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EP1213484A1 - Compressor stator stage - Google Patents

Compressor stator stage Download PDF

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Publication number
EP1213484A1
EP1213484A1 EP00870292A EP00870292A EP1213484A1 EP 1213484 A1 EP1213484 A1 EP 1213484A1 EP 00870292 A EP00870292 A EP 00870292A EP 00870292 A EP00870292 A EP 00870292A EP 1213484 A1 EP1213484 A1 EP 1213484A1
Authority
EP
European Patent Office
Prior art keywords
blades
ferrules
fixed
series
rectifier stage
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP00870292A
Other languages
German (de)
French (fr)
Other versions
EP1213484B1 (en
Inventor
Mathieu Bos
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aero Boosters SA
Original Assignee
Techspace Aero SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Techspace Aero SA filed Critical Techspace Aero SA
Priority to DE60026687T priority Critical patent/DE60026687T2/en
Priority to EP00870292A priority patent/EP1213484B1/en
Priority to US10/000,830 priority patent/US6595747B2/en
Publication of EP1213484A1 publication Critical patent/EP1213484A1/en
Application granted granted Critical
Publication of EP1213484B1 publication Critical patent/EP1213484B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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.
  • the blades are joined to the ferrules, both interior and exterior, by rivets, bolts or welds.
  • the use of these means of joining presents the major drawback of disrupt the flow and generate a pressure drop in the aerodynamic vein.
  • the present invention aims to provide a solution which simplifies the assembly of the blades fixed to both the inner ferrule and the ferrule exterior.
  • the present invention aims to allow a solution that offers great simplicity of assembly and which does not require assembly operations additional.
  • the present invention also aims to propose a solution that allows the vein aerodynamics of the flow is not affected by the presence welds or rivets at the ferrule.
  • the present invention also aims to allow a low cost solution.
  • 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 one of ferrules, and preferably the two inner ferrules and exterior, are provided with lights which allow the passage of said blades in these lights in order to allow their attachment to the ferrules.
  • blades also have at least one and preferably at their two ends, an opening intended to allow the passage of a locking element. This element of locking will advantageously allow the joining of the blades to at least one and preferably to the two ferrules on the non-functional side, i.e. side of the inner face for the inner ferrule and side of the outer face for the outer shell.
  • the joining of the blades to the ferrule or to the ferrules is carried out by passing a strip in one or several pieces, which successively crosses all always blades of the same rectifier stage, and this from non-functional side of the ferrules.
  • this strip presents a elastic function and will be embedded in an elastomeric element which protects the different parts, and especially the locking elements.
  • Figure 1 shows a general view of the compression stage of a turbofan.
  • Figure 2 shows the solution implemented work by the present invention to secure blades fixed to both exterior and interior ferrules.
  • a portion 16 and 17 of said fixed blades 60,61,62,63, ... exceeds ferrules 4 and 5.
  • the different portions 16 or 17 each also have an opening 20,21,22,23, ... and 30,31,32, ... which allows the introduction of an element of locking (40 and 50 respectively).
  • Said element of locking here takes the form of a strip which, in crossing simultaneously either every day 20,21,22, ..., either every day 30,31,32, ... fixed blades 60,61,62,63, ..., secures said fixed vanes to inner 4 and outer 5 ferrules. This occurs on the non-functional side of said shell, that is to say on the inner face of the inner shroud 4 and on the outer face of the outer shell 5.
  • this strip presents a elastic function and consists of a single piece.
  • the strip can understand several pieces.
  • the fixed blades are secured to the two ferrules in this way, on the one hand to the inner ferrule 4 and on the other hand to the outer shroud 5, by through two locking elements 40 and 50. Another possibility is that the fixed blades are not secured together with only one of the two ferrules.
  • Such a securing device has several advantages. First of all, it does not entail any defect in the aerodynamic flow stream, which reduces strongly the pressure drops in it.
  • Another advantage is that it allows to assemble and secure two types of parts without mechanical link, fixed vanes and ferrule, without modification of the functional aspect of these two types of rooms.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A diffuser stage comprises concentric external and internal (4) flanges connected to each other by a series of fixed blades (60,61,62). At least one of the flanges has a series of slots (14,15) for the passage of the blades. The blades have at their ends (16,17) a cut-out (20,21,22, 30,31,32) for the passage of a locking element (40,50) which simultaneously unites all the blades in the diffuser stage.

Description

Objet de l'inventionSubject of the invention

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.

Etat de la techniqueState of the art

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.

Un 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.An important problem in the case of floors rectifiers 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.

Habituellement, on solidarise les aubes aux viroles, tant intérieure qu'extérieure, par des rivets, des boulons 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, bolts or welds. However, the use of these means of joining presents the major drawback of disrupt the flow and generate a pressure drop in the aerodynamic vein.

Buts de l'inventionAims of the invention

La présente invention vise à proposer une solution qui permette de simplifier l'assemblage des aubes fixes tant à la virole intérieure qu'à la virole extérieure.The present invention aims to provide a solution which simplifies the assembly of the blades fixed to both the inner ferrule and the ferrule exterior.

En particulier, la présente invention vise à permettre une solution qui offre une grande simplicité de montage et qui 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 which does not require assembly operations additional.

La présente invention vise également à proposer une solution qui permette que la veine aérodynamique du flux ne soit pas altérée par la présence de soudures ou des rivets au niveau de la virole.The present invention also aims to propose a solution that allows the vein aerodynamics of the flow is not affected by the presence welds or rivets at the ferrule.

La présente invention vise également à permettre une solution d'un coût peu élevé.The present invention also aims to allow a low cost solution.

Principaux éléments caractéristiques de l'inventionMain characteristic features of the invention

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 une des viroles, et de préférence les deux viroles intérieure et extérieure, sont munies de lumières qui permettent le passage desdites aubes dans ces lumières en vue de permettre leur solidarisation aux viroles. Dans ce but, les aubes présentent également à au moins une et de préférence à leurs deux extrémités, un ajour destiné à permettre le passage d'un élément de verrouillage. Cet élément de verrouillage permettra de manière avantageuse la solidarisation des aubes à au moins une et de préférence aux deux viroles du côté non fonctionnel, c'est-à-dire du côté de la face interne pour la virole intérieure et du côté de la face externe pour la virole extérieure.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 one of ferrules, and preferably the two inner ferrules and exterior, are provided with lights which allow the passage of said blades in these lights in order to allow their attachment to the ferrules. For this purpose, blades also have at least one and preferably at their two ends, an opening intended to allow the passage of a locking element. This element of locking will advantageously allow the joining of the blades to at least one and preferably to the two ferrules on the non-functional side, i.e. side of the inner face for the inner ferrule and side of the outer face for the outer shell.

Selon la présente invention, la solidarisation des aubes à la virole ou aux viroles s'effectue par le passage d'un bandeau en un seul ou plusieurs morceaux, qui traverse successivement tous les ajours des aubes d'un même étage redresseur, et ceci du côté non fonctionnel des viroles.According to the present invention, the joining of the blades to the ferrule or to the ferrules is carried out by passing a strip in one or several pieces, which successively crosses all always blades of the same rectifier stage, and this from non-functional side of the ferrules.

Avantageusement, ce bandeau présente une fonction élastique et sera noyé dans un élément élastomère qui permet de protéger les différentes pièces, et en particulier les éléments de verrouillage.Advantageously, this strip presents a elastic function and will be embedded in an elastomeric element which protects the different parts, and especially the locking elements.

Brève description des dessinsBrief description of the drawings

La figure 1 représente une vue générale de l'étage de compression d'un turbofan.Figure 1 shows a general view of the compression stage of a turbofan.

La figure 2 représente la solution mise en oeuvre par la présente invention pour solidariser des aubes fixes aux viroles tant extérieure qu'intérieure. Figure 2 shows the solution implemented work by the present invention to secure blades fixed to both exterior and interior ferrules.

Description d'une forme d'exécution préférée de l'inventionDescription of a preferred embodiment of the invention

La solution proposée par la présente invention en vue de solidariser les aubes fixes 6 aux viroles 4 et 5 pour un étage redresseur 2 est décrite à la figure 2. Bien entendu, la même solution pourrait être adaptée à chaque étage redresseur 2',2",... Chaque virole, tant la virole intérieure 4 que la virole extérieure 5, est pourvue d'une série de lumières ou ajours (respectivement les séries 14 et 15) qui permettent le passage des aubes fixes 60,61,62,63,... par une de leurs extrémités à la virole correspondante.The solution proposed by this invention for securing the stationary vanes 6 to ferrules 4 and 5 for a rectifier stage 2 is described in figure 2. Of course, the same solution could be adapted to each rectifier stage 2 ', 2 ", ... Each ferrule, both the inner ring 4 and the outer ring 5, is provided with a series of lights or openings (respectively series 14 and 15) which allow the passage of the blades fixed 60,61,62,63, ... by one of their ends at the corresponding ferrule.

Il en résulte qu'une fois que les aubes fixes 60,61,62,63,... seront fixées sur lesdites viroles, une portion 16 et 17 desdites aubes fixes 60,61,62,63,... dépasse des viroles 4 et 5. Les différentes portions 16 ou 17 présentent chacune elles aussi un ajour 20,21,22,23,... et 30,31,32,... qui permet l'introduction d'un élément de verrouillage (respectivement 40 et 50). Ledit élément de verrouillage prend ici la forme d'un bandeau qui, en traversant simultanément soit tous les ajours 20,21,22,..., soit tous les ajours 30,31,32,... des aubes fixes 60,61,62,63,..., solidarise lesdites aubes fixes aux viroles intérieure 4 et extérieure 5. Ceci se produit sur la face non fonctionnelle de ladite virole, c'est-à-dire sur la face interne de la virole intérieure 4 et sur la face externe de la virole extérieure 5.As a result, once the vanes are fixed 60,61,62,63, ... will be fixed on said ferrules, a portion 16 and 17 of said fixed blades 60,61,62,63, ... exceeds ferrules 4 and 5. The different portions 16 or 17 each also have an opening 20,21,22,23, ... and 30,31,32, ... which allows the introduction of an element of locking (40 and 50 respectively). Said element of locking here takes the form of a strip which, in crossing simultaneously either every day 20,21,22, ..., either every day 30,31,32, ... fixed blades 60,61,62,63, ..., secures said fixed vanes to inner 4 and outer 5 ferrules. This occurs on the non-functional side of said shell, that is to say on the inner face of the inner shroud 4 and on the outer face of the outer shell 5.

De préférence, ce bandeau présente une fonction élastique et est constitué d'un seul morceau. Selon une autre forme d'exécution, le bandeau peut comprendre plusieurs morceaux.Preferably, this strip presents a elastic function and consists of a single piece. According to another embodiment, the strip can understand several pieces.

Il est à noter que dans le cas représenté à la figure 2, les aubes fixes sont solidarisées aux deux viroles de cette manière, d'une part à la virole intérieure 4 et d'autre part à la virole extérieure 5, par l'intermédiaire de deux éléments de verrouillage 40 et 50. Une autre possibilité est que les aubes fixes ne soient solidarisées ainsi qu'à une seule des deux viroles.It should be noted that in the case shown in Figure 2, the fixed blades are secured to the two ferrules in this way, on the one hand to the inner ferrule 4 and on the other hand to the outer shroud 5, by through two locking elements 40 and 50. Another possibility is that the fixed blades are not secured together with only one of the two ferrules.

De préférence, les extrémités 16 ou 17 des aubes fixes 60,61,62,63,... au niveau desquelles passe le l'élément de verrouillage 40 ou 50 sont noyées dans un élément élastomère 18 ou 19.Preferably, the ends 16 or 17 of the fixed blades 60,61,62,63, ... at which the the locking element 40 or 50 are embedded in a elastomer element 18 or 19.

Un tel dispositif de solidarisation présente plusieurs avantages. Tout d'abord, il n'entraíne aucun défaut dans la veine aérodynamique du flux, ce qui réduit fortement les pertes de charge dans celui-ci.Such a securing device has several advantages. First of all, it does not entail any defect in the aerodynamic flow stream, which reduces strongly the pressure drops in it.

Il est simple à réaliser et facile à monter et à démonter. En outre, il garantit une utilisation optimale de la matière. Un autre avantage est qu'il permet d'assembler et de solidariser deux types de pièces sans lien mécanique, les aubes fixes et la virole, sans modification de l'aspect fonctionnel de ces deux types de pièces.It is simple to make and easy to assemble and disassemble. In addition, it guarantees use optimal material. Another advantage is that it allows to assemble and secure two types of parts without mechanical link, fixed vanes and ferrule, without modification of the functional aspect of these two types of rooms.

Claims (4)

Etage redresseur (2) d'un compresseur (1) comprenant une virole extérieure (5) et une virole intérieure (4), toutes deux concentriques et de préférence circulaires et reliées l'une à l'autre par une série d'aubes fixes (60,61,62,63,...), caractérisé en ce qu'au moins une des viroles est pourvue d'une série de lumières ou ajours (séries 14 ou 15) qui permettent le passage desdites aubes (60,61,62,63,...) dans ces lumières ou ajours, les aubes fixes (60,61,62,63,...) présentant à au moins une de leurs extrémités (16 ou 17) un ajour (20,21,22,... ou 30,31,32,...) destiné à permettre le passage d'au moins un élément de verrouillage (40 ou 50) permettant de solidariser simultanément toutes les aubes (60,61,62,63,...) présentes dans l'étage redresseur (2) et ceci du côté non fonctionnel de la virole.Rectifier stage (2) of a compressor (1) comprising an outer shroud (5) and an inner shroud (4), both concentric and preferably circular and connected to each other by a series of fixed blades (60,61,62,63, ...), characterized in that at least one of the ferrules is provided with a series of lights or openings (series 14 or 15) which allow the passage of said blades (60,61 , 62.63, ...) in these lights or openings, the fixed vanes (60,61,62,63, ...) having at least one of their ends (16 or 17) an openwork (20,21 , 22, ... or 30,31,32, ...) intended to allow the passage of at least one locking element (40 or 50) allowing all the blades to be secured simultaneously (60,61,62,63 , ...) present in the rectifier stage (2) and this on the non-functional side of the shell. Etage redresseur selon la revendication 1, caractérisé en ce que l'élément de verrouillage (40 ou 50) se présente sous la forme d'un bandeau qui traverse successivement tous les ajours (20,21,22,... ou 30,31,32,...) des aubes successives (60,61,62,63,...).Rectifier stage according to claim 1, characterized in that the locking element (40 or 50) is in the form of a strip which passes successively through all the openings (20,21,22, ... or 30,31 , 32, ...) of successive blades (60,61,62,63, ...). Etage redresseur selon la revendication 2, caractérisé en ce que le bandeau se présente en un ou plusieurs morceaux présentant une fonction élastique.Rectifier stage according to claim 2, characterized in that the strip is presented in one or more pieces having an elastic function. Etage redresseur selon l'une des revendications précédentes, caractérisé en ce que l'extrémité (16 ou 17) des aubes fixes (60,61,62,63,...) au niveau de laquelle passe l'élément de verrouillage (40 ou 50) est noyée dans un élément élastomère (18 ou 19).Rectifier stage according to one of the preceding claims, characterized in that the end (16 or 17) of the fixed vanes (60,61,62,63, ...) at which the locking element (40 or 50) is embedded in an elastomeric element (18 or 19).
EP00870292A 2000-12-06 2000-12-06 Compressor stator stage Expired - Lifetime EP1213484B1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE60026687T DE60026687T2 (en) 2000-12-06 2000-12-06 Stator stage of a compressor
EP00870292A EP1213484B1 (en) 2000-12-06 2000-12-06 Compressor stator stage
US10/000,830 US6595747B2 (en) 2000-12-06 2001-11-30 Guide vane stage of a compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00870292A EP1213484B1 (en) 2000-12-06 2000-12-06 Compressor stator stage

Publications (2)

Publication Number Publication Date
EP1213484A1 true EP1213484A1 (en) 2002-06-12
EP1213484B1 EP1213484B1 (en) 2006-03-15

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EP00870292A Expired - Lifetime EP1213484B1 (en) 2000-12-06 2000-12-06 Compressor stator stage

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US (1) US6595747B2 (en)
EP (1) EP1213484B1 (en)
DE (1) DE60026687T2 (en)

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EP2977559B1 (en) * 2014-07-25 2017-06-07 Safran Aero Boosters SA Axial turbomachine stator and corresponding turbomachine
RU2724420C2 (en) * 2014-08-26 2020-06-23 Сафран Эркрафт Энджинз Guide blade from composite material, gas turbine engine and method of making guide vane
USD805176S1 (en) 2016-05-06 2017-12-12 Airius Ip Holdings, Llc Air moving device
USD820967S1 (en) 2016-05-06 2018-06-19 Airius Ip Holdings Llc Air moving device
US10487852B2 (en) 2016-06-24 2019-11-26 Airius Ip Holdings, Llc Air moving device
US10767502B2 (en) 2016-12-23 2020-09-08 Rolls-Royce Corporation Composite turbine vane with three-dimensional fiber reinforcements
USD886275S1 (en) 2017-01-26 2020-06-02 Airius Ip Holdings, Llc Air moving device
RU2656168C1 (en) * 2017-04-13 2018-05-31 Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Gas turbine engine compressor straightener blades
USD885550S1 (en) 2017-07-31 2020-05-26 Airius Ip Holdings, Llc Air moving device
US10619498B2 (en) 2017-09-06 2020-04-14 United Technologies Corporation Fan exit stator assembly
US20190078469A1 (en) * 2017-09-11 2019-03-14 United Technologies Corporation Fan exit stator assembly retention system
USD887541S1 (en) 2019-03-21 2020-06-16 Airius Ip Holdings, Llc Air moving device
CA3136808A1 (en) 2019-04-17 2020-10-22 Airius Ip Holdings, Llc Air moving device with bypass intake
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
US11898450B2 (en) 2021-05-18 2024-02-13 Rtx Corporation Flowpath assembly for gas turbine engine
US11781432B2 (en) 2021-07-26 2023-10-10 Rtx Corporation Nested vane arrangement for gas turbine engine

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CN103835771B (en) * 2012-11-27 2017-04-26 赛峰航空助推器股份有限公司 Axial Turbomachine Stator with Segmented Inner Shell
CN103835771A (en) * 2012-11-27 2014-06-04 航空技术空间股份有限公司 Axial Turbomachine Stator with Segmented Inner Shell
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US10190426B2 (en) 2014-03-06 2019-01-29 Safran Ceramics Stator sector for a turbine engine, and a method of fabricating it
EP3266986A1 (en) * 2016-07-06 2018-01-10 United Technologies Corporation Segmented stator assembly with potting for vane retainment
EP3266985A1 (en) * 2016-07-06 2018-01-10 United Technologies Corporation Ring stator with potting for vane retainment
US10450878B2 (en) 2016-07-06 2019-10-22 United Technologies Corporation Segmented stator assembly
US10633988B2 (en) 2016-07-06 2020-04-28 United Technologies Corporation Ring stator
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DE60026687D1 (en) 2006-05-11
DE60026687T2 (en) 2006-11-09
US20020085916A1 (en) 2002-07-04
EP1213484B1 (en) 2006-03-15
US6595747B2 (en) 2003-07-22

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