EP1217168A1 - Axial fixation of gas turbine rotor blades - Google Patents
Axial fixation of gas turbine rotor blades Download PDFInfo
- Publication number
- EP1217168A1 EP1217168A1 EP00870311A EP00870311A EP1217168A1 EP 1217168 A1 EP1217168 A1 EP 1217168A1 EP 00870311 A EP00870311 A EP 00870311A EP 00870311 A EP00870311 A EP 00870311A EP 1217168 A1 EP1217168 A1 EP 1217168A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- rotor
- boss
- ring
- section
- blades
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/326—Locking of axial insertion type blades by other means
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
- F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
Definitions
- the present invention relates to a floor rotor of a compressor or turbine that includes a succession of rotor blades rotor stages separated each time by rectifier stages, distributors (or stator). Said rotating vanes are mounted on a rotor which is generally in the form of a disc.
- the present invention relates more precisely by means of retention or solidarity said blades on the rotor in a stage rotor.
- Compressors and coaxial turbines are well known per se, and are used in several types application. In particular, they are used in dual-body engines, turbofans or turbojet engines. We notice also their presence in power plants. These compressors or turbines low or high pressure are essentially consisting of several stages of blades rotating or rotor stages separated by storeys stator, distributor or rectifier to reposition (distribute or straighten) the vector velocity of the fluid leaving the previous stage before send it to the next compartment.
- Each of the stator stages is constituted of fixed vanes which are either fixed on rings concentric interior (ferrules) is assembled by segments on crankcases.
- the rotor stages consist of vanes rotating mounted on a rotor presenting itself usually in the form of a disc.
- the blades at their base a part called more commonly referred to as "dawn bulb" which takes the form of a succession of excrescences and troughs and which may adapt to a complementary female cavity located in the rotor disk.
- the succession of excrescences and hollow of the nest will prevent the dawn from separating radially when moving by action of the centrifugal force.
- the problem to be solved then remains the upstream and downstream retention of said rotating blades on the rotor.
- Several ways of securing said vanes rotating can be considered.
- a first possibility is the use rings and retaining flanges.
- a ring which present in the form of a flat ring, serves as a circlip and allows the downstream retention of said blades when they are arranged on the rotor, while the retaining flange allows upstream retention and further anti-rotation of the flat ring. Said flange is then fixed and centered between two successive rotor discs.
- Another method of fixing vanes mobile or rotating on said rotor is done using rivets that guarantee both the retention upstream than the downstream retention.
- the housing of the rivet is in this case machined for two-thirds of its circumference on dawn, the last remaining third on the disk. Riveting is then done by expansion of the tubular part of the rivet after setting up all the blades in the corresponding rotor stage.
- the present invention aims to provide a solution that allows to secure the rotating blades or mobile to a disk serving as a rotor.
- the present invention aims to allow retention both upstream and downstream while using only one piece for all blades.
- the present invention also aims to significantly reduce the exposure time or mounting and to facilitate maintenance of the rotor stage.
- the present invention relates to a means for of retention or joining for a moving blade on a rotor body in a rotor stage of a compressor or of an axial turbine, characterized in that it presents itself in the form of a ring opened by a slot on a certain section, this section presenting on a side radial excess material in the form of a boss.
- the section on which the extra material in the form of a boss is present basically corresponds to the expected distance between two successive moving blades.
- the additional amount of material in the form of a boss is drawn and calculated so as to mechanically compensate the lack of material due to the presence of the slit.
- the ring has in section a conical shape, with the exception of the section with a surplus of material in the form of a boss.
- the present invention furthermore relates to a rotor stage of a compressor or an axial turbine comprising a series of rotating vanes mounted on a rotor body, said blades having a flat and a dawn bulb, each dawn bulb presenting on a first face an excrescence in the form of a beaver tooth which will serve as a frank stop by positioning itself directly in contact with said rotor body and secondly on the opposite side an excrescence in the form of a hook which will allow the placement of the retention means according to the present invention.
- Figure 1 represents a general view of a low-pressure turbine of a turbofan in which are present a succession of distributor floors and floors rotor.
- FIG. 2 represents a sectional view of a blade provided with means for securing to the rotor.
- Figure 3 shows a perspective view of the bulb of a blade intended to be used according to mounting method of the present invention.
- Figure 4 shows a perspective view fastening means implemented according to the present invention of rotating vanes to the rotor.
- Figure 5 shows a perspective view of the fastening ring according to the present invention.
- Figures 6a to 6c show the principle mounting the ring according to the present invention.
- Each distributor stage 2,2 ', 2 ", ... is essentially consisting of blades 2,2 ', 2' ', ... contained between two indoor platforms 4,4 ', 4 ", ... and outdoor 5,5 ', 5 ", ...
- Each rotor stage consists of the rotating blades 3.3 ', 3 ", ... all connected to rotor 1 by retention means.
- the gas first strikes the first rotor of the low pressure turbine then its velocity vector is repositioned by the first floor distributor stator low pressure 3 before hitting the second rotor stage 2 'to be repositioned in 3', etc.
- the gas undergoes a thrust cycle - redistribution of speeds at the end of which its energy kinetics gradually decreases as well as its pressure, while the rotor work grows by adding up from floor to floor.
- a rotating dawn 3 typically presents in the form of a flat 30 linked to a bulb of dawn 31.
- the different bulbs 31,31 ', 31 "will be machined so that they can be arranged successively around a disk 10 which serves as a rotor, as shown in Figure 4.
- the placement of the rotating vanes 3 on the rotor 10 is by sliding between the teeth of the disc. Indeed, the dawn bulbs 31,31 ', 31 "have a shape male consisting of a succession of excrescences and hollow to which essentially corresponds a cavity complementary female made in the disk 10 serving rotor, these cavities creating "teeth" on the disc.
- the bulbs 31.31 ', 31 each have, on the one hand, on a first face, an excrescence in the form of a tooth of beaver 32 which will serve as a free stop by positioning itself directly in contact with the rotor disk 10, and on the other side, on the opposite side, an outgrowth under hook form 33 which will allow the placement of a ring 40.
- this ring 40 is advantageously allow the joining of all the dawn bulbs 31,31 ', 31 "on the same rotor disk 10. Such a ring is shown in detail in FIG.
- this ring 40 has a slot 41, preferably cut at an angle, so that one can perform the establishment of the ring in pre-empting it and then releasing it.
- this ring 40 presents on at least a radial flank 42 an extra material in the form of a boss 45.
- this boss 45 is present on a portion that basically corresponds to the planned distance between two successive blades as well as shown in Figure 4. This distance is also said slot 41.
- the boss also has the advantage to prevent rotation of the ring 40 with respect to record 10.
- said boss 45 is drawn and calculated to exactly match the lack of material due to the presence of the slot 41.
- the boss 45 therefore has purpose of proposing an unbalance which must compensate exactly the lack of material due to the slit 41.
- the ring 40 as shown FIG. 2 shows a conical section which, when rotor stage operation, decrease or even remove the axial play of the dawn on the disc and therefore of reduce the vibrations that could be generated by the centrifugal force.
- Figures 6a-6c show the implementation place of the ring 40 on the rotor disk 10.
- the ring 40 is configured in such a way in the free state (Fig. 6a), it has some A.
- we will have tendency to pinch when assembling in order to preload the ring Fig. 6b.
- the ring will loosen so that will position perfectly between two rotating blades as well as shown in Figure 5.
- This ring is preferably made in one metal material that allows its use to high temperatures.
- this allows retention with one piece which is the ring and this for all the blades, which significantly reduces the exposure time and mounting and to facilitate maintenance.
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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 rotorique d'un compresseur ou d'une turbine qui comprend une succession d'étages rotoriques d'aubes tournantes séparés chaque fois par des étages redresseurs, distributeurs (ou statoriques). Lesdites aubes tournantes sont montées sur un rotor qui se présente en règle générale sous la forme d'un disque.The present invention relates to a floor rotor of a compressor or turbine that includes a succession of rotor blades rotor stages separated each time by rectifier stages, distributors (or stator). Said rotating vanes are mounted on a rotor which is generally in the form of a disc.
La présente invention se rapporte plus précisément au moyen de rétention ou solidarisation desdites aubes mobiles sur le rotor dans un étage rotorique.The present invention relates more precisely by means of retention or solidarity said blades on the rotor in a stage rotor.
Les compresseurs et turbines 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 ou turbines basse ou haute pression sont essentiellement constitués de plusieurs étages d'aubes tournantes ou étages rotoriques séparés par des étages statoriques, distributeurs ou redresseurs qui ont pour but de repositionner (distribuer ou redresser) le vecteur vitesse du fluide sortant de l'étage précédent avant de l'envoyer vers le compartiment suivant.Compressors and coaxial turbines are well known per se, and are used in several types application. In particular, they are used in dual-body engines, turbofans or turbojet engines. We notice also their presence in power plants. These compressors or turbines low or high pressure are essentially consisting of several stages of blades rotating or rotor stages separated by storeys stator, distributor or rectifier to reposition (distribute or straighten) the vector velocity of the fluid leaving the previous stage before send it to the next compartment.
Chacun des étages statoriques est constitué d'aubes fixes qui sont soit fixées sur des anneaux concentriques intérieurs (viroles) soit assemblées par segments sur des carters.Each of the stator stages is constituted of fixed vanes which are either fixed on rings concentric interior (ferrules) is assembled by segments on crankcases.
Les étages rotoriques sont constitués d'aubes tournantes montées sur un rotor se présentant habituellement sous la forme d'un disque. Les aubes tournantes présentent à leur base une partie appelée plus communément "bulbe d'aube" qui prend la forme d'une succession d'excroissances et de creux et qui pourra s'adapter à une cavité femelle complémentaire située dans le disque du rotor. La succession d'excroissances et de creux de l'emboítement empêchera l'aube de se désolidariser radialement lors de la mise en mouvement par action de la force centrifuge.The rotor stages consist of vanes rotating mounted on a rotor presenting itself usually in the form of a disc. The blades at their base a part called more commonly referred to as "dawn bulb" which takes the form of a succession of excrescences and troughs and which may adapt to a complementary female cavity located in the rotor disk. The succession of excrescences and hollow of the nest will prevent the dawn from separating radially when moving by action of the centrifugal force.
Le problème à résoudre reste alors la rétention amont et aval desdites aubes tournantes sur le rotor. Plusieurs manières de solidariser lesdites aubes tournantes peuvent être envisagées.The problem to be solved then remains the upstream and downstream retention of said rotating blades on the rotor. Several ways of securing said vanes rotating can be considered.
Une première possibilité est l'utilisation d'anneaux et flasques de retenue. Un anneau, qui se présente sous la forme d'un anneau plat, sert de circlip et permet la rétention aval desdites aubes lorsqu'elles sont disposées sur le rotor, tandis que le flasque de retenue permet la rétention amont et en outre l'anti-rotation de l'anneau plat. Ledit flasque est ensuite fixé et centré entre deux disques successifs du rotor.A first possibility is the use rings and retaining flanges. A ring, which present in the form of a flat ring, serves as a circlip and allows the downstream retention of said blades when they are arranged on the rotor, while the retaining flange allows upstream retention and further anti-rotation of the flat ring. Said flange is then fixed and centered between two successive rotor discs.
Un autre procédé de fixation des aubes mobiles ou tournantes sur ledit rotor s'effectue à l'aide de rivets qui permettent de garantir tant la rétention amont que la rétention aval. Le logement du rivet est dans ce cas usiné pour les deux tiers de sa circonférence sur l'aube, le dernier tiers restant sur le disque. Le rivetage se fait ensuite par expansion de la partie tubulaire du rivet après avoir mis en place toutes les aubes dans l'étage rotorique correspondant.Another method of fixing vanes mobile or rotating on said rotor is done using rivets that guarantee both the retention upstream than the downstream retention. The housing of the rivet is in this case machined for two-thirds of its circumference on dawn, the last remaining third on the disk. Riveting is then done by expansion of the tubular part of the rivet after setting up all the blades in the corresponding rotor stage.
La présente invention vise à fournir une solution qui permette de solidariser les aubes tournantes ou mobiles à un disque servant de rotor.The present invention aims to provide a solution that allows to secure the rotating blades or mobile to a disk serving as a rotor.
En outre, la présente invention vise à permettre une rétention tant amont qu'aval tout en n'utilisant qu'une seule pièce pour toutes les aubes.In addition, the present invention aims to allow retention both upstream and downstream while using only one piece for all blades.
La présente invention vise également à réduire de façon significative le temps de pose ou de montage et à faciliter la maintenance de l'étage rotorique.The present invention also aims to significantly reduce the exposure time or mounting and to facilitate maintenance of the rotor stage.
La présente invention se rapporte à un moyen de rétention ou solidarisation pour aube mobile sur un corps rotorique dans un étage rotorique d'un compresseur ou d'une turbine axial, caractérisé en ce qu'il se présente sous la forme d'un anneau ouvert par une fente sur une certaine section, cette section présentant sur un flanc radial un surcroít de matière sous la forme d'un bossage.The present invention relates to a means for of retention or joining for a moving blade on a rotor body in a rotor stage of a compressor or of an axial turbine, characterized in that it presents itself in the form of a ring opened by a slot on a certain section, this section presenting on a side radial excess material in the form of a boss.
De préférence, la section sur laquelle le surcroít de matière sous la forme d'un bossage est présent correspond essentiellement à la distance prévue entre deux aubes mobiles successives.Preferably, the section on which the extra material in the form of a boss is present basically corresponds to the expected distance between two successive moving blades.
De manière avantageuse, le surcroít de matière se présentant sous la forme d'un bossage est dessiné et calculé de manière à compenser mécaniquement le manque de matière dû à la présence de la fente.Advantageously, the additional amount of material in the form of a boss is drawn and calculated so as to mechanically compensate the lack of material due to the presence of the slit.
Selon une forme de réalisation avantageuse de l'invention, l'anneau présente en coupe une forme conique, à l'exception de la section présentant un surcroít de matière sous forme d'un bossage.According to an advantageous embodiment of the invention, the ring has in section a conical shape, with the exception of the section with a surplus of material in the form of a boss.
La présente invention se rapporte en outre à un étage rotorique d'un compresseur ou d'une turbine axial comprenant une série d'aubes tournantes montées sur un corps rotorique, lesdites aubes présentant un plat et un bulbe d'aube, chaque bulbe d'aube présentant sur une première face une excroissance sous forme de dent de castor qui servira de butée franche en se positionnant directement en contact avec ledit corps rotorique et d'autre part sur la face opposée une excroissance sous forme de crochet qui va permettre le placement du moyen de rétention selon la présente invention.The present invention furthermore relates to a rotor stage of a compressor or an axial turbine comprising a series of rotating vanes mounted on a rotor body, said blades having a flat and a dawn bulb, each dawn bulb presenting on a first face an excrescence in the form of a beaver tooth which will serve as a frank stop by positioning itself directly in contact with said rotor body and secondly on the opposite side an excrescence in the form of a hook which will allow the placement of the retention means according to the present invention.
La figure 1 représente une vue générale d'une turbine basse pression d'un turbofan dans lequel sont présents une succession d'étages distributeurs et d'étages rotoriques.Figure 1 represents a general view of a low-pressure turbine of a turbofan in which are present a succession of distributor floors and floors rotor.
La figure 2 représente une vue en coupe d'une aube munie des moyens de solidarisation au rotor.FIG. 2 represents a sectional view of a blade provided with means for securing to the rotor.
La figure 3 représente une vue en perspective du bulbe d'une aube destinée à être utilisée selon le procédé de montage de la présente invention.Figure 3 shows a perspective view of the bulb of a blade intended to be used according to mounting method of the present invention.
La figure 4 représente une vue en perspective des moyens de solidarisation mis en oeuvre selon la présente invention des aubes tournantes au rotor.Figure 4 shows a perspective view fastening means implemented according to the present invention of rotating vanes to the rotor.
La figure 5 représente une vue en perspective de l'anneau de solidarisation selon la présente invention.Figure 5 shows a perspective view of the fastening ring according to the present invention.
Les figures 6a à 6c représentent le principe de montage de l'anneau selon la présente invention. Figures 6a to 6c show the principle mounting the ring according to the present invention.
La figure 1 représente la turbine basse pression d'un turbofan. Cette turbine est constituée de plusieurs étages successifs, chacun 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 30,30',30",... correspondant à plusieurs étages rotoriques successifs, et - d'autre part des pièces fixes constituant les étages statoriques distributeurs 2,2',2",... séparant les étages rotoriques 3,3',3",...
- on the one hand, moving parts which are essentially constituted by the
rotor 1 provided with several series ofblades - on the other hand, fixed parts constituting the
stator distributor stages rotor stages
Chaque étage distributeur 2,2',2",... est
essentiellement constitué d'aubes 2,2',2'',... contenues
entre deux plateformes intérieure 4,4',4",... et extérieure
5,5',5",...Each
Chaque étage rotorique est constitué par les
aubes tournantes 3,3',3",... toutes reliées au rotor 1 par
des moyens de rétention.Each rotor stage consists of the
rotating blades 3.3 ', 3 ", ... all connected to
Le gaz frappe d'abord le premier rotor de la
turbine basse pression puis son vecteur vitesse est
repositionné par le distributeur du premier étage
statorique basse pression 3 avant de frapper le deuxième
étage rotorique 2' pour être à nouveau repositionné en 3',
etc. Le gaz subit ainsi un cycle de poussée -
redistribution des vitesses à l'issue duquel son énergie
cinétique diminue progressivement ainsi que sa pression,
tandis que le travail rotorique croít en s'additionnant
d'étage en étage.The gas first strikes the first rotor of the
low pressure turbine then its velocity vector is
repositioned by the first floor distributor
stator
Aux figures 2 et 3, une aube tournante 3 se
présente classiquement sous la forme d'un plat 30 lié à un
bulbe d'aube 31. Les différents bulbes 31,31',31" seront
usinés de telle sorte qu'ils puissent être disposés
successivement autour d'un disque 10 qui sert de rotor,
ainsi que représenté à la figure 4.In Figures 2 and 3, a rotating
Le placement des aubes tournantes 3 sur le
rotor 10 se fait par glissement entre les dents du disque.
En effet, les bulbes d'aube 31,31',31" présentent une forme
mâle constituée d'une succession d'excroissances et de
creux à laquelle correspond essentiellement une cavité
femelle complémentaire réalisée dans le disque 10 servant
de rotor, ces cavités créant des « dents » sur le disque.The placement of the rotating
Afin de garantir tant une rétention amont
qu'une rétention aval, il est prévu que les bulbes
d'aube 31,31',31" présentent chacun, d'une part, sur une
première face, une excroissance sous forme de dent de
castor 32 qui servira de butée franche en se positionnant
directement en contact avec le disque rotorique 10, et
d'autre part, sur la face opposée, une excroissance sous
forme de crochet 33 qui va permettre le placement d'un
anneau 40.In order to guarantee both upstream retention
that downstream retention, it is expected that the bulbs
31.31 ', 31 "each have, on the one hand, on a
first face, an excrescence in the form of a tooth of
La présence de cet anneau 40 va
avantageusement permettre la solidarisation de tous les
bulbes d'aube 31,31',31" sur le même disque rotorique 10.
Un tel anneau est représenté en détail à la figure 5.The presence of this
Selon une caractéristique importante de la
présente invention, cet anneau 40 présente une fente 41, de
préférence découpée en biais, de manière à ce que l'on
puisse effectuer la mise en place de l'anneau en
précontraignant celui-ci et en le relâchant ensuite.According to an important characteristic of the
the present invention, this
En outre, cet anneau 40 présente sur au moins
un flanc radial 42 un surcroít de matière sous la forme
d'un bossage 45. Avantageusement, ce bossage 45 est présent
sur une portion qui correspond essentiellement à la
distance prévue entre deux aubes successives ainsi que
représenté à la figure 4. Sur cette distance se trouve
également ladite fente 41. In addition, this
Le bossage présente en outre l'avantage
d'empêcher la rotation de l'anneau 40 par rapport au
disque 10.The boss also has the advantage
to prevent rotation of the
De plus, ledit bossage 45 est dessiné et
calculé pour correspondre exactement au manque de matière
dû à la présence de la fente 41. Le bossage 45 a donc pour
but de proposer un balourd qui doit compenser exactement le
manque de matière dû à la fente 41.In addition, said
En outre, l'anneau 40, ainsi que représenté à
la figure 2, présente une section conique qui permet, lors
du fonctionnement de l'étage rotorique, de diminuer ou même
supprimer le jeu axial de l'aube sur le disque et donc de
diminuer les vibrations qui pourraient être générées par la
force centrifuge.In addition, the
Les figures 6a-6c représentent la mise en
place de l'anneau 40 sur le disque rotorique 10. En
particulier, l'anneau 40 est configuré de telle manière
qu'à l'état libre (Fig. 6a), il présente une certaine
ouverture A. Pour permettre sa mise en place, on aura
tendance à effectuer un pincement lors du montage de
manière à précontraindre l'anneau (Fig. 6b). Après sa mise
en place (Fig. 6c), l'anneau se relâchera de sorte qu'il se
positionnera parfaitement entre deux aubes tournantes ainsi
que représenté à la figure 5.Figures 6a-6c show the implementation
place of the
Cet anneau est de préférence réalisé en un matériau métallique qui permet son utilisation à des températures élevées.This ring is preferably made in one metal material that allows its use to high temperatures.
De manière particulièrement avantageuse, ceci permet de réaliser la rétention à l'aide d'une seule pièce qui est l'anneau et ceci pour toutes les aubes, ce qui permet de réduire de manière significative le temps de pose et de montage et d'en faciliter la maintenance.In a particularly advantageous way, this allows retention with one piece which is the ring and this for all the blades, which significantly reduces the exposure time and mounting and to facilitate maintenance.
Claims (5)
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP20000870311 EP1217168B1 (en) | 2000-12-21 | 2000-12-21 | Axial fixation of gas turbine rotor blades |
| DE60029114T DE60029114D1 (en) | 2000-12-21 | 2000-12-21 | Axial fixation of rotor blades of a gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP20000870311 EP1217168B1 (en) | 2000-12-21 | 2000-12-21 | Axial fixation of gas turbine rotor blades |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1217168A1 true EP1217168A1 (en) | 2002-06-26 |
| EP1217168B1 EP1217168B1 (en) | 2006-06-28 |
Family
ID=8175882
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP20000870311 Expired - Lifetime EP1217168B1 (en) | 2000-12-21 | 2000-12-21 | Axial fixation of gas turbine rotor blades |
Country Status (2)
| Country | Link |
|---|---|
| EP (1) | EP1217168B1 (en) |
| DE (1) | DE60029114D1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2918785A1 (en) * | 2014-03-12 | 2015-09-16 | Rolls-Royce plc | A bladed rotor |
| EP3647545A1 (en) * | 2018-10-31 | 2020-05-06 | United Technologies Corporation | Turbine blade assembly, corresponding gas turbine engine and corresponding methode of securing a turbine blade |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4349318A (en) * | 1980-01-04 | 1982-09-14 | Avco Corporation | Boltless blade retainer for a turbine wheel |
| US5256035A (en) * | 1992-06-01 | 1993-10-26 | United Technologies Corporation | Rotor blade retention and sealing construction |
| US5320492A (en) * | 1992-07-22 | 1994-06-14 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Sealing and retaining device for a rotor notched with pin settings receiving blade roots |
| FR2729709A1 (en) * | 1995-01-25 | 1996-07-26 | Snecma | Turbine rotor seal and retainer |
-
2000
- 2000-12-21 DE DE60029114T patent/DE60029114D1/en not_active Expired - Lifetime
- 2000-12-21 EP EP20000870311 patent/EP1217168B1/en not_active Expired - Lifetime
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4349318A (en) * | 1980-01-04 | 1982-09-14 | Avco Corporation | Boltless blade retainer for a turbine wheel |
| US5256035A (en) * | 1992-06-01 | 1993-10-26 | United Technologies Corporation | Rotor blade retention and sealing construction |
| US5320492A (en) * | 1992-07-22 | 1994-06-14 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Sealing and retaining device for a rotor notched with pin settings receiving blade roots |
| FR2729709A1 (en) * | 1995-01-25 | 1996-07-26 | Snecma | Turbine rotor seal and retainer |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2918785A1 (en) * | 2014-03-12 | 2015-09-16 | Rolls-Royce plc | A bladed rotor |
| US10138741B2 (en) | 2014-03-12 | 2018-11-27 | Rolls-Royce Plc | Bladed rotor |
| EP3647545A1 (en) * | 2018-10-31 | 2020-05-06 | United Technologies Corporation | Turbine blade assembly, corresponding gas turbine engine and corresponding methode of securing a turbine blade |
Also Published As
| Publication number | Publication date |
|---|---|
| DE60029114D1 (en) | 2006-08-10 |
| EP1217168B1 (en) | 2006-06-28 |
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