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EP1331402A1 - Steuereinrichtung für Statorschaufel - Google Patents

Steuereinrichtung für Statorschaufel Download PDF

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Publication number
EP1331402A1
EP1331402A1 EP03290058A EP03290058A EP1331402A1 EP 1331402 A1 EP1331402 A1 EP 1331402A1 EP 03290058 A EP03290058 A EP 03290058A EP 03290058 A EP03290058 A EP 03290058A EP 1331402 A1 EP1331402 A1 EP 1331402A1
Authority
EP
European Patent Office
Prior art keywords
link
pivot
blade
recess
clamping cap
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
EP03290058A
Other languages
English (en)
French (fr)
Other versions
EP1331402B1 (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 Moteurs 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 SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
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 angle blades variable setting. It finds a particular application in the field aeronautics, especially for controlling angular positions air inlet guide vanes in turbomachine compressors, such as aircraft turbomachines.
  • Known devices for controlling wedging vanes variable in a turbomachine usually include a control 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 control ring by a articulation and a second end mounted on the pivot of a blade respectively.
  • Synchronized modification of the angular position of the blades is produced by rotation of the ring around the axis of the turbomachine.
  • the link between each link and the ring includes at least one degree of freedom in rotation about an axis directed substantially radially with respect to the ring.
  • the link being rigidly mounted on the pivot of the corresponding dawn, the rotation of the ring induces other movements relative between the ring and the part of the rod mounted on the pivot dawn.
  • connection in the form of a ball joint or the like which, in addition to rotation around a substantially radial axis relative to the ring, allows a rotation about an axis having a substantially circumferential direction relative to the ring. It has also been proposed to make a connection offering an additional degree of freedom in translation in a substantially radial direction relative to the ring.
  • the present invention therefore aims to overcome such drawbacks by proposing a control device using fixing means of the link which allow it to be held without play on the pivot of dawn.
  • An object of the invention is also to remove the imprecision drive.
  • variable setting angle for compressor rectifier turbomachine comprising a rod, connecting means forming articulation between a first end of the link and a ring of control, 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 made in the pivot of the blade and intended to receive the second end of the link, the recess having at least one plane edge inclined with respect to a plane median longitudinal of the recess and cooperating with an inclined edge matching the second end of the link, and a hat tightening applied to the second end of the link and on which the fixing means act, the clamping cap comprising a internal surface ensuring flat contact with the external face of the second end of the link on which the cap is applied tightening to keep the second end of the link without play on the pivot of the blade by contact between the inclined edges.
  • the second end of the link is positioned no play on the dawn pivot thanks to the inclined planes made at level of the radial recess and of the second end of the link.
  • the immobilization of the second end of the link on the pivot of the blade is obtained by the clamping cap, and its blocking in rotation by the fixing means.
  • the precision of rotation drive between the link and the pivot of the blade is improved.
  • a groove on the inner surface of the hat tightening and in which the second end is partially engaged of the link advantageously ensures anti-rotation of the tightening cap compared to other parts.
  • the radial recess in the pivot of the blade presents advantageously two edges inclined planes symmetrical with respect to a median longitudinal plane of the recess in order to obtain a blockage symmetrical of the rod on the pivot of the blade.
  • the two flat edges inclined can also be asymmetrical with respect to the median plane of the recess to ensure a polarization between a leading edge and a trailing edge of the link.
  • FIG. 1 very partially represents part of turbomachine, for example of an airplane turbojet, provided with blades 10 with variable pitch angle. These blades are for example blades turbomachine compressor input guidelines, distributed around of the axis of the turbomachine. In this figure 1, only one blade is represented.
  • the control of angular positions blades 10 is produced by a control ring 20 surrounding a casing 22 of the turbomachine (shown only partially on the Figure 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 a joint.
  • this joint is produced by an axis or finger 24 passing through the first end 32 of the rod 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 fastening means 40 shown in Figure 1 are conventionally formed of a screw-nut system comprising an axial threaded rod 14 integral with the pivot 12 of the blade and a clamping nut 42.
  • the means of fixing can also be achieved by an attached screw and a self-locking sleeve (not shown) located in pivot 12 of the blade if the height of the blade pivot allows the fitting of such a socket. In this case, an orifice is made axially in the pivot of the blade for the passage of the attached screw.
  • Figures 2 and 3 illustrate in more detail an embodiment of a connection between link and pivot of blade according to the invention.
  • a radial recess 16 delimited laterally by planar edges 16a, 16b inclined relative to the longitudinal plane median P of the recess 16 and the connecting rod 30.
  • the angle of inclination 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 part of its thickness delimited by two lateral edges 34a, 34b inclined relative to the plane longitudinal median P of the link.
  • the inclinations of the edges 34a, 34b correspond to those of the edges 16a, 16b of the recess 16 on which they support each other.
  • this support is achieved by the flat bottom 48a of a groove 48 formed radially in the cap 44 and matching the shape of the second end 34 of the link in the part thereof adjacent to the face 36.
  • edges 34a, 34b are inclined symmetrically with respect to the median longitudinal plane P, as well as the edges 16a, 16b. It could be otherwise. In particular, only two edges in contact, for example 34a and 16a, can be inclined, the others 34b, 16b not being.
  • position asymmetry is meant that the distance D1 (FIG. 2) between one of the planar edges 16a, 16b and the plane median P is greater or less than the distance D2 between the other edge plane 16a, 16b and the median plane P.
  • the link 30 has, at level of its second end 34, a part having a thickness more as large as that of part of its first end 32. This characteristic allows better seating of the second end 34 of the link in the recess 16 formed in the pivot 12 from dawn.
  • the control device can also have a sleeve 50 disposed 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 the blade 10 is mounted.
  • This sleeve 50 is intended to allow centering of the pivot 12 of the blade with a material anti-friction interposed between the opening of the casing and the pivot of the blade.
  • a shim 54 for adjusting the clearance interposed between the clamping cap 44 and the socket 50 can then be advantageously provided in order to hold account for a possible axial clearance between these parts.
  • the hat clamp 44 is also supported at its periphery on the adjustment shim 54.
  • an anti-friction washer 56 can be disposed between the rim 52 of the opening of the casing 22 and the base of the pivot 12 of the blade.

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)
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 true EP1331402A1 (de) 2003-07-30
EP1331402B1 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
JP2010523898A (ja) * 2007-04-10 2010-07-15 エリオット・カンパニー 可変入口案内翼を有する遠心圧縮機
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

Citations (6)

* 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
US4314791A (en) * 1978-03-09 1982-02-09 Motoren- Und Turbinen-Union Munchen Gmbh Variable stator cascades for axial-flow turbines of gas turbine engines
FR2599785A1 (fr) * 1986-06-04 1987-12-11 Snecma Aubage directeur d'entree d'air a calage variable pour turboreacteur
US5024580A (en) * 1989-06-17 1991-06-18 Rolls-Royce Plc Control of variable stator vanes
US5407322A (en) * 1992-09-30 1995-04-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Variable phase vane
EP1010862A2 (de) * 1998-12-16 2000-06-21 General Electric Company Beilagscheibe und Dichtung für eine verstellbare Leitschaufel

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2253030A1 (de) * 1972-10-28 1974-05-09 Sljusarew Vorrichtung zur schaufelverstellung des leitapparats einer stroemungsmaschine
US6019574A (en) * 1998-08-13 2000-02-01 General Electric Company Mismatch proof variable stator vane
FR2814206B1 (fr) * 2000-09-18 2002-12-20 Snecma Moteurs Dispositif de commande d'aubes a calage variable

Patent Citations (6)

* 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
US4314791A (en) * 1978-03-09 1982-02-09 Motoren- Und Turbinen-Union Munchen Gmbh Variable stator cascades for axial-flow turbines of gas turbine engines
FR2599785A1 (fr) * 1986-06-04 1987-12-11 Snecma Aubage directeur d'entree d'air a calage variable pour turboreacteur
US5024580A (en) * 1989-06-17 1991-06-18 Rolls-Royce Plc Control of variable stator vanes
US5407322A (en) * 1992-09-30 1995-04-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Variable phase vane
EP1010862A2 (de) * 1998-12-16 2000-06-21 General Electric Company Beilagscheibe und Dichtung für eine verstellbare Leitschaufel

Also Published As

Publication number Publication date
RU2295655C2 (ru) 2007-03-20
FR2835294A1 (fr) 2003-08-01
EP1331402B1 (de) 2007-10-31
ES2292916T3 (es) 2008-03-16
JP4073794B2 (ja) 2008-04-09
CA2418233A1 (fr) 2003-07-29
CA2418233C (fr) 2011-05-31
US6796767B2 (en) 2004-09-28
UA79734C2 (uk) 2007-07-25
DE60317119D1 (de) 2007-12-13
JP2003227494A (ja) 2003-08-15
US20030143066A1 (en) 2003-07-31
DE60317119T2 (de) 2008-08-07
FR2835294B1 (fr) 2004-04-16

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