EP0893577A1 - Cooling device for a turbomachine shroud - Google Patents

Cooling device for a turbomachine shroud Download PDF

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Publication number
EP0893577A1
EP0893577A1 EP98401872A EP98401872A EP0893577A1 EP 0893577 A1 EP0893577 A1 EP 0893577A1 EP 98401872 A EP98401872 A EP 98401872A EP 98401872 A EP98401872 A EP 98401872A EP 0893577 A1 EP0893577 A1 EP 0893577A1
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EP
European Patent Office
Prior art keywords
wall
cover
ring
holes
orifices
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
EP98401872A
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German (de)
French (fr)
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EP0893577B1 (en
Inventor
Daniel Jean Marey
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 Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Publication of EP0893577A1 publication Critical patent/EP0893577A1/en
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Publication of EP0893577B1 publication Critical patent/EP0893577B1/en
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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the subject of the invention is a device for ventilating a turbomachine ring.
  • the problem we are trying to solve here is the machine yield loss that the subtraction of the induced ventilation flow: on seeks to limit this flow to the minimum necessary for a good ventilation.
  • the solution chosen consists of arrange in the room behind the ring, and in which the gas supply duct opens, a annular distributor comprising a pierced wall holes and a cover placed between the wall and the conduit and pierced with other orifices, intended for restrict the flow of gas; these holes of lids are fewer and have a section total smaller than the holes in the wall.
  • a stator 1 of a turbomachine is equipped spacers 2 (only one of which is shown) intended to support as many 3 rings which contribute to delimit the gas flow stream of the machine in front of circular stages of moving rotor blades 4.
  • the subject of the invention is an annular housing 5 composed of a cover 6 and a wall 7.
  • the housing 5 is housed in a room 8 delimited by the spacer 2 and the ring 3, and it cuts it between this and the outlet 9 of a gas supply circuit relatively fresh from the bottom of the combustion; the rest of the power circuit is not shown because it is not original, but we may refer to French patent 2,416,345 cited higher for more detail.
  • the integrity of the case 5 is ensured by providing the cover 6 and the wall 7 lateral edges 10 and 11 circular and likewise diameter which are joined in pairs by welds, rivets or other means; the side edges 11 of the wall 7 are also fixed to the spacer 2.
  • the wall 7 is foraminated, that is to say pierced with numerous orifices 12, here substantially more long as wide thanks to their finesse and fairly large wall thickness 7.
  • the cover 6 is pierced by other holes 13, less numerous than those 12 of wall 7 but whose cross section opening hours is also quite small. They are established at the top of projections 14 obtained by pushing back the material of the cover 6 towards the outside of the case 5 and whose shape is more or less conical so that the orifices 13 communicate with the interior of the housing 5 by pavilions 15 opening towards the wall 7.
  • the gas entering chamber 8 accumulates in front of the housing 5 and passes through the holes 13 then 12 to come and lick the ring 3 before being evacuated in the gas flow stream passing through holes 16 drilled through the ring 3.
  • the constitution of orifices 13 precisely calibrated allows to restrict the gas flow through them without excessively reducing the flow load thanks to the flared shape of the pavilions 15.
  • the projections 14 can however be oriented to favor the mean direction of gas flow in the box 5 to one region or the other of the wall 7.
  • the gas flow is therefore distributed properly in the housing 5 and flows out through the orifices 12, who distribute it by directing it with precision and with the desired spatial distribution towards different portions of the ring 3.
  • the density and direction of the orifices 12 can therefore vary over the wall 7.
  • the conception of the invention is certainly applicable to other parts of the machine than the high pressure turbine rings, and it can also be used with charged gases to warm up the structure on which they are blown.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Motor Or Generator Cooling System (AREA)

Abstract

The ventilation device for the turbo-machine ring (3) comprises a supply circuit (9) for gas originating from the turbo-machine discharging into a chamber (8) behind the ring. The chamber is cut by an annular distributor with its wall (7) drilled with distribution holes (12). The distributor is in the shape of a case (5) with a cover (6), placed between the wall and the circuit, drilled with holes (13) restricting the gas flow.

Description

Le sujet de l'invention est un dispositif de ventilation d'un anneau de turbomachine.The subject of the invention is a device for ventilating a turbomachine ring.

De tels systèmes ont été déjà largement employés pour refroidir certaines parties de turbomachines soumises à des échauffements très importants, et notamment les anneaux statoriques des turbines à haute pression, où la température peut atteindre 1500°C environ. Du gaz de ventilation sous pression est soustrait d'une autre partie, plus fraíche, de la machine, et s'écoule dans un conduit qui aboutit à une chambre située derrière l'anneau à refroidir. Le gaz vient donc lécher l'anneau et évacue sa chaleur avant de quitter la chambre par des orifices de sortie ménagés à travers l'anneau ou des parties avoisinantes de la machine pour rejoindre la veine d'écoulement des gaz ou passer au refroidissement d'un autre anneau.Such systems have already been widely used to cool parts of turbomachines subjected to very high temperatures important, and in particular the stator rings of high pressure turbines, where the temperature can reach approximately 1500 ° C. Ventilation gas under pressure is subtracted from another part plus fresh, from the machine, and flows into a duct which leads to a room behind the ring at cool. The gas therefore comes to lick the ring and evacuates its heat before leaving the room through orifices outlet formed through the ring or parts neighboring the machine to join the vein gas flow or cool to a another ring.

Le problème auquel on s'efforce de remédier ici est la perte de rendement de la machine que la soustraction du débit de ventilation induit : on cherche à limiter ce débit au minimum nécessaire à une bonne ventilation. La solution retenue consiste à disposer dans la chambre derrière l'anneau, et dans laquelle le conduit d'alimentation en gaz débouche, un distributeur annulaire comprenant une paroi percée d'orifices ainsi qu'un couvercle placé entre la paroi et le conduit et percé d'autres orifices, destinés à restreindre l'écoulement du gaz ; ces orifices de couvercles sont moins nombreux et ont une section totale plus petite que les orifices de la paroi.The problem we are trying to solve here is the machine yield loss that the subtraction of the induced ventilation flow: on seeks to limit this flow to the minimum necessary for a good ventilation. The solution chosen consists of arrange in the room behind the ring, and in which the gas supply duct opens, a annular distributor comprising a pierced wall holes and a cover placed between the wall and the conduit and pierced with other orifices, intended for restrict the flow of gas; these holes of lids are fewer and have a section total smaller than the holes in the wall.

Le couvercle et la paroi coupent successivement la chambre, ce qui oblige le gaz de ventilation à les traverser successivement avant d'atteindre l'anneau à refroidir. La paroi foraminée a pour but essentiel de répartir convenablement le gaz de ventilation sur les différentes parties de l'anneau. On en trouve de nombreux exemples dans l'art antérieur, parmi lesquels on peut citer le brevet américain 5 273 396 et le brevet français 2 416 345, qui présentent en plus l'intérêt de comporter un couvercle ressemblant à celui de l'invention. Toutefois, le couvercle du premier brevet cité est simplement destiné à la fixation de la paroi sur la surface de la chambre et consiste en un ensemble de bordures latérales entourant des évidements sous lesquels la paroi foraminée s'étend, et il est évident que ces évidements n'ont aucun effet de restriction du débit de gaz de ventilation. Le couvercle du second brevet antérieur est au contraire continu et a pour seul but de réduire le volume de la chambre d'écoulement du gaz ; l'entrée du gaz est produite par des orifices latéraux percés à travers l'anneau. Il s'agit d'une conception différente où les perçages n'ont pas non plus pour but de restreindre l'écoulement du gaz.Lid and wall cut successively the chamber, which forces the gas to ventilation to cross them successively before reach the ring to cool. The foraminous wall has essential purpose of distributing the gas properly ventilation on the different parts of the ring. We there are many examples in the prior art, among which we can cite the American patent 5,273,396 and French Patent 2,416,345, which also have the advantage of having a cover resembling that of the invention. However, the cover of the first cited patent is simply intended to the fixing of the wall on the surface of the chamber and consists of a set of side borders surrounding recesses under which the wall foramine stretches out, and it's obvious that these recesses have no effect of restricting the gas flow from ventilation. The cover of the second earlier patent is on the contrary continuous and has the sole purpose of reducing the volume of the gas flow chamber; the entrance gas is produced through side holes drilled at across the ring. It is a different design where the holes are also not intended to restrict gas flow.

La nature de l'invention, sa constitution générale et les avantages particuliers à certaines de ses réalisations seront maintenant décrits plus concrètement à l'aide des figures suivantes :

  • la figure 1 est une représentation d'un anneau de turbine équipé de l'invention,
  • et la figure 2 illustre une autre réalisation de l'invention.
The nature of the invention, its general constitution and the advantages particular to certain of its embodiments will now be described more concretely with the aid of the following figures:
  • FIG. 1 is a representation of a turbine ring fitted with the invention,
  • and Figure 2 illustrates another embodiment of the invention.

Un stator 1 de turbomachine est équipé d'entretoises 2 (dont une seule est représentée) destinées à soutenir autant d'anneaux 3 qui contribuent à délimiter la veine d'écoulement des gaz de la machine devant des étages circulaires d'aubes mobiles de rotor 4. Le sujet de l'invention est un boítier 5 annulaire composé d'un couvercle 6 et d'une paroi 7. Le boítier 5 est logé dans une chambre 8 délimitée par l'entretoise 2 et l'anneau 3, et il la coupe entre celui-ci et le débouché 9 d'un circuit d'alimentation en gaz relativement frais originaire du fond de la chambre de combustion ; le reste du circuit d'alimentation n'est pas représenté car il n'est pas original, mais on pourra se reporter au brevet français 2 416 345 cité plus haut pour plus de détail. L'intégrité du boítier 5 est assurée en pourvoyant le couvercle 6 et la paroi 7 de bords latéraux 10 et 11 circulaires et de même diamètre qui sont unis par paires par des soudures, des rivets ou d'autres moyens ; les bords latéraux 11 de la paroi 7 sont par ailleurs fixés à l'entretoise 2.A stator 1 of a turbomachine is equipped spacers 2 (only one of which is shown) intended to support as many 3 rings which contribute to delimit the gas flow stream of the machine in front of circular stages of moving rotor blades 4. The subject of the invention is an annular housing 5 composed of a cover 6 and a wall 7. The housing 5 is housed in a room 8 delimited by the spacer 2 and the ring 3, and it cuts it between this and the outlet 9 of a gas supply circuit relatively fresh from the bottom of the combustion; the rest of the power circuit is not shown because it is not original, but we may refer to French patent 2,416,345 cited higher for more detail. The integrity of the case 5 is ensured by providing the cover 6 and the wall 7 lateral edges 10 and 11 circular and likewise diameter which are joined in pairs by welds, rivets or other means; the side edges 11 of the wall 7 are also fixed to the spacer 2.

La paroi 7 est foraminée, c'est-à-dire percée de nombreux orifices 12, ici sensiblement plus longs que larges grâce à leur finesse et à une épaisseur assez importante de la paroi 7. Le couvercle 6 est percé par d'autres orifices 13, moins nombreux que ceux 12 de la paroi 7 mais dont la section d'ouverture est également assez réduite. Ils sont établis au sommet de saillies 14 obtenues en repoussant la matière du couvercle 6 vers l'extérieur du boítier 5 et dont la forme est plus ou moins conique pour que les orifices 13 communiquent avec l'intérieur du boítier 5 par des pavillons 15 s'ouvrant vers la paroi 7.The wall 7 is foraminated, that is to say pierced with numerous orifices 12, here substantially more long as wide thanks to their finesse and fairly large wall thickness 7. The cover 6 is pierced by other holes 13, less numerous than those 12 of wall 7 but whose cross section opening hours is also quite small. They are established at the top of projections 14 obtained by pushing back the material of the cover 6 towards the outside of the case 5 and whose shape is more or less conical so that the orifices 13 communicate with the interior of the housing 5 by pavilions 15 opening towards the wall 7.

Le gaz entrant dans la chambre 8 s'accumule devant le boítier 5 et traverse les orifices 13 puis 12 pour venir lécher l'anneau 3 avant d'être évacué dans la veine d'écoulement des gaz en traversant des orifices 16 percés à travers l'anneau 3. La constitution des orifices 13 calibrés avec précision permet de restreindre le débit de gaz qui les traverse sans réduire excessivement la charge de l'écoulement grâce à la forme évasée des pavillons 15. Les saillies 14 peuvent cependant être orientées pour favoriser la direction moyenne de l'écoulement des gaz dans le boítier 5 vers une région ou l'autre de la paroi 7. L'écoulement du gaz se répartit donc convenablement dans le boítier 5 et s'en écoule par les orifices 12, qui le distribuent en le dirigeant avec précision et avec la répartition spatiale souhaitée vers les différentes portions de l'anneau 3. La densité et la direction des orifices 12 peuvent donc varier sur la paroi 7. Une telle construction de la paroi n'est cependant pas indispensable, et on peut préférer celle de la figure 2, plus simple et légère, où la paroi 7 épaisse est remplacée par une paroi 7' aussi mince que le couvercle 6. Tout le reste de la description est valable, si ce n'est que les orifices 12', qui peuvent avoir d'ailleurs la même répartition que les orifices 12, sont beaucoup plus courts et n'exercent donc pas d'effet directionnel sensible sur l'écoulement des gaz. La seule possibilité de réglage offerte avec cette construction est donc la répartition du refroidissement au moyen de la densité variable des orifices 12'. The gas entering chamber 8 accumulates in front of the housing 5 and passes through the holes 13 then 12 to come and lick the ring 3 before being evacuated in the gas flow stream passing through holes 16 drilled through the ring 3. The constitution of orifices 13 precisely calibrated allows to restrict the gas flow through them without excessively reducing the flow load thanks to the flared shape of the pavilions 15. The projections 14 can however be oriented to favor the mean direction of gas flow in the box 5 to one region or the other of the wall 7. The gas flow is therefore distributed properly in the housing 5 and flows out through the orifices 12, who distribute it by directing it with precision and with the desired spatial distribution towards different portions of the ring 3. The density and direction of the orifices 12 can therefore vary over the wall 7. Such a construction of the wall is not however not essential, and we can prefer that of Figure 2, simpler and lighter, where the wall 7 thick is replaced by a wall 7 'as thin as cover 6. All the rest of the description is valid, except that the 12 'orifices, which can moreover have the same distribution as the orifices 12, are much shorter and therefore do not exercise significant directional effect on gas flow. The only adjustment option offered with this construction so is the distribution of cooling by means of the variable density of the orifices 12 '.

La restriction du débit de gaz de ventilation est obtenue à condition que la section totale des orifices 13 du couvercle 6 soit plus petite que celle des orifices 12 de la paroi 7, dont on ne peut réduire excessivement le nombre sous peine de produire des irrégularités de refroidissement de l'anneau 3. On voit que le débit de gaz peut être réduit même si les orifices 12 de la paroi 7 sont nombreux.Restriction of gas flow from ventilation is obtained provided that the cross-section total of the holes 13 of the cover 6 is smaller than that of the orifices 12 of the wall 7, of which may reduce the number excessively or else produce cooling irregularities of ring 3. We see that the gas flow can be reduced even if the orifices 12 of the wall 7 are numerous.

Enfin, la conception de l'invention est certainement applicable à d'autres parties de la machine que les anneaux de turbine à haute pression, et elle peut aussi être employée avec des gaz chargés d'échauffer la structure sur laquelle ils sont soufflés.Finally, the conception of the invention is certainly applicable to other parts of the machine than the high pressure turbine rings, and it can also be used with charged gases to warm up the structure on which they are blown.

Claims (3)

Dispositif de ventilation d'un anneau (3) de turbomachine comprenant un circuit d'alimentation (9) en gaz de ventilation originaire d'une autre portion de la turbomachine débouchant dans une chambre (8) derrière l'anneau (3), la chambre (8) étant coupée par un distributeur annulaire comprenant une paroi (7) percée d'orifices (12) entre l'anneau (3) et le circuit (9), caractérisé en ce que le distributeur est en forme de boítier (5) et comprend un couvercle (6) placé entre la paroi (7) et le circuit (9) et percé d'orifices (13) de restriction d'écoulement du gaz, les orifices (13) du couvercle étant moins nombreux, ayant une section totale plus petite que les orifices (12) de la paroi et étant disposés sur des saillies (14) obtenues en repoussant la matière du couvercle (6) vers l'extérieur du boítier (5) et forment des pavillons (15) s'ouvrant vers la paroi.Ring ventilation device (3) of a turbomachine comprising a circuit supply (9) of originating ventilation gas another portion of the turbomachine opening into a chamber (8) behind the ring (3), the chamber (8) being cut by an annular distributor comprising a wall (7) pierced with orifices (12) between the ring (3) and the circuit (9), characterized in that the dispenser is in the form of a housing (5) and includes a cover (6) placed between the wall (7) and the circuit (9) and pierced with holes (13) for restriction gas flow, the holes (13) of the cover being less numerous, having a total cross section more small than the holes (12) in the wall and being arranged on projections (14) obtained by pushing back the material of the cover (6) towards the outside of the case (5) and form pavilions (15) opening towards the wall. Dispositif de ventilation selon la revendication 1, caractérisé en ce que la paroi (7) possède une épaisseur sensiblement plus grande que le couvercle (6) et les orifices (12) de la paroi sont plus longs que larges.Ventilation device according to claim 1, characterized in that the wall (7) has a thickness significantly greater than the cover (6) and the orifices (12) of the wall are longer than wide. Dispositif de ventilation selon l'une quelconque des revendications 1 ou 2, caractérisé en ce que le couvercle et la paroi sont unis par des paires de bords latéraux (10, 11) circulaires de même diamètre.Ventilation device according to one any of claims 1 or 2, characterized in that the cover and the wall are united in pairs of circular lateral edges (10, 11) likewise diameter.
EP98401872A 1997-07-24 1998-07-23 Cooling device for a turbomachine shroud Expired - Lifetime EP0893577B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9709399A FR2766517B1 (en) 1997-07-24 1997-07-24 DEVICE FOR VENTILATION OF A TURBOMACHINE RING
FR9709399 1997-07-24

Publications (2)

Publication Number Publication Date
EP0893577A1 true EP0893577A1 (en) 1999-01-27
EP0893577B1 EP0893577B1 (en) 2003-08-27

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EP98401872A Expired - Lifetime EP0893577B1 (en) 1997-07-24 1998-07-23 Cooling device for a turbomachine shroud

Country Status (6)

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US (1) US5964575A (en)
EP (1) EP0893577B1 (en)
JP (1) JP3808211B2 (en)
CA (1) CA2243333C (en)
DE (1) DE69817477T2 (en)
FR (1) FR2766517B1 (en)

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CN103161520A (en) * 2013-03-01 2013-06-19 哈尔滨汽轮机厂有限责任公司 First class turbine protective ring of middle-low calorific value gas turbine and disassembling method thereof
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US20140271154A1 (en) * 2013-03-14 2014-09-18 General Electric Company Casing for turbine engine having a cooling unit
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US11193386B2 (en) * 2016-05-18 2021-12-07 Raytheon Technologies Corporation Shaped cooling passages for turbine blade outer air seal
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EP2093384A3 (en) * 2008-02-24 2012-05-30 United Technologies Corporation Filter system for blade outer air seal
US8439639B2 (en) 2008-02-24 2013-05-14 United Technologies Corporation Filter system for blade outer air seal
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WO2016028310A1 (en) * 2014-08-22 2016-02-25 Siemens Aktiengesellschaft Shroud cooling system for shrouds adjacent to airfoils within gas turbine engines
US9963996B2 (en) 2014-08-22 2018-05-08 Siemens Aktiengesellschaft Shroud cooling system for shrouds adjacent to airfoils within gas turbine engines
EP3219932A1 (en) * 2016-03-16 2017-09-20 United Technologies Corporation Blade outer air seal with flow guide manifold
US10337346B2 (en) 2016-03-16 2019-07-02 United Technologies Corporation Blade outer air seal with flow guide manifold

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JP3808211B2 (en) 2006-08-09
JPH1181907A (en) 1999-03-26
DE69817477T2 (en) 2004-06-09
DE69817477D1 (en) 2003-10-02
US5964575A (en) 1999-10-12
FR2766517B1 (en) 1999-09-03
CA2243333C (en) 2007-11-06
EP0893577B1 (en) 2003-08-27
CA2243333A1 (en) 1999-01-24
FR2766517A1 (en) 1999-01-29

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