EP0696675B1 - Dispositif d'assemblage d'un étage circulaire d'aubes pivotantes - Google Patents
Dispositif d'assemblage d'un étage circulaire d'aubes pivotantes Download PDFInfo
- Publication number
- EP0696675B1 EP0696675B1 EP95401862A EP95401862A EP0696675B1 EP 0696675 B1 EP0696675 B1 EP 0696675B1 EP 95401862 A EP95401862 A EP 95401862A EP 95401862 A EP95401862 A EP 95401862A EP 0696675 B1 EP0696675 B1 EP 0696675B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- guide vanes
- pivots
- assembling
- circular stage
- ring
- 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
Links
Images
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
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/14—Two-dimensional elliptical
- F05D2250/141—Two-dimensional elliptical circular
Definitions
- the invention relates to a device assembling a circular stage of pivoting vanes, often called variable pitch vanes and which found in a large number of modern turbomachines, usually on the first stages of the compressor, so to modify the gas flow characteristics according to the speeds of the machine.
- the pivoting blades of the same stage are in general controlled by a common compound device a control ring and connecting rods hinged to the control ring and at the different blades and located around the blades, outside the stator which delimits the gas flow stream through which the blades extend; the other ends of the blades, adjacent to the rotor, are joined by an assembly annular.
- This assembly was traditionally composed of two rings, one upstream and the other in downstream, which were brought together and assembled by bolts so as to trap the pivots between them vanes and bushings for pivoting. This solution was disadvantageous because of the number relatively large of bolts that was needed to the assembly of the rings and the additional weight which resulted.
- US-A-4,395,195 describes a system for retaining the internal ends of blades pivoting composed of two groups of overlapping annular segments in the direction of the circumference, the internal segments joining at mid-length external segments.
- the internal segments which are nested in the external segments are drilled and supported by individual washers associated with pivot grooves the ends of the pivoting vanes by preventing it from sliding and moving in the radial direction.
- the annular structure can be separate from the rail or integrated into it.
- the ring is advantageously continuous and the days are then of suitable forms so that one can mount the pivots in the ring.
- the days are slots opening on one side of the ring or recesses comprising parts enlarged by which you can slide the intact parts, not notched by the grooves of the pivots.
- the device constituting the invention and the adjacent parts of the machine are shown completely in Figures 1 and 2.
- the vanes 1 with timing variable are distributed in circular stages between stages of the same shape of rotor blades 2 rigidly linked to a rotor 3.
- the blades 1 are assigned to the flow straightening and are finished at the exterior by a control pivot 4 which passes through a stator cover 5 and ends outside of this by a hexagonal or square head 6 on which one engaged an operating key 7, to the end of a control rod 8 of which the other end slides through a pivoting shaft end 9 a control ring 10, the rotation of which around the machine axis rotates the connecting rods control 8 and the vanes 1 of the whole stage.
- the vanes 1 are finished at their end opposite by a guide pivot 11 rotating in a bush 12 provided with circular shoulders 13 and 14 with its two ends.
- the sleeve 12 is engaged in the holes 15 of a compound retaining ring 16, as seen in Figure 2, sectors 17 completed at their ends in the angular direction by a half of drilling. When sectors 17 are assembled, the drilling halves come together to form holes 15 complete in which the sockets 12 and the pivots 11 are trapped.
- Sectors 17 are not not directly connected to each other, but strung in a rail 18 composed of two half-rings 19 attached between them by 20 bolts at their junctions.
- the rail 18 has substantially a trough section forming a hollow 21. It is composed of a bottom 22 of edges of which stand two sides 23 and 24 of which each has a rim 25 or 26 which projects above from the bottom 22 and which surrounds a ledge, 27 or 28 respectively, outside sectors 17 to imprison them.
- the sidewall 23 further comprises a internal rim 29, and the rim 27 and the flange 13 are trapped between the edges 25 and 29; and one outer edge 30 is arranged on the other side of the sectors 17 so that the rim 26 is trapped between the flanges 28 and 30 which are parallel.
- the bottom 22 carries a layer of material 31 called abradable, i.e. easy to wear or erode, on its internal face, in front of wipers 32 in the form of circular ridge, which stand up from the rotor 3.
- abradable i.e. easy to wear or erode
- wipers 32 touch easy wear material 31 during the service of the machine, rub on it and wear it out by shaping it to their shape leaving subsist that a very slight game that almost opposes perfect for leaks at this point in the machine.
- a ring 33 is housed in the recess 21 and engaged in grooves 34 pivots 11.
- the ring 33 is continuous over its entire circumference and therefore common to all pivots 11.
- Figure 3 shows a concrete example of realization which makes it possible to carry out the assembly: the ring 33 is provided with 35 days composed of a part wide 36, with a diameter greater than that of the pivots 11, which can therefore be engaged through the ring 33 at this place, and a narrow part 37 whose width is less than the diameter of the pivots 11 but greater than throat bottom diameter 34.
- the narrow parts 37 and wide 36 of each day 35 are contiguous and successive on the circumference of the ring 33, a rotational movement of the ring 33 allows, after having driven the pivots 11 through the parts wide 36 so that the grooves 34, 33 arrive at height of the ring 33, to send the edges 38 of the narrow parts 37 in the grooves 34 to retain thus the vanes 1 in the radial direction of the machine.
- Figure 4 shows that other designs are possible to ensure the same holding effect, and that especially the 35 days in form of recesses in the center of the ring 33 can be replaced by slots 39 whose width is identical to that of the narrow parts 37 and which extend sideways to one of the edges of the ring 33.
- the ring 33 is then embedded in the grooves 34 by a movement in the axis of the machine.
- FIG. 6 shows a variant where the rail 18 'is modified: the side 23 is absent and the other flank 24 'is different because its edge 26' is oriented towards the outside of the recess 21; ledges 28 ' and 30 'of sectors 17' of ring 16 'are then directed into the interior of the assembly to trap this rim 26 '.
- Side 23 is replaced by an extension 50 of sectors 17 'at this location so keep the junction with the 18 'rail and cover the hollow 21.
- the bottom 22 of the rail 18 is now provided with a flange 51 oriented towards the outside of the assembly and engaged between two overlapping edges 52 and 53 of the extension 50.
- the ring 33 separated from the rail 18 can be guaranteed against accidental displacement in service which could cause disassembly of the assembly.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Description
- la figure 1 est une vue d'une première réalisation de l'invention,
- la figure 2 est une vue de côté de la figure 1 selon la ligne II-II,
- les figures 3 et 4 représentent deux réalisations de l'anneau, et
- les figures 5 et 6 représentent deux autres réalisations possibles pour l'invention.
Claims (8)
- Dispositif d'assemblage d'un étage circulaire d'aubes (1) pivotantes, comprenant un ensemble de secteurs (17, 17') joints en anneau (16, 16') et munis d'évidements (15) pour loger des douilles (12) de support pivotant de pivots (11) des aubes (1) et des gorges (34) dans ces pivots (11), un rail annulaire (18, 18') sur lequel les secteurs sont retenus, caractérisé par une structure (33, 43) annulaire pourvue de jours (35, 39, 47), des parties (38, 48) de la structure annulaire adjacentes aux jours étant engagées dans lesdites gorges (34) des pivots (11).
- Dispositif d'assemblage d'un étage circulaire d'aubes pivotantes selon la revendication 1, caractérisé en ce que le rail est à section en creux (21) et comprend une partie de fond (22) recouvrant les pivots (11), la structure annulaire (33, 43) étant disposée entre le fond (22) et les secteurs (17, 17').
- Dispositif d'assemblage d'un étage circulaire d'aubes pivotantes selon la revendication 2, caractérisé en ce que la partie de fond (22) porte une couche de matière d'usure facile (31) appartenant à un dispositif d'étanchéité (32).
- Dispositif d'assemblage d'un étage circulaire d'aubes pivotantes selon l'une quelconque des revendications 1 à 3, caractérisé en ce que la structure annulaire (33) est un anneau continu distinct du rail (18).
- Dispositif d'assemblage d'un étage circulaire d'aubes pivotantes selon la revendication 4, caractérisé en ce que les jours sont composés de deux portions adjacentes dont la première (36) est plus large que le diamètre des pivots et la seconde (37) plus étroite que le diamètre des pivots (11), sauf aux gorges (34).
- Dispositif d'assemblage d'un étage circulaire d'aubes pivotantes selon la revendication 4, caractérisé en ce que les jours (39) sont des fentes débouchant sur un des côtés de l'anneau.
- Dispositif d'assemblage d'un étage circulaire d'aubes pivotantes selon l'une quelconque des revendications 1 à 3, caractérisé en ce que la structure annulaire (43) est intégrée au rail (18, 18').
- Dispositif d'assemblage d'un étage circulaire d'aubes pivotantes selon les revendications 2 et 7, caractérisé en ce que la structure annulaire a une section en double cornière, les cornières (44) étant chacune composées d'une première âme (45) s'élevant du fond (22) et d'une seconde âme (46), les premières âmes étant parallèles et les secondes âmes étant cocylindriques et dirigées l'une vers l'autre à partir des premières âmes.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9409867A FR2723614B1 (fr) | 1994-08-10 | 1994-08-10 | Dispositif d'assemblage d'un etage circulaire d'aubes pivotantes. |
FR9409867 | 1994-08-10 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0696675A1 EP0696675A1 (fr) | 1996-02-14 |
EP0696675B1 true EP0696675B1 (fr) | 1998-09-30 |
Family
ID=9466205
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP95401862A Expired - Lifetime EP0696675B1 (fr) | 1994-08-10 | 1995-08-09 | Dispositif d'assemblage d'un étage circulaire d'aubes pivotantes |
Country Status (4)
Country | Link |
---|---|
US (1) | US5636968A (fr) |
EP (1) | EP0696675B1 (fr) |
DE (1) | DE69505074T2 (fr) |
FR (1) | FR2723614B1 (fr) |
Families Citing this family (48)
Publication number | Priority date | Publication date | Assignee | Title |
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US6189682B1 (en) * | 1995-05-31 | 2001-02-20 | David A. Hill | Position control apparatus and method for controlling the movement of a block in a woodworking machine |
DE19752534C1 (de) * | 1997-11-27 | 1998-10-08 | Daimler Benz Ag | Radialdurchströmte Abgasturboladerturbine |
FR2775731B1 (fr) | 1998-03-05 | 2000-04-07 | Snecma | Etage circulaire d'aubes aux extremites interieures unies par un anneau de liaison |
US6019574A (en) * | 1998-08-13 | 2000-02-01 | General Electric Company | Mismatch proof variable stator vane |
EP1205639A1 (fr) * | 2000-11-09 | 2002-05-15 | General Electric Company | Système de fixation des aubes statoriques variables dans une virole interieure de turbines |
US6413043B1 (en) * | 2000-11-09 | 2002-07-02 | General Electric Company | Inlet guide vane and shroud support contact |
DE10161292A1 (de) | 2001-12-13 | 2003-06-26 | Rolls Royce Deutschland | Lagerring zur Lagerung von Schaufelfüßen von verstellbaren Statorschaufeln im Hochdruckverdichter einer Gasturbine |
US6843638B2 (en) * | 2002-12-10 | 2005-01-18 | Honeywell International Inc. | Vane radial mounting apparatus |
GB2400416B (en) * | 2003-04-12 | 2006-08-16 | Rolls Royce Plc | Improvements in or relating to control of variable stator vanes in a gas turbine engine |
US7255530B2 (en) * | 2003-12-12 | 2007-08-14 | Honeywell International Inc. | Vane and throat shaping |
US7125222B2 (en) | 2004-04-14 | 2006-10-24 | General Electric Company | Gas turbine engine variable vane assembly |
US7387370B2 (en) * | 2004-04-29 | 2008-06-17 | Hewlett-Packard Development Company, L.P. | Microfluidic architecture |
FR2874977A1 (fr) * | 2004-09-07 | 2006-03-10 | Snecma Moteurs Sa | Douille de support pivotant pour pivot d'aube a calage variable de turbomachine |
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 |
DE102005042747A1 (de) * | 2005-09-05 | 2007-03-08 | Rolls-Royce Deutschland Ltd & Co Kg | Leitschaufelkranz 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 |
US7806652B2 (en) * | 2007-04-10 | 2010-10-05 | United Technologies Corporation | Turbine engine variable stator vane |
US7854586B2 (en) * | 2007-05-31 | 2010-12-21 | United Technologies Corporation | Inlet guide vane inner air seal surge retaining mechanism |
DE102008021683A1 (de) * | 2008-04-30 | 2009-11-05 | Rolls-Royce Deutschland Ltd & Co Kg | Rotierende Einheit für einen Axialkompressor |
DE102009038623B4 (de) * | 2009-08-26 | 2012-01-19 | Rolls-Royce Deutschland Ltd & Co Kg | Leitschaufelkranz für den Verdichter einer Fluggasturbine |
EP2405104A1 (fr) * | 2010-07-08 | 2012-01-11 | Siemens Aktiengesellschaft | Compresseur et moteur à turbine à gaz associé |
EP2728123A1 (fr) * | 2012-11-06 | 2014-05-07 | MTU Aero Engines GmbH | Turbomachine et procédé d'assemblage associé de turbomachine |
EP2735707B1 (fr) * | 2012-11-27 | 2017-04-05 | Safran Aero Boosters SA | Redresseur de turbomachine axiale avec virole interne segmentée et compresseur associé |
US20140234087A1 (en) * | 2013-02-17 | 2014-08-21 | United Technologies Corporation | Inlet guide vane retention feature |
EP2787177B1 (fr) * | 2013-04-02 | 2017-01-18 | MTU Aero Engines AG | Turbomachine axiale et procédé de montage |
EP2787180A1 (fr) * | 2013-04-04 | 2014-10-08 | MTU Aero Engines GmbH | Agencement d'aubes directrices pour une turbomachine |
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 |
US9790806B2 (en) | 2014-06-06 | 2017-10-17 | United Technologies Corporation | Case with vane retention feature |
DE102014223975A1 (de) * | 2014-11-25 | 2016-05-25 | MTU Aero Engines AG | Leitschaufelkranz und Strömungsmaschine |
EP3170987B1 (fr) * | 2015-11-17 | 2020-02-19 | MTU Aero Engines GmbH | Système de bague intérieure pour turbomachine |
US10393145B2 (en) | 2016-03-02 | 2019-08-27 | General Electric Company | Asymmetric alignment system for a variable stator vane |
DE102016215807A1 (de) * | 2016-08-23 | 2018-03-01 | MTU Aero Engines AG | Innenring für einen Leitschaufelkranz einer Strömungsmaschine |
EP3315729A1 (fr) | 2016-10-26 | 2018-05-02 | MTU Aero Engines GmbH | Palier d'aube directrice interne ellipsoïde |
DE102017109952A1 (de) * | 2017-05-09 | 2018-11-15 | Rolls-Royce Deutschland Ltd & Co Kg | Rotorvorrichtung einer Strömungsmaschine |
DE102017222209A1 (de) * | 2017-12-07 | 2019-06-13 | MTU Aero Engines AG | Leitschaufelanbindung sowie Strömungsmaschine |
DE102018202119A1 (de) | 2018-02-12 | 2019-08-14 | MTU Aero Engines AG | Hebelanbindung einer Leitschaufelverstellung für Strömungsmaschinen |
DE102018203442A1 (de) | 2018-03-07 | 2019-09-12 | MTU Aero Engines AG | Innenring für eine Turbomaschine, Leitschaufelkranz mit einem Innenring, Turbomaschine und Verfahren zur Herstellung eines Innenrings |
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 |
US10746041B2 (en) | 2019-01-10 | 2020-08-18 | Raytheon Technologies Corporation | Shroud and shroud assembly process for variable vane assemblies |
CN110656981B (zh) * | 2019-10-09 | 2022-03-25 | 莱芜钢铁集团有限公司 | 一种trt静叶可调机构定位方法 |
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 |
US11624293B2 (en) * | 2021-02-08 | 2023-04-11 | Pratt & Whitney Canada Corp. | Variable guide vane assembly and bushing therefor |
DE102021120384A1 (de) * | 2021-08-05 | 2023-02-09 | MTU Aero Engines AG | Leitschaufelkranz für eine Strömungsmaschine, Strömungsmaschine und Verfahren zum Montieren eines Leitschaufelkranzes |
DE102021129534A1 (de) * | 2021-11-12 | 2023-05-17 | MTU Aero Engines AG | Leitschaufelanordnung einer Strömungsmaschine und Verfahren zur Montage einer Leitschaufelanordnung |
Family Cites Families (12)
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US3079128A (en) * | 1961-01-23 | 1963-02-26 | Burge Joseph | Sealing and securing means for turbomachine blading |
DE2152365C3 (de) * | 1971-02-03 | 1973-12-06 | Carrier Corp., Syracuse, N.Y. (V.St.A.) | Einrichtung zum Lagern der inneren Enden von drehbar gelagerten Leitschaufeln einer Axial Stromungs maschine |
US4395195A (en) * | 1980-05-16 | 1983-07-26 | United Technologies Corporation | Shroud ring for use in a gas turbine engine |
FR2556410B1 (fr) * | 1983-12-07 | 1986-09-12 | Snecma | Dispositif de centrage de l'anneau interieur d'un stator a ailettes a calage variable |
GB2151309B (en) * | 1983-12-15 | 1987-10-21 | Gen Electric | Variable turbine nozzle guide vane support |
US4792277A (en) * | 1987-07-08 | 1988-12-20 | United Technologies Corporation | Split shroud compressor |
US4834613A (en) * | 1988-02-26 | 1989-05-30 | United Technologies Corporation | Radially constrained variable vane shroud |
FR2648182B1 (fr) * | 1989-06-07 | 1991-08-30 | Snecma | Systeme de verrouillage provisoire de positionnement d'aubes a calage variable pendant le montage et turbomachine le comportant |
CA2082709A1 (fr) * | 1991-12-02 | 1993-06-03 | Srinivasan Venkatasubbu | Aubage de stator a incidence variable pour compresseur a ecoulement axial de turbomachine |
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. |
FR2708311B1 (fr) * | 1993-07-28 | 1995-09-01 | Snecma | Stator de turbomachine à aubes pivotantes et anneau de commande. |
US5492446A (en) * | 1994-12-15 | 1996-02-20 | General Electric Company | Self-aligning variable stator vane |
-
1994
- 1994-08-10 FR FR9409867A patent/FR2723614B1/fr not_active Expired - Fee Related
-
1995
- 1995-07-27 US US08/508,169 patent/US5636968A/en not_active Expired - Lifetime
- 1995-08-09 DE DE69505074T patent/DE69505074T2/de not_active Expired - Lifetime
- 1995-08-09 EP EP95401862A patent/EP0696675B1/fr not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
FR2723614A1 (fr) | 1996-02-16 |
US5636968A (en) | 1997-06-10 |
EP0696675A1 (fr) | 1996-02-14 |
DE69505074T2 (de) | 1999-03-11 |
FR2723614B1 (fr) | 1996-09-13 |
DE69505074D1 (de) | 1998-11-05 |
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