EP1059420B1 - Housing for a high pressure compressor - Google Patents

Housing for a high pressure compressor Download PDF

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Publication number
EP1059420B1
EP1059420B1 EP00401609A EP00401609A EP1059420B1 EP 1059420 B1 EP1059420 B1 EP 1059420B1 EP 00401609 A EP00401609 A EP 00401609A EP 00401609 A EP00401609 A EP 00401609A EP 1059420 B1 EP1059420 B1 EP 1059420B1
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EP
European Patent Office
Prior art keywords
shroud
rings
casing
sectors
ventilation
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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EP00401609A
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German (de)
French (fr)
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EP1059420A1 (en
Inventor
Pascal Gérard Gervais
Pascal Michel Daniel Lejeune
Carmen Miraucourt
Jacky Serge Naudet
Patrice Suet
Monique Andrée Thore
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Safran Aircraft Engines SAS
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SNECMA Moteurs SA
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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
    • F01D11/16—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
    • 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
    • F04D29/545—Ducts

Definitions

  • the subject of this invention is a stator at heterogeneous structure that could be applied in particular to high pressure compressors of gas turbines.
  • the rotor and stator structure of gas turbines is often cooled or broken down by the air taken from the flow that runs through the machine.
  • the air taken for ventilation in downstream originates from a part of the machine where he has already been compressed, which made it much more heated as the air from the ventilation upstream.
  • the invention consists of a compressor stator provided with a upstream ventilation of cooling air and downstream ventilation of air warmer than at the upstream, upstream and downstream ventilation being defined with respect to the normal direction of circulation of the main air flow and comprising a ferrule delimiting a stream of gas flow, characterized in that it comprises a first portion ferrule, subject to upstream ventilation, continuous annular structure on a circumference and in a first material, and a second portion of ferrule, subject to downstream ventilation, with structure formed of angular sectors juxtaposed and in one second material having a coefficient of expansion larger than the first material.
  • the first and second materials may be chosen respectively from lower coefficient of expansion materials such as TA6V and titanium alloys INC0909, TiAl type intermetallic, having an average coefficient of linear expansion less than 10 ⁇ 10 -6 m per degree; and among materials with a larger coefficient of expansion, such as nickel-based alloys of the INC0718, RENE77 and derivative type, having an average coefficient of linear expansion close to 15 ⁇ 10 -6 m per degree.
  • lower coefficient of expansion materials such as TA6V and titanium alloys INC0909, TiAl type intermetallic, having an average coefficient of linear expansion less than 10 ⁇ 10 -6 m per degree
  • materials with a larger coefficient of expansion such as nickel-based alloys of the INC0718, RENE77 and derivative type, having an average coefficient of linear expansion close to 15 ⁇ 10 -6 m per degree.
  • Figure 1 is an overview of a high-pressure compressor a gas turbine
  • Figure 2 is an enlarged view the downstream portion of the stator of this compressor
  • the FIG. 2A a similar view of another embodiment possible of the invention
  • Figures 3 and 4 are two cuts of the upstream and downstream parts of the compressor
  • Figure 5 is an enlarged view of the upstream part of the compressor.
  • a stator 7 surrounds the rotor 1 and comprises, in internal lining of a carcass 8, a portion 9 to which the invention relates and which consists of a support casing 10 and a ferrule 11 supported by the housing 10, turned towards the rotor 1 and which serves to delimit a ring vein 12 of gas flow in which the moving blade stages 6 and blade stages stationary 13 flow rectification, which are attached to the shell 11 and alternate with the floors previously mentioned.
  • abradable 15 formed of a honeycomb structure or more generally of easy erosion, which is dug by ribs 16 opposite erected on the envelope 3 and which form with it a seal at labyrinth.
  • the tips of the moving blades 6 are free of any equipment and end up close of the ferrule 11.
  • the internal portion 9 of the stator 7 presents discontinuities, which are openings of air sampling from vein 12, noted by references 17, 18 and which give in rooms 19 and 20 established between the portion 9 and the carcass 8 and through which the air taken from the vein 12 to ventilate in particular the housing 10 and subject it to temperature and dilation thermal determined.
  • the inside of the rotor 1 is it also ventilated, firstly through a piercing 21 of the casing 3 located upstream of the rotor 1 and by which fresh air, at approximately the same temperature as the one who enters the room 19, is sucked, then by another bore 22 of the casing 3, substantially to the right of the second opening 18.
  • Sectors 23 and 23 'adjacent are united by flexible tongues 24 sealing, extending into grooves longitudinal edges of the sectors and joining by their ends 25, between circles of sectors 23 and 23 'consecutive; and by other tabs 26 flexible established in grooves purely or obliquely radial edges of sectors 23 and 23 ', and extending from the first tongues 24 to the housing 10.
  • This arrangement effectively prevents the gases, very hot there, from vein 12 to flee between sectors 23 and 23 'to reach the housing 10 and risk of damaging it.
  • the tabs 24 and 26 isolate empty volumes 27 (which can also be filled with insulation at the heat) that appear between each of the circles of sectors 23 and 23 'and associated rings 28 of the housing 10.
  • each of them comprises a rear lip 31 protruding towards inside and back, and that is enclosed between a lip 32 of one of the rings 28, located radially outward, and a lip 33 or 33 ' pointing forward and established either in front of sectors 23, that is to the front of ring 28 located on further downstream; and sectors 23 and 23 'include still an outer lip 34 at the front, which cooperates with lips 33 to enclose lips 31 and 32 directed to the rear.
  • Sectors 23 ' differ in that they only include one lip unique at the front, bearing the reference 35 and oriented towards the rear, and which is housed in a groove 36 of the ring 28 located furthest forward.
  • This mode assembly is simpler than a mode inspired by more traditional ring fastening designs of ferrule, illustrated in Figure 2A, where the lips 31 and 32 are united by separate seals 37 with a cross-section staple and where the ferrule elements comprise a rib 38 relatively high ending in a lip 39 forward facing and housed in a groove of the adjacent ring; however, it is possible to adopt this less favorable design if desired.
  • the 50 tenon nesting systems allow in all cases of linking sectors 23 and 23 'to rings 28 in the angular direction; many achievements are within the reach of the skilled person.
  • the mode of linking sectors 23 and 23 'to Rings 28 is quite flexible and absorbs deformations without receiving strong constraints.
  • the rings 28 are preferably continuous on the circumference for give a simpler structure and a better mechanical resistance.
  • a nickel-based alloy, type INCO718, high coefficient of expansion can be used for this downstream part of the compressor.
  • the housing 10 is at this place composed of rings 40, joined together by bolts 42 enclosing flanges 41 which the end, as well as the carcass 8, in the manner of rings 28; but these rings 40 still include protuberances 43 and 43 'radially on the inside, which open out on the 12th vein of airflow and are therefore exposed to its temperature. Two of these protuberances 43 are wide enough to extend in front of a stage of moving blades 6 respective.
  • the ferrule 11 is here formed at a time by the protuberances 43 and 43 'and by rings 44 support of the stationary vanes 13; the rings 44 finish at the front and back by lips 45 who enter grooves of the growths 43 and 43 '.
  • mechanical systems 46 with interlocking tenon join the rings 40 to the rings 44 concentric against mutual rotations.
  • the major difference with downstream design is that the rings 44 are continuous on a circumference while as the rings 40. It is estimated that, as heating up are less important upstream, and that the temperature differences between the housing 10 and the ferrule 11 are less important also it is more simple and more advantageous to have a structure similar for both, the risks of deformation and excessive stress being reduced.
  • the material used has a coefficient of dilation less than that used for build the downstream of the crankcase, because we observe that Slower dilations than these materials undergo regulate a little the evolution of the dilatation during transient phases and allow finally better control games at the end of the blade blades 6.
  • An alloy of the Inconel 909 type may be recommended or an intermetallic type TiAl.
  • the rotor 1 can be built in a material whose coefficient of expansion is close of that used for the stator rings 40 in look, for example a titanium alloy.

Description

Le sujet de cette invention est un stator à structure hétérogène susceptible de s'appliquer en particulier aux compresseurs à haute pression de turbines à gaz.The subject of this invention is a stator at heterogeneous structure that could be applied in particular to high pressure compressors of gas turbines.

La structure du rotor et du stator des turbines à gaz est souvent refroidie ou ventilée par de l'air prélevé de l'écoulement qui parcourt la machine. On rencontre même des doubles ventilations associées à des doubles prélèvements, où une ventilation d'une partie aval du stator et du rotor fait suite à une première ventilation du stator et du rotor effectuée plus en amont. L'air prélevé pour la ventilation en aval est originaire d'une partie de la machine où il a déjà été comprimé, ce qui l'a beaucoup plus échauffé que l'air de la ventilation en amont. Le problème habituel d'obtenir un réglage correct des diamètres du stator et du rotor afin d'éviter l'augmentation excessive des jeux au bout des aubes, qui accroítrait les fuites d'air et les pertes de rendement, ou au contraire la disparition de ces jeux, qui aurait pour conséquence un frottement des aubes du rotor sur le stator, devient alors bien difficile à résoudre à cause de ces conditions hétérogènes de ventilation, qui induisent des températures et des dilatations thermiques différentes entre les portions respectivement soumises aux deux ventilations. Une autre source de difficultés provient de ce que les différentes parties de la machine, même celles qui sont situées à un même niveau du compresseur, sont portées à des températures différentes selon qu'elles sont proches de l'air de ventilation ou de l'air plus chaud de la veine d'écoulement : il en résulte des dilatations inégales, des déformations et des contraintes dans le stator. Enfin, les variations de température sont plus rapides à certains endroits, de sorte que les problèmes précédents peuvent devenir plus ou moins aigus localement, pendant les phases de changement de régime. Aucune structure connue de stator ne donne entière satisfaction dans ces conditions.The rotor and stator structure of gas turbines is often cooled or broken down by the air taken from the flow that runs through the machine. There are even double breakdowns associated with double sampling, where a breakdown of one downstream part of the stator and the rotor follows a first stator and rotor ventilation performed further upstream. The air taken for ventilation in downstream originates from a part of the machine where he has already been compressed, which made it much more heated as the air from the ventilation upstream. The problem usual to obtain a correct adjustment of the diameters of the stator and rotor to prevent the increase excessive games at the end of the blades, which would increase air leaks and yield losses, or at contrary to the disappearance of these games, which would have consequence a friction of the blades of the rotor on the stator, then becomes very difficult to solve because of these heterogeneous ventilation conditions, which induce temperatures and dilations different thermal between portions respectively subject to both breakdowns. A Another source of difficulty is that different parts of the machine, even those that are located at the same level of the compressor, are brought to different temperatures depending on whether they are close to the ventilation air or warmer air of the flow vein: this results in unequal dilatations, deformities and constraints in the stator. Finally, the variations of temperatures are faster in some places, so that the previous problems can become more or less acute locally, during the phases of regime change. No known stator structure gives complete satisfaction in these conditions.

Des exemples connus de réalisations antérieures sont décrits notammnent par US-A-5 160 241 qui montre des aménagements sur les prélévements d'air à travers un carter de stator de compresseur et par US-A-5 314 303 qui montre l'adjonction d'un anneau intermédiaire de blocage des variations de dilatation.Known examples of previous embodiments are described especially by US-A-5,160,241 which shows facilities on air withdrawals through a compressor stator housing and US-A-5,314,303 which shows the addition of a ring intermediate blocking of dilation variations.

L'idée de l'invention consiste à scinder la structure du stator de part et d'autre de la jonction des zones de ventilations et de construire différemment le stator entre les portions soumises à la ventilation en amont et celles qui sont soumises à la ventilation en aval. Sous sa forme la plus générale, l'invention consiste en un stator de compresseur muni d'une ventilation en amont d'air de refroidissement et une ventilation en aval d'air plus chaud qu'à la ventilation amont, amont et aval étant définis par rapport au sens normal de circulation du flux d'air principal et comprenant une virole délimitant une veine d'écoulement de gaz, caractérisé en ce qu'il comprend une première portion de virole, soumise à la ventilation en amont, à structure annulaire continue sur une circonférence et en un premier matériau, et une deuxième portion de virole, soumise à la ventilation aval, à structure formée de secteurs angulaires juxtaposés et en un deuxième matériau ayant un coefficient de dilatation plus grand que le premier matériau. The idea of the invention is to split the stator structure on both sides of the junction zones of breakdowns and build differently the stator between the portions subjected to the ventilation upstream and those subject to ventilation downstream. In its most general form, the invention consists of a compressor stator provided with a upstream ventilation of cooling air and downstream ventilation of air warmer than at the upstream, upstream and downstream ventilation being defined with respect to the normal direction of circulation of the main air flow and comprising a ferrule delimiting a stream of gas flow, characterized in that it comprises a first portion ferrule, subject to upstream ventilation, continuous annular structure on a circumference and in a first material, and a second portion of ferrule, subject to downstream ventilation, with structure formed of angular sectors juxtaposed and in one second material having a coefficient of expansion larger than the first material.

Les premier et deuxième matériaux peuvent être choisis, respectivement parmi des matériaux à coefficient de dilatation plus bas tels que TA6V et alliages de titane, INC0909, intermétalliques du type TiAl, ayant un coefficient moyen de dilatation linéique inférieur à 10.10-6 m par degré ; et parmi des matériaux à coefficient de dilatation plus grand tels que des alliages à base de nickel du type INC0718, RENE77 et dérivés, ayant un coefficient moyen de dilatation linéique voisin de 15.10-6 m par degré.The first and second materials may be chosen respectively from lower coefficient of expansion materials such as TA6V and titanium alloys INC0909, TiAl type intermetallic, having an average coefficient of linear expansion less than 10 × 10 -6 m per degree; and among materials with a larger coefficient of expansion, such as nickel-based alloys of the INC0718, RENE77 and derivative type, having an average coefficient of linear expansion close to 15 × 10 -6 m per degree.

Une explication plus détaillée de l'invention, de ses caractéristiques, buts et avantages sera fournie à l'aide des figures, dont la figure 1 est une vue d'ensemble d'un compresseur à haute pression d'une turbine à gaz ; la figure 2 est une vue agrandie de la partie aval du stator de ce compresseur ; la figure 2A une vue analogue d'une autre réalisation possible de l'invention ; les figures 3 et 4 sont deux coupes de la partie amont et de la partie aval du compresseur ; et la figure 5 est une vue agrandie de la partie amont du compresseur.A more detailed explanation of the invention, its characteristics, aims and advantages will be provided using the figures, of which Figure 1 is an overview of a high-pressure compressor a gas turbine; Figure 2 is an enlarged view the downstream portion of the stator of this compressor; the FIG. 2A a similar view of another embodiment possible of the invention; Figures 3 and 4 are two cuts of the upstream and downstream parts of the compressor; and Figure 5 is an enlarged view of the upstream part of the compressor.

Un compresseur à haute pression tel que celui de la figure 1 comprend un rotor central 1 entraíné par une ligne d'arbres 2 et composé d'une enveloppe 3 de forme fuselée composée d'anneaux 4 juxtaposés et séparés par des disques 5 au droit d'étages d'aubes mobiles 6. Un stator 7 entoure le rotor 1 et comprend, en doublure interne d'une carcasse 8, une portion 9 sur laquelle porte l'invention et qui se compose d'un carter 10 de support et d'une virole 11 soutenue par le carter 10, tournée vers le rotor 1 et qui sert à délimiter une veine 12 annulaire d'écoulement des gaz dans laquelle s'étendent les étages d'aubes mobiles 6 et des étages d'aubes stationnaires 13 de redressement de l'écoulement, qui sont accrochés à la virole 11 et alternent avec les étages précédemment mentionnés. Il est habituel que les bouts des aubes stationnaires 13, situés devant l'enveloppe 3 du rotor 1, portent des anneaux de liaison 14 garnis de bandes circulaires de matière dite abradable 15, formée d'une structure en nid d'abeilles ou plus généralement d'érosion facile, qui est creusée par des nervures 16 en regard érigées sur l'enveloppe 3 et qui forment avec elle un joint d'étanchéité à labyrinthe. Cependant, les bouts des aubes mobiles 6 sont libres de tout équipement et finissent tout près de la virole 11.A high pressure compressor such as that of Figure 1 comprises a central rotor 1 driven by a line of trees 2 and composed of a envelope 3 of tapered shape composed of rings 4 juxtaposed and separated by disks 5 to the right of moving blades 6. A stator 7 surrounds the rotor 1 and comprises, in internal lining of a carcass 8, a portion 9 to which the invention relates and which consists of a support casing 10 and a ferrule 11 supported by the housing 10, turned towards the rotor 1 and which serves to delimit a ring vein 12 of gas flow in which the moving blade stages 6 and blade stages stationary 13 flow rectification, which are attached to the shell 11 and alternate with the floors previously mentioned. It is usual for tips of stationary vanes 13, located in front of the casing 3 of the rotor 1, wear rings of binding 14 lined with circular strips of so-called abradable 15, formed of a honeycomb structure or more generally of easy erosion, which is dug by ribs 16 opposite erected on the envelope 3 and which form with it a seal at labyrinth. However, the tips of the moving blades 6 are free of any equipment and end up close of the ferrule 11.

La portion 9 interne du stator 7 présente des discontinuités, qui sont des ouvertures de prélèvement d'air de la veine 12, notées par les références 17, 18 et qui donnent dans des chambres respectives 19 et 20 établies entre la portion 9 et la carcasse 8 et par lesquelles transite l'air prélevé de la veine 12 pour ventiler en particulier le carter 10 et le soumettre à une température et une dilatation thermique déterminée. L'intérieur du rotor 1 est lui aussi ventilé, tout d'abord à travers un perçage 21 de l'enveloppe 3 situé en amont du rotor 1 et par lequel de l'air frais, sensiblement à la même température que celui qui entre dans la chambre 19, est aspiré, puis par un autre perçage 22 de l'enveloppe 3, sensiblement au droit de la deuxième ouverture 18. Les chambres 19 et 20 divisent la stator 7 en deux zones de ventilation, devant lesquelles elles s'étendent respectivement et qui sont situées de part et d'autre de l'ouverture 19 d'entrée dans la chambre aval 20, qui sépare la portion 9 en deux. Deux zones de ventilation de positions semblables existent sur le rotor 1, de part et d'autre du perçage 22.The internal portion 9 of the stator 7 presents discontinuities, which are openings of air sampling from vein 12, noted by references 17, 18 and which give in rooms 19 and 20 established between the portion 9 and the carcass 8 and through which the air taken from the vein 12 to ventilate in particular the housing 10 and subject it to temperature and dilation thermal determined. The inside of the rotor 1 is it also ventilated, firstly through a piercing 21 of the casing 3 located upstream of the rotor 1 and by which fresh air, at approximately the same temperature as the one who enters the room 19, is sucked, then by another bore 22 of the casing 3, substantially to the right of the second opening 18. Rooms 19 and divide the stator 7 into two zones of ventilation, before which they extend respectively and which are located on both sides of the inlet opening 19 in the downstream chamber 20, which separates portion 9 in two. Two ventilation zones similar positions exist on rotor 1, on both sides of the hole 22.

Malgré les précautions prises pour égaliser les dilatations thermiques entre les diverses parties du rotor 1 et du stator 7, notamment en prévoyant pour chacun d'eux des conditions de ventilation identiques, l'expérience montre qu'on est embarrassé pour trouver des conditions de fonctionnement satisfaisantes, en ne laissant subsister que des jeux modérés entre les aubes mobiles 6 et la virole 11. Le problème est plus aigu pour la partie aval, parcourue par de l'air plus chaud et soumise à une ventilation également plus chaude. On préconise alors (figures 2 et 3) de construire la virole 11 sous forme de secteurs 23, dont on peut trouver un nombre variable sur une circonférence, peut-être une dizaine, et dont l'extension longitudinale peut aussi être variable ; dans le cas présent, on propose deux cercles de secteurs 23 présentant une partie avant de support d'aube stationnaire 13 et une partie arrière située au droit d'un étage d'aubes mobiles 6, et un troisième cercle de secteurs 23' qui est plus court et ne comprend qu'une portion faisant face à un étage d'aubes mobiles 6. Les secteurs 23 et 23' adjacents sont unis par des languettes 24 souples d'étanchéité, s'étendant dans des rainures longitudinales des bords des secteurs et se joignant par leurs extrémités 25, entre des cercles de secteurs 23 et 23' consécutifs ; et par d'autres languettes 26 souples établies dans des rainures purement ou obliquement radiales des bords des secteurs 23 et 23', et s'étendant des premières languettes 24 au carter 10. Cette disposition empêche efficacement les gaz, très chauds à cet endroit, de la veine 12 de fuir entre les secteurs 23 et 23' pour atteindre le carter 10 et risquer de l'endommager. En particulier, on remarque que les languettes 24 et 26 isolent des volumes vides 27 (pouvant d'ailleurs être emplis d'un isolant à la chaleur) qui apparaissent entre chacun des cercles de secteurs 23 et 23' et des anneaux 28 associés du carter 10. Le carter 10 est donc exposé uniquement à l'air entrant dans la chambre avant 20, et la virole 11 à l'air de la veine 12. Les anneaux 28 successifs sont joints entre eux et à la carcasse 8 en unissant des brides 29 qui les terminent au moyen de boulons 30. Il est intéressant de remarquer aussi le mode de liaison et d'assemblage des secteurs 23 et 23' : chacun d'eux comprend une lèvre arrière 31, saillant vers l'intérieur et vers l'arrière, et qui est enserrée entre une lèvre 32 d'un des anneaux 28, située radialement vers l'extérieur, et une lèvre 33 ou 33' pointant vers l'avant et établie soit à l'avant des secteurs 23, soit à l'avant de l'anneau 28 situé le plus en aval ; et les secteurs 23 et 23' comprennent encore une lèvre extérieure 34 à l'avant, qui coopère avec les lèvres 33 pour enserrer entre elles les lèvres 31 et 32 dirigées vers l'arrière. Les secteurs 23' diffèrent en ce qu'ils ne comprennent qu'une lèvre unique à l'avant, portant la référence 35 et orientée vers l'arrière, et qui est logée dans une rainure 36 de l'anneau 28 situé le plus en avant. Ce mode d'assemblage est plus simple qu'un mode inspiré de conceptions plus traditionnelles de fixation d'anneaux de virole, illustré à la figure 2A, où les lèvres 31 et 32 sont unies par des joints séparés 37 à section en agrafe et où les éléments de virole comprennent une nervure 38 relativement haute finissant en une lèvre 39 orientée vers l'avant et logée dans une rainure de l'anneau adjacent ; il est toutefois possible d'adopter cette conception moins favorable si on le souhaite. Des systèmes 50 à imbrication de tenon permettent dans tous les cas de lier les secteurs 23 et 23' aux anneaux 28 en direction angulaire ; de nombreuses réalisations sont à la portée de l'homme du métier.Despite the precautions taken to equalize thermal expansion between the various parts rotor 1 and the stator 7, in particular by providing for each of them identical ventilation conditions, experience shows that one is embarrassed to find satisfactory operating conditions, not leaving only moderate games between the blades mobile 6 and the ferrule 11. The problem is more acute for the downstream part, covered by warmer air and subject to even warmer ventilation. We then advocates (Figures 2 and 3) to build the ferrule 11 in the form of sectors 23, which can be find a variable number on a circumference, maybe ten, and whose longitudinal extension can also be variable; in this case, we proposes two circles of sectors 23 presenting a front portion of stationary blade support 13 and a rear part located at the right of a blade stage mobiles 6, and a third circle of sectors 23 'which is shorter and includes only one serving facing a stage of moving blades 6. Sectors 23 and 23 'adjacent are united by flexible tongues 24 sealing, extending into grooves longitudinal edges of the sectors and joining by their ends 25, between circles of sectors 23 and 23 'consecutive; and by other tabs 26 flexible established in grooves purely or obliquely radial edges of sectors 23 and 23 ', and extending from the first tongues 24 to the housing 10. This arrangement effectively prevents the gases, very hot there, from vein 12 to flee between sectors 23 and 23 'to reach the housing 10 and risk of damaging it. In particular, we notice that the tabs 24 and 26 isolate empty volumes 27 (which can also be filled with insulation at the heat) that appear between each of the circles of sectors 23 and 23 'and associated rings 28 of the housing 10. The housing 10 is exposed only to air entering the room before 20, and the shell 11 to the air of the vein 12. The successive rings 28 are between them and the carcass 8 by uniting flanges 29 which terminate them by means of bolts 30. It is interesting to note also the mode of connection and assembly of sectors 23 and 23 ': each of them comprises a rear lip 31 protruding towards inside and back, and that is enclosed between a lip 32 of one of the rings 28, located radially outward, and a lip 33 or 33 ' pointing forward and established either in front of sectors 23, that is to the front of ring 28 located on further downstream; and sectors 23 and 23 'include still an outer lip 34 at the front, which cooperates with lips 33 to enclose lips 31 and 32 directed to the rear. Sectors 23 ' differ in that they only include one lip unique at the front, bearing the reference 35 and oriented towards the rear, and which is housed in a groove 36 of the ring 28 located furthest forward. This mode assembly is simpler than a mode inspired by more traditional ring fastening designs of ferrule, illustrated in Figure 2A, where the lips 31 and 32 are united by separate seals 37 with a cross-section staple and where the ferrule elements comprise a rib 38 relatively high ending in a lip 39 forward facing and housed in a groove of the adjacent ring; however, it is possible to adopt this less favorable design if desired. of the 50 tenon nesting systems allow in all cases of linking sectors 23 and 23 'to rings 28 in the angular direction; many achievements are within the reach of the skilled person.

La construction de la virole 11 en secteurs angulaires 23 et 23' permet de ne pas créer des contraintes de compression sensibles le long de la circonférence et qui proviendrait de l'élévation de température plus rapide de la virole 11 que du carter 10. Les dilatations plus importantes de la virole 11 qu'on subit tout de même se traduisent simplement par une diminution des jeux entre secteurs angulaires 23 et 23' adjacents et par une flexion éventuelle des languettes 24 et 26, qui sont souples. Le risque de déformations irrégulières de la virole 11 par ovalisation ou création d'ondulations, qui conduiraient à des jeux variables en bout des aubes mobiles 6, ou même à un frettage de la virole 11 contre le carter 10 consécutif à une expansion radiale excessive, est ainsi évité. Le mode de liaison des secteurs 23 et 23' aux anneaux 28 est assez souple et absorbe les déformations sans recevoir de fortes contraintes. Les anneaux 28 sont de préférence continus sur la circonférence pour donner une structure plus simple et une meilleure résistance mécanique. De plus, on préconise que les anneaux 28 comme les secteurs 23 et 23' soient construits en une matière ayant un coefficient de dilatation élevé, c'est-à-dire d'une matière qui conduise bien la chaleur, afin de subir aussi rapidement que possible les dilatations entraínées par l'échauffement au cours des changements de régime. On conseille de construire le rotor 1 dans le même matériau en regard des anneaux 28 du stator 7. Un alliage à base de nickel, du type INCO718, à haut coefficient de dilatation peut être employé pour cette partie aval du compresseur.The construction of the ferrule 11 in sectors angular 23 and 23 'makes it possible not to create compressive compressive stresses along the circumference and that would come from the elevation of faster temperature of the ferrule 11 than the crankcase 10. The larger expansions of ferrule 11 that we suffer all the same are simply translated by a reduction of the games between angular sectors 23 and 23 'and by a possible bending of the tongues 24 and 26, which are flexible. The risk of irregular deformations of ferrule 11 by ovalisation or creation of undulations, which would lead at variable games at the end of the blades 6, or even with a hoop 11 ferrule against the housing 10 consecutive to excessive radial expansion, is thus avoid. The mode of linking sectors 23 and 23 'to Rings 28 is quite flexible and absorbs deformations without receiving strong constraints. The rings 28 are preferably continuous on the circumference for give a simpler structure and a better mechanical resistance. In addition, it is recommended that rings 28 as sectors 23 and 23 'are constructed of a material having a coefficient of high dilatation, that is to say of a material which lead the heat well, so as to also undergo quickly as possible the dilations caused by warm-up during regime changes. We advise to build the rotor 1 in the same material facing the rings 28 of the stator 7. A nickel-based alloy, type INCO718, high coefficient of expansion can be used for this downstream part of the compressor.

Les moindres variations de température auxquelles la partie amont du stator 7 est exposée justifient qu'on lui donne une structure différente, comme on le voit sur les figures 4 et 5. Le carter 10 est à cet endroit composé d'anneaux 40, unis entre eux par des boulons 42 enserrant des brides 41 qui les terminent, ainsi que la carcasse 8, à la façon des anneaux 28 ; mais ces anneaux-ci 40 comprennent encore des excroissances 43 et 43' radialement à l'intérieur, qui débouchent sur la veine 12 d'écoulement d'air et sont donc exposées à sa température. Deux de ces excroissances 43 sont suffisamment larges pour s'étendre en regard d'un étage d'aubes mobiles 6 respectif. The slightest temperature variations to which the upstream portion of the stator 7 is exposed justify giving it a different structure, as seen in Figures 4 and 5. The housing 10 is at this place composed of rings 40, joined together by bolts 42 enclosing flanges 41 which the end, as well as the carcass 8, in the manner of rings 28; but these rings 40 still include protuberances 43 and 43 'radially on the inside, which open out on the 12th vein of airflow and are therefore exposed to its temperature. Two of these protuberances 43 are wide enough to extend in front of a stage of moving blades 6 respective.

La virole 11 est donc ici formée à la fois par les excroissances 43 et 43' et par des anneaux 44 de support des aubes stationnaires 13 ; les anneaux 44 finissent à l'avant et à l'arrière par des lèvres 45 qui entrent dans des rainures des excroissances 43 et 43'. Enfin, des systèmes mécaniques 46 à imbrication de tenon unissent les anneaux 40 aux anneaux 44 concentriques contre les rotations mutuelles. La différence majeure avec la conception en aval est que les anneaux 44 sont continus sur une circonférence tout comme les anneaux 40. On estime en effet que comme les échauffements sont moins importants en amont, et que les différences de température entre le carter 10 et la virole 11 sont moins importantes également, il est plus simple et plus avantageux d'avoir une structure analogue pour les deux, les risques de déformations et de contraintes excessives étant réduits. De plus, on préconise que le matériau employé ait un coefficient de dilatation moins important que celui qu'on emploie pour construire l'aval du carter, car on observe que les dilatations plus lentes que ces matériaux subissent régularisent un peu l'évolution de la dilatation pendant les phases transitoires et permettent finalement de mieux maítriser les jeux en bout de pale des aubes mobiles 6. Un alliage du type Inconel 909 peut être conseillé ou un intermétallique du type TiAl. Ici encore, le rotor 1 peut être construit dans un matériau dont le coefficient de dilatation est proche de celui utilisé pour les anneaux 40 de stator en regard, par exemple un alliage de titane.The ferrule 11 is here formed at a time by the protuberances 43 and 43 'and by rings 44 support of the stationary vanes 13; the rings 44 finish at the front and back by lips 45 who enter grooves of the growths 43 and 43 '. Finally, mechanical systems 46 with interlocking tenon join the rings 40 to the rings 44 concentric against mutual rotations. The major difference with downstream design is that the rings 44 are continuous on a circumference while as the rings 40. It is estimated that, as heating up are less important upstream, and that the temperature differences between the housing 10 and the ferrule 11 are less important also it is more simple and more advantageous to have a structure similar for both, the risks of deformation and excessive stress being reduced. In addition, recommends that the material used has a coefficient of dilation less than that used for build the downstream of the crankcase, because we observe that Slower dilations than these materials undergo regulate a little the evolution of the dilatation during transient phases and allow finally better control games at the end of the blade blades 6. An alloy of the Inconel 909 type may be recommended or an intermetallic type TiAl. Here again, the rotor 1 can be built in a material whose coefficient of expansion is close of that used for the stator rings 40 in look, for example a titanium alloy.

Claims (8)

  1. Compressor stator provided with upstream ventilation (17, 19) with cooling air and downstream ventilation (18, 20) with warmer air than at the upstream ventilation {upstream and downstream being defined with respect to the normal direction of circulation of the main air flow} and comprising a shroud (11) delimiting a gas flow channel (12), characterized in that it comprises a first portion of shroud, subjected to the upstream ventilation (17), having a continuous annular structure (44) over a circumference and made of a first material, and a second portion of shroud, subjected to the downstream ventilation, having a structure formed of juxtaposed angular sectors (23) and made of a second material having a higher coefficient of expansion than the first material.
  2. Stator according to Claim 1, characterized in that the first and second materials are chosen, respectively, from a group of materials having a lower coefficient of expansion such as TA6V and titanium alloys, TNC0909, intermetallic alloys of the TiAl type, having an average coefficient of expansion lower than 10.10-6 m per degree; and from a group of materials having a higher coefficient of expansion such as nickel-based alloys of the INC0718, RENE77 and derivatives type, having an average linear coefficient of expansion in the vicinity of 15.10-6 m per degree.
  3. Stator according to any one of Claims 1 or 2, characterized in that it comprises a casing (10) supporting the shroud (11), the casing (10) delimiting a chamber (19) being part of the upstream ventilation and a chamber (20) being part of the downstream ventilation, and in that the casing is formed as a continuous annular structure (28, 40) over a circumference in front of the two chambers.
  4. Stator according to Claim 3, characterized in that the casing (10) is composed of rings (28, 40) forming an extension to and a continuous assembly in front of the first portion of shroud and in front of the second portion of shroud.
  5. Stator according to Claim 4, characterized in that the rings of the casing in front of the second part of the shroud are respectively associated with annular assemblies of juxtaposed sectors (23, 23') of the shroud, and the sectors (23) mostly comprise a pair of concentric lips (33, 34) at one end, clamping a lip (31) of an opposite end of sectors (23, 23') of an adjacent assembly and a lip (32) of a ring of the casing associated with the said adjacent annular assembly.
  6. Stator according to Claim 3, characterized in that the rings of the casing in front of the first part of the shroud have excrescences (43, 43') extending between the shroud rings and also delimiting the flow channel (12), the shroud rings being interleaved between the excrescences.
  7. Stator according to any one of Claims 1 to 6, characterized in that the sectors (23, 23') are connected by flexible tongues (24, 26).
  8. Stator according to any one of Claims 1 to 7, characterized in that the first and second shroud positions are located in front of portions of a rotor (1) constructed in the first material and in the second material respectively.
EP00401609A 1999-06-10 2000-06-08 Housing for a high pressure compressor Expired - Lifetime EP1059420B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9907315A FR2794816B1 (en) 1999-06-10 1999-06-10 HIGH PRESSURE COMPRESSOR STATOR
FR9907315 1999-06-10

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EP1059420A1 EP1059420A1 (en) 2000-12-13
EP1059420B1 true EP1059420B1 (en) 2004-12-08

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EP00401609A Expired - Lifetime EP1059420B1 (en) 1999-06-10 2000-06-08 Housing for a high pressure compressor

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US (1) US6390771B1 (en)
EP (1) EP1059420B1 (en)
JP (1) JP4124552B2 (en)
DE (1) DE60016505T2 (en)
FR (1) FR2794816B1 (en)

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US6390771B1 (en) 2002-05-21
JP4124552B2 (en) 2008-07-23
EP1059420A1 (en) 2000-12-13
DE60016505D1 (en) 2005-01-13
FR2794816A1 (en) 2000-12-15
FR2794816B1 (en) 2001-07-06
DE60016505T2 (en) 2005-11-03
JP2001012396A (en) 2001-01-16

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