EP0821134B1 - Arrangement and method for controlling the stator ring diameter - Google Patents
Arrangement and method for controlling the stator ring diameter Download PDFInfo
- Publication number
- EP0821134B1 EP0821134B1 EP97401775A EP97401775A EP0821134B1 EP 0821134 B1 EP0821134 B1 EP 0821134B1 EP 97401775 A EP97401775 A EP 97401775A EP 97401775 A EP97401775 A EP 97401775A EP 0821134 B1 EP0821134 B1 EP 0821134B1
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- EP
- European Patent Office
- Prior art keywords
- stator ring
- diameter
- arrangement
- setting
- ducts
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
- F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
Definitions
- the invention relates to an arrangement and a stator ring diameter adjustment process so reduce the play with the rotor blade ends that this ring surrounds; it therefore applies to turbomachinery and was first designed for a turbine at high pressure of a two-stage turbine, without this application is exclusive.
- US-A-4,337,016 describes arrangements for cooling a turbine stator ring associated with an external blowing device on the turbine casing.
- the adjustment arrangement in accordance with the invention is characterized in that it comprises a housing element hollowed out and occupied by a cavity communicating through conduits to rooms located in upstream and downstream of the ring and which surround a vein gas circulation delimited by the ring.
- This housing element is linked to the ring and located between the ring facing the rotor and the device surrounding gas blowing.
- the corresponding method of adjusting diameter of a stator ring linked to a periphery housing element internal consists, while blowing gas on an outer periphery of this element like previously to produce a gas flow essentially convective through the element of casing, away from the stator ring and between the outer and inner edges.
- FIG. 1 shows part of high-pressure turbine at one stage upstream 1 and one stage downstream 2.
- stages 1 and 2 comprises, from of a rotor 3 and towards the outside, a group of blades mobile 4 linked to the rotor 3, a hoop 5 surrounding the movable blades 4, from which it is separated by a small play 6, a casing element 7 to which the hoop 5 is fixed by 8 and 9 circular adjustments on its sides upstream and downstream, and the blowing distributor 10, called shower collar as already mentioned, and which consists of a circular tube with holes 11 opening towards the casing element 7 a little distance from him.
- the blowing distributor 10 is supplied with air by a duct not shown leading to the compressor.
- the essential element of the invention is located on a part outer 15 of the casing element 7, which is hollowed out a cavity 16 divided into two halves, a groove upstream 17 and a downstream groove 18, by a partition 19 transverse, flat and circular.
- Upstream conduits 20 leading to an upstream chamber 21 open into the upstream groove 17, and likewise downstream conduits 22 leading downstream chamber 23 open into the downstream groove 18.
- the upstream 21 and downstream 23 chambers are located around bladed distributors 33 and 34 preceding each of the movable blade stages 4.
- Blade rings 35 and 36 intended to support the vanes of the distributors 33 and 34 isolate the chambers 21 and 23 from the vein 31 of gas flow in which the vanes and movable extend, so that the air which occupies them rooms 21 and 23 is little agitated and remains even little near stagnating in their bottoms, where conduits 20 and 22 open.
- a rollover 40 which isolates a chamber background 41 from the rest of the chamber 21 and into which the upstream conduits 20 open.
- the draft that can pass through chamber 21 runs along the cowling 40 and can only cross it by holes 42 perpendicular to its flow for enter the chamber bottom 41
- the flow towards downstream through cavity 16 and conduits 20 and 22 is therefore of low flow, which favors convection movements and heat exchanges obtained by this means, in particular in the cavity 16.
- the temperature of the casing element 7 thus tends to equalize without significant air sampling product.
- the flow is further slowed by the eccentric position of 24 days piercing the partition 19 to communicate the gorges 17 and 18.
- These days 24 are in the form of axially offset lunules and radially of conduits 20 and 22: while these emerge at the bottom of gorges 17 and 18, days 24 are operated against their edge, near the distributor 10, from which they are only separated by a hoop 25 integrated into the casing element 7 and used to close the cavity 16 once it has been dug.
- the air travels the upstream gorge 17 outwards and turn back in the downstream groove 18 by crossing the cavity 16.
- the Figure 3 also shows that the days 24 extend, in angular direction in the cavity 16, halfway pairs of upstream 20 or downstream 22 conduits, which produces air circulation in the cavity 16. All of these provisions further increase convection.
- Air from upstream chamber 21 can also be taken and directed directly to the turbine ring hoop 5 to adjust the diameter of this one directly.
- a distributor 30 in the form of an openwork plate divides and equalizes the air flow in front of the surface internal hoop 5. It is actually a known system used concurrently with the invention and which is only recalled here to better distinguish this last. In particular, a relatively important gas is directly blown on the hoop 5.
- the convection circuit is here placed closer to the stator ring 5 and is split into two elements each of which is located in an annular rib 43 or 44 for connecting a casing outside 45 to a spacer 46 carrying the ring stator 5.
- the ribs 43 and 44 are provided with spoilers 47 engaged under retaining edges 48 of the spacer 46 to constitute this connection, and we finds a spoiler 49 on the spacer 46, which is engaged under an edge 50 of the stator ring 5; all these borders 48 and 50 are retained in circular grooves drawn by the spoilers 47 and 49.
- a jumper 51 connects two flanges circulars 52 and 53 of the spacer 30 and the ring stator 5 to prevent it from moving axial.
- the two elements of the convection circuit here also include a cavity 16 divided in two parallel circular grooves 17 and 18 by a partition 19.
- the communication channels of the grooves outside extend around the cavities 16, and the days (54 here) drilled through the partitions 19 are located at their inner circumferences to be offset radially of the conduits, as in the embodiment previous. They can also be offset angularly from these conduits.
- the upstream conduits 55 of the cavity 16 in the rib 43 open into a circular collecting chamber 56 substantially closed by a cover 57 and which communicates with conduits gas supply 65 by as many holes 58.
- the downstream conduits 59 of this same cavity 16 open out in an intermediate chamber 60 in which still open the upstream conduits 61 on the other cavity 16, located in the rib 14; the conduits downstream 62 from this other cavity 16 open into a other chamber 66.
- a deflector cover 67 is arranged in room 56, in front of the outlet of the conduits gas supply 65, to reverse the flow of it and make it gradually take a angular direction.
- An upstream conduit 55 is sheltered from the gas inlet through the deflector cowling 67 and is So found in the bottom of room 56 where the gas is pretty much stagnant.
- FIG. 5 finally shows the application of this system to a realization without the spacer 30: the fastening elements 49 to 53 defined above then directly join the stator ring 5 to the ribs 13 and 14. All other provisions of the Figure 4 are unchanged.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Description
L'invention concerne un agencement et un procédé de réglage de diamètre d'anneau de stator afin de réduire le jeu avec les extrémités d'aubes de rotor que cet anneau entoure ; elle s'applique donc aux turbomachines et a d'abord été conçue pour une turbine à haute pression d'une turbine en deux étages, sans que cette application soit exclusive.The invention relates to an arrangement and a stator ring diameter adjustment process so reduce the play with the rotor blade ends that this ring surrounds; it therefore applies to turbomachinery and was first designed for a turbine at high pressure of a two-stage turbine, without this application is exclusive.
La difficulté d'obtenir un jeu constant entre les rotors et les anneaux de stator qui les entourent pendant le fonctionnement du moteur est due aux dilatations et contractions mécaniques variables sous l'effet des variations de vitesse et de l'échauffement différentiel entre les éléments, à cause notamment de la différence des inerties thermiques. On est donc contraint d'accepter des jeux plus importants à certains régimes de fonctionnement, ce qui implique une perte de rendement.The difficulty of getting consistent play between the rotors and the stator rings which surround during engine operation is due with variable mechanical expansions and contractions due to variations in speed and differential heating between the elements, because including the difference in thermal inertia. We is therefore forced to accept larger games to certain operating regimes, which involves loss of yield.
Pour réduire ces jeux, il a déjà été proposé d'envoyer de l'air à une température variable sur le carter de turbine afin de favoriser la dilatation ou la contraction du carter soutenant l'anneau de stator. L'air est prélevé au compresseur et son débit est réglé en réponse à un paramètre du moteur indiquant par exemple la température ou la vitesse. Cet air pénètre ensuite dans ces conduits communément appelés « colliers à douche » disposés coaxialement autour du carter de turbine, puis s'en échappe par de multiples orifices et vient toucher le carter par des points d'impact. Mais on observe un défaut d'homogénéité du réglage à cause de ce caractère discontinu, concentré en quelques points, de la projection d'air, et des défauts sont aussi constatés dans certaines phases du vol, où il n'y a pas d'impact. C'est donc l'objet essentiel de l'invention que de proposer un agencement de réglage de jeu entre stator et rotor de ce genre tout en atténuant ou évitant cette ovalisation du carter de stator, en favorisant l'homogénéisation thermique de celui-ci.To reduce these games, it has already been offered to send air at a variable temperature on the turbine housing to promote expansion or contraction of the supporting housing the stator ring. The air is taken from the compressor and its flow is adjusted in response to a motor parameter indicating for example temperature or speed. This air then enters these conduits commonly called "shower collars" arranged coaxially around the turbine housing, then escapes with multiple orifices and comes to touch the casing with impact points. But we observe a defect consistency of the setting because of this character discontinuous, concentrated in a few points, from the air projection, and faults are also noted in certain phases of the flight, where there is no impact. It is therefore the essential object of the invention to propose a clearance adjustment arrangement between the stator and rotor like this while attenuating or avoiding this ovalization of the stator housing, favoring thermal homogenization thereof.
On connaít par GB-A-2 062 117 le contrôle du jeu à l'extrémité d'aubes de turbine par une variation de pression et de la température d'un gaz circulant activement dans une cavité ménagée à l'intérieur d'anneaux massifs du carter de turbine.We know from GB-A-2 062 117 the control of the play at the end of turbine blades by a pressure and temperature variation of a gas actively circulating in a cavity inside massive rings of the turbine housing.
US-A-4 337 016 décrit des dispositions de refroidissement d'un anneau de stator de turbine associées à un dispositif de soufflage externe sur le carter de turbine.US-A-4,337,016 describes arrangements for cooling a turbine stator ring associated with an external blowing device on the turbine casing.
L'agencement de réglage conforme à l'invention est caractérisé en ce qu'il comprend un élément de carter évidé et occupé par une cavité communiquant par des conduits à des chambres situées en amont et en aval de l'anneau et qui entourent une veine de circulation de gaz délimitée par l'anneau. Cet élément de carter est lié à l'anneau et situé entre l'anneau qui fait face au rotor et le dispositif environnant de soufflage de gaz.The adjustment arrangement in accordance with the invention is characterized in that it comprises a housing element hollowed out and occupied by a cavity communicating through conduits to rooms located in upstream and downstream of the ring and which surround a vein gas circulation delimited by the ring. This housing element is linked to the ring and located between the ring facing the rotor and the device surrounding gas blowing.
Comme les chambres sont relativement isolées de la veine, elles ne sont parcourues que par de faibles courants et le gaz qui les emplit est à peu près stagnant devant les endroits où débouchent les conduits menant aux chambres , si bien que les écoulements à l'intérieur de la cavité sont essentiellement convectifs et favorisent ainsi l'homogénéisation de la température de l'élément de carter dans les meilleures conditions.As the rooms are relatively isolated from the vein, they are crossed only by weak currents and the gas which fills them is little near stagnant in front of the places where the conduits leading to the bedrooms, so that the flows inside the cavity are essentially convective and thus favor homogenization of the element temperature crankcase in the best conditions.
Le procédé correspondant de réglage de diamètre d'un anneau de stator lié à un pourtour interne d'élément de carter consiste, tout en soufflant du gaz sur un pourtour externe de cet élément comme auparavant, à produire un écoulement de gaz essentiellement convectif à travers l'élément de carter, à l'écart de l'anneau de stator et entre les pourtours externe et interne.The corresponding method of adjusting diameter of a stator ring linked to a periphery housing element internal consists, while blowing gas on an outer periphery of this element like previously to produce a gas flow essentially convective through the element of casing, away from the stator ring and between the outer and inner edges.
L'invention va maintenant être décrite à l'aide des figures suivantes, annexées à titre illustratif et non limitatif :
- la figure 1 est une vue générale de l'agencement et des pièces environnantes de la turbomachine,
- la figure 2 représente plus précisément les parties caractéristiques de l'invention,
- la figure 3 est une coupe de l'anneau de carter à travers la cavité,
- la figure 4 illustre un autre mode de réalisation de l'invention,
- et la figure 5 est une variante de cet autre mode de réalisation.
- FIG. 1 is a general view of the arrangement and of the surrounding parts of the turbomachine,
- FIG. 2 represents more precisely the characteristic parts of the invention,
- FIG. 3 is a section through the casing ring through the cavity,
- FIG. 4 illustrates another embodiment of the invention,
- and FIG. 5 is a variant of this other embodiment.
La figure 1 représente une partie de
turbine à haute pression à un étage-amont 1 et un étage
aval 2. Chacun des étages 1 et 2 comprend, à partir
d'un rotor 3 et vers l'extérieur, un groupe d'aubes
mobiles 4 liées au rotor 3, une frette 5 entourant les
aubes mobiles 4, dont elle est séparée par un petit jeu
6, un élément de carter 7 auquel la frette 5 est fixée
par des ajustements 8 et 9 circulaires sur ses flancs
amont et aval, et le distributeur de soufflage 10,
appelé collier à douche comme on l'a déjà mentionné, et
qui consiste en un tube circulaire traversé d'orifices
11 s'ouvrant vers l'élément de carter 7 à peu de
distance de lui. Le distributeur de soufflage 10 est
alimenté en air par un conduit non représenté menant au
compresseur. Quant aux ajustements 8 et 9, ils
consistent en des emboítement de béquets circulaires 12
et 13 de la frette 5 de l'élément de carter 7 entre eux
ou entre les lèvres d'un joint circulaire à section en
U 14. Toutes ces dispositions déjà connues ne sont
rappelées que pour mémoire et ne font donc pas l'objet
d'une description détaillée. La frette 5 constitue donc
l'anneau de stator dont il faut régler le diamètre pour
optimiser la largeur du jeu 6.Figure 1 shows part of
high-pressure turbine at one stage upstream 1 and one stage
downstream 2. Each of stages 1 and 2 comprises, from
of a
L'élément essentiel de l'invention, mieux
visible sur la figure 2, est situé sur une partie
externe 15 de l'élément de carter 7, qui est creusé
d'une cavité 16 divisée en deux moitiés, une gorge
amont 17 et une gorge aval 18, par une cloison 19
transversale, plane et circulaire. Des conduits amont
20 menant à une chambre amont 21 débouchent dans la
gorge amont 17, et de même des conduits aval 22 menant
à une chambre aval 23 débouchent dans la gorge aval 18.
Les chambres amont 21 et aval 23 sont situées autour
des distributeurs aubagés 33 et 34 précédant chacun des
étages d'aubes mobiles 4. Des anneaux d'aubes 35 et 36
destinés à soutenir les aubes des distributeurs 33 et
34 isolent les chambres 21 et 23 de la veine 31 de
circulation des gaz dans laquelle les aubes fixes et
mobiles s'étendent, de sorte que l'air qui occupe les
chambres 21 et 23 est peu agité et reste même à peu
près stagnant dans leurs fonds, où les conduits 20 et
22 débouchent. On remarque à ce sujet un capotage 40
qui isole un fond de chambre 41 du reste de la chambre
21 et dans lequel les conduits amont 20 débouchent. Le
courant d'air pouvant parcourir la chambre 21 longe le
capotage 40 et ne peut le traverser que par des
perçages 42 perpendiculaires à son écoulement pour
pénétrer dans le fond de chambre 41 L'écoulement vers
l'aval à travers la cavité 16 et les conduits 20 et 22
est donc de faible débit, ce qui favorise les
mouvements de convection et les échanges thermiques
obtenus par ce moyen, notamment dans la cavité 16. La
température de l'élément de carter 7 tend ainsi à
s'égaliser sans qu'un prélèvement important d'air soit
produit. The essential element of the invention, better
visible in Figure 2, is located on a part
outer 15 of the casing element 7, which is hollowed out
a
L'écoulement est encore ralenti par la
position excentrée de jours 24 perçant la cloison 19
pour faire communiquer les gorges 17 et 18. Ces jours
24 sont en forme de lunules décalées axialement et
radialement des conduits 20 et 22 : alors que ceux-ci
débouchent au fond des gorges 17 et 18, les jours 24
sont opérés contre leur bord, près du distributeur 10,
dont elles ne sont séparées que par une frette 25
intégrée à l'élément de carter 7 et servant à fermer la
cavité 16 une fois celle-ci creusée. L'air parcourt la
gorge amont 17 vers l'extérieur et rebrousse chemin
dans la gorge aval 18 en traversant la cavité 16. La
figure 3 montre aussi que les jours 24 s'étendent, en
direction angulaire dans la cavité 16, à mi-chemin de
paires des conduits amont 20 ou aval 22, ce qui produit
un brassage de l'air dans la cavité 16. Toutes ces
dispositions accroissent encore la convection.The flow is further slowed by the
eccentric position of 24 days piercing the
De l'air provenant de la chambre amont 21
peut aussi être prélevé et dirigé directement vers la
frette 5 d'anneau de turbine pour régler le diamètre de
celle-ci directement.Air from
On remarque aussi qu'un autre écoulement de
la chambre amont 21 existe à travers l'élément de
carter 7 de l'étage amont 1 de turbine, le long d'un
canal 28 s'ouvrant sur une chambre 29 fermée par la
frette 5. Un distributeur 30 en forme de plaque ajourée
divise et égalise le flux d'air devant la surface
interne de la frette 5. Il s'agit en vérité d'un
système connu utilisé concurremment à l'invention et
qui n'est rappelé ici que pour mieux distinguer cette
dernière. En particulier, un débit relativement
important de gaz est directement soufflé sur la frette
5.We also notice that another flow of
the
Une autre réalisation importante est
illustrée à la figure 4. Le circuit à convection est
ici placé plus près de l'anneau de stator 5 et est
dédoublé en deux éléments dont chacun est situé dans
une nervure annulaire 43 ou 44 de liaison d'un carter
extérieur 45 à une entretoise 46 porteuse de l'anneau
de stator 5. Les nervures 43 et 44 sont munies de
béquets 47 engagés sous des bordures de retenue 48 de
l'entretoise 46 pour constituer cette liaison, et on
retrouve un béquet 49 sur l'entretoise 46, qui est
engagé sous une bordure 50 de l'anneau de stator 5 ;
toutes ces bordures 48 et 50 sont retenues dans des
gorges circulaires dessinées par les béquets 47 et 49.
Enfin, un cavalier 51 relie entre elles deux brides
circulaires 52 et 53 de l'entretoise 30 et de l'anneau
de stator 5 pour interdire à celui-ci un déplacement
axial.Another important achievement is
illustrated in figure 4. The convection circuit is
here placed closer to the
Les deux éléments du circuit à convection
comprennent ici aussi une cavité 16 divisée en deux
gorges circulaires parallèles 17 et 18 par une cloison
19. Mais, contrairement à la réalisation précédente,
les conduits de communication de gorges à l'extérieur
s'étendent autour des cavités 16, et les jours (54 ici)
percés à travers les cloisons 19 sont situés à leurs
circonférences intérieures pour être décalés
radialement des conduits, comme dans la réalisation
précédente. Ils peuvent aussi être décalés
angulairement de ces conduits. Les conduits amont 55 de
la cavité 16 dans la nervure 43 débouchent dans une
chambre collectrice circulaire 56 sensiblement fermée
par un capotage 57 et qui communique à des conduits
d'alimentation en gaz 65 par autant de perçages 58. Les
conduits aval 59 de cette même cavité 16 débouchent
dans une chambre intermédiaire 60 dans laquelle
débouchent encore les conduits amont 61 de l'autre
cavité 16, située dans la nervure 14 ; les conduits
aval 62 de cette autre cavité 16 débouchent dans une
autre chambre 66. Un capotage déflecteur 67 est disposé
dans la chambre 56, devant le débouché des conduits
d'alimentation en gaz 65, pour infléchir l'écoulement
de celui-ci et lui faire prendre progressivement une
direction angulaire. Un conduit amont 55 est abrité de
l'entrée des gaz par le capotage déflecteur 67 et se
retrouve donc dans un fond de la chambre 56 où le gaz
est à peu près stagnant. Un avantage de cette
réalisation est lié à la présence des cavités 16 dans
des nervures 13 et 14 épaisses et rigides par rapport
aux éléments environnants et proches de l'anneau de
stator 5. Cette circonstance permet de régler avec
précision et rapidité le jeu 6 entre les aubes 4 et
l'anneau de stator 5. Le gaz soufflé par les orifices
58 et circulant le long de la chambre collectrice
circulaire 56 assure par cela même la mise de l'anneau
de stator 5 au diamètre moyen souhaité,et la
circulation par convection du gaz à travers les cavités
16 assure l'uniformisation du diamètre sur la
circonférence. De plus, les cavités 16, creusées dans
des nervures 13 et 14 nécessaires par ailleurs pour
soutenir l'anneau de stator 5, ne nécesessitent pas
d'ajouter un élément particulier dans la machine. Une
autre économie provient de l'unité du circuit de
convection pour les deux cavités 16.The two elements of the convection circuit
here also include a
La figure 5 montre enfin l'application de
ce système à une réalisation dépourvue de l'entretoise
30 : les éléments de fixation 49 à 53 définis plus haut
unissent alors directement l'anneau de stator 5 aux
nervures 13 et 14. Toutes les autres dispositions de la
figure 4 sont inchangées.Figure 5 finally shows the application of
this system to a realization without the spacer
30: the
Claims (9)
- Arrangement for setting the diameter of a stator ring (5) by means of a surrounding gas-blowing device (10, 56, 65), characterized in that it comprises, connected to the ring (5) and situated between the ring and the gas-blowing device (10, 56, 65), a hollowed out casing element (7, 43, 44, 45) occupied by a cavity (16) communicating via ducts (20, 22, 55, 59, 61, 62) with chambers (21, 23, 56, 60, 663) upstream and downstream of the ring which surround a gas circulation passage delimited by the ring and which are occupied by gas that is more or less stagnant in front of the ducts (20, 22, 55, 61, 62), the cavity (16) and the ducts (20, 22, 55, 59, 61, 62) extending away from the stator ring, and in that the cavity is divided by a perforated partition (19) into an upstream half (17) into which the ducts (20, 55, 61) communicating with the upstream chamber (21, 56, 60) open and a downstream half (18) into which the ducts (22, 59, 62) communicating with the downstream chamber (23, 60, 66) open.
- Arrangement for setting the diameter of a stator ring according to Claim 1, characterized in that the partition (19) is provided with apertures (24, 54) radially offset from the ducts.
- Arrangement for setting the diameter of a stator ring according to Claim 1, characterized in that the partition is provided with apertures (24, 54) angularly offset from the ducts.
- Arrangement for setting the diameter of a stator ring according to any one of Claims 1 to 3, characterized in that one of the chambers (21) belongs to a circuit for blowing gas over the stator ring (5).
- Arrangement for setting the diameter of a stator ring according to any one of Claims 1 to 3, characterized in that one of the chambers (56) belongs to the surrounding gas-blowing device.
- Arrangement for setting the diameter of a stator ring according to any one of Claims 1 to 5, characterized in that the cavity is arranged on a stator ring support rib (13, 14).
- Arrangement for setting the diameter of a stator ring according to Claim 6, characterized in that it comprises two cavities arranged in two parallel stator ring support ribs (13, 14), the cavities (16) communicating with one another via ducts (59, 61) and an intermediate chamber (60).
- Arrangement for setting the diameter of a stator ring according to any one of Claims 1 to 7, characterized in that one of the chambers (21, 56) is home to a gaseous flow and in that a cowling (40, 67) situated in the said chamber delimits therein a chamber end wall (41) more or less devoid of flow into which the ducts (20, 55) of the cavity communicating with the said chamber open.
- Method for setting the diameter of a stator ring (5) connected to an internal periphery of a casing element (7), consisting in blowing gas onto an external periphery of the casing element, characterized in that it consists in producing an essentially convective gaseous flow through the casing element away from the stator ring and between the internal and external peripheries.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR9609364A FR2751694B1 (en) | 1996-07-25 | 1996-07-25 | ARRANGEMENT AND METHOD FOR ADJUSTING THE STATOR RING DIAMETER |
| FR9609364 | 1996-07-25 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0821134A1 EP0821134A1 (en) | 1998-01-28 |
| EP0821134B1 true EP0821134B1 (en) | 2004-03-24 |
Family
ID=9494470
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP97401775A Expired - Lifetime EP0821134B1 (en) | 1996-07-25 | 1997-07-24 | Arrangement and method for controlling the stator ring diameter |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US5915919A (en) |
| EP (1) | EP0821134B1 (en) |
| CA (1) | CA2211428C (en) |
| DE (1) | DE69728222T2 (en) |
| FR (1) | FR2751694B1 (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2780443B1 (en) * | 1998-06-25 | 2000-08-04 | Snecma | HIGH PRESSURE TURBINE STATOR RING OF A TURBOMACHINE |
| DE10019437A1 (en) * | 2000-04-19 | 2001-12-20 | Rolls Royce Deutschland | Method and device for cooling the housings of turbines of jet engines |
| US8801370B2 (en) * | 2006-10-12 | 2014-08-12 | General Electric Company | Turbine case impingement cooling for heavy duty gas turbines |
| US7740443B2 (en) * | 2006-11-15 | 2010-06-22 | General Electric Company | Transpiration clearance control turbine |
| FR3002972B1 (en) * | 2013-03-06 | 2015-04-17 | Snecma | DEVICE FOR VENTILATION OF A STATOR CASING OF A TURBOMACHINE COMPRISING AN AXIAL ADJUSTMENT |
| FR3002971B1 (en) * | 2013-03-06 | 2015-04-17 | Snecma | DEVICE FOR VENTILATION OF A STATOR CASE OF A TURBOMACHINE, COMPRISING AN ADJUSTMENT ON CIRCUMFERENCES |
| DE102018203442A1 (en) | 2018-03-07 | 2019-09-12 | MTU Aero Engines AG | Inner ring for a turbomachine, vane ring with an inner ring, turbomachinery and method of making an inner ring |
| US11015475B2 (en) * | 2018-12-27 | 2021-05-25 | Rolls-Royce Corporation | Passive blade tip clearance control system for gas turbine engine |
Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2712727A (en) * | 1950-05-17 | 1955-07-12 | Rolls Royce | Gas turbine power plants with means for preventing or removing ice formation |
| US3966354A (en) * | 1974-12-19 | 1976-06-29 | General Electric Company | Thermal actuated valve for clearance control |
| GB2047354B (en) * | 1979-04-26 | 1983-03-30 | Rolls Royce | Gas turbine engines |
| US4337016A (en) * | 1979-12-13 | 1982-06-29 | United Technologies Corporation | Dual wall seal means |
| GB2062117B (en) * | 1980-10-20 | 1983-05-05 | Gen Electric | Clearance control for turbine blades |
| FR2540560B1 (en) * | 1983-02-03 | 1987-06-12 | Snecma | DEVICE FOR SEALING MOBILE BLADES OF A TURBOMACHINE |
| DE3909369A1 (en) * | 1988-03-31 | 1989-10-26 | Gen Electric | GAS TURBINE GAP CONTROL |
| GB2236147B (en) * | 1989-08-24 | 1993-05-12 | Rolls Royce Plc | Gas turbine engine with turbine tip clearance control device and method of operation |
| FR2685936A1 (en) * | 1992-01-08 | 1993-07-09 | Snecma | DEVICE FOR CONTROLLING THE GAMES OF A TURBOMACHINE COMPRESSOR HOUSING. |
| FR2688539A1 (en) * | 1992-03-11 | 1993-09-17 | Snecma | Turbomachine stator including devices for adjusting the clearance between the stator and the blades of the rotor |
| GB9210642D0 (en) * | 1992-05-19 | 1992-07-08 | Rolls Royce Plc | Rotor shroud assembly |
| JPH06173712A (en) * | 1992-12-14 | 1994-06-21 | Toshiba Corp | Cooling device for gas turbine casing |
| US5593277A (en) * | 1995-06-06 | 1997-01-14 | General Electric Company | Smart turbine shroud |
-
1996
- 1996-07-25 FR FR9609364A patent/FR2751694B1/en not_active Expired - Fee Related
-
1997
- 1997-07-11 US US08/893,521 patent/US5915919A/en not_active Expired - Lifetime
- 1997-07-17 CA CA002211428A patent/CA2211428C/en not_active Expired - Fee Related
- 1997-07-24 DE DE69728222T patent/DE69728222T2/en not_active Expired - Lifetime
- 1997-07-24 EP EP97401775A patent/EP0821134B1/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| DE69728222D1 (en) | 2004-04-29 |
| US5915919A (en) | 1999-06-29 |
| FR2751694B1 (en) | 1998-09-04 |
| CA2211428C (en) | 2006-03-14 |
| EP0821134A1 (en) | 1998-01-28 |
| CA2211428A1 (en) | 1998-01-25 |
| DE69728222T2 (en) | 2005-03-10 |
| FR2751694A1 (en) | 1998-01-30 |
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