EP2914818B1 - Exhaust housing hub for a turbomachine - Google Patents
Exhaust housing hub for a turbomachine Download PDFInfo
- Publication number
- EP2914818B1 EP2914818B1 EP13795819.5A EP13795819A EP2914818B1 EP 2914818 B1 EP2914818 B1 EP 2914818B1 EP 13795819 A EP13795819 A EP 13795819A EP 2914818 B1 EP2914818 B1 EP 2914818B1
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- European Patent Office
- Prior art keywords
- hub
- wall
- connecting wall
- inner channel
- arms
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- 238000011144 upstream manufacturing Methods 0.000 claims description 14
- 230000000295 complement effect Effects 0.000 claims description 2
- 210000003462 vein Anatomy 0.000 description 49
- 230000035882 stress Effects 0.000 description 10
- 238000005266 casting Methods 0.000 description 3
- 239000003351 stiffener Substances 0.000 description 3
- 229920000297 Rayon Polymers 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000002964 rayon Substances 0.000 description 2
- 230000001052 transient effect Effects 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 229910000623 nickel–chromium alloy Inorganic materials 0.000 description 1
- 230000003071 parasitic effect Effects 0.000 description 1
- 230000002028 premature Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
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- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
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- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting arrangements
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- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
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- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
Definitions
- the invention generally relates to the field of turbomachines, and more particularly the exhaust casings of turbomachines.
- a turbomachine has a main direction extending along a longitudinal axis, and typically comprises, upstream to downstream in the direction of the gas flow, a blower, a low pressure compressor, a high pressure compressor, a combustion chamber , a high pressure turbine, and a low pressure turbine comprising in particular an exhaust casing.
- the exhaust casing contributes to delimiting the primary stream of the fluid (or flow of gas) passing through the turbomachine, and ensures, via the bearing support, the concentricity between the rotor and the stator of the turbomachine, as well as the attachment of the engine downstream to the nacelle.
- the exhaust casing is therefore one of the main structural parts of the engine subject to very high thermal levels, and in which transit loads of extreme unbalance.
- the hub generally comprises a flange (of very diverse shapes), connected at an inner portion, to one or more bearing supports adapted to center the rotor on the axis of the turbomachine, and at an outer portion, the exit cone (or exhaust cone, or "Plug” in English) via an external mounting flange.
- This flange is also surmounted by a sheet defining the vein, in the lower part, and having openings adapted to receive the arms.
- hubs are traditionally of very little shape deformable (say Y or H among others), and this type of architecture induces high stresses in the entire housing, for example, at the intersection between the edge of the housing. attack of the arms and the flask (s).
- the exhaust casing undergoes very high temperatures and very large transient thermal gradients. This is particularly the case of the hub, between its lower part, or at the mounting flanges of the bearing support, and its upper part, or at the level of the vein sheet.
- the hub must be able to withstand breaking forces and moments resulting from a dawn loss.
- the hub is sufficiently rigid. However, it must also be able to mechanically admit a sufficient internal deformation (or, if it is associated with tangential arms, a free rotation around the crankcase axis) to be able to ensure the overall service life of the crankcase. 'exhaust.
- vein plate and the flange in two separate parts, in order to allow their relative movement during the thermal expansion of the parts in operation and thus to reduce the stresses applied to them and to their level. intersection with the arms.
- additional fastening means such as flanges and nuts, which increases the size of the hub and therefore increases the overall weight and cost of the casing.
- Significant flow leakage in the interstices may further result from this embodiment. It therefore remains necessary for some exhaust casings to form the flange and the vein plate integrally, that is to say in one piece.
- An object of the invention is therefore to provide a hub and a housing, in particular an exhaust casing, which can be adapted to a larger number of turbomachines, which makes it possible to improve the life of the casing, while being able to withstand the extreme vibratory loads (for example the loads induced by the loss of a blade), that is to say, the loads coming from the housing interfaces (such as the bearings, the exit cone, as well as all the parts adjacent to the exhaust casing) and the very large thermal gradients that can be achieved in use in this type of casing, and to meet the objectives of space, mass and flexibility, while being simple to perform and for a moderate cost.
- extreme vibratory loads for example the loads induced by the loss of a blade
- the housing interfaces such as the bearings, the exit cone, as well as all the parts adjacent to the exhaust casing
- the very large thermal gradients that can be achieved in use in this type of casing, and to meet the objectives of space, mass and flexibility, while being simple to perform and for a moderate cost.
- the invention provides an exhaust casing hub of a turbomachine, comprising internal fixing flanges adapted to be fixed to a bearing support, a wall an annular connecting wall and an annular internal vein wall, the connecting wall connecting the internal vein wall to the internal fixing flanges, wherein a radial section of the connecting wall is curved, the hub further comprising a series of ribs extending radially between the connecting wall and the wall; internal vein.
- the hub then has sufficient flexibility to enable it to withstand the very large thermal gradients in the exhaust casing and to let the exhaust casing "breathe” globally so as not to force the expansion of the casing too much. outer ferrule.
- the ribs which form locally optimized reinforcements, can withstand the stresses in the case of forces and extreme moments generated at the borders of the means by the possible loss of a fan blade.
- the hub thus produced is dimensionally adapted to the dynamic stresses experienced by the exhaust casing, in compliance with the mass specifications, and can be obtained by a single casting step, without other mechanically welded operations.
- the invention proposes a turbomachine comprising such a housing.
- the hub 2 is generally annular in shape and is adapted to be connected internally to bearing supports 5 via internal fastening flanges 24, and downstream, at an outer portion, to an exit cone of FIG. exhaust via external clamps 26.
- the hub 2 comprises an annular internal stream wall 20 disposed opposite the outer shell 3, adapted to delimit the internal vein of the gas flow, from which extends radially inwardly an annular connecting wall 22 .
- the intersection between the connecting wall 22 and the internal vein wall 20 may lie at the right of the leading edge BA of the arms 4 of the exhaust casing 1, and comprises an extra thickness arranged to standardize in this area radial 360 ° displacements and limit the creation of over-constraints.
- the internal fastening flanges 24 are integrally formed with the connecting wall 22, and extend from its free end 23, while the external fastening flanges 26 are integrally formed with the inner vein wall 20 and extend from its free end 21.
- a radial section (that is to say in a plane normal to the longitudinal axis X) of the connecting wall 22 is curved and has a shape of lyre or comma, which makes the hub 2 sufficiently flexible to accompany the expansion of the arms 4 and the outer shell 3, but sufficiently rigid from a thermal and mechanical point of view at the intersection between the internal vein wall 20 and the leading edge of the arms 4 to standardize radial deformations on 360 ° in the inner vein wall 20.
- the concavity of the radial section of the connecting wall 22 is oriented upstream, without point of inflection, in order to be deformable (opening or closing) and compensate for the relative expansions caused by the thermal gradients of the hub 2 relative to the outer shell 3 in the exhaust casing 1.
- the connecting wall 22 can indeed deform in bending under the effect of the various deformations, thanks to its shape makes it more flexible.
- the second portion 22c and the third portion 22c together form the concave portion of the connecting wall 22.
- the first portion 22a on the one hand, and the second portion 22b and the third portion 22c on the other hand, have a substantially equal curvilinear length. Furthermore, the intersection between the connecting wall 22 and the internal vein wall 20 is generally in line with the free end 23 of the connecting wall 22, that is to say in the same plane radial passing through the axis X of the casing 1.
- the connecting wall 22 may be relatively thin.
- the thickness of the connecting wall may be of the order of the thickness of the internal vein wall, or between 1 mm and 3 mm.
- the hub 2 can therefore deform at the connecting wall 22 which opens and flexes (its curvature then being greater than at rest) or lengthens and tends to separate the inner vein wall 20 from the internal fastening flange 24, thus avoiding damaging the rest of the hub 2 or the exhaust casing 1
- the internal vein wall 20 may be integrally formed with the connecting wall 22, that is to say in one piece, so as to eliminate the risk of leakage and reduce the overall size and mass of the hub 2 It is also relatively thin in order to optimize the overall mass of the hub 2, except at the leading edge BA, where as will be seen later, the internal vein wall 20 may have an annular extra thickness 29 so to standardize 360 ° radial deformations.
- the internal vein wall 20 and the connecting wall 22 are preferably obtained by casting in a conventional material for the hub 2, that is to say a material capable of resisting, in long use, the very high temperatures experienced by the hub 2 (of the order of 650 ° C to 700 ° C) while supporting the oligo-cyclic and vibratory fatigue and having a good resistance under load.
- the walls 20 and 22 may be made of a nickel-chromium alloy.
- the arms 4 of the exhaust casing 1 extend between the internal vein wall 20 of the hub 2 and the outer shell 3.
- the arms 4 are preferably made in two parts, a first part 42, forming the foot of the arms 4, extending radially from the internal vein wall 20, and a second portion 44, forming the body of the arms 4, extending radially from the outer shell 3.
- the feet 42 are preferably made integrally with the inner vein wall 20 of the hub 2, while the bodies 44 may be formed integrally with the shell 3, for example by casting.
- the two arm portions 42, 44 are then positioned opposite to be fixed together, for example by welding along a weld plane 43, in order to connect the hub 2 and the outer shell 3.
- the feet 42 extend over a height less than or equal to one quarter of the total height of the arms 4.
- the release of the hub 2, formed of a portion of the internal fastening clamps 24 and external 26, connection walls 22, internal vein 20 and feet 42, can then be made more easily than if the weld plane 43 was further away from the inner wall of vein 20.
- Feet 42 have a non-zero height so not to interfere, given the weld plane 43, with the radius of connection of the arms 4 to the inner vein wall 20.
- the inner vein wall 20 of the hub 2 may further comprise ribs 28.
- the ribs 28 extend from preferably between the inner vein wall 20 and the connecting wall 22, opposite the arms 4 of the exhaust casing 1. This improves the resistance to deformation of the hub 2 resulting from thermal stresses and loading in extreme loads.
- the hub 2 may comprise two ribs 28 opposite each arm 4 of the exhaust casing 1.
- the ribs 28 may be formed integrally with the inner vein wall 20 and the connecting wall 22. As illustrated in FIGS. Figures 2 and 3 , the ribs may each comprise two radial edges 28a, 28b disposed in the extension of the upper surface wall and the lower surface respectively, and which extend parallel to the axis X of the connecting wall 20 to the downstream end 21 of the internal vein wall 20, up to the right of the trailing edge BF of the arms 4.
- the radial edges 28a, 28b of the ribs therefore have a convergent shape from upstream to downstream in the direction of the gas flow, then meet, and are thus able to better withstand the loading imposed by the arms 4 and the bearing support hub 2.
- the height of the ribs 28 may furthermore vary between their upstream end, at the level of the connecting wall 20, and their downstream end, at the right of the trailing edge BF of the arms. 4.
- the height of the ribs 28 is maximum at the connecting wall 22, then decreases downstream until the edges 28a and 28b meet, where it stabilizes to the downstream end of the ribs 28, as illustrated in Figures 2 and 3 , in order to optimize the overall mass of the hub 2 while guaranteeing the load-bearing resistance of the ribs 28.
- the hub 2 may further comprise a stiffener 28c, for uniformly distributing the 360 ° radial deformations downstream of the internal vein wall 20, in the vicinity of the trailing edges BF of the arms 4 and to support the ribs under the charges that pass through these ribs.
- the stiffener 28c may in particular be an annular ridge coaxial with the hub 2, extending radially from the internal vein wall 20 at the downstream end of the ribs 28, or at the right of the trailing edge BF of the arms 4.
- the stiffener 28c extends over a height equal to the height of the downstream end of the ridges 28a, 28b of the rib 28.
- the hub 2 may further comprise an annular extra thickness 29 at the intersection between its connecting wall 22 and its internal vein wall 20, at the right of the leading edge BA of the arms 4.
- This extra thickness 29 which is visible on figures 1 and 3 , makes it possible in fact to standardize the 360 ° radial deformations of the internal vein wall 20 despite the thermal or load stresses to the exhaust casing 1.
- This extra thickness 29 also makes it possible to locally reinforce the hub 2 and to improve its resistance to stress in the case of forces and extreme moments generated at the borders of the hub 2 by the possible loss of a fan blade.
- the excess thickness 29 is preferably local and does not extend over the entire internal vein wall 20, and remains thin in order to reduce the overall mass of the hub 2.
- the extra thickness may have a radial cross-section. thickness between 4 mm and 8 mm, typically of the order of 5 mm.
- the excess thickness 29 can be arranged at the junction between the connecting wall 22 and the internal vein wall 20, and extends generally along the third portion 22c of the connecting wall 22.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
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Description
L'invention concerne de manière générale le domaine des turbomachines, et plus particulièrement les carters d'échappement des turbomachines.The invention generally relates to the field of turbomachines, and more particularly the exhaust casings of turbomachines.
Une turbomachine présente une direction principale s'étendant selon un axe longitudinal, et comporte typiquement, d'amont en aval dans le sens de l'écoulement des gaz, une soufflante, un compresseur basse pression, un compresseur haute pression, une chambre de combustion, une turbine haute pression, et une turbine basse pression comprenant notamment un carter d'échappement. Le carter d'échappement contribue à délimiter la veine primaire du fluide (ou flux des gaz) traversant la turbomachine, et assure, par l'intermédiaire du support de paliers, la concentricité entre le rotor et le stator de la turbomachine, ainsi que l'accrochage de l'aval du moteur à la nacelle. Le carter d'échappement est donc l'une des pièces principales de structure du moteur sujette à des niveaux thermiques très élevés, et dans lequel transitent des charges de balourds extrêmes.A turbomachine has a main direction extending along a longitudinal axis, and typically comprises, upstream to downstream in the direction of the gas flow, a blower, a low pressure compressor, a high pressure compressor, a combustion chamber , a high pressure turbine, and a low pressure turbine comprising in particular an exhaust casing. The exhaust casing contributes to delimiting the primary stream of the fluid (or flow of gas) passing through the turbomachine, and ensures, via the bearing support, the concentricity between the rotor and the stator of the turbomachine, as well as the attachment of the engine downstream to the nacelle. The exhaust casing is therefore one of the main structural parts of the engine subject to very high thermal levels, and in which transit loads of extreme unbalance.
Ce carter d'échappement comprend conventionnellement :
- un moyeu, centré sur l'axe de la turbomachine,
- une virole externe, coaxiale avec le moyeu, et
- un ensemble de bras, ou manchettes, reliant le moyeu et la virole externe.
- a hub, centered on the axis of the turbomachine,
- an outer shell, coaxial with the hub, and
- a set of arms, or sleeves, connecting the hub and the outer shell.
Le moyeu comprend généralement un flasque (de formes très diverses), connecté au niveau d'une partie interne, à un (ou des) support(s) de palier(s) adaptés pour centrer le rotor sur l'axe de la turbomachine, et au niveau d'une partie externe, au cône de sortie (ou cône d'échappement, ou « Plug » en anglais) via une bride de fixation externe. Ce flasque est par ailleurs surmonté d'une tôle délimitant la veine, en partie inférieure, et présentant des ouvertures adaptées pour recevoir les bras.The hub generally comprises a flange (of very diverse shapes), connected at an inner portion, to one or more bearing supports adapted to center the rotor on the axis of the turbomachine, and at an outer portion, the exit cone (or exhaust cone, or "Plug" in English) via an external mounting flange. This flange is also surmounted by a sheet defining the vein, in the lower part, and having openings adapted to receive the arms.
Ces moyeux sont traditionnellement de forme très peu déformable (dites en Y ou H entre autres), et ce type d'architecture induit de fortes contraintes dans l'ensemble du carter, par exemple, au niveau de l'intersection entre le bord d'attaque des bras et le(s) flasque(s). Par ailleurs, lorsque la turbomachine est en fonctionnement, le carter d'échappement subit des températures très élevées et des gradients thermiques transitoires très importants. C'est particulièrement le cas du moyeu, entre sa partie inférieure, soit au niveau des brides de fixation du support de paliers, et sa partie supérieure, soit au niveau de la tôle de veine. Enfin, le moyeu doit être capable de supporter en tenue à la rupture les efforts et moments résultant d'une perte d'aube.These hubs are traditionally of very little shape deformable (say Y or H among others), and this type of architecture induces high stresses in the entire housing, for example, at the intersection between the edge of the housing. attack of the arms and the flask (s). Moreover, when the turbomachine is in operation, the exhaust casing undergoes very high temperatures and very large transient thermal gradients. This is particularly the case of the hub, between its lower part, or at the mounting flanges of the bearing support, and its upper part, or at the level of the vein sheet. Finally, the hub must be able to withstand breaking forces and moments resulting from a dawn loss.
Il est donc nécessaire que le moyeu soit suffisamment rigide. Cependant, il doit également être capable d'admettre mécaniquement une déformation interne suffisante (ou, s'il est associé à des bras tangentiels, une rotation libre autour de l'axe du carter) pour pouvoir assurer la durée de vie globale du carter d'échappement.It is therefore necessary that the hub is sufficiently rigid. However, it must also be able to mechanically admit a sufficient internal deformation (or, if it is associated with tangential arms, a free rotation around the crankcase axis) to be able to ensure the overall service life of the crankcase. 'exhaust.
Compte-tenu de la rigidité du moyeu, les contraintes dues aux forts gradients thermiques (écarts de températures moyennes et/ou locales) transitoires se trouvent déplacées vers la virole externe et notamment au niveau des bords d'attaque et de fuite des bras. Cependant, en assouplissant le moyeu du carter d'échappement pour répartir les déformations et limiter les contraintes appliquées aux différentes pièces qui le constituent, on le sensibilise davantage à son environnement externe dans la turbomachine, en particulier en vibratoire et sous charges extrêmes. Il est donc nécessaire de maintenir une rigidité minimum afin que celui-ci reste stable et robuste même en cas de changement des contraintes mécaniques et vibratoires subies par la turbomachine (modification des champs thermiques, des charges extrêmes, etc.).Given the rigidity of the hub, the stresses due to strong thermal gradients (transient average and / or local temperature differences) are displaced towards the outer shell and in particular at the leading and trailing edges of the arms. However, by softening the hub of the exhaust casing to distribute the deformations and limit the stresses applied to the various parts that constitute it, it is more aware of its external environment in the turbomachine, especially vibratory and under extreme loads. It is therefore necessary to maintain a minimum rigidity so that it remains stable and robust even in the event of a change in the mechanical and vibratory stresses to which the turbomachine is subjected (modification of thermal fields, extreme loads, etc.).
On cherche donc à proposer un moyeu qui soit à la fois capable de compenser les dilatations thermiques et d'uniformiser les déformations radiales sur 360° au niveau de l'intersection de la paroi de veine interne et du bord d'attaque des bras, sans pour autant faire obstacle aux déformations du reste du carter d'échappement afin d'empêcher la dégradation prématurée de celui-ci.It is therefore sought to provide a hub that is both capable of compensating for thermal expansion and of uniform 360 ° radial deformations at the intersection of the internal vein wall and the leading edge of the arms, without however, to deformations of the rest of the exhaust casing to prevent premature degradation of the exhaust casing.
Les solutions proposées de nos jours ne sont généralement pas applicables à tout type de turbomachine, car elles impliquent souvent l'ajout de pièces, qui représentent à la fois un surcoût et une masse non négligeables, sont trop complexes à mettre en oeuvre, ou sont trop volumineuses.The solutions proposed today are generally not applicable to any type of turbomachine, because they often involve the addition of parts, which represent both a significant extra cost and mass, are too complex to implement, or are too bulky.
Par exemple, afin de compenser les dilatations relatives des différentes partie du carter, il a été proposé d'intégrer des bras de manière tangentielle plutôt que radiale entre le moyeu et la virole externe. De la sorte, lors des dilatations relatives des pièces dues aux gradients thermiques dans le carter d'échappement, le moyeu tourne par rapport à la virole externe, ce qui permet d'éviter le poinçonnement des bras et le risque de perforation de la virole externe par des déformations relatives différentes entre deux ou plusieurs pièces adjacentes. Cependant, dans certains carters d'échappement, la distance entre le moyeu et la virole externe est très courte, ce qui limite la possibilité de mettre en oeuvre de tels bras tangentiels. Cette solution n'est donc pas envisageable pour tous les types de turbomachines.For example, in order to compensate for the relative expansions of the various parts of the housing, it has been proposed to incorporate arms tangentially rather than radially between the hub and the outer shell. In this way, during the relative expansions of the parts due to thermal gradients in the exhaust casing, the hub rotates relative to the outer shell, which avoids the punching of the arms and the risk of perforation of the outer shell by different relative deformations between two or more adjacent pieces. However, in some exhaust casings, the distance between the hub and the outer shell is very short, which limits the possibility of implementing such tangential arms. This solution is therefore not feasible for all types of turbomachines.
Il a également été proposé de réaliser la tôle de veine et le flasque en deux pièces distinctes, afin de permettre leur mouvement relatif lors de la dilatation thermique des pièces en fonctionnement et de réduire ainsi les contraintes appliquées à celles-ci et au niveau de leur intersection avec les bras. Cependant, la séparation de la tôle de veine du moyeu implique l'utilisation de moyens de fixation supplémentaires, tels que des brides et des écrous, ce qui augmente l'encombrement du moyeu et donc accroît la masse globale et le coût du carter. D'importantes fuites de l'écoulement dans les interstices peuvent en outre résulter de cette forme de réalisation. Il reste donc nécessaire pour certains carters d'échappement de former le flasque et la tôle de veine intégralement, c'est-à-dire d'une seule pièce.It has also been proposed to make the vein plate and the flange in two separate parts, in order to allow their relative movement during the thermal expansion of the parts in operation and thus to reduce the stresses applied to them and to their level. intersection with the arms. However, the separation of the vein plate from the hub involves the use of additional fastening means, such as flanges and nuts, which increases the size of the hub and therefore increases the overall weight and cost of the casing. Significant flow leakage in the interstices may further result from this embodiment. It therefore remains necessary for some exhaust casings to form the flange and the vein plate integrally, that is to say in one piece.
On a également proposé dans le document
Un objectif de l'invention est donc de proposer un moyeu ainsi qu'un carter, notamment un carter d'échappement, pouvant être adapté sur un plus grand nombre de turbomachines, qui permette d'améliorer la durée de vie du carter, tout en étant capable de supporter les charges vibratoires extrêmes (dont par exemple les charges induites par la perte d'une aube), c'est-à-dire, les charges provenant des interfaces du carter (tels que les paliers, le cône de sortie, ainsi que l'ensemble des pièces adjacentes au carter d'échappement) ainsi que les gradients thermiques très important pouvant être atteints en utilisation dans ce type de carter, et de répondre aux objectifs d'encombrement, de masse et de souplesse, tout en étant simple à réaliser et pour un coût modéré.An object of the invention is therefore to provide a hub and a housing, in particular an exhaust casing, which can be adapted to a larger number of turbomachines, which makes it possible to improve the life of the casing, while being able to withstand the extreme vibratory loads (for example the loads induced by the loss of a blade), that is to say, the loads coming from the housing interfaces (such as the bearings, the exit cone, as well as all the parts adjacent to the exhaust casing) and the very large thermal gradients that can be achieved in use in this type of casing, and to meet the objectives of space, mass and flexibility, while being simple to perform and for a moderate cost.
Pour cela, l'invention propose un moyeu de carter d'échappement d'une turbomachine, comprenant des brides de fixation internes adaptées pour être fixées à un support de paliers, une paroi une paroi de connexion annulaire et une paroi de veine interne annulaire, la paroi de connexion reliant la paroi de veine interne aux brides de fixation internes, dans lequel une section radiale de la paroi de connexion est courbe, le moyeu comprenant en outre une série de nervures s'étendant radialement entre la paroi de connexion et la paroi de veine interne.For this, the invention provides an exhaust casing hub of a turbomachine, comprising internal fixing flanges adapted to be fixed to a bearing support, a wall an annular connecting wall and an annular internal vein wall, the connecting wall connecting the internal vein wall to the internal fixing flanges, wherein a radial section of the connecting wall is curved, the hub further comprising a series of ribs extending radially between the connecting wall and the wall; internal vein.
Le moyeu présente alors une souplesse suffisante pour lui permet de supporter les gradients thermiques très importants dans le carter d'échappement et de laisser « respirer » globalement le carter d'échappement afin de ne pas contraindre trop fortement la dilatation de la virole externe. Par ailleurs, les nervures, qui forment des renforts localement optimisés, permettent de supporter les sollicitations dans le cas d'efforts et de moments extrêmes générés aux frontières du moyen par la perte éventuelle d'une aube de soufflante. Enfin, le moyeu ainsi réalisé est dimensionnellement adapté aux sollicitations dynamiques subies par le carter d'échappement, dans le respect des spécifications de masse, et peut être obtenu par une unique étape de fonderie, sans autres opérations mécano-soudées.The hub then has sufficient flexibility to enable it to withstand the very large thermal gradients in the exhaust casing and to let the exhaust casing "breathe" globally so as not to force the expansion of the casing too much. outer ferrule. Moreover, the ribs, which form locally optimized reinforcements, can withstand the stresses in the case of forces and extreme moments generated at the borders of the means by the possible loss of a fan blade. Finally, the hub thus produced is dimensionally adapted to the dynamic stresses experienced by the exhaust casing, in compliance with the mass specifications, and can be obtained by a single casting step, without other mechanically welded operations.
Certaines caractéristiques préférées mais non limitatives du moyeu de carter sont les suivantes :
- la paroi de connexion, la paroi de veine interne et les brides de fixation internes sont formées intégralement,
- la courbure de la section radiale de la paroi de connexion est dépourvue de point d'inflexion,
- la paroi de connexion présente une concavité orientée vers l'amont du carter,
- la section radiale de la paroi de connexion comprend, des brides de fixation internes vers la paroi de veine interne une première portion, sensiblement droite, s'étendant radialement en direction de l'aval du moyeu et une deuxième portion, de forme incurvée, dont la concavité est orientée vers l'amont du moyeu,
- une extrémité amont (par rapport au sens de l'écoulement gazeux dans le carter d'échappement) de la paroi de connexion, située au niveau de la jonction entre la paroi de connexion et la paroi de veine interne, présente une tangente sensiblement parallèle à la paroi de veine interne,
- le moyeu comprend en outre une surépaisseur à l'intersection entre la paroi de veine interne et la paroi de connexion,
- le moyeu comprend en outre des premières portions de bras, s'étendant depuis la paroi de veine interne et formées intégralement avec celle-ci, et adaptées pour être fixées sur des deuxièmes portions de bras complémentaires du carter,
- la surépaisseur s'étend au droit d'un bord d'attaque des premières portions de bras, et
- le moyeu comprend en outre une arête annulaire s'étendant radialement depuis la paroi de veine interne en aval de la série de nervures.
- the connecting wall, the inner vein wall and the internal fixing flanges are integrally formed,
- the curvature of the radial section of the connecting wall is devoid of inflection point,
- the connecting wall has a concavity oriented upstream of the housing,
- the radial section of the connecting wall comprises, from the internal fixing flanges towards the inner-vein wall, a first substantially straight portion extending radially towards the downstream end of the hub and a second portion of curved shape, of which the concavity is oriented upstream of the hub,
- an upstream end (with respect to the direction of the gas flow in the exhaust casing) of the connecting wall, situated at the junction between the connecting wall and the internal vein wall, has a tangent substantially parallel to the internal vein wall,
- the hub further comprises an extra thickness at the intersection between the internal vein wall and the connecting wall,
- the hub further comprises first arm portions, extending from the inner vein wall and formed integrally therewith, and adapted to be attached to second complementary arm portions of the housing,
- the extra thickness extends to the right of a leading edge of the first arm portions, and
- the hub further comprises an annular ridge extending radially from the inner vein wall downstream of the series of ribs.
Selon un deuxième aspect, l'invention propose également un carter d'échappement pour une turbomachine, présentant une direction principale s'étendant selon un axe longitudinal et comprenant
- un moyeu comme décrit ci-dessus, centré sur l'axe longitudinal,
- une virole externe, coaxiale avec le moyeu, et
- un ensemble de bras reliant la paroi de veine interne du moyeu à la virole externe.
- a hub as described above, centered on the longitudinal axis,
- an outer shell, coaxial with the hub, and
- a set of arms connecting the inner vein wall of the hub to the outer shell.
Selon un troisième aspect, l'invention propose une turbomachine comprenant un tel carter.According to a third aspect, the invention proposes a turbomachine comprising such a housing.
D'autres caractéristiques, buts et avantages de la présente invention apparaîtront mieux à la lecture de la description détaillée qui va suivre, faite en référence aux figures annexées données à titre d'exemples non limitatifs et sur lesquelles :
- La
figure 1 est une vue en coupe partielle d'un exemple de carter d'échappement d'une turbomachine conforme à l'invention, - La
figure 2 est une vue en perspective d'un exemple de réalisation d'un moyeu 2 conforme à l'invention, et - La
figure 3 est une vue partielle en perspective de l'exemple de carter d'échappement de lafigure 1 , et - La
figure 4 est une vue en détails de lafigure 1 .
- The
figure 1 is a partial sectional view of an exemplary exhaust casing of a turbomachine according to the invention, - The
figure 2 is a perspective view of an exemplary embodiment of ahub 2 according to the invention, and - The
figure 3 is a partial perspective view of the example of exhaust casing of thefigure 1 , and - The
figure 4 is a detailed view of thefigure 1 .
Dans ce qui suit, l'invention va être décrite dans son application à un carter d'échappement d'une turbomachine. Ceci n'est cependant pas limitatif, dans la mesure où elle s'applique à tout carter annulaire soumis à des gradients thermiques et devant être capable de supporter des charges importantes.In what follows, the invention will be described in its application to an exhaust casing of a turbomachine. This is however not limiting, insofar as it applies to any annular casing subjected to thermal gradients and having to be able to withstand heavy loads.
Un carter d'échappement 1 d'une turbomachine conforme à l'invention présente une direction principale s'étendant selon un axe longitudinal X et comprend:
un moyeu 2, centré sur l'axe X du carter d'échappement 1,- une virole
externe 3, coaxiale avec le moyeu 2, et - un ensemble
de bras 4,reliant le moyeu 2 et la viroleexterne 3.
- a
hub 2, centered on the X axis of the exhaust casing 1, - an
outer shell 3, coaxial with thehub 2, and - a set of
arms 4, connecting thehub 2 and theouter shell 3.
Le moyeu 2 est de forme globalement annulaire et est adapté pour être connecté en partie interne à des supports de palier 5 via des brides de fixation internes 24, et en aval, au niveau d'une partie externe, à un cône de sortie d'échappement via des brides de fixation externes 26.The
Le moyeu 2 comprend une paroi de veine interne 20 annulaire, disposée en regard de la virole externe 3, adaptée pour délimiter la veine interne de l'écoulement de gaz, de laquelle s'étend radialement vers l'intérieur une paroi de connexion 22 annulaire. Comme illustré sur la
Les brides de fixation internes 24 sont formées d'une pièce avec la paroi de connexion 22, et s'étendent depuis son extrémité libre 23, tandis que les brides de fixation externes 26 sont formées intégralement avec la paroi de veine interne 20 et s'étendent depuis son extrémité libre 21.The
Une section radiale (c'est-à-dire dans un plan normal à l'axe longitudinal X) de la paroi de connexion 22 est courbe et présente une forme de lyre ou de virgule, ce qui permet de rendre le moyeu 2 suffisamment souple pour accompagner la dilatation des bras 4 et de la virole externe 3, mais suffisamment rigide d'un point de vue thermique et mécanique au niveau de l'intersection entre la paroi de veine interne 20 et le bord d'attaque des bras 4 pour uniformiser les déformations radiales sur 360° dans la paroi de veine interne 20. La concavité de la section radiale de la paroi de connexion 22 est orientée vers l'amont, sans point d'inflexion, afin de pouvoir se déformer (en s'ouvrant ou en se fermant) et compenser les dilatations relatives engendrées par les gradients thermiques du moyeu 2 par rapport à la virole externe 3 dans le carter d'échappement 1. La paroi de connexion 22 peut en effet se déformer en flexion sous l'effet des différentes déformations, grâce à sa forme qui la rend plus souple.A radial section (that is to say in a plane normal to the longitudinal axis X) of the connecting
Par exemple, comme illustré par exemple sur la
une première portion 22a, sensiblement droite, s'étendant radialement en direction de la bridede fixation externe 26. Cette première portion présente donc une section radiale globalement inclinée en direction de l'aval (dans le sens de l'écoulement des gaz dans le carter d'échappement) suivant un angle α compris entre 20° et 60°, de préférence de l'ordre de 40°. Ici, l'angle α est mesuré entre l'axe Xa suivant lequel s'étend la premièreportion 22a de la paroi de connexion, et l'axe sensiblement Y perpendiculaire à l'axe du carter d'échappement passant par le bord d'attaque BA dubras 4 ;- une deuxième
portion 22b de forme incurvée, dont la concavité est orientée vers l'amont du moyeu 2. Par exemple, la section radiale de la deuxième portion 2b peut présenter un rayon R2 compris entre 15 mm et 30 mm, de préférence entre 15 mm et 20 mm, par exemple de l'ordre de 18,5 mm, et - une troisième
portion 22c, de forme incurvée, dont la concavité est orientée vers l'amont du moyeu et dont l'extrémité amont est située au niveau de la jonction entre la paroi de connexion 22 et la paroi de veineinterne 20. Au niveau de cette extrémité amont, la troisièmeportion 22c présente une tangente sensiblement parallèle à la paroi de veine interne 20, de manière à former une jonction adoucie ne perturbant pas l'écoulement dans le carter d'échappement.La troisième portion 22c et la paroi de veine interne 20 présentent donc un point de tangence. Par exemple, la section radiale de la troisième portion présente un rayon R1 compris entre 5 mm et 20 mm, de préférence entre 10 mm et 15 mm, par exemple de l'ordre de 12 mm.
- a
first portion 22a, substantially straight, extending radially in the direction of theouter fastening flange 26. This first portion therefore has a radial section generally inclined towards the downstream (in the direction of the flow of gas in the exhaust casing) at an angle α of between 20 ° and 60 °, preferably of the order of 40 °. Here, the angle α is measured between the axis Xa along which extends thefirst portion 22a of the connecting wall, and the axis substantially Y perpendicular to the axis of the exhaust casing passing through the edge of BA attack ofarm 4; - a
second portion 22b of curved shape, whose concavity is oriented upstream of thehub 2. For example, the radial section of the second portion 2b may have a radius R2 between 15 mm and 30 mm, preferably between 15 mm and 20 mm, for example of the order of 18.5 mm, and - a
third portion 22c, curved in shape, whose concavity is oriented upstream of the hub and whose upstream end is located at the junction between the connectingwall 22 and theinner vein wall 20. At the this upstream end, thethird portion 22c has a tangent substantially parallel to theinner vein wall 20, so as to form a softened junction does not disturb the flow in the exhaust casing. Thethird portion 22c and theinner vein wall 20 thus have a point of tangency. For example, the section radial of the third portion has a radius R1 between 5 mm and 20 mm, preferably between 10 mm and 15 mm, for example of the order of 12 mm.
La deuxième portion 22c et la troisième portion 22c forment ensemble la partie concave de la paroi de connexion 22.The
La première portion 22a d'une part, et la deuxième portion 22b et la troisième portion 22c d'autre part, présentent une longueur curviligne sensiblement égale. Par ailleurs, l'intersection entre la paroi de connexion 22 et la paroi de veine interne 20 se trouve globalement à l'aplomb de l'extrémité libre 23 de la paroi de connexion 22, c'est-à-dire dans le même plan radial passant par l'axe X du carter 1.The
La paroi de connexion 22 peut être relativement fine. Par exemple, l'épaisseur de la paroi de connexion peut être de l'ordre de l'épaisseur de la paroi de veine interne, soit entre 1 mm et 3 mm.The connecting
Au cours des diverses sollicitations subies par le moyeu 2, le moyeu 2 peut donc se déformer au niveau de la paroi de connexion 22 qui s'ouvre et fléchit (sa courbure étant alors plus importante qu'au repos) ou s'allonge et tend à écarter la paroi de veine interne 20 de la bride de fixation interne 24, évitant ainsi d'endommager le reste du moyeu 2 ou le carter d'échappement 1During the various stresses experienced by the
La paroi de veine interne 20 peut être formée intégralement avec la paroi de connexion 22, c'est-à-dire d'une seule pièce, de manière à éliminer les risques de fuites et réduire l'encombrement et la masse globale du moyeu 2. Elle est en outre relativement mince afin d'optimiser la masse globale du moyeu 2, sauf au niveau du bord d'attaque BA, où comme on le verra par la suite, la paroi de veine interne 20 peut présenter une surépaisseur annulaire 29 afin d'uniformiser les déformations radiales sur 360°.The
La paroi de veine interne 20 et la paroi de connexion 22 sont de préférence obtenues par coulage dans un matériau conventionnel pour le moyeu 2, c'est-à-dire un matériau capable de résister, en longue utilisation, aux très hautes températures subies par le moyeu 2 (de l'ordre de 650°C à 700°C) tout en supportant la fatigue oligo-cyclique et vibratoire et en présentant une bonne tenue sous charge. Par exemple, les parois 20 et 22 peuvent être réalisées dans un alliage de nickel-chrome.The
Les bras 4 du carter d'échappement 1 s'étendent entre la paroi de veine interne 20 du moyeu 2 et la virole externe 3. Pour des questions de faisabilité, les bras 4 sont de préférence réalisés en deux parties, une première partie 42, formant le pied des bras 4, s'étendant radialement depuis la paroi de veine interne 20, et une deuxième partie 44, formant le corps des bras 4, s'étendant radialement depuis la virole externe 3.The
Les pieds 42 sont de préférence réalisés intégralement avec la paroi de veine interne 20 du moyeu 2, tandis que les corps 44 peuvent être formés intégralement avec la virole 3, par exemple par coulage. Les deux parties de bras 42, 44 sont alors positionnées en regard afin d'être fixées ensemble, par exemple par soudure le long d'un plan de soudure 43, afin de relier le moyeu 2 et la virole externe 3.The
Selon une forme de réalisation, les pieds 42 s'étendent sur une hauteur inférieure ou égale à un quart de la hauteur totale des bras 4. Le démoulage du moyeu 2, formé d'une partie des brides de fixation internes 24 et externes 26, des parois de connexion 22, de la veine interne 20 et des pieds 42, peut alors être réalisé plus facilement que si le plan de soudure 43 était plus éloigné de la paroi interne de veine 20. Les pieds 42 ont cependant une hauteur non nulle afin de ne pas interférer, compte tenu du plan de soudure 43, avec le rayon de raccordement des bras 4 à la paroi de veine interne 20.According to one embodiment, the
Afin d'améliorer la tenue en charge, notamment en charges extrêmes (perte d'aube, etc.) ou des paliers, la paroi de veine interne 20 du moyeu 2 peut en outre comprendre des nervures 28. Les nervures 28 s'étendent de préférence entre la paroi de veine interne 20 et la paroi de connexion 22, en regard des bras 4 du carter d'échappement 1. Cela améliore la résistance aux déformations du moyeu 2 résultant des contraintes thermiques et du chargement en charges extrêmes.In order to improve the load carrying capacity, especially in extreme loads (dawn loss, etc.) or bearings, the
Par exemple, le moyeu 2 peut comprendre deux nervures 28 en regard de chaque bras 4 du carter d'échappement 1.For example, the
Les nervures 28 peuvent être formées intégralement avec la paroi de veine interne 20 et la paroi de connexion 22. Comme illustré sur les
La hauteur des nervures 28 (selon la direction radiale par rapport à l'axe X) peut en outre varier entre leur extrémité amont, au niveau de la paroi de connexion 20, et leur extrémité aval, au droit du bord de fuite BF des bras 4. Ici, la hauteur des nervures 28 est maximale au niveau de la paroi de connexion 22, puis diminue en direction aval jusqu'à ce que les arêtes 28a et 28b se rejoignent, où elle se stabilise jusqu'à l'extrémité aval des nervures 28, comme illustré sur les
Par ailleurs, le moyeu 2 peut en outre comprendre un raidisseur 28c, permettant de répartir uniformément les déformations radiales sur 360° en aval de la paroi de veine interne 20, au voisinage des bords de fuite BF des bras 4 et de soutenir les nervures sous les charges qui transitent par ces nervures. Le raidisseur 28c peut notamment être une arête annulaire coaxiale au moyeu 2, s'étendant radialement depuis la paroi de veine interne 20 au niveau de l'extrémité aval des nervures 28, soit au droit du bord de fuite BF des bras 4. Ici, le raidisseur 28c s'étend sur une hauteur égale à la hauteur de l'extrémité aval des arêtes 28a, 28b de la nervure 28.Furthermore, the
Enfin, le moyeu 2 peut en outre comprendre une surépaisseur 29 annulaire au niveau de l'intersection entre sa paroi de connexion 22 et sa paroi de veine interne 20, au droit du bord d'attaque BA des bras 4. Cette surépaisseur 29, qui est visible sur les
La surépaisseur 29 est de préférence locale et ne s'étend pas sur l'ensemble de la paroi de veine interne 20, et reste mince afin de réduire la masse globale du moyeu 2. Par exemple, la surépaisseur peut présenter une section radiale d'épaisseur comprise entre 4 mm et 8 mm, typiquement de l'ordre de 5 mm. Comme visible sur les figures, la surépaisseur 29 peut être disposée au niveau de la jonction entre la paroi de connexion 22 et la paroi de veine interne 20, et s'étend globalement le long de la troisième portion 22c de la paroi de connexion 22.The
Claims (12)
- A hub (2) of an exhaust housing (1) of a turbomachine, including inner attachment flanges (24) intended to be attached to a bearing support (5), an annular connecting wall (22) and an annular inner channel wall (20), the connecting wall (22) connecting the inner channel wall (20) to the inner attachment flanges (24), and
a radial section of the connecting wall (22) being curved, the hub being in characterized in that it further includes a series of ribs (28) extending radially between the connecting wall (22) and the inner channel wall (20). - The hub (2) according to claim 1, wherein the connecting wall (22), the inner channel wall (20) and the inner attachment flanges (24) are formed integrally.
- The hub (2) according to one of claims 1 or 2, wherein the curvature of the radial section of the connecting wall (22) has no inflection point.
- The hub (2) according to one of claims 1 to 3, wherein the connecting wall (22) has a concavity oriented upstream of the housing (1).
- The hub (2) according to one of claims 1 to 4, wherein the radial section of the connecting wall (22) includes, from the inner attachment flanges (24) to the inner channel wall (20):- a first portion (22a), substantially straight, extending radially in the direction downstream of the hub (2); and- a second portion (22b, 22c) with a curved shape, the concavity whereof is oriented upstream of the hub (2).
- The hub (2) according to one of claims 1 to 5, wherein an upstream end of the connecting wall (22), located at the junction between the connecting wall (22) and the inner channel wall (20) has a tangent substantially parallel to the inner channel wall (20).
- The hub (2) according to one of claims 1 to 6, further including an excess thickness (29) at the intersection between the inner channel wall (20) and the connecting wall (22).
- The hub (2) according to one of claims 1 to 7, wherein the hub (2) further comprises first portions of arms (42), extending from the inner channel wall (20) and formed integrally therewith, and intended to be attached to second portions of arms (44) complementary to the housing (1).
- The hub (2) according to claims 7 and 8 in combination, wherein the excess thickness (29) extends at right angle with a leading edge (BA) of the first portions of arms (42).
- The hub (2) according to one of claims 1 to 9, further including an annular ridge (28c) extending radially from the inner channel wall (20) downstream of the series of ribs (28).
- An exhaust housing (1) for a turbomachine, having a principal direction extending along a longitudinal axis (X) and including- a hub (2) according to one of claims 1 to 10, centered on the longitudinal axis (X),- an external frame (3) coaxial with the hub (2), and- a set of arms (4) connecting the inner channel wall (20) to the outer frame (3).
- A turbomachine, characterized in that it includes an exhaust housing (1) according to claim 11.
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FR1260439A FR2997444B1 (en) | 2012-10-31 | 2012-10-31 | HUB FOR A TURBOMACHINE |
PCT/FR2013/052519 WO2014068220A1 (en) | 2012-10-31 | 2013-10-22 | Exhaust housing hub for a turbomachine |
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EP2914818B1 true EP2914818B1 (en) | 2017-06-21 |
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Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3013387B1 (en) * | 2013-11-20 | 2015-11-20 | Snecma | BEARING SUPPORT HAVING A GEOMETRY FACILITATING THE EVACUATION OF FOUNDRY CORES |
US11274563B2 (en) * | 2016-01-21 | 2022-03-15 | General Electric Company | Turbine rear frame for a turbine engine |
FR3048015B1 (en) * | 2016-02-19 | 2020-03-06 | Safran Aircraft Engines | DAWN OF TURBOMACHINE, COMPRISING A FOOT WITH REDUCED CONCENTRATIONS OF CONSTRAINT |
US10343765B2 (en) * | 2016-06-02 | 2019-07-09 | United Technologies Corporation | Toroidal spinner aft flange |
FR3072712B1 (en) * | 2017-10-20 | 2019-09-27 | Safran Aircraft Engines | TURBOMACHINE REAR PART HAVING AN EFFORTS PATH EXTENDING BETWEEN EJECTION CONE AND EXHAUST CASE INTERNAL VIROLE |
US10746049B2 (en) * | 2018-03-30 | 2020-08-18 | United Technologies Corporation | Gas turbine engine case including bearing compartment |
FR3091904A1 (en) * | 2019-01-17 | 2020-07-24 | Airbus Operations | INTERNAL STRUCTURE OF A PRIMARY EJECTION DUCT |
FR3097259B1 (en) * | 2019-06-12 | 2021-05-21 | Safran Helicopter Engines | ANNULAR PART OF A BEARING SUPPORT FOR A TURBOMACHINE |
FR3097900B1 (en) | 2019-06-26 | 2021-06-04 | Safran Aircraft Engines | Turbomachine outlet bearing bracket |
US11286814B1 (en) * | 2020-09-17 | 2022-03-29 | Pratt & Whitney Canada Corp. | Exhaust duct of gas turbine engine |
US11448097B1 (en) | 2021-05-27 | 2022-09-20 | Pratt & Whitney Canada Corp. | Turbine exhaust strut internal core structure |
US11629615B2 (en) * | 2021-05-27 | 2023-04-18 | Pratt & Withney Canada Corp. | Strut reinforcing structure for a turbine exhaust case |
US11725525B2 (en) * | 2022-01-19 | 2023-08-15 | Rolls-Royce North American Technologies Inc. | Engine section stator vane assembly with band stiffness features for turbine engines |
US11898467B2 (en) * | 2022-02-11 | 2024-02-13 | Pratt & Whitney Canada Corp. | Aircraft engine struts with stiffening protrusions |
Family Cites Families (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3117826A (en) * | 1962-08-31 | 1964-01-14 | Gen Electric | Intermediate rotor support structure |
US4989406A (en) * | 1988-12-29 | 1991-02-05 | General Electric Company | Turbine engine assembly with aft mounted outlet guide vanes |
JPH09324699A (en) * | 1996-06-05 | 1997-12-16 | Ishikawajima Harima Heavy Ind Co Ltd | Frame structure of gas turbine |
US6511284B2 (en) | 2001-06-01 | 2003-01-28 | General Electric Company | Methods and apparatus for minimizing gas turbine engine thermal stress |
US6672966B2 (en) * | 2001-07-13 | 2004-01-06 | Honeywell International Inc. | Curvic coupling fatigue life enhancement through unique compound root fillet design |
US7097412B2 (en) * | 2003-02-14 | 2006-08-29 | United Technologies Corporation | Turbine engine bearing support |
CA2533425C (en) * | 2003-07-29 | 2012-09-25 | Pratt & Whitney Canada Corp. | Turbofan case and method of making |
US7370467B2 (en) * | 2003-07-29 | 2008-05-13 | Pratt & Whitney Canada Corp. | Turbofan case and method of making |
FR2859002A1 (en) * | 2003-08-18 | 2005-02-25 | Snecma Moteurs | Abradable surface for gas turbine engine housing surrounding fan, is made from a resin with glass balls over a layer of thermoformable foam |
SE527711C2 (en) * | 2004-10-06 | 2006-05-16 | Volvo Aero Corp | Bearing rack structure and gas turbine engine incorporating the bearing rack structure |
US7371046B2 (en) * | 2005-06-06 | 2008-05-13 | General Electric Company | Turbine airfoil with variable and compound fillet |
US7762509B2 (en) * | 2007-10-18 | 2010-07-27 | United Technologies Corp. | Gas turbine engine systems involving rotatable annular supports |
WO2010071499A1 (en) * | 2008-12-19 | 2010-06-24 | Volvo Aero Corporation | Spoke for a stator component, stator component and method for manufacturing a stator component |
EP2216516A1 (en) * | 2009-02-04 | 2010-08-11 | ABB Turbo Systems AG | Burst protection device for radial compressor |
US8408011B2 (en) | 2009-04-30 | 2013-04-02 | Pratt & Whitney Canada Corp. | Structural reinforcement strut for gas turbine case |
US9765648B2 (en) * | 2011-12-08 | 2017-09-19 | Gkn Aerospace Sweden Ab | Gas turbine engine component |
CA3013015C (en) * | 2012-06-15 | 2020-06-02 | United Technologies Corporation | High durability turbine exhaust case |
-
2012
- 2012-10-31 FR FR1260439A patent/FR2997444B1/en active Active
-
2013
- 2013-10-22 RU RU2015120552A patent/RU2670645C9/en active
- 2013-10-22 WO PCT/FR2013/052519 patent/WO2014068220A1/en active Application Filing
- 2013-10-22 JP JP2015538532A patent/JP6209218B2/en active Active
- 2013-10-22 BR BR112015009659-0A patent/BR112015009659B1/en active IP Right Grant
- 2013-10-22 CN CN201380069494.2A patent/CN104903549B/en active Active
- 2013-10-22 CA CA2889751A patent/CA2889751C/en active Active
- 2013-10-22 EP EP13795819.5A patent/EP2914818B1/en active Active
- 2013-10-22 US US14/439,998 patent/US9970320B2/en active Active
Non-Patent Citations (1)
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BR112015009659A2 (en) | 2017-07-04 |
FR2997444A1 (en) | 2014-05-02 |
US20150285098A1 (en) | 2015-10-08 |
US9970320B2 (en) | 2018-05-15 |
JP2015533399A (en) | 2015-11-24 |
BR112015009659B1 (en) | 2021-01-19 |
RU2670645C9 (en) | 2018-12-11 |
EP2914818A1 (en) | 2015-09-09 |
CN104903549A (en) | 2015-09-09 |
RU2670645C2 (en) | 2018-10-24 |
CA2889751C (en) | 2020-07-28 |
JP6209218B2 (en) | 2017-10-04 |
CN104903549B (en) | 2017-07-07 |
RU2015120552A (en) | 2016-12-20 |
WO2014068220A1 (en) | 2014-05-08 |
FR2997444B1 (en) | 2018-07-13 |
CA2889751A1 (en) | 2014-05-08 |
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