EP1265031A1 - Fixation de casquettes métalliques sur des parois de chambre de combustion CMC de turbomachine - Google Patents
Fixation de casquettes métalliques sur des parois de chambre de combustion CMC de turbomachine Download PDFInfo
- Publication number
- EP1265031A1 EP1265031A1 EP02291360A EP02291360A EP1265031A1 EP 1265031 A1 EP1265031 A1 EP 1265031A1 EP 02291360 A EP02291360 A EP 02291360A EP 02291360 A EP02291360 A EP 02291360A EP 1265031 A1 EP1265031 A1 EP 1265031A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- walls
- axial
- external
- internal
- 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
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2211/00—Thermal dilatation prevention or compensation
Definitions
- the present invention relates to the specific field of turbomachinery and it is more particularly interested in the problem posed by the mounting of a metal bottom of the combustion chamber of a turbomachine on walls made of CMC type composite material (ceramic matrix composite) from this room.
- the turbine high pressure including its inlet distributor (HPT nozzle), the system the combustion chamber as well as the casing (also called casing) of this chamber are made of metallic type materials.
- HPT nozzle inlet distributor
- the system the combustion chamber as well as the casing (also called casing) of this chamber are made of metallic type materials.
- the use of a chamber entirely metallic proves from a thermal point of view totally unsuitable and it must be resorted to a chamber made from high composite materials CMC type temperature.
- these materials being very expensive and of low resistance to high mechanical stress, their use is most often limited to the combustion chamber itself and more particularly to its only axial walls, the inlet distributor of the high pressure turbine, the injection system and the remaining casing then produced more conventionally in metallic materials.
- Gold, metallic materials and composite materials have very different coefficients of thermal expansion. This results in particularly acute problems, particularly with regard to the connection between composite material walls of the combustion chamber and the chamber bottom metallic.
- the present invention overcomes these drawbacks by proposing an assembly of metal chamber bottom capable of absorbing induced displacements by the differences in the expansion coefficients between this metallic background and the composite walls of the combustion chamber.
- An object of the invention is also to produce an assembly having good dynamic strength and good sealing.
- annular combustion chamber comprising external and internal axial walls of composite material and a chamber bottom of metallic material, said chamber bottom being held in position on said external external and internal walls by fixing means, characterized in that said fixing means pass through annular cavities intended to receive cylindrical end portions of said external and internal axial walls and created between peripheral edges of said chamber bottom and backward facing parts facing them, a determined clearance J between said peripheral edges and the facing faces of said external and internal axial walls being provided so as to allow in operation a free radial expansion of said chamber bottom relative to said axial walls.
- the fixing means consist of a plurality of bolts, of preferably with captive nut.
- the external and internal axial walls are provided with a plurality of holes intended to cooperate with said fixing means once these mounted on said chamber bottom.
- this chamber bottom can further include means for sealing between said bottom of chamber and said axial walls.
- These sealing means include a seal circular type "lamellae" mounted in a circular groove of said bottom metal chamber and intended to ensure support on said axial wall of the combustion chamber opposite.
- said circular joint "to slats” has in its downstream part a spoiler intended to provide support O-ring on said axial wall opposite the combustion chamber. He must be segmented and it is kept in abutment against said axial wall by means of a elastic element fixed on said metal chamber bottom. This elastic element consists of a leaf spring.
- the chamber bottom can integrate in addition internal and external metallic material caps which extend upstream its peripheral edges and allow better control of the dynamic outfit.
- the fairing (or cap) outer 34 extending upstream (relative to the flow F) the outer wall 26 of the combustion chamber and the internal fairing (or cap) 36 extending upstream (relative to flow F) the internal wall 28 of the combustion are directly integrated into the bottom of the chamber 30 and are therefore made of metallic material (thereby simplifying the general shape of the upstream ends of the combustion chamber which can therefore be formed by simple cylindrical parts).
- a configuration with a fairing (single monobloc cap in toric shape) connecting the two ends upstream walls of the combustion chamber (and then provided with openings for the passage of the injection nozzles 22) is also possible.
- the metallic annular bottom 30 of the combustion which has a coefficient of thermal expansion very different from that of external axial 26 and internal 28 walls made of composite material of the combustion, is kept in position on the upstream cylindrical ends of the axial walls by a plurality of fixing means 38, 40 regularly distributed around the longitudinal axis 10.
- These fixing means pass through annular cavities 42, 44, intended to receive the cylindrical end portions of these axial walls, and created between peripheral edges of the chamber bottom 30 and opposite parts 46, 48 extending the caps 34, 36 towards downstream.
- the fixing means 38, 40 are formed by a plurality of metal bolts of the captive nut type, i.e. each comprising a screw 38a, a nut 38b and a stop cage 38c fixed on the chamber bottom 30 (advantageously by spot welding) and ensuring rotation lock of the nut.
- the tightening when mounting
- the screw is obtained directly by simply screwing in the screw without the need for the use of special tools for immobilizing the nut in rotation (pliers for example), this being obtained very simply by the single cage Stop.
- disassembly can also be done very simply so reverse by simply loosening the screw.
- a clearance J between the internal faces of the external axial 28 and internal 26 walls and the peripheral edges opposite the chamber bottom 30 is calculated so as to allow in operation a free expansion of the metal cap relative to these axial walls of composite material .
- This play in fact makes it possible to absorb the expansions of the chamber bottom without damaging the axial composite walls which move little radially.
- the system of double centering of the external 26 and internal 28 walls in the corresponding cavities 42, 44 makes it possible to ensure a relative tightness of the chamber bottom while also serving for the axial maintenance during mounting (cold) as during the flight phases. at cruising speed (hot).
- these are provided with holes 26a, 28b intended to receive sockets 38d, 40d crossed by the screw axes of the fixing means 38, 40 previously mounted on the chamber bottom, the permanent contact of the screws with the cap 34, 36 limiting the risk of losing the tightening torque during this assembly.
- These sockets on which the axial walls 26, 28 will slide when the bottom expands chamber 30 further promote the centering and support of these axial walls.
- FIG. 2 generally illustrates a second embodiment example the detail of which is shown in Figure 2a and in which to ensure better sealing between the external axial wall 26 or internal wall 28 and the chamber bottom 30, a “lamellar” type circular seal 50, 52 is mounted in a circular groove 54, 56 made at the end of the downstream return part 46, 48 of the cap external 34 or internal 36.
- This seal comprises in its downstream part a spoiler 58, 60 intended to ensure an O-ring support on the opposite axial wall 26, 28 of the combustion chamber.
- the seal is pressed against the wall by an element elastic 62, 64, preferably a leaf spring, and held in position by a plurality of pins 66, 68 integral with the downstream end of the cap.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Gasket Seals (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- la figure 1 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine incorporant un premier exemple de réalisation d'un assemblage selon l'invention,
- la figure la montre un détail de l'assemblage de la figure 1,
- la figure 2 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine incorporant un second exemple de réalisation d'un assemblage selon l'invention, et
- la figure 2a montre un détail de l'assemblage de la figure 2.
- une enveloppe annulaire externe (ou carter externe) 12, d'axe longitudinal 10,
- une enveloppe annulaire interne (ou carter interne) coaxiale 14,
- un espace annulaire 16 compris entre les deux enveloppes 12 et 14 recevant le comburant comprimé, généralement de l'air, provenant en amont d'un compresseur (non représenté) de la turbomachine, au travers d'un conduit annulaire de diffusion 18 (on notera la présence de la grille de diffusion 18a) définissant un flux général F d'écoulement des gaz,
Claims (10)
- Chambre de combustion annulaire comportant des parois axiales externe (26) et interne (28) en matériau composite et un fond de chambre (30) en matériau métallique, ledit fond de chambre étant maintenu en position sur lesdites parois axiales externe et interne par des moyens de fixation (38, 40), caractérisée en ce que lesdits moyens de fixation traversent des cavités annulaires (42, 44) destinées à recevoir des parties cylindriques d'extrémité desdites parois axiales externe et interne et créées entre des bords périphériques dudit fond de chambre et des parties en retour vers l'aval (46, 48) leur faisant face, un jeu déterminé J entre lesdits bords périphériques et les faces en regard desdites parois axiales externe et interne étant prévu de façon à permettre en fonctionnement une libre dilatation radiale dudit fond de chambre par rapport auxdites parois axiales.
- Chambre de combustion selon la revendication 1, caractérisée en ce que lesdits moyens de fixation sont constitués par une pluralité de boulons, de préférence à écrou prisonnier.
- Chambre de combustion selon la revendication 1, caractérisée en ce que lesdites parois axiales externe et interne sont pourvues d'une pluralité de trous (26a, 28b) destinés à coopérer avec lesdits moyens de fixation une fois ceux-ci montés sur ledit fond de chambre.
- Chambre de combustion selon la revendication 1, caractérisée en ce que ledit fond de chambre comporte en outre des moyens (50-68) pour assurer l'étanchéité entre ledit fond de chambre et lesdites parois axiales.
- Chambre de combustion selon la revendication 4, caractérisée en ce que lesdits moyens d'étanchéité comportent un joint circulaire de type « à lamelles » (50, 52) monté dans une gorge circulaire (54, 56) dudit fond de chambre métallique et destiné à assurer un appui sur ladite paroi axiale en regard de la chambre de combustion en regard.
- Chambre de combustion selon la revendication 5, caractérisée en ce que ledit joint circulaire « à lamelles » comporte dans sa partie aval un béquet (58, 60) destiné à assurer un appui torique sur ladite paroi axiale en regard de la chambre de combustion.
- Chambre de combustion selon la revendication 5, caractérisée en ce que ledit joint circulaire d'étanchéité est sectorisé.
- Chambre de combustion selon la revendication 5, caractérisée en ce que ledit joint circulaire d'étanchéité est maintenu en appui contre ladite paroi axiale au moyen d'un élément élastique (62, 64) fixé sur ledit fond de chambre métallique.
- Chambre de combustion selon la revendication 8, caractérisée en ce que ledit élément élastique est constitué par un ressort à lames.
- Chambre de combustion selon la revendication 1, caractérisée en ce que ledit fond de chambre intègre des casquettes interne et externe en matériau métallique (34, 36) qui prolongent vers l'amont ses bords périphériques.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0107374 | 2001-06-06 | ||
FR0107374A FR2825786B1 (fr) | 2001-06-06 | 2001-06-06 | Fixation de casquettes metalliques sur des parois de chambre de combustion cmc de turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1265031A1 true EP1265031A1 (fr) | 2002-12-11 |
EP1265031B1 EP1265031B1 (fr) | 2007-09-12 |
Family
ID=8863995
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02291360A Expired - Lifetime EP1265031B1 (fr) | 2001-06-06 | 2002-06-04 | Fixation de casquettes métalliques sur des parois de chambre de combustion CMC de turbomachine |
Country Status (5)
Country | Link |
---|---|
US (1) | US6655148B2 (fr) |
EP (1) | EP1265031B1 (fr) |
JP (1) | JP3984104B2 (fr) |
DE (1) | DE60222324T2 (fr) |
FR (1) | FR2825786B1 (fr) |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2887015A1 (fr) * | 2005-06-14 | 2006-12-15 | Snecma Moteurs Sa | Assemblage d'une chambre de combustion annulaire de turbomachine |
EP1767858A1 (fr) * | 2005-09-23 | 2007-03-28 | Snecma | Chambre de combustion de moteur à turbine à gaz avec carénage |
EP1775517A2 (fr) * | 2005-10-12 | 2007-04-18 | General Electric Company | Système à boulons pour attacher une chemise en céramique à une structure en métal |
FR2896575A1 (fr) * | 2006-01-26 | 2007-07-27 | Snecma Sa | Chambre de combustion annulaire d'une turbomachine |
FR2905166A1 (fr) * | 2006-08-28 | 2008-02-29 | Snecma Sa | Chambre de combustion annulaire d'une turbomachine. |
FR2914399A1 (fr) * | 2007-03-27 | 2008-10-03 | Snecma Sa | Carenage pour fond de chambre de combustion. |
EP1719949A3 (fr) * | 2005-04-27 | 2009-09-02 | United Technologies Corporation | Support métallique d'une chemise de chambre de combustion en céramique de turbine à gaz |
EP3115690A1 (fr) * | 2015-07-06 | 2017-01-11 | General Electric Company | Chemise de chambre de combustion en cmc thermiquement couplé |
EP3139092A1 (fr) * | 2015-09-02 | 2017-03-08 | General Electric Company | Ensemble chambre de combustion pour une turbomachine |
EP3139094A1 (fr) * | 2015-09-02 | 2017-03-08 | General Electric Company | Ensemble chambre de combustion pour une turbomachine |
US11149646B2 (en) | 2015-09-02 | 2021-10-19 | General Electric Company | Piston ring assembly for a turbine engine |
US11402097B2 (en) | 2018-01-03 | 2022-08-02 | General Electric Company | Combustor assembly for a turbine engine |
Families Citing this family (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6895761B2 (en) * | 2002-12-20 | 2005-05-24 | General Electric Company | Mounting assembly for the aft end of a ceramic matrix composite liner in a gas turbine engine combustor |
US6904757B2 (en) * | 2002-12-20 | 2005-06-14 | General Electric Company | Mounting assembly for the forward end of a ceramic matrix composite liner in a gas turbine engine combustor |
FR2855249B1 (fr) * | 2003-05-20 | 2005-07-08 | Snecma Moteurs | Chambre de combustion ayant une liaison souple entre un fond de chambre et une paroi de chambre |
US7237389B2 (en) * | 2004-11-18 | 2007-07-03 | Siemens Power Generation, Inc. | Attachment system for ceramic combustor liner |
US7762076B2 (en) * | 2005-10-20 | 2010-07-27 | United Technologies Corporation | Attachment of a ceramic combustor can |
FR2906350B1 (fr) * | 2006-09-22 | 2009-03-20 | Snecma Sa | Chambre de combustion annulaire d'une turbomachine |
US9127565B2 (en) * | 2008-04-16 | 2015-09-08 | Siemens Energy, Inc. | Apparatus comprising a CMC-comprising body and compliant porous element preloaded within an outer metal shell |
US10436446B2 (en) | 2013-09-11 | 2019-10-08 | General Electric Company | Spring loaded and sealed ceramic matrix composite combustor liner |
EP3052862A4 (fr) * | 2013-10-04 | 2016-11-02 | United Technologies Corp | Panneau de chambre de combustion doté de plusieurs fixations |
DE102015212573A1 (de) * | 2015-07-06 | 2017-01-12 | Rolls-Royce Deutschland Ltd & Co Kg | Gasturbinenbrennkammer mit integriertem Turbinenvorleitrad sowie Verfahren zu deren Herstellung |
US10197278B2 (en) | 2015-09-02 | 2019-02-05 | General Electric Company | Combustor assembly for a turbine engine |
US10281153B2 (en) * | 2016-02-25 | 2019-05-07 | General Electric Company | Combustor assembly |
US10393380B2 (en) * | 2016-07-12 | 2019-08-27 | Rolls-Royce North American Technologies Inc. | Combustor cassette liner mounting assembly |
US20180051880A1 (en) * | 2016-08-18 | 2018-02-22 | General Electric Company | Combustor assembly for a turbine engine |
US10837640B2 (en) | 2017-03-06 | 2020-11-17 | General Electric Company | Combustion section of a gas turbine engine |
US11293637B2 (en) * | 2018-10-15 | 2022-04-05 | Raytheon Technologies Corporation | Combustor liner attachment assembly for gas turbine engine |
US11255547B2 (en) * | 2018-10-15 | 2022-02-22 | Raytheon Technologies Corporation | Combustor liner attachment assembly for gas turbine engine |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
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US3911672A (en) * | 1974-04-05 | 1975-10-14 | Gen Motors Corp | Combustor with ceramic liner |
US5291732A (en) * | 1993-02-08 | 1994-03-08 | General Electric Company | Combustor liner support assembly |
EP1152191A2 (fr) * | 2000-05-05 | 2001-11-07 | General Electric Company | Chambre de combustion ayant une chemise de chambre de combustion faite de matériau composite à matrice céramique |
-
2001
- 2001-06-06 FR FR0107374A patent/FR2825786B1/fr not_active Expired - Fee Related
-
2002
- 2002-06-03 JP JP2002161065A patent/JP3984104B2/ja not_active Expired - Lifetime
- 2002-06-04 EP EP02291360A patent/EP1265031B1/fr not_active Expired - Lifetime
- 2002-06-04 DE DE60222324T patent/DE60222324T2/de not_active Expired - Lifetime
- 2002-06-05 US US10/160,729 patent/US6655148B2/en not_active Expired - Lifetime
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3911672A (en) * | 1974-04-05 | 1975-10-14 | Gen Motors Corp | Combustor with ceramic liner |
US5291732A (en) * | 1993-02-08 | 1994-03-08 | General Electric Company | Combustor liner support assembly |
EP1152191A2 (fr) * | 2000-05-05 | 2001-11-07 | General Electric Company | Chambre de combustion ayant une chemise de chambre de combustion faite de matériau composite à matrice céramique |
Cited By (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7647779B2 (en) | 2005-04-27 | 2010-01-19 | United Technologies Corporation | Compliant metal support for ceramic combustor liner in a gas turbine engine |
EP1719949A3 (fr) * | 2005-04-27 | 2009-09-02 | United Technologies Corporation | Support métallique d'une chemise de chambre de combustion en céramique de turbine à gaz |
US8122727B2 (en) | 2005-04-27 | 2012-02-28 | United Technologies Corporation | Compliant metal support for ceramic combustor liner in a gas turbine engine |
EP2458282A1 (fr) * | 2005-04-27 | 2012-05-30 | United Technologies Corporation | Support métallique souple de chemise de chambre de combustion en céramique dans un moteur à turbine à gaz |
EP1734305A3 (fr) * | 2005-06-14 | 2013-05-01 | Snecma | Assemblage d'une chambre de combustion annulaire de turbomachine |
EP1734305A2 (fr) * | 2005-06-14 | 2006-12-20 | Snecma | Assemblage d'une chambre de combustion annulaire de turbomachine |
US7849696B2 (en) | 2005-06-14 | 2010-12-14 | Snecma | Assembling an annular combustion chamber of a turbomachine |
FR2887015A1 (fr) * | 2005-06-14 | 2006-12-15 | Snecma Moteurs Sa | Assemblage d'une chambre de combustion annulaire de turbomachine |
FR2891351A1 (fr) * | 2005-09-23 | 2007-03-30 | Snecma | Chambre de combustion de moteur a turbine a gaz avec carenage |
US7617688B2 (en) | 2005-09-23 | 2009-11-17 | Snecma | Combustion chamber of a gas turbine engine with an upstream fairing for separating the gas stream, annular wall forming a cap of the upstream fairing of the chamber, and gas turbine engine with the chamber |
EP1767858A1 (fr) * | 2005-09-23 | 2007-03-28 | Snecma | Chambre de combustion de moteur à turbine à gaz avec carénage |
EP1775517A3 (fr) * | 2005-10-12 | 2007-04-25 | General Electric Company | Système à boulons pour attacher une chemise en céramique à une structure en métal |
EP1775517A2 (fr) * | 2005-10-12 | 2007-04-18 | General Electric Company | Système à boulons pour attacher une chemise en céramique à une structure en métal |
FR2896575A1 (fr) * | 2006-01-26 | 2007-07-27 | Snecma Sa | Chambre de combustion annulaire d'une turbomachine |
FR2905166A1 (fr) * | 2006-08-28 | 2008-02-29 | Snecma Sa | Chambre de combustion annulaire d'une turbomachine. |
US8387395B2 (en) | 2006-08-28 | 2013-03-05 | Snecma | Annular combustion chamber for a turbomachine |
EP1898155A1 (fr) * | 2006-08-28 | 2008-03-12 | Snecma | Chambre de combustion annulaire d'une turbomachine |
US7861531B2 (en) | 2007-03-27 | 2011-01-04 | Snecma | Fairing for a combustion chamber end wall |
EP1978305A1 (fr) | 2007-03-27 | 2008-10-08 | Snecma | Carénage pour fond de chambre de combustion |
FR2914399A1 (fr) * | 2007-03-27 | 2008-10-03 | Snecma Sa | Carenage pour fond de chambre de combustion. |
US10801729B2 (en) | 2015-07-06 | 2020-10-13 | General Electric Company | Thermally coupled CMC combustor liner |
EP3115690A1 (fr) * | 2015-07-06 | 2017-01-11 | General Electric Company | Chemise de chambre de combustion en cmc thermiquement couplé |
EP3139092A1 (fr) * | 2015-09-02 | 2017-03-08 | General Electric Company | Ensemble chambre de combustion pour une turbomachine |
EP3139094A1 (fr) * | 2015-09-02 | 2017-03-08 | General Electric Company | Ensemble chambre de combustion pour une turbomachine |
US9976746B2 (en) | 2015-09-02 | 2018-05-22 | General Electric Company | Combustor assembly for a turbine engine |
US11149646B2 (en) | 2015-09-02 | 2021-10-19 | General Electric Company | Piston ring assembly for a turbine engine |
US11898494B2 (en) | 2015-09-02 | 2024-02-13 | General Electric Company | Piston ring assembly for a turbine engine |
US11402097B2 (en) | 2018-01-03 | 2022-08-02 | General Electric Company | Combustor assembly for a turbine engine |
Also Published As
Publication number | Publication date |
---|---|
JP2003021335A (ja) | 2003-01-24 |
JP3984104B2 (ja) | 2007-10-03 |
FR2825786B1 (fr) | 2003-10-17 |
DE60222324D1 (de) | 2007-10-25 |
DE60222324T2 (de) | 2008-06-12 |
US6655148B2 (en) | 2003-12-02 |
EP1265031B1 (fr) | 2007-09-12 |
US20020184886A1 (en) | 2002-12-12 |
FR2825786A1 (fr) | 2002-12-13 |
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Legal Events
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