EP1331402A1 - Dispositif de commande d'aube variable - Google Patents
Dispositif de commande d'aube variable Download PDFInfo
- 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
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
-
- 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)
Abstract
Description
- la figure 1 est une vue en coupe longitudinale d'un dispositif de commande selon l'invention ;
- la figure 2 est une vue en coupe selon le plan II-II de la figure 1 ; et
- la figure 3 est une vue en perspective et en écorché du dispositif de commande de la figure 1.
Claims (10)
- Dispositif de commande d'aube à angle de calage variable pour redresseur de compresseur de turbomachine, comportant une biellette (30), des moyens de liaison (24, 26) formant articulation entre une première extrémité (32) de la biellette et un anneau de commande (20), et des moyens de fixation (40) d'une deuxième extrémité (34) de la biellette sur un pivot (12) d'une aube (10) à commander,
caractérisé en ce qu'il comporte en outreun évidement radial (16) pratiqué dans le pivot de l'aube et destiné à recevoir la deuxième extrémité (34) de la biellette (30), ledit évidement comportant au moins un bord plan (16a, 16b) incliné par rapport à un plan longitudinal médian (P) de l'évidement et coopérant avec un bord incliné correspondant (34a, 34b) de la deuxième extrémité de la biellette,et un chapeau de serrage (44) appliqué sur la deuxième extrémité de la biellette et sur lequel agissent les moyens de fixation (40), ledit chapeau de serrage comportant une surface interne (48a) assurant un contact plan avec la face externe (36) de la deuxième extrémité de la biellette sur laquelle est appliqué ledit chapeau de serrage pour maintenir sans jeu la deuxième extrémité (34) de la biellette (30) sur le pivot (12) de l'aube par contact entre lesdits bords inclinés. - Dispositif selon la revendication 1, caractérisé en ce que l'évidement radial (16) pratiqué dans le pivot (12) de l'aube présente deux bords plans inclinés (16a, 16b) symétriques par rapport au plan longitudinal médian (P) de l'évidement.
- Dispositif selon la revendication 1, caractérisé en ce que l'évidement radial (16) pratiqué dans le pivot (12) de l'aube présente deux bords plans inclinés (16a, 16b) asymétriques par rapport au plan longitudinal médian (P) de l'évidement.
- Dispositif selon l'une quelconque des revendications précédentes, caractérisé en ce que la surface interne (48a) du chapeau de serrage (44) comporte une rainure (48) de forme complémentaire à la face externe (36) de la deuxième extrémité (34) de la biellette (30) sur laquelle est appliqué ledit chapeau de serrage.
- Dispositif selon l'une quelconque des revendications précédentes, caractérisé en ce que la biellette (30) présente, au niveau de sa deuxième extrémité (34), une partie ayant une épaisseur plus grande que celle de sa première extrémité (32).
- Dispositif selon l'une quelconque des revendications précédentes, caractérisé en ce qu'il comporte en outre une douille (50) disposée autour du pivot (12) de l'aube et destinée à permettre un centrage du pivot de l'aube dans une ouverture d'un carter (22).
- Dispositif selon la revendication 6, caractérisé en ce qu'il comporte en outre une cale de réglage (54) interposée entre le chapeau de serrage (44) et la douille (50).
- Dispositif selon la revendication 7, caractérisé en ce le chapeau de serrage (44) s'appuie également à sa périphérie sur la cale de réglage (54).
- Dispositif de commande d'aube à angle de calage variable pour redresseur de compresseur de turbomachine, comportant une biellette (30), des moyens de liaison (24, 26) formant articulation entre une première extrémité (32) de la biellette et un anneau de commande (20), et des moyens de fixation (40) d'une deuxième extrémité (34) de la biellette sur un pivot (12) d'une aube (10) à commander,
caractérisé en ce qu'il comporte en outreun évidement radial (16) pratiqué dans le pivot de l'aube et destiné à recevoir la deuxième extrémité (34) de la biellette, ledit évidement comportant au moins un bord plan (16a, 16b) incliné par rapport à un plan longitudinal médian (P) de l'évidement et coopérant avec un bord incliné correspondant (34a, 34b) de la deuxième extrémité de la biellette,et un chapeau de serrage (44) appliqué sur la deuxième extrémité de la biellette et sur lequel agissent les moyens de fixation (40), ledit chapeau de serrage comportant, au niveau d'une surface interne (48a), une rainure (48) de forme complémentaire à la partie adjacente à la face externe (36) de la deuxième extrémité de la biellette sur laquelle est appliqué ledit chapeau de serrage pour maintenir sans jeu la deuxième extrémité (34) de la biellette (30) sur le pivot (12) de l'aube par contact entre lesdits bords inclinés. - Redresseur de compresseur de turbomachine comportant une pluralité de dispositifs de commande d'aube à angle de calage variable selon l'une quelconque des revendications précédentes.
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 (fr) | 2003-07-30 |
EP1331402B1 EP1331402B1 (fr) | 2007-10-31 |
Family
ID=8871421
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP03290058A Expired - Lifetime EP1331402B1 (fr) | 2002-01-29 | 2003-01-10 | Dispositif de commande d'aube variable |
Country Status (9)
Country | Link |
---|---|
US (1) | US6796767B2 (fr) |
EP (1) | EP1331402B1 (fr) |
JP (1) | JP4073794B2 (fr) |
CA (1) | CA2418233C (fr) |
DE (1) | DE60317119T2 (fr) |
ES (1) | ES2292916T3 (fr) |
FR (1) | FR2835294B1 (fr) |
RU (1) | RU2295655C2 (fr) |
UA (1) | UA79734C2 (fr) |
Families Citing this family (6)
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 |
Citations (6)
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 (fr) * | 1998-12-16 | 2000-06-21 | General Electric Company | Rondelle et joint pour une aube variable |
Family Cites Families (3)
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 |
-
2002
- 2002-01-29 FR FR0201022A patent/FR2835294B1/fr not_active Expired - Fee Related
-
2003
- 2003-01-10 EP EP03290058A patent/EP1331402B1/fr not_active Expired - Lifetime
- 2003-01-10 DE DE60317119T patent/DE60317119T2/de not_active Expired - Lifetime
- 2003-01-10 ES ES03290058T patent/ES2292916T3/es not_active Expired - Lifetime
- 2003-01-24 JP JP2003016009A patent/JP4073794B2/ja not_active Expired - Fee Related
- 2003-01-27 CA CA2418233A patent/CA2418233C/fr not_active Expired - Fee Related
- 2003-01-28 RU RU2003102522/06A patent/RU2295655C2/ru not_active IP Right Cessation
- 2003-01-28 UA UA2003010766A patent/UA79734C2/uk unknown
- 2003-01-28 US US10/352,123 patent/US6796767B2/en not_active Expired - Lifetime
Patent Citations (6)
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 (fr) * | 1998-12-16 | 2000-06-21 | General Electric Company | Rondelle et joint pour une aube variable |
Also Published As
Publication number | Publication date |
---|---|
JP4073794B2 (ja) | 2008-04-09 |
CA2418233C (fr) | 2011-05-31 |
FR2835294B1 (fr) | 2004-04-16 |
JP2003227494A (ja) | 2003-08-15 |
US6796767B2 (en) | 2004-09-28 |
CA2418233A1 (fr) | 2003-07-29 |
UA79734C2 (uk) | 2007-07-25 |
RU2295655C2 (ru) | 2007-03-20 |
ES2292916T3 (es) | 2008-03-16 |
US20030143066A1 (en) | 2003-07-31 |
EP1331402B1 (fr) | 2007-10-31 |
FR2835294A1 (fr) | 2003-08-01 |
DE60317119T2 (de) | 2008-08-07 |
DE60317119D1 (de) | 2007-12-13 |
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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 |
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17P | Request for examination filed |
Effective date: 20030117 |
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Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PT SE SI SK TR |
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AX | Request for extension of the european patent |
Extension state: AL LT LV MK RO |
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AKX | Designation fees paid |
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