 represents, in a very partial way, a part of a turbomachine, for example an airplane turbojet, provided with vanes 10 with a variable pitch angle. These vanes are, for example, guide vanes at the turbomachine compressor inlet, distributed around the axis of the turbomachine. In this Figure 1, only one blade is shown.
  • the control of the angular positions of the blades 10 is performed by a control ring 20 surrounding a casing 22 of the turbomachine (shown only partially in FIG. 1) and a plurality of links 30.
  • Each link 30 comprises a first end 32 connected to the control ring 20 by connecting means forming articulation.
  • this articulation is performed by an axis or finger 24 passing through the first end 32 of the link 30 and engaged in a housing 26 of the control ring 20.
  • a second end 34 of the rod 30 is mounted on a pivot 12 of the blade 10 by means of fixing means 40.
  • the fixing means 40 shown in FIG. 1 are conventionally formed of a screw-nut system comprising an axial threaded rod 14 secured to the pivot 12 of the blade and a clamping nut 42.
  • the fastening means may also be formed by a screw and a self-braking sleeve (not shown) implanted in the pivot 12 of the dawn if the height of the pivot of the blade allows the installation of such a socket. In this case, an orifice is made axially in the pivot of the blade for the passage of the reported screw.
  • FIGS. 2 and 3 illustrate in more detail an embodiment of a connection between rod and blade pivot in accordance with the invention.
  • a radial recess 16 delimited laterally by flat edges 16a, 16b inclined with respect to the longitudinal plane median P of the recess 16 and the rod 30.
  • the inclination angle is for example between 35 ° and 55 °.
  • the second end 34 of the rod 30 provided with an orifice 35 for the passage of the threaded rod 14 (or of the attached screw) is engaged in the radial recess 16 over a part of its thickness delimited by two lateral edges 34a, 34b inclined relative to the median longitudinal plane P of the rod.
  • the inclinations of the edges 34a, 34b correspond to those of the edges 16a, 16b of the recess 16 on which they rest.
  • a cap 44 provided with a bore 46 for the passage of the threaded rod 14 (or the screw insert) is supported on a flat outer face 36 of the second end 34 of the rod.
  • this support is provided by the planar bottom 48a of a groove 48 made radially in the cap 44 and matching the shape of the second end 34 of the rod in the portion thereof adjacent to the face 36 .
  • edges 34a, 34b are inclined symmetrically with respect to the median longitudinal plane P, as are the edges 16a, 16b. It may be otherwise. In particular, only two edges in contact, for example 34a and 16a, can be inclined, the others 34b, 16b are not.
  • position asymmetry of the inclined plane edges 16a, 16b with respect to the median plane P of the recess 16 so as to provide a keying between a leading edge and a trailing edge of the link 30
  • position asymmetry it is meant that the distance D1 (FIG. 2) between one of the plane edges 16a, 16b and the median plane P is greater or less than the distance D2 between the other plane edge 16a, 16b and the median plane P.
  • the link 30 has, at its second end 34, a portion having a greater thickness. large than that of a portion of its first end 32. This feature provides a better seat of the second end 34 of the link in the recess 16 formed in the pivot 12 of the blade.
  • the control device may also comprise a bushing 50 arranged around the pivot 12 of the blade, between the clamping cap 44 and the flange 52 of an opening of the casing 22 of the turbomachine in which is mounted the blade 10.
  • This sleeve 50 is intended to allow a centering of the pivot 12 of the blade with an anti-friction material interposed between the opening of the housing and the pivot of the blade.
  • a shim 54 for adjusting the clearance interposed between the clamping cap 44 and the sleeve 50 can then be advantageously provided to take account of any axial play between these parts.
  • the clamping cap 44 also bears at its periphery on the adjusting wedge 54.
  • an anti-friction washer 56 can be arranged between the rim 52 of the opening of the housing 22 and the base of the pivot 12 of dawn.

Landscapes

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

Claims (10)

  1. Vorrichtung zum Steuern einer Schaufel mit variablem Anstellwinkel für den Leitapparat eines Turbomaschinenverdichters, umfassend einen Schwingarm (30), Verbindungsmittel (24, 26), die zwischen einem ersten Ende (32) des Schwingarms und einem Verstellring (20) ein Gelenk bilden, sowie Mittel (40) zum Befestigen eines zweiten Endes (34) des Schwingarms an einem Drehgelenk (12) einer zu steuernden Schaufel (10),
    dadurch gekennzeichnet, daß sie ferner umfaßt
    - eine radiale Ausnehmung (16), die in dem Drehgelenk der Schaufel ausgebildet und dazu bestimmt ist, das zweite Ende (34) des Schwingarms (30) aufzunehmen, wobei die genannte Ausnehmung wenigstens eine plane Kante (16a, 16b) aufweist, die gegenüber einer Mittellängsebene (P) der Ausnehmung (16) und des Schwingarms (30) geneigt ist und die mit einer entsprechenden geneigten Kante (34a, 34b) des zweiten Endes des Schwingarms zusammenwirkt,
    - sowie eine Klemmkappe (44), die auf das zweite Ende des Schwingarms aufgesetzt ist und auf die die Befestigungsmittel (40) wirken, wobei die Klemmkappe eine plane Innenfläche (48a) aufweist, die einen flächigen Kontakt mit der Außenfläche (36) des zweiten Endes des Schwingarms, auf das die genannte Klemmkappe aufgesetzt ist, sicherstellt, um das zweite Ende (34) des Schwingarms (30) an dem Drehgelenk (12) der Schaufel durch Kontakt zwischen den geneigten Kanten spielfrei zu halten.
  2. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß die in dem Drehgelenk (12) der Schaufel ausgebildete radiale Ausnehmung (16) zwei geneigte plane Kanten (16a, 16b) aufweist, die in bezug auf die Mittellängsebene (P) der Ausnehmung symmetrisch sind.
  3. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß die in dem Drehgelenk (12) der Schaufel ausgebildete radiale Ausnehmung (16) zwei geneigte plane Kanten (16a, 16b) aufweist, die in bezug auf die Mittellängsebene (P) der Ausnehmung asymmetrisch sind.
  4. Vorrichtung nach irgendeinem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Innenfläche (48a) der Klemmkappe (44) eine Nut (48) aufweist, deren Form zur Außenfläche (36) des zweiten Endes (34) des Schwingarms (30), auf das die Klemmkappe aufgesetzt ist, komplementär ist.
  5. Vorrichtung nach irgendeinem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß der Schwingarm (30) im Bereich seines zweiten Endes (34) einen Teil aufweist, dessen Dicke größer als die seines ersten Endes (32) ist.
  6. Vorrichtung nach irgendeinem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß sie ferner eine Buchse (50) aufweist, die um das Drehgelenk (12) der Schaufel herum angeordnet und dazu bestimmt ist, ein Zentrieren des Drehgelenks der Schaufel in einer Öffnung eines Gehäuses (22) zu ermöglichen.
  7. Vorrichtung nach Anspruch 6, dadurch gekennzeichnet, daß sie ferner eine Einstellscheibe (54) umfaßt, die zwischen der Klemmkappe (44) und der Buchse (50) eingefügt ist.
  8. Vorrichtung nach Anspruch 7, dadurch gekennzeichnet, daß die Klemmkappe (44) auch an ihrem Umfang an der Einstellscheibe (54) anliegt.
  9. Leitapparat eines Turbomaschinenverdichters, der eine Vielzahl von Vorrichtungen zum Steuern einer Schaufel mit variablem Anstellwinkel nach irgendeinem der vorhergehenden Ansprüche umfaßt.
  10. Turbomaschine, die wenigstens eine Vorrichtung zum Steuern einer Schaufel mit variablem Anstellwinkel nach irgendeinem der vorhergehenden Ansprüche umfaßt.
EP03290058A 2002-01-29 2003-01-10 Steuereinrichtung für Statorschaufel Expired - Lifetime EP1331402B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0201022 2002-01-29
FR0201022A FR2835294B1 (fr) 2002-01-29 2002-01-29 Dispositif de commande d'aube a angle de calage variable a liaison sans jeu

Publications (2)

Publication Number Publication Date
EP1331402A1 EP1331402A1 (de) 2003-07-30
EP1331402B1 true EP1331402B1 (de) 2007-10-31

Family

ID=8871421

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03290058A Expired - Lifetime EP1331402B1 (de) 2002-01-29 2003-01-10 Steuereinrichtung für Statorschaufel

Country Status (9)

Country Link
US (1) US6796767B2 (de)
EP (1) EP1331402B1 (de)
JP (1) JP4073794B2 (de)
CA (1) CA2418233C (de)
DE (1) DE60317119T2 (de)
ES (1) ES2292916T3 (de)
FR (1) FR2835294B1 (de)
RU (1) RU2295655C2 (de)
UA (1) UA79734C2 (de)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100172745A1 (en) * 2007-04-10 2010-07-08 Elliott Company Centrifugal compressor having adjustable inlet guide vanes
US8414248B2 (en) 2008-12-30 2013-04-09 Rolls-Royce Corporation Variable geometry vane
IT1401664B1 (it) * 2010-08-31 2013-08-02 Nuova Pignone S R L Dispositivo di centraggio e sistema per anello di guida.
GB201711582D0 (en) * 2017-07-19 2017-08-30 Rolls Royce Plc Unison ring assembly
CN109986386B (zh) * 2019-05-13 2024-03-15 福建省华银铝业有限公司 一种电梯刹车片加工装置及加工方法
CN116907436B (zh) * 2023-09-12 2023-11-14 沈阳华钛实业有限公司 一种航空发动机叶片检测装置及其检测方法

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2842305A (en) * 1955-11-01 1958-07-08 Gen Electric Compressor stator assembly
DE2253030A1 (de) * 1972-10-28 1974-05-09 Sljusarew Vorrichtung zur schaufelverstellung des leitapparats einer stroemungsmaschine
DE2810240C2 (de) * 1978-03-09 1985-09-26 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Verstelleitgitter für axial durchströmte Turbinen, insbesondere Hochdruckturbinen von Gasturbinentriebwerken
FR2599785B1 (fr) * 1986-06-04 1990-10-12 Snecma Aubage directeur d'entree d'air a calage variable pour turboreacteur
GB8913988D0 (en) * 1989-06-17 1989-08-09 Rolls Royce Plc Improvements in or relating to control of variable stator vanes
FR2696208B1 (fr) * 1992-09-30 1994-11-10 Snecma Aube à calage variable.
US6019574A (en) * 1998-08-13 2000-02-01 General Electric Company Mismatch proof variable stator vane
US6146093A (en) * 1998-12-16 2000-11-14 General Electric Company Variable vane seal and washer
FR2814206B1 (fr) * 2000-09-18 2002-12-20 Snecma Moteurs Dispositif de commande d'aubes a calage variable

Also Published As

Publication number Publication date
RU2295655C2 (ru) 2007-03-20
FR2835294A1 (fr) 2003-08-01
DE60317119T2 (de) 2008-08-07
EP1331402A1 (de) 2003-07-30
DE60317119D1 (de) 2007-12-13
JP2003227494A (ja) 2003-08-15
CA2418233A1 (fr) 2003-07-29
ES2292916T3 (es) 2008-03-16
CA2418233C (fr) 2011-05-31
UA79734C2 (uk) 2007-07-25
US6796767B2 (en) 2004-09-28
US20030143066A1 (en) 2003-07-31
FR2835294B1 (fr) 2004-04-16
JP4073794B2 (ja) 2008-04-09

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