EP0947668A1 - Etage circulaire d'aubes de turbomachine aux extrémités intérieures unies par un anneau de liaison - Google Patents
Etage circulaire d'aubes de turbomachine aux extrémités intérieures unies par un anneau de liaison Download PDFInfo
- Publication number
- EP0947668A1 EP0947668A1 EP99400514A EP99400514A EP0947668A1 EP 0947668 A1 EP0947668 A1 EP 0947668A1 EP 99400514 A EP99400514 A EP 99400514A EP 99400514 A EP99400514 A EP 99400514A EP 0947668 A1 EP0947668 A1 EP 0947668A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- ring
- pivots
- support ring
- notches
- lips
- 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
- 230000000149 penetrating effect Effects 0.000 claims description 4
- 238000000605 extraction Methods 0.000 abstract description 2
- 238000010276 construction Methods 0.000 description 4
- 239000012634 fragment Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000014759 maintenance of location Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
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
- 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
- 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
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/14—Two-dimensional elliptical
- F05D2250/141—Two-dimensional elliptical circular
Definitions
- the invention relates to a floor circular blades with inner ends united by a connecting ring.
- Such a construction is encountered in turbomachinery for stages of blades of stator-related rectifiers: the outer ends blades are supported by the stator and inner ends by a common connecting ring to all the blades of the floor and which therefore contributes to stiffen their assembly by uniting them.
- the outer ends and inner blades consist of supported pivots in respective bearings of the stator and the ring liaison.
- This device is effective but present the disadvantage that we must provide a ring which increases the weight and the cost of machine manufacturing.
- the invention therefore relates to a device having the same effects but lacking of this inconvenience of having to add an unnecessary part moreover: it is proposed to ensure the retention of inner pivots by a structural element already present in the link ring and that we are content to modify slightly.
- the invention can be defined as a circular stage of blades having outer pivots housed in bearings of pivoting of a stator and internal pivots housed in inner pivot bearings of a ring link ;
- the connecting ring is composed of a support ring and stiffening ring interlaced, the support ring carrying the bearings of internal pivoting and the stiffening ring ends in two lips directed towards each other and penetrating in respective grooves of the support ring, the interior pivots being hollowed out with a notch; according to the invention, one of the lips extends to through the support ring and enters the gashes.
- the notches do not extend only over a sector of circumference and therefore offer a stop to the angular displacements of dawn, which is also interesting when it is broken.
- a particular embodiment is distinguishes by a construction in two sections of blade pivots for easier assembly: the lips of the stiffening ring extend over circles of two different diameters, and the pivots are formed of two sections, including an engaged journal section in a bearing socket and an enlarged section, located between the journal and a blade of the dawn, the notches being dug in the enlarged sections, the lip opposite lip penetrating notches extending in front of the trunnions.
- the machine includes an external stator 1 and at least one blade stage 2 equipped with the invention; the vanes 2 have a first pivot end outside 3 passing through the stator 1 at the location of a outer bearing 4 and an opposite end forming a inner pivot 5 engaged in a bearing 6 of a ring connecting 7 common to all the vanes 2 of the stage.
- the outer pivot 3 is provided with shoulders 8 and 9 between which the bearing 4 is retained, which limits the radial movement of blade 2 in the machine (on could also speak of axial displacement in considering the direction of pivots 3 and 5).
- the pivot outside 3 comes out of stator 1 and ends in one connection with a control lever 10 of which the other end is connected to a common control ring 11 to all the vanes 2 of the stage; the control ring 11 is arranged around stator 1, and it suffices to turn to control the rotation of the levers 10 and that of the vanes 2 around their pivots 3 and 5.
- the connecting ring 7 is essentially composed of a support ring 12, in which the bearings 6 are hollowed out, and a stiffening ring 13 wrapping part of the support ring 12.
- the reason for this construction can be explained by reference to Figure 2: we see that the ring of support 12 is not unitary but composed of sectors 14 abutments, two, four or eight in number current achievements, and that the stiffening ring 13 is the way to keep them in place. It is itself composed of two semi-circular sectors 15 and reunited with each other.
- the stiffening ring 13 has a section similar to that of a rail and having a bottom 17 under the ring support 12, sidewalls 18 partially covering the flat faces of the support ring 12 and the lips 19 and 20 located at the end of the sides 18 and 19 penetrating in grooves 22 and 23 of the connecting ring 12. As the lips 20 and 21 are directed one towards the other, they hold the stiffening ring 13 on the support ring 12 and keep them interlaced.
- the inner bearing 6 is formed by a sleeve 27 engaged through a hole in the connecting ring 12 and of which the outer surface is threaded: like the pivot interior 5 is actually composed of a pin 28 engaged in the socket 27 and a widening 29 located between the pin 28 and a blade 30 of the blade 2, we see that the setting of the connecting ring 7 is produced by screwing the sockets 27 into the holes threaded from the support ring 12 until the outer ends 31 of sockets 27 abut against the extended parts 29. This prohibits deflections and vibrations in the radial direction of the connecting ring 7.
- cylindrical lips 20 and 21 do not belong to circles of the same diameter but, as one of the flanks 19 is much wider than the other 18, the lip 21 which he wears extends in front the widened part 29, while the other comes only in front of the pin 28.
- This lip 21 is further long enough to fit into a cut 31 in the enlarged part 29, the groove 23 which is there partner crossing right through a wall of the connecting ring 12.
- the material of the enlarged part 29 which is located between the notch 31 and the pin 28 forms a rim 32 which abuts against the lip 21 in outward movement of dawn 2 due to example to a rupture of it, and opposes the extraction of the inner pivot 5. The retention of dawn is therefore assured with this construction particularly simple, in accordance with the objective announced above.
- Figure 3 completes the presentation of this invention by perhaps representing more clearly its main elements, the socket 27 having however been omitted from representation for clarity.
- the notch 31 advantageously does not extend that on a sector of circumference and therefore ends in two lateral abutment surfaces 33 which limit the angular deflection of blade 2 by touching the lip 21, which is particularly advantageous in the event of breaking of dawn 2, when the blade fragment 30 adjoining the inner pivot 5 would be feathered (i.e. would freely follow the direction of the gas flow) erratically.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Control Of Turbines (AREA)
- Synchronous Machinery (AREA)
Abstract
Description
- la figure 1 est une demi-coupe longitudinale d'un étage d'aubes de redresseur, montrant une de ces aubes ;
- la figure 2 est une vue de face de l'étage d'aubes ;
- et la figure 3 représente plus en détail l'imbrication d'un pivot intérieur d'aube dans l'anneau de support.
Claims (3)
- Etage circulaire d'aubes (2) ayant des pivots extérieurs (3) logés dans des paliers (4) de pivotement extérieurs d'un stator (1) et des pivots intérieurs (5) logés dans des paliers (6) de pivotement intérieurs d'un anneau de liaison (7) composé d'un anneau de support (12) et d'un anneau de raidissage (13) entrelacés, l'anneau de support (12) portant les paliers (6) de pivotement intérieurs et l'anneau de raidissage (13) finissant en deux lèvres (20, 21) dirigées l'une vers l'autre et pénétrant dans des rainures (22, 23) respectives de l'anneau de support (12), les pivots intérieurs (5) étant creusés d'entailles (31), caractérisé en ce qu'une desdites lèvres s'étend à travers l'anneau de support (12) et pénètre dans les entailles (31).
- Etage circulaire d'aubes suivant la revendication 1, caractérisé en ce que les entailles (31) ne s'étendent que sur un secteur de circonférence.
- Etage circulaire d'aubes suivant la revendication 1, caractérisé en ce que les lèvres (21, 22) de l'anneau de raidissage (13) s'étendent sur des cercles de deux diamètres différents, et les pivots sont formés de deux sections (28, 29), dont une section de tourillon (28) engagée dans une douille (27) du palier (6) et une section élargie (29), située entre le tourillon et une pale (30) de l'aube, les entailles (31) étant creusées dans les sections élargies (29), la lèvre (20) opposée à la lèvre (21) pénétrant dans la rainure s'étendant devant les tourillons (28).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9802675A FR2775731B1 (fr) | 1998-03-05 | 1998-03-05 | Etage circulaire d'aubes aux extremites interieures unies par un anneau de liaison |
FR9802675 | 1998-03-05 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0947668A1 true EP0947668A1 (fr) | 1999-10-06 |
EP0947668B1 EP0947668B1 (fr) | 2000-05-03 |
Family
ID=9523676
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99400514A Expired - Lifetime EP0947668B1 (fr) | 1998-03-05 | 1999-03-04 | Etage circulaire d'aubes de turbomachine aux extrémités intérieures unies par un anneau de liaison |
Country Status (6)
Country | Link |
---|---|
US (1) | US6129512A (fr) |
EP (1) | EP0947668B1 (fr) |
JP (1) | JP3877032B2 (fr) |
CA (1) | CA2263255C (fr) |
DE (1) | DE69900004T2 (fr) |
FR (1) | FR2775731B1 (fr) |
Families Citing this family (53)
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DE10016745B4 (de) * | 2000-04-04 | 2005-05-19 | Man B & W Diesel Ag | Axialströmungsmaschine mit einem eine Reihe von verstellbaren Leitschaufeln umfassenden Leitapparat |
US6547002B1 (en) * | 2000-04-17 | 2003-04-15 | Weatherford/Lamb, Inc. | High pressure rotating drilling head assembly with hydraulically removable packer |
EP1205639A1 (fr) * | 2000-11-09 | 2002-05-15 | General Electric Company | Système de fixation des aubes statoriques variables dans une virole interieure de turbines |
DE10161292A1 (de) | 2001-12-13 | 2003-06-26 | Rolls Royce Deutschland | Lagerring zur Lagerung von Schaufelfüßen von verstellbaren Statorschaufeln im Hochdruckverdichter einer Gasturbine |
US7125222B2 (en) * | 2004-04-14 | 2006-10-24 | General Electric Company | Gas turbine engine variable vane assembly |
FR2875270B1 (fr) * | 2004-09-10 | 2006-12-01 | Snecma Moteurs Sa | Retenue des clavettes de centrage des anneaux sous aubes de stator a calage variable d'un moteur a turbine a gaz |
DE102005040574A1 (de) * | 2005-08-26 | 2007-03-15 | Rolls-Royce Deutschland Ltd & Co Kg | Spaltkontrollvorrichtung für eine Gasturbine |
FR2899637B1 (fr) * | 2006-04-06 | 2010-10-08 | Snecma | Aube de stator a calage variable de turbomachine |
DE102006024085B4 (de) | 2006-05-23 | 2020-04-16 | MTU Aero Engines AG | Turboverdichter in Axialbauweise |
US7713022B2 (en) * | 2007-03-06 | 2010-05-11 | United Technologies Operations | Small radial profile shroud for variable vane structure in a gas turbine engine |
US9353643B2 (en) * | 2007-04-10 | 2016-05-31 | United Technologies Corporation | Variable stator vane assembly for a turbine engine |
US7806652B2 (en) * | 2007-04-10 | 2010-10-05 | United Technologies Corporation | Turbine engine variable stator vane |
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 |
US8500394B2 (en) * | 2008-02-20 | 2013-08-06 | United Technologies Corporation | Single channel inner diameter shroud with lightweight inner core |
US8328512B2 (en) | 2009-06-05 | 2012-12-11 | United Technologies Corporation | Inner diameter shroud assembly for variable inlet guide vane structure in a gas turbine engine |
DE102009038623B4 (de) * | 2009-08-26 | 2012-01-19 | Rolls-Royce Deutschland Ltd & Co Kg | Leitschaufelkranz für den Verdichter einer Fluggasturbine |
US8727730B2 (en) * | 2010-04-06 | 2014-05-20 | General Electric Company | Composite turbine bucket assembly |
EP2405104A1 (fr) * | 2010-07-08 | 2012-01-11 | Siemens Aktiengesellschaft | Compresseur et moteur à turbine à gaz associé |
FR2966530B1 (fr) * | 2010-10-21 | 2012-11-02 | Snecma | Etage redresseur a calage variable pour un compresseur d'une turbomachine |
US8961125B2 (en) * | 2011-12-13 | 2015-02-24 | United Technologies Corporation | Gas turbine engine part retention |
US9410443B2 (en) | 2012-01-27 | 2016-08-09 | United Technologies Corporation | Variable vane damping assembly |
EP2636849B1 (fr) * | 2012-03-05 | 2017-11-01 | MTU Aero Engines GmbH | Compresseur |
FR2988787B1 (fr) * | 2012-04-03 | 2016-01-22 | Snecma | Redresseur a calage variable pour compresseur de turbomachine comprenant deux anneaux internes |
EP2696041B1 (fr) * | 2012-08-07 | 2020-01-22 | MTU Aero Engines AG | Assemblage de stator d'une turbine à gaz et procédé de montage |
US9140133B2 (en) | 2012-08-14 | 2015-09-22 | United Technologies Corporation | Threaded full ring inner air-seal |
EP2725200B1 (fr) | 2012-10-25 | 2018-06-06 | MTU Aero Engines AG | Stator et turbomachine |
EP2725202A1 (fr) * | 2012-10-25 | 2014-04-30 | MTU Aero Engines GmbH | Agencement de support d'étanchéité d'anneau intérieur pour assemblage des aubes statoriques variables d'une turbomachine |
EP2728123A1 (fr) | 2012-11-06 | 2014-05-07 | MTU Aero Engines GmbH | Turbomachine et procédé d'assemblage associé de turbomachine |
US20140234087A1 (en) * | 2013-02-17 | 2014-08-21 | United Technologies Corporation | Inlet guide vane retention feature |
DE102013211629A1 (de) * | 2013-06-20 | 2015-01-08 | MTU Aero Engines AG | Leitschaufelanordnung und Verfahren zum Montieren einer Leitschaufel |
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 |
DE102014205986B4 (de) | 2014-03-31 | 2021-03-18 | MTU Aero Engines AG | Leitschaufelkranz und Strömungsmaschine |
US9784285B2 (en) * | 2014-09-12 | 2017-10-10 | Honeywell International Inc. | Variable stator vane assemblies and variable stator vanes thereof having a locally swept leading edge and methods for minimizing endwall leakage therewith |
GB201418321D0 (en) * | 2014-10-16 | 2014-12-03 | Rolls Royce Plc | Mounting arrangement for variable stator vane |
DE102014223975A1 (de) * | 2014-11-25 | 2016-05-25 | MTU Aero Engines AG | Leitschaufelkranz und Strömungsmaschine |
US10358932B2 (en) * | 2015-06-29 | 2019-07-23 | United Technologies Corporation | Segmented non-contact seal assembly for rotational equipment |
DE102015220371A1 (de) | 2015-10-20 | 2017-04-20 | MTU Aero Engines AG | Innenringsystem, Leitschaufelkranz und Strömungsmaschine |
DE102016215807A1 (de) * | 2016-08-23 | 2018-03-01 | MTU Aero Engines AG | Innenring für einen Leitschaufelkranz einer Strömungsmaschine |
US11168704B2 (en) | 2017-03-30 | 2021-11-09 | Mitsubishi Power, Ltd. | Variable stator vane and compressor |
DE102017109952A1 (de) * | 2017-05-09 | 2018-11-15 | Rolls-Royce Deutschland Ltd & Co Kg | Rotorvorrichtung einer Strömungsmaschine |
DE102017211316A1 (de) * | 2017-07-04 | 2019-01-10 | MTU Aero Engines AG | Turbomaschinen-Dichtring |
DE102018210601A1 (de) * | 2018-06-28 | 2020-01-02 | MTU Aero Engines AG | Segmentring zur montage in einer strömungsmaschine |
FR3085060B1 (fr) | 2018-08-17 | 2020-10-09 | Safran Aircraft Engines | Anneau de guidage d'aubes a calage variable et procede de montage dudit anneau |
DE102018213983A1 (de) * | 2018-08-20 | 2020-02-20 | MTU Aero Engines AG | Verstellbare Leitschaufelanordnung, Leitschaufel, Dichtungsträger und Turbomaschine |
US10808568B2 (en) | 2018-09-12 | 2020-10-20 | Raytheon Technologies Corporation | Airfoil assembly for a gas turbine engine |
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 |
FR3115818B1 (fr) * | 2020-10-30 | 2023-10-20 | Safran Aircraft Engines | Soufflante de turbomachine comprenant des pales à calage variable |
CN112065777B (zh) * | 2020-11-10 | 2021-01-19 | 中国航发上海商用航空发动机制造有限责任公司 | 压气机进口导流叶片的调节精度保持结构 |
US11549388B2 (en) * | 2021-01-18 | 2023-01-10 | Raytheon Technologies Corporation | Inner shroud assembly for gas turbine engine variable vane system |
FR3123885B1 (fr) * | 2021-06-15 | 2023-06-16 | Safran Aircraft Engines | Redresseur non carene de turbomachine equipe d’aubes de stator fixees a des pivots et turbomachine correspondante |
DE102021120384A1 (de) * | 2021-08-05 | 2023-02-09 | MTU Aero Engines AG | Leitschaufelkranz für eine Strömungsmaschine, Strömungsmaschine und Verfahren zum Montieren eines Leitschaufelkranzes |
US12078071B1 (en) * | 2023-02-21 | 2024-09-03 | Rolls-Royce Corporation | Segmented compressor inner band for variable vanes in gas turbine engines |
US11879480B1 (en) | 2023-04-07 | 2024-01-23 | Rolls-Royce North American Technologies Inc. | Sectioned compressor inner band for variable pitch vane assemblies in gas turbine engines |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3079128A (en) * | 1961-01-23 | 1963-02-26 | Burge Joseph | Sealing and securing means for turbomachine blading |
US3224194A (en) * | 1963-06-26 | 1965-12-21 | Curtiss Wright Corp | Gas turbine engine |
FR2723614A1 (fr) * | 1994-08-10 | 1996-02-16 | Snecma | Dispositif d'assemblage d'un etage circulaire d'aubes pivotantes. |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3567331A (en) * | 1969-07-25 | 1971-03-02 | Gen Motors Corp | Variable vane cascades |
FR2685033B1 (fr) * | 1991-12-11 | 1994-02-11 | Snecma | Stator dirigeant l'entree de l'air a l'interieur d'une turbomachine et procede de montage d'une aube de ce stator. |
FR2742799B1 (fr) * | 1995-12-20 | 1998-01-16 | Snecma | Palier d'extremite interne d'aube pivotante |
-
1998
- 1998-03-05 FR FR9802675A patent/FR2775731B1/fr not_active Expired - Fee Related
-
1999
- 1999-02-19 US US09/252,821 patent/US6129512A/en not_active Expired - Lifetime
- 1999-02-22 JP JP04317499A patent/JP3877032B2/ja not_active Expired - Lifetime
- 1999-03-01 CA CA002263255A patent/CA2263255C/fr not_active Expired - Lifetime
- 1999-03-04 DE DE69900004T patent/DE69900004T2/de not_active Expired - Lifetime
- 1999-03-04 EP EP99400514A patent/EP0947668B1/fr not_active Expired - Lifetime
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3079128A (en) * | 1961-01-23 | 1963-02-26 | Burge Joseph | Sealing and securing means for turbomachine blading |
US3224194A (en) * | 1963-06-26 | 1965-12-21 | Curtiss Wright Corp | Gas turbine engine |
FR2723614A1 (fr) * | 1994-08-10 | 1996-02-16 | Snecma | Dispositif d'assemblage d'un etage circulaire d'aubes pivotantes. |
Also Published As
Publication number | Publication date |
---|---|
JP3877032B2 (ja) | 2007-02-07 |
EP0947668B1 (fr) | 2000-05-03 |
CA2263255C (fr) | 2009-02-24 |
FR2775731A1 (fr) | 1999-09-10 |
DE69900004D1 (de) | 2000-06-08 |
JPH11315702A (ja) | 1999-11-16 |
US6129512A (en) | 2000-10-10 |
DE69900004T2 (de) | 2001-03-01 |
FR2775731B1 (fr) | 2000-04-07 |
CA2263255A1 (fr) | 1999-09-05 |
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Legal Events
Date | Code | Title | Description |
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