EP1213483A1 - Compressor stator stage - Google Patents
Compressor stator stage Download PDFInfo
- Publication number
- EP1213483A1 EP1213483A1 EP00870290A EP00870290A EP1213483A1 EP 1213483 A1 EP1213483 A1 EP 1213483A1 EP 00870290 A EP00870290 A EP 00870290A EP 00870290 A EP00870290 A EP 00870290A EP 1213483 A1 EP1213483 A1 EP 1213483A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blades
- retention
- openings
- ferrule
- stiffening
- 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.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
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- 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
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
Definitions
- the present invention relates to a stage rectifier of a compressor comprising a succession rectifier or stator stages separated by stages rotor blades, each rectifier stage consisting of fixed vanes connecting an inner ferrule to an outer shell.
- Coaxial compressors are well known in itself, and are used in several types of application. In particular, they are used in double motors body, turbofans or turbojets. We also note their presence in power plants. These compressors low or high pressure basically consist of several stages of rotating blades or rotor stages separated by stator stages or rectifiers which have to reposition (straighten) the speed vector of the fluid leaving the previous stage before sending it to the next compartment.
- Each of these rectifier stages is essentially consisting of fixed vanes connecting a ferrule exterior to an interior ferrule, both concentric.
- stiffening solutions have been considered.
- stiffeners in bandage shape machined on the inner shell or on the outer shell and on the non-functional side has been proposed.
- These bandages or stairs can also be made of an insert by welding or riveting.
- the blades are joined to the ferrules, both interior and exterior, by rivets or welds.
- the use of these means of solidarity has the major drawback of disturbing flow and generate a pressure drop in the vein aerodynamic.
- the present invention aims to provide a solution which allows to combine the functions of stiffening of the inner shell and retention of blades of a rectifier stage of an axial compressor.
- the present invention aims to allow a solution that offers great simplicity of assembly and does not require assembly operations additional.
- the present invention also aims to propose a solution in which the aerodynamic vein flux is not affected by the presence of welds or rivets at the ferrule.
- the present invention also aims to allow the realization of a solution of a low cost Student.
- the present invention relates to a stage rectifier of a compressor comprising two ferrules, one inner ferrule and outer ferrule, both concentric and preferably circular and connected one to the other by a series of fixed vanes. At least the ferrule interior has lights or openings that allow the passage of said blades in these lights. Dawn themselves have at their end which will be arranged on the side of the inner shell a second opening intended for allow the passage of a retention part and stiffening having an elastic function. This retention and stiffening piece will allow advantageously the joining of the blades two by two on the non-functional side, i.e. on the side of the face internal, from the inner shell.
- this retention and stiffening part is present in the form of a cut, formed and folded sheet in two and is provided with two flat studs intended to be housed in the openings of two successive blades.
- this piece is folded allows it to provide a spring function for example a spring type " hair pin ".
- the assembly will be quick and easy, and will be carried out by applying precompression to said part of retention and stiffening that we will position then in the two openings of two successive blades and which we will then simply release. Once this part is mounted, the spring effect spreads the two blades successive linked.
- the placement of said piece will be against the edge of the openings of the shell.
- these parts will then be embedded in an elastomeric element.
- Figure 1 shows a general view of the compression stage of a turbofan with a stiffening of the ferrules according to the state of the art.
- Figure 2 shows a detail of the figure 1 showing the stiffening device according to the state of the technique including stiffeners at the inner ferrule.
- FIG. 3 represents the device for retention used in the solution according to this invention.
- FIG. 4 represents the device for retention according to the invention arranged at a ferrule interior and two successive blades so as to allow the stiffening of said inner shell and the blade retention function on this ferrule.
- Each rectifier stage 2,2 ', 2 ", ... is essentially consisting of an inner shell respectively 4.4 ', 4 ", ..., an outer ferrule respectively 5.5 ', 5 “, ... and a series of fixed blades respectively 6.6 ', 6 ", ... connecting said ferrule inner and outer ferrule.
- said interior ferrules 4.4 ', 4 ", ... and said outer ferrules 5.5', 5", ... are specific to each of the rectifier stages 2,2 ', 2 ", ... More specifically, the interior ferrules 4,4 ', 4 ", ... and the outer ferrules 5.5 ', 5 ", ... are presented under the form of metal sheets in the form of rings while the series of fixed blades 6,6 ', 6 ", ... correspond to metal sheets radially connecting an inner ferrule to an outer shell for each series.
- the gas first passes through the first stage rectifier 2 of the compressor where its speed vector is repositioned to be driven by the first floor rotor of rotating vanes 3 before joining the second rectifier stage 2 'to be again repositioned in 3 ', etc.
- the gas thus undergoes a cycle training - repositioning after which its kinetic energy gradually decreases while its pressure increases.
- stairs 8 are machined in the sheet of the inner shell 4 to stiffen said ferrule, and in particular the first stage rectifier 2.
- the alternative proposed by this invention consists in stiffening a ferrule while ensuring a retention function of the vanes at said ferrule.
- the blade retention piece 100 is described in detail in Figure 3. We observe that it is mainly in the form of a cut sheet, formed and folded 110 provided with two flat tenons 117 and 119.
- the shape and composition of the sheet 110 are such that the part 100 can be assimilated to a spring of "hairpin" type.
- Figure 4 shows the basic principle of the present invention and explains how the part of retention and stiffening 100 is arranged at level a ferrule and two successive blades to ensure the both the stiffening of this shell and the retention of two successive blades at this shell.
- the ferrule and preferably the inner ferrule 4
- the ends 51, 51 'of said blades themselves have openings 52.52 '.
- Said blades 60,61,62, ... are secured to the ferrule 4 using the retention and stiffening part 100.
- the flat studs 117 and 119 of said piece of retention and stiffening 100 are housed in openings 52, 52 'of the two successive blades 60,61,62, ...
- the retention and stiffening part 100 thus makes it possible to joining the blades two by two (60 and 61, 62 and 63, etc.) at the level of the rectifier stages.
- we exert on it precompression see arrows in Figure 3 as we would do this using sugar tongs.
- piece 100 so that its flattened studs 117, 119 come to stay in the openings respectively 52 and 52 'of successive blades 60,61,62, ...
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
La présente invention se rapporte à un étage redresseur d'un compresseur comprenant une succession d'étages redresseurs ou statoriques séparés par des étages rotoriques d'aubes tournantes, chaque étage redresseur étant constitué d'aubes fixes reliant une virole intérieure à une virole extérieure.The present invention relates to a stage rectifier of a compressor comprising a succession rectifier or stator stages separated by stages rotor blades, each rectifier stage consisting of fixed vanes connecting an inner ferrule to an outer shell.
Les compresseurs coaxiaux sont bien connus en soi, et sont utilisés dans plusieurs types d'application. En particulier, ils sont utilisés dans les moteurs double corps, turbofans ou turboréacteurs. On note aussi leur présence dans les centrales électriques. Ces compresseurs basse ou haute pression sont essentiellement constitués de plusieurs étages d'aubes tournantes ou étages rotoriques séparés par des étages statoriques ou redresseurs qui ont pour but de repositionner (redresser) le vecteur vitesse du fluide sortant de l'étage précédent avant de l'envoyer vers le compartiment suivant.Coaxial compressors are well known in itself, and are used in several types of application. In particular, they are used in double motors body, turbofans or turbojets. We also note their presence in power plants. These compressors low or high pressure basically consist of several stages of rotating blades or rotor stages separated by stator stages or rectifiers which have to reposition (straighten) the speed vector of the fluid leaving the previous stage before sending it to the next compartment.
Chacun de ces étages redresseurs est constitué essentiellement d'aubes fixes reliant une virole extérieure à une virole intérieure, toutes deux concentriques.Each of these rectifier stages is essentially consisting of fixed vanes connecting a ferrule exterior to an interior ferrule, both concentric.
Le problème est que ces étages redresseurs sont soumis à des efforts relativement importants dus entre autres aux vibrations qui provoquent rapidement une usure par fatigue.The problem is that these rectifier stages are subjected to relatively large forces due between others to vibrations which quickly cause wear out of fatigue.
Afin de résoudre ce problème de fatigue, il a été proposé de rigidifier les viroles. En rigidifiant les viroles, et en particulier les viroles intérieures des premiers étages de compression, on permet en effet de déplacer les fréquences propres de certains modes de sollicitation qui usent de manière excessive lesdites viroles.In order to resolve this fatigue problem, he been proposed to stiffen the ferrules. By stiffening the ferrules, and in particular the inner ferrules of the first stages of compression, it is indeed possible to shift the natural frequencies of certain modes of solicitations that excessively wear out said ferrules.
Plusieurs solutions de rigidification ont été envisagées. En particulier l'utilisation de raidisseurs en forme de bandage usinés sur la virole intérieure ou sur la virole extérieure et du côté non fonctionnel a été proposée. On a également proposé d'usiner des escaliers dans la tôle des viroles intérieure ou extérieure. Ces bandages ou escaliers peuvent également être constitués d'une pièce rapportée par soudage ou par rivetage. En outre, afin d'augmenter l'étanchéité d'un étage à l'autre, il est habituel de disposer sous la tôle de la virole intérieure du redresseur un élément élastomère qui scelle l'aube fixe sur la virole intérieure et qui servira également de joint entre les éléments tournants et fixes. Ceci permet d'éviter un retour des gaz vers l'étage précédent, qui pourrait entraíner un décrochage moteur dans le cas d'un turbofan.Several stiffening solutions have been considered. In particular the use of stiffeners in bandage shape machined on the inner shell or on the outer shell and on the non-functional side has been proposed. We also proposed to machine stairs in the sheet of interior or exterior ferrules. These bandages or stairs can also be made of an insert by welding or riveting. In in addition, in order to increase the tightness from one floor to another, it is usual to have under the sheet of the ferrule inside of the rectifier an elastomeric element which seals the fixed dawn on the inner shell and which will serve also of joint between the rotating and fixed elements. This avoids a return of gases to the floor previous, which could cause an engine stall in the case of a turbofan.
Néanmoins, les diverses solutions proposées selon l'état de la technique sont des solutions relativement coûteuses étant donné que la matière nécessaire pour usiner la tôle des viroles est relativement importante.Nevertheless, the various solutions proposed according to the state of the art are solutions relatively expensive since the material necessary to machine the sheet metal of the ferrules is relatively important.
Un autre problème important dans le cas des étages redresseurs d'un compresseur est qu'il convient de solidariser de manière particulièrement efficace lesdites aubes aux viroles. En effet, cette solidarisation des aubes aux viroles doit être optimale de manière à pouvoir faire face à des accidents tels que le bris d'une aube ou l'ingestion d'un corps étranger tel qu'un oiseau dans ledit turboréacteur.Another important problem in the case of rectifier stages of a compressor is that it should particularly effectively securing said vanes with ferrules. Indeed, this joining of the blades to the ferrules must be optimal so that it can do face accidents such as breaking a dawn or ingestion of a foreign body such as a bird in said turbojet.
De plus, un déplacement des aubes par rapport aux viroles provoque une usure importante avec un cric de fatigue qui peut provoquer le bris desdites aubes ou même de la virole.In addition, a displacement of the blades relative the ferrules causes significant wear with a jack fatigue which can cause breakage of said blades or even of the shell.
Habituellement, on solidarise les aubes aux viroles, tant intérieure qu'extérieure, par des rivets ou des soudures. Néanmoins, le recours à ces moyens de solidarisation présente l'inconvénient majeur de perturber le flux et de générer une perte de charge dans la veine aérodynamique.Usually, the blades are joined to the ferrules, both interior and exterior, by rivets or welds. However, the use of these means of solidarity has the major drawback of disturbing flow and generate a pressure drop in the vein aerodynamic.
La présente invention vise à proposer une solution qui permette de combiner les fonctions de rigidification de la virole intérieure et de rétention des aubes d'un étage redresseur d'un compresseur axial.The present invention aims to provide a solution which allows to combine the functions of stiffening of the inner shell and retention of blades of a rectifier stage of an axial compressor.
En particulier, la présente invention vise à permettre une solution qui offre une grande simplicité de montage et ne nécessite pas d'opérations d'assemblage supplémentaires.In particular, the present invention aims to allow a solution that offers great simplicity of assembly and does not require assembly operations additional.
La présente invention vise également à proposer une solution dans laquelle la veine aérodynamique du flux n'est pas altérée par la présence de soudures ou de rivets au niveau de la virole.The present invention also aims to propose a solution in which the aerodynamic vein flux is not affected by the presence of welds or rivets at the ferrule.
La présente invention vise également à permettre la réalisation d'une solution d'un coût peu élevé. The present invention also aims to allow the realization of a solution of a low cost Student.
La présente invention se rapporte à un étage redresseur d'un compresseur comprenant deux viroles, une virole intérieure et une virole extérieure, toutes deux concentriques et de préférence circulaires et reliées l'une à l'autre par une série d'aubes fixes. Au moins la virole intérieure est munie de lumières ou ajours qui permettent le passage desdites aubes dans ces lumières. Les aubes elles-mêmes présentent à leur extrémité qui sera disposée du côté de la virole intérieure un second ajour destiné à permettre le passage d'une pièce de rétention et de rigidification présentant une fonction élastique. Cette pièce de rétention et de rigidification permettra de manière avantageuse la solidarisation des aubes deux à deux du côté non fonctionnel, c'est-à-dire du côté de la face interne, de la virole intérieure.The present invention relates to a stage rectifier of a compressor comprising two ferrules, one inner ferrule and outer ferrule, both concentric and preferably circular and connected one to the other by a series of fixed vanes. At least the ferrule interior has lights or openings that allow the passage of said blades in these lights. Dawn themselves have at their end which will be arranged on the side of the inner shell a second opening intended for allow the passage of a retention part and stiffening having an elastic function. This retention and stiffening piece will allow advantageously the joining of the blades two by two on the non-functional side, i.e. on the side of the face internal, from the inner shell.
Selon une forme d'exécution particulièrement préférée, cette pièce de rétention et de rigidification se présente sous la forme d'une tôle découpée, formée et pliée en deux et est munie de deux tenons plats destinés à être logés dans les ajours de deux aubes successives.According to a particular embodiment preferred, this retention and stiffening part is present in the form of a cut, formed and folded sheet in two and is provided with two flat studs intended to be housed in the openings of two successive blades.
De manière particulièrement avantageuse, le fait que cette pièce soit pliée permet qu'elle assure une fonction de ressort par exemple un ressort de type « épingle à cheveux ».Particularly advantageously, the fact that this piece is folded allows it to provide a spring function for example a spring type " hair pin ".
De manière particulièrement avantageuse, on observe que le montage sera rapide et aisé, et s'effectuera en exerçant une précompression sur ladite pièce de rétention et de rigidification que l'on positionnera ensuite dans les deux ajours de deux aubes successives et que l'on relâchera ensuite simplement. Une fois que cette pièce est montée, l'effet ressort écarte les deux aubes successives reliées. Particularly advantageously, we observe that the assembly will be quick and easy, and will be carried out by applying precompression to said part of retention and stiffening that we will position then in the two openings of two successive blades and which we will then simply release. Once this part is mounted, the spring effect spreads the two blades successive linked.
De manière particulièrement avantageuse, le placement de ladite pièce se fera contre le bord des ajours de la virole.Particularly advantageously, the placement of said piece will be against the edge of the openings of the shell.
Ceci provoque de manière particulièrement avantageuse un effet de rétention desdites aubes à la virole intérieure mais également un effet de rigidification de l'ensemble de la virole intérieure, permettant ainsi un déplacement des fréquences propres de certains modes de sollicitation sur les viroles.This particularly causes advantageous a retention effect of said blades at the inner shell but also a stiffening effect of the entire inner shell, thus allowing displacement of the natural frequencies of certain modes of stress on the ferrules.
De manière particulièrement avantageuse, ces pièces seront ensuite noyées dans un élément élastomère.Particularly advantageously, these parts will then be embedded in an elastomeric element.
La figure 1 représente une vue générale de l'étage de compression d'un turbofan avec un dispositif de rigidification des viroles selon l'état de la technique.Figure 1 shows a general view of the compression stage of a turbofan with a stiffening of the ferrules according to the state of the art.
La figure 2 représente un détail de la figure 1 montrant le dispositif de rigidification selon l'état de la technique comprenant des raidisseurs au niveau de la virole intérieure.Figure 2 shows a detail of the figure 1 showing the stiffening device according to the state of the technique including stiffeners at the inner ferrule.
La figure 3 représente le dispositif de rétention utilisé dans la solution selon la présente invention.FIG. 3 represents the device for retention used in the solution according to this invention.
La figure 4 représente le dispositif de rétention selon l'invention disposé au niveau d'une virole intérieure et de deux aubes successives de manière à permettre la rigidification de ladite virole intérieure et la fonction de rétention des aubes sur cette virole.FIG. 4 represents the device for retention according to the invention arranged at a ferrule interior and two successive blades so as to allow the stiffening of said inner shell and the blade retention function on this ferrule.
La figure 1 représente l'étage de compression d'un turbofan. Cet étage de compression est composé de deux types de pièces :
- d'une part, des pièces mobiles qui sont essentiellement
constituées par le
rotor 1 muni de plusieurs séries d'aubes mobiles 3,3',3",... correspondant à plusieurs étages rotoriques successifs, et - d'autre part des pièces fixes constituant les étages
statoriques redresseurs
- on the one hand, moving parts which are essentially constituted by the
rotor 1 provided with several series of moving blades 3.3 ′, 3 ", ... corresponding to several successive rotor stages, and - on the other hand, fixed parts constituting the
stator rectifier stages rotor stages
Chaque étage redresseur 2,2',2",... est
essentiellement constitué par une virole intérieure
respectivement 4,4',4",..., une virole extérieure
respectivement 5,5',5",... et une série d'aubes fixes
respectivement 6,6',6",... reliant lesdites virole
intérieure et virole extérieure.Each
De préférence, lesdites viroles intérieures
4,4',4",... et lesdites viroles extérieures 5,5',5",...
sont propres à chacun des étages redresseurs 2,2',2",...
Plus précisément, les viroles intérieures 4,4',4",... et
les viroles extérieures 5,5',5",... se présentent sous la
forme de tôles métalliques en forme de bagues tandis que
les séries d'aubes fixes 6,6',6",... correspondent à des
tôles métalliques reliant radialement une virole intérieure
à une virole extérieure pour chaque série.Preferably, said interior ferrules
4.4 ', 4 ", ... and said outer ferrules 5.5', 5", ...
are specific to each of the
En outre, habituellement, une pièce
élastomérique 7,7',7",... est présente sur la surface
interne des viroles intérieures 4,4',4",...
correspondantes. Ces pièces élastomériques 7,7',7",...
jouent le rôle de joints entre deux étages rotorique et
statorique qui se succèdent.In addition, usually a room
elastomeric 7,7 ', 7 ", ... is present on the surface
internal of
Le gaz traverse d'abord le premier étage
redresseur 2 du compresseur où son vecteur vitesse est
repositionné afin d'être entraíné par le premier étage
rotorique d'aubes tournantes 3 avant de rejoindre le
deuxième étage redresseur 2' pour être à nouveau
repositionné en 3', etc. Le gaz subit ainsi un cycle
d'entraínement - repositionnement à l'issue duquel son
énergie cinétique diminue progressivement tandis que sa
pression croít.The gas first passes through the
Selon l'état de la technique et comme
représenté aux figures 1 et 2, des escaliers 8 sont usinés
dans la tôle de la virole intérieure 4 pour rigidifier
ladite virole, et en particulier le premier étage
redresseur 2.According to the state of the art and as
shown in Figures 1 and 2,
L'alternative proposée par la présente invention consiste à rigidifier une virole tout en assurant une fonction de rétention des aubes à ladite virole.The alternative proposed by this invention consists in stiffening a ferrule while ensuring a retention function of the vanes at said ferrule.
La pièce 100 de rétention des aubes est
décrite en détail à la figure 3. On observe qu'elle se
présente essentiellement sous la forme d'une tôle découpée,
formée et repliée 110 munie de deux tenons plats 117 et
119. La conformation et la composition de la tôle 110 sont
telles que la pièce 100 peut être assimilée à un ressort de
type «épingle à cheveux».The
La figure 4 représente le principe à la base
de la présente invention et explique comment la pièce de
rétention et de rigidification 100 est disposée au niveau
d'une virole et de deux aubes successives pour assurer à la
fois la rigidification de cette virole et la rétention des
deux aubes successives à cette virole. Selon ce principe,
la virole, et de préférence la virole intérieure 4, est
pourvue de lumières ou ajours 42,42' qui permettent la
fixation, de préférence sur la face interne de ladite
virole 4, des aubes successives 60,61,62,... par leurs
extrémités 51,51'. Les extrémités 51,51' desdites aubes
présentent elles-mêmes des ajours 52,52'. Lesdites aubes
60,61,62,... sont solidarisées à la virole 4 à l'aide de la
pièce de rétention et de rigidification 100. Plus
précisément, les tenons plats 117 et 119 de ladite pièce de
rétention et de rigidification 100 sont logés dans les
ajours 52, 52' des deux aubes successives 60,61,62,... La
pièce de rétention et de rigidification 100 permet ainsi de
solidariser les aubes deux à deux (60 et 61, 62 et 63,
etc.) au niveau des étages redresseurs. Concrètement, pour
mettre en place la pièce de rétention et de rigidification
100 au niveau des aubes 60,61,62,..., on exerce sur elle
une précompression (voir les flèches sur la figure 3) comme
on le ferait en utilisant une pince à sucre. On positionne
ensuite la pièce 100 de façon à ce que ses tenons aplatis
117, 119 viennent se loger dans les ajours respectivement
52 et 52' des aubes successives 60,61,62,... Enfin on
relâche simplement ladite pièce 100. Une fois montée,
l'effet ressort de la pièce de rétention et de
rigidification 100 agit en maintenant les aubes successives
60,61,62,... écartées.Figure 4 shows the basic principle
of the present invention and explains how the part of
retention and
Enfin, il est habituel de noyer tout le dispositif, c'est-à-dire la pièce de rétention et de rigidification 100 et les extrémités des aubes, dans un élément élastomère 200 qui permet de sceller l'extrémité de l'aube à la virole.Finally, it is usual to drown all device, i.e. the retention and stiffening 100 and the tips of the blades, in a elastomeric element 200 which makes it possible to seal the end of dawn at the ferrule.
En outre, ceci permet d'augmenter l'étanchéité de tout l'étage redresseur.In addition, this increases the tightness of the entire rectifier stage.
Claims (4)
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE60026686T DE60026686T2 (en) | 2000-12-06 | 2000-12-06 | Stator stage of a compressor |
| EP00870290A EP1213483B1 (en) | 2000-12-06 | 2000-12-06 | Compressor stator stage |
| US10/001,122 US6655912B2 (en) | 2000-12-06 | 2001-11-30 | Guide vane stage of a compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP00870290A EP1213483B1 (en) | 2000-12-06 | 2000-12-06 | Compressor stator stage |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1213483A1 true EP1213483A1 (en) | 2002-06-12 |
| EP1213483B1 EP1213483B1 (en) | 2006-03-15 |
Family
ID=8175867
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP00870290A Expired - Lifetime EP1213483B1 (en) | 2000-12-06 | 2000-12-06 | Compressor stator stage |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US6655912B2 (en) |
| EP (1) | EP1213483B1 (en) |
| DE (1) | DE60026686T2 (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2072760A1 (en) | 2007-12-21 | 2009-06-24 | Techspace aero | Device for attaching vanes to a stage collar of a turbomachine stator and associated attachment method |
| US9771815B2 (en) | 2012-12-24 | 2017-09-26 | Safran Aero Boosters Sa | Blade-retaining plate with internal cut-outs for a turbomachine stator |
| EP3406854A1 (en) * | 2017-05-26 | 2018-11-28 | United Technologies Corporation | Stator assembly with retention clip for gas turbine engine |
| EP3412873A1 (en) * | 2017-06-09 | 2018-12-12 | United Technologies Corporation | Stator assembly with retention clip for gas turbine engine |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6984108B2 (en) * | 2002-02-22 | 2006-01-10 | Drs Power Technology Inc. | Compressor stator vane |
| US7651319B2 (en) | 2002-02-22 | 2010-01-26 | Drs Power Technology Inc. | Compressor stator vane |
| US7108480B2 (en) * | 2004-05-28 | 2006-09-19 | General Electric Company | Method and apparatus for balancing turbine rotors |
| US20090110552A1 (en) * | 2007-10-31 | 2009-04-30 | Anderson Rodger O | Compressor stator vane repair with pin |
| US9045985B2 (en) | 2012-05-31 | 2015-06-02 | United Technologies Corporation | Stator vane bumper ring |
| US9777594B2 (en) | 2015-04-15 | 2017-10-03 | Siemens Energy, Inc. | Energy damping system for gas turbine engine stationary vane |
| DE102016210454A1 (en) * | 2016-06-14 | 2017-12-14 | MTU Aero Engines AG | Balancing weight for a blade of a turbine stage |
| US10655502B2 (en) | 2017-05-26 | 2020-05-19 | United Technologies Corporation | Stator assembly with retention clip for gas turbine engine |
| US10533456B2 (en) | 2017-05-26 | 2020-01-14 | United Technologies Corporation | Stator assembly with contoured retention clip for gas turbine engine |
| US10557412B2 (en) | 2017-05-30 | 2020-02-11 | United Technologies Corporation | Systems for reducing deflection of a shroud that retains fan exit stators |
| US10724389B2 (en) * | 2017-07-10 | 2020-07-28 | Raytheon Technologies Corporation | Stator vane assembly for a gas turbine engine |
| US20190078469A1 (en) * | 2017-09-11 | 2019-03-14 | United Technologies Corporation | Fan exit stator assembly retention system |
| US10808559B2 (en) | 2018-06-01 | 2020-10-20 | Raytheon Technologies Corporation | Guide vane retention assembly for gas turbine engine |
| US11852038B2 (en) * | 2019-11-07 | 2023-12-26 | Rtx Corporation | Stator retention of gas turbine engine |
| CN111734499B (en) * | 2020-04-21 | 2022-08-19 | 中国航发沈阳发动机研究所 | Booster stage stator blade limiting block and booster stage stator part with same |
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| GB748912A (en) * | 1950-08-01 | 1956-05-16 | Rolls Royce | Improvements in or relating to blade assemblies of compressors and turbines and likemachines |
| US2812159A (en) * | 1952-08-19 | 1957-11-05 | Gen Electric | Securing means for turbo-machine blading |
| FR2671140A1 (en) * | 1990-12-27 | 1992-07-03 | Snecma | Guide vanes for a turbo machine compressor |
| US5569019A (en) * | 1993-12-22 | 1996-10-29 | Alliedsignal Inc. | Tear-away composite fan stator vane |
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| US4452564A (en) * | 1981-11-09 | 1984-06-05 | The Garrett Corporation | Stator vane assembly and associated methods |
| FR2697285B1 (en) * | 1992-10-28 | 1994-11-25 | Snecma | Blade end locking system. |
| US6409472B1 (en) * | 1999-08-09 | 2002-06-25 | United Technologies Corporation | Stator assembly for a rotary machine and clip member for a stator assembly |
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2000
- 2000-12-06 EP EP00870290A patent/EP1213483B1/en not_active Expired - Lifetime
- 2000-12-06 DE DE60026686T patent/DE60026686T2/en not_active Expired - Fee Related
-
2001
- 2001-11-30 US US10/001,122 patent/US6655912B2/en not_active Expired - Fee Related
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB748912A (en) * | 1950-08-01 | 1956-05-16 | Rolls Royce | Improvements in or relating to blade assemblies of compressors and turbines and likemachines |
| US2812159A (en) * | 1952-08-19 | 1957-11-05 | Gen Electric | Securing means for turbo-machine blading |
| FR2671140A1 (en) * | 1990-12-27 | 1992-07-03 | Snecma | Guide vanes for a turbo machine compressor |
| US5569019A (en) * | 1993-12-22 | 1996-10-29 | Alliedsignal Inc. | Tear-away composite fan stator vane |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2072760A1 (en) | 2007-12-21 | 2009-06-24 | Techspace aero | Device for attaching vanes to a stage collar of a turbomachine stator and associated attachment method |
| US9771815B2 (en) | 2012-12-24 | 2017-09-26 | Safran Aero Boosters Sa | Blade-retaining plate with internal cut-outs for a turbomachine stator |
| EP3406854A1 (en) * | 2017-05-26 | 2018-11-28 | United Technologies Corporation | Stator assembly with retention clip for gas turbine engine |
| US10590783B2 (en) | 2017-05-26 | 2020-03-17 | United Technologies Corporation | Stator assembly with retention clip for gas turbine engine |
| EP3412873A1 (en) * | 2017-06-09 | 2018-12-12 | United Technologies Corporation | Stator assembly with retention clip for gas turbine engine |
| US10767503B2 (en) | 2017-06-09 | 2020-09-08 | Raytheon Technologies Corporation | Stator assembly with retention clip for gas turbine engine |
Also Published As
| Publication number | Publication date |
|---|---|
| US20020085913A1 (en) | 2002-07-04 |
| DE60026686T2 (en) | 2006-10-05 |
| EP1213483B1 (en) | 2006-03-15 |
| DE60026686D1 (en) | 2006-05-11 |
| US6655912B2 (en) | 2003-12-02 |
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