EP1329639B1 - Centripetal air bleed device - Google Patents
Centripetal air bleed device Download PDFInfo
- Publication number
- EP1329639B1 EP1329639B1 EP03290061A EP03290061A EP1329639B1 EP 1329639 B1 EP1329639 B1 EP 1329639B1 EP 03290061 A EP03290061 A EP 03290061A EP 03290061 A EP03290061 A EP 03290061A EP 1329639 B1 EP1329639 B1 EP 1329639B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- compressor
- air
- holes
- groove
- interstice
- 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.)
- Expired - Lifetime
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
- F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
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- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
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- 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
- F04D29/58—Cooling; Heating; Diminishing heat transfer
- F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
- F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine
Definitions
- the invention relates to an axial turbomachine compressor equipped with a device for the centripetal sampling of air in the vein of the compressor, this sampling air being intended for the cooling of the turbine, said compressor comprising two blades of mobile blades which extend radially outwardly at the periphery of two consecutive disks joined together by an outer shell provided with bores and a stationary straightening rotor ring disposed in the vein between said two rotor blade rings, said bores serving as inputs for air auditing said sampling device and opening into an annular groove provided under the gap separating the inner platforms of the straightening vanes, the rim of the upstream disk, said groove communicating with said vein by said gap.
- centripetal air sampling device disposed inside the high-pressure rotor, is to bring a flow of air taken from a compressor stage to the turbine stages to be cooled. It is important that the cooling air arriving in the blades of the high pressure turbine, subjected to high temperatures, has a sufficient pressure to allow the formation of a protective air film around the blades of the turbine, and a temperature as low as possible.
- the sampling device may comprise sampling channels provided in the upstream disk, as is disclosed by FR 2,609,500 and FR 2,614,654 , or sampling tubes arranged in the annular cavity separating the two disks, as is disclosed by US 5,475,313 .
- the object of the invention is to provide easy to implement and inexpensive means that can significantly reduce the temperature of the air delivered to the high pressure turbine and reduce pressure losses, all things being equal. elsewhere.
- the document UK 712,051 describes a sampling system where air guide vanes are arranged downstream of the ring of straightening vanes being fixed between two annular walls.
- the invention relates to a turbomachine axial compressor equipped with a centripetal air sampling device in the vein of said compressor, this air being intended for the cooling of the turbine, said compressor comprising two blades of mobile blades which extend radially. outwardly at the periphery of two consecutive disks assembled by an outer shell provided with bores and a ring of stationary straightening vanes disposed in the vein between said two rotor blades, said bores serving as air inlets to said sampling device and opening into an annular groove provided under the gap between the inner platforms of the straightening vanes of the rim of the upstream disk, said groove communicating with said vein through said interstice, characterized in that said annular groove in which open said holes are located between the most upstream blade crown and the crown of rectifying blades and in that fixed guiding means imparting to the flow of air flowing in said groove a centripetal swirling motion in the direction of rotation of the compressor are arranged at least partly under said inner platforms of the straightening vanes and are integral with these, to
- the relative total temperature of the air in the bores is substantially lowered compared to the same temperature in a conventional compressor, which improves the cooling of the turbine blades for the same flow, and increases their service life.
- the pressure losses are also reduced, which improves the flow of air taken compared to the state of the art for identical bores and sampling devices and increases the rate of overpressure in the vanes of the turbine.
- Said guide means are arranged at least partly under the inner platforms of the straightening vanes.
- the means for guiding the air in the groove comprise a plurality of blade profiles evenly distributed around the axis of rotation of the compressor.
- leading edges of the blading profiles extend at least partly in the gap.
- the angle of attack of the profiles is determined according to the tangential velocity and the local radial velocity of the air passing through the gap.
- the blade profiles increase the coefficient of air entrainment in the groove, which allows for the same total air temperature, to decrease the relative total temperature.
- the improvement of the drive coefficient thanks to the proposed blade profiles is about 30% compared to the state of the art, which corresponds to a decrease in the relative total temperature of approximately 40 ° C. This makes it possible to multiply the life of the blades of the turbine by two, for the same flow taken.
- the figure 1 shows a compressor 1 of an X axis turbomachine according to the state of the art equipped with a centripetal sampling device 2.
- This compressor 1 comprises an upstream disk 3 having at its periphery a first ring of moving blades 4 disposed in the vein 5, a downstream disc 6 having at its periphery a second ring of moving blades 7 axially offset in the vein 5, and a ring of stationary straightening vanes 8 arranged in the vein 5 between the first and the second ring of moving blades.
- the upstream disk 3 and the downstream disk 6 are interconnected by an outer shell 9 provided with a sealing labyrinth 10 cooperating with the inner face of the inner platforms 11 of the straightening vanes 8.
- a groove 12 is provided under interstice 13 which separates the rim of the upstream disk 3, inner platforms 11.
- Holes 14 formed in the outer shell 9 open into the groove 12. These holes 14 allow the introduction of a sampling air flow rate in the centripetal sampling device 2 which in the example shown on the figure 1 comprises radial channels 15 formed in the wall of the upstream disk 3.
- the sampled air is conducted radially inwards by the radial channels 15 and deflected rearwardly by the radially inner portion 16 of the upstream disk 3, and flows axially to the stages of the turbine driving the compressor 1.
- the speed chart of the figure 3 shows that the relative speed Vr 1 of the air in the vicinity of the bores 14 relative to the periphery of the upstream disk 3 is relatively high.
- Va 1 denotes the absolute speed of the air and
- Ve represents the speed of the rim of the disc 3.
- the figure 2 shows the same compressor 1 equipped with fixed guide means 20 for printing air flowing in the groove 12 between the gap 13 and the holes 14 a centripetal swirling motion in the direction of rotation of the compressor 1.
- the air has an absolute velocity Va 2 whose norm is equal to the norm of the absolute velocity Va 1 , but which is substantially directed tangentially to the periphery of the outer shell 9, so that the velocity relative Vr 2 of the air relative to the upstream disk 3 is significantly lower than the relative speed Vr 1 of the state of the art, as is shown in FIG. figure 4 .
- the guide means 20 are arranged in the groove 12 under the upstream portion of the inner platforms 11 of the straightening vanes 8.
- These guide means 20 comprise a plurality of blade profiles 21 or fins regularly distributed around the axis of rotation X of the compressor 1 and whose leading edges 22 extend at least partly in the gap 13.
- the angle of attack ⁇ of these profiles 21 is determined as a function of the tangential speed and the local radial velocity of the air passing through the gap 13.
- the vane profiles 21 are drawn in such a way that the air entering through the gap 13 and flowing between the vane profiles 21 comes out with a velocity Va 2 , represented by an arrow or vector on the Figures 4 and 6 substantially tangential to the drive speed Ve of the rotor in order to substantially reduce the relative speed Vr 2 of the air entering the bores 14.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
L'invention concerne un compresseur axial de turbomachine équipé d'un dispositif de prélèvement centripète d'air dans la veine du compresseur, cet air de prélèvement étant destiné au refroidissement de la turbine, ledit compresseur comportant deux couronnes d'aubes mobiles qui s'étendent radialement vers l'extérieur à la périphérie de deux disques consécutifs assemblés par une virole extérieure munie de perçages et une couronne d'aubes redresseuses fixe disposée dans la veine entre lesdites deux couronnes d'aubes mobiles, lesdits perçages servant d'entrées d'air audit dispositif de prélèvement et débouchant dans une gorge annulaire prévue sous l'interstice séparant les plates-formes intérieures des aubes redresseuses, de la jante du disque amont, ladite gorge communiquant avec ladite veine par ledit interstice.The invention relates to an axial turbomachine compressor equipped with a device for the centripetal sampling of air in the vein of the compressor, this sampling air being intended for the cooling of the turbine, said compressor comprising two blades of mobile blades which extend radially outwardly at the periphery of two consecutive disks joined together by an outer shell provided with bores and a stationary straightening rotor ring disposed in the vein between said two rotor blade rings, said bores serving as inputs for air auditing said sampling device and opening into an annular groove provided under the gap separating the inner platforms of the straightening vanes, the rim of the upstream disk, said groove communicating with said vein by said gap.
Le rôle du dispositif de prélèvement centripète d'air, disposé à l'intérieur du rotor à haute pression, est d'amener un débit d'air prélevé dans un étage de compresseur vers les étages de turbine à refroidir. Il est important que l'air de refroidissement arrivant dans les aubages de la turbine à haute pression, soumis à des températures élevées, ait une pression suffisante pour permettre la formation d'un film d'air de protection autour des aubes de la turbine, et une température aussi faible que possible.The role of the centripetal air sampling device, disposed inside the high-pressure rotor, is to bring a flow of air taken from a compressor stage to the turbine stages to be cooled. It is important that the cooling air arriving in the blades of the high pressure turbine, subjected to high temperatures, has a sufficient pressure to allow the formation of a protective air film around the blades of the turbine, and a temperature as low as possible.
Le dispositif de prélèvement peut comporter des canaux de prélèvement ménagés dans le disque amont, ainsi que cela est divulgué par
Le débit d'air prélevé dans la veine pénètre dans la gorge annulaire par l'interstice séparant les plates-formes intérieures des aubes redresseuses de la jante du disque amont dans une direction sensiblement axiale et transite ensuite par les perçages de la virole en rotation. On conçoit donc que les vitesses relatives de l'air à l'entrée des perçages, par rapport au disque en rotation est relativement élevée, ce qui se traduit par une élévation de la température totale relative de l'air dans les perçages et une perte de charge non négligeable dans cette zone. Cette élévation de température se retrouve évidemment dans le débit d'air délivré dans les aubes de la turbine. La perte de charge se traduit par une diminution du débit d'air prélevé.The flow of air taken from the vein enters the annular groove through the gap between the inner platforms of the straightening vanes of the rim of the upstream disk in a substantially axial direction and then passes through the holes of the rotating shell. It is therefore conceivable that the relative velocities of the air at the inlet of the bores relative to the rotating disc is relatively high, which results in an increase in the relative total temperature of the air in the bores and a loss. not negligible load in this area. This rise in temperature is obviously found in the air flow delivered in the vanes of the turbine. The pressure drop results in a decrease in the air flow taken.
Le but de l'invention est de proposer des moyens faciles à mettre en oeuvre et peu coûteux qui permettent de diminuer sensiblement la température de l'air délivré dans la turbine à haute pression et de diminuer les pertes de charge, toutes choses étant égales par ailleurs.The object of the invention is to provide easy to implement and inexpensive means that can significantly reduce the temperature of the air delivered to the high pressure turbine and reduce pressure losses, all things being equal. elsewhere.
Le document
L'invention concerne un compresseur axial de turbomachine équipé d'un dispositif de prélèvement centripète d'air dans la veine dudit compresseur, cet air étant destiné au refroidissement de la turbine, ledit compresseur comportant deux couronnes d'aubes mobiles qui s'étendent radialement vers l'extérieur à la périphérie de deux disques consécutifs assemblés par une virole extérieure munie de perçages et une couronne d'aubes redresseuses fixes disposée dans la veine entre lesdits deux couronnes d'aubes mobiles, lesdits perçages servant d'entrées d'air audit dispositif de prélèvement et débouchant dans une gorge annulaire prévue sous l'interstice séparant les plates-formes intérieures des aubes redresseuses de la jante du disque amont, ladite gorge communiquant avec ladite veine par ledit interstice, caractérisé en ce que ladite gorge annulaire dans laquelle débouchent lesdits perçages se situe entre la couronne d'aubes mobiles la plus en amont et la couronne d'aubes redresseuses et en ce que des moyens de guidage fixes imprimant au flux d'air circulant dans ladite gorge un mouvement tourbillonnaire centripète dans le sens de rotation du compresseur sont disposés au moins en partie sous lesdites plates-formes intérieures des aubes redresseuses et sont solidaires de celles-ci, pour diminuer la vitesse relative de l'air entrant dans lesdits perçages par rapport à ces perçages en rotation.The invention relates to a turbomachine axial compressor equipped with a centripetal air sampling device in the vein of said compressor, this air being intended for the cooling of the turbine, said compressor comprising two blades of mobile blades which extend radially. outwardly at the periphery of two consecutive disks assembled by an outer shell provided with bores and a ring of stationary straightening vanes disposed in the vein between said two rotor blades, said bores serving as air inlets to said sampling device and opening into an annular groove provided under the gap between the inner platforms of the straightening vanes of the rim of the upstream disk, said groove communicating with said vein through said interstice, characterized in that said annular groove in which open said holes are located between the most upstream blade crown and the crown of rectifying blades and in that fixed guiding means imparting to the flow of air flowing in said groove a centripetal swirling motion in the direction of rotation of the compressor are arranged at least partly under said inner platforms of the straightening vanes and are integral with these, to reduce the relative speed of the air entering said holes relative to these rotating holes.
Il en résulte que la température totale relative de l'air dans les perçages est sensiblement abaissée par rapport à la même température dans un compresseur traditionnel, ce qui améliore le refroidissement des aubes de turbine pour un même débit, et augmente leur durée de vie.As a result, the relative total temperature of the air in the bores is substantially lowered compared to the same temperature in a conventional compressor, which improves the cooling of the turbine blades for the same flow, and increases their service life.
Les pertes de charge sont également diminuées, ce qui améliore le débit d'air prélevé par rapport à l'état de la technique, pour des perçages et dispositifs de prélèvement identiques et augmente le taux de surpression dans les aubes de la turbine.The pressure losses are also reduced, which improves the flow of air taken compared to the state of the art for identical bores and sampling devices and increases the rate of overpressure in the vanes of the turbine.
L'ensemble des deux améliorations obtenues grâce à l'invention, permet de diminuer le débit d'air nécessaire pour le refroidissement des aubes de la turbine, et par le fait même la consommation spécifique de carburant, pour une même durée de vie des aubages de la turbine à refroidir.The combination of the two improvements obtained by virtue of the invention makes it possible to reduce the air flow required for cooling the vanes of the turbine, and consequently the specific fuel consumption, for the same service life of the vanes. of the turbine to cool.
Lesdits moyens de guidage sont disposés au moins en partie sous les plates-formes intérieures des aubes redresseuses.Said guide means are arranged at least partly under the inner platforms of the straightening vanes.
Avantageusement les moyens de guidage de l'air dans la gorge comportent une pluralité de profils d'aubage régulièrement répartis autour de l'axe de rotation du compresseur.Advantageously, the means for guiding the air in the groove comprise a plurality of blade profiles evenly distributed around the axis of rotation of the compressor.
De préférence, les bords d'attaque des profils d'aubage s'étendent au moins en partie dans l'interstice.Preferably, the leading edges of the blading profiles extend at least partly in the gap.
L'angle d'attaque des profils est déterminé en fonction de la vitesse tangentielle et de la vitesse radiale locale de l'air passant par l'interstice.The angle of attack of the profiles is determined according to the tangential velocity and the local radial velocity of the air passing through the gap.
Ceci permet de ne pas modifier la norme de la vitesse de l'air dans la gorge et par le fait même de ne pas modifier la pression statique.This makes it possible not to modify the norm of the speed of the air in the groove and thus not to modify the static pressure.
Les profils d'aubage augmente le coefficient d'entraînement de l'air dans la gorge, ce qui permet pour la même température totale de l'air, d'en diminuer la température totale relative.The blade profiles increase the coefficient of air entrainment in the groove, which allows for the same total air temperature, to decrease the relative total temperature.
L'amélioration du coefficient d'entraînement grâce aux profils d'aubage proposés est de 30 % environ par rapport à l'état de la technique, ce qui correspond à une diminution de la température totale relative de 40°C environ. Ceci permet de multiplier la durée de vie des aubes de la turbine par deux, pour le même débit prélevé.The improvement of the drive coefficient thanks to the proposed blade profiles is about 30% compared to the state of the art, which corresponds to a decrease in the relative total temperature of approximately 40 ° C. This makes it possible to multiply the life of the blades of the turbine by two, for the same flow taken.
D'autres avantages et caractéristiques de l'invention ressortiront à la lecture de la description suivante faite à titre d'exemple et en référence aux dessins annexés dans lesquels :
- la
figure 1 est une demi-vue axiale d'un compresseur de turbomachine équipé d'un dispositif de prélèvement d'air centripète, selon l'art antérieur, - la
figure 2 est une demi-vue axiale d'un compresseur de turbomachine selon l'invention équipé du même dispositif de prélèvement d'air centripète, - la
figure 3 montre le diagramme des vitesses de l'air près des perçages en l'absence de moyens de guidage de l'air, - la
figure 4 montre le diagramme des vitesses de l'air près des perçages obtenues grâce aux moyens de guidage de l'air selon l'invention, - la
figure 5 est une vue axiale des profils de guidage de l'air dans la gorge, et - la
figure 6 est une vue en perspective de l'avant des plates-formes des aubes redresseuses équipées de profils de guidage selon l'invention.
- the
figure 1 is an axial half-view of a turbomachine compressor equipped with a centripetal air sampling device, according to the prior art, - the
figure 2 is an axial half-view of a turbomachine compressor according to the invention equipped with the same device for extracting centripetal air, - the
figure 3 shows the air velocity diagram near the holes in the absence of air guiding means, - the
figure 4 shows the diagram of the velocities of the air near the holes obtained thanks to the means of guiding the air according to the invention, - the
figure 5 is an axial view of the air guide profiles in the throat, and - the
figure 6 is a perspective view of the front of the platforms of the straightening vanes equipped with guide profiles according to the invention.
La
Ce compresseur 1 comporte un disque amont 3 ayant à sa périphérie une première couronne d'aubes mobiles 4 disposée dans la veine 5, un disque aval 6 présentant à sa périphérie une deuxième couronne d'aubes mobiles 7 décalée axialement dans la veine 5, et une couronne d'aubes redresseuses 8 fixes disposée dans la veine 5 entre la première et la deuxième couronne d'aubes mobiles.This
Le disque amont 3 et le disque aval 6 sont reliés entre eux par une virole extérieure 9 munie d'un labyrinthe d'étanchéité 10 coopérant avec la face intérieure des plates-formes intérieures 11 des aubes redresseuses 8. Une gorge 12 est ménagée sous l'interstice 13 qui sépare la jante du disque amont 3, des plates-formes intérieures 11. Des perçages 14 ménagés dans la virole extérieure 9 débouchent dans la gorge 12. Ces perçages 14 permettent l'introduction d'un débit d'air de prélèvement dans le dispositif de prélèvement centripète 2 qui dans l'exemple montré sur la
Le diagramme des vitesses de la
La
A la sortie de ces moyens, l'air a une vitesse absolue Va2 dont la norme est égale à la norme de la vitesse absolue Va1, mais qui est sensiblement dirigée tangentiellement à la périphérie de la virole externe 9, afin que la vitesse relative Vr2 de l'air par rapport au disque amont 3 soit nettement inférieure à la vitesse relative Vr1 de l'état de la technique, ainsi que cela est montré sur la
Ainsi que cela est montré sur les
Ces moyens de guidage 20 comportent une pluralité de profils d'aubage 21 ou ailettes régulièrement répartis autour de l'axe de rotation X du compresseur 1 et dont les bords d'attaque 22 s'étendent au moins en partie dans l'interstice 13. L'angle d'attaque α de ces profils 21 est déterminé en fonction de la vitesse tangentielle et de la vitesse radiale locale de l'air passant par l'interstice 13.These guide means 20 comprise a plurality of
Les profils d'aubage 21 sont dessinés de telle manière que l'air entrant par l'interstice 13 et s'écoulant entre les profils d'aubage 21 en ressort avec une vitesse Va2, représentée par une flèche ou vecteur sur les
Claims (6)
- An axial compressor for a turbomachine, the compressor being fitted with a device (2) for centripetally bleeding turbine-cooling air from a stream (5) of air flowing through said compressor, said compressor comprising two rings of moving blades (4, 7) extending radially outwards from the peripheries of two consecutive disks (3, 6) joined together by an outer shroud (9) having holes (14), and further comprising a ring of fixed stator vanes (8) placed in the stream (5) between said two rings of moving blades, said holes serving as air inlets to said bleed device and opening out into an annular groove (12) provided beneath the interstice (13) separating the inner platforms (11) of the stator vanes (8) from the rim of the upstream disk, said groove communicating with said stream via said interstice, the compressor being characterised in that said annular groove (12) into which said holes (14) open out is located between the ring of moving blades (4) that is in the most upstream position and the ring of stator vanes (8) and in that fixed guide means (20) imparting centripetal swirling motion on the air flowing in said groove (12) with the motion rotating in the same direction as the compressor, are disposed at least in part beneath the inner platforms (11) of the stator vanes and are fixed thereto, so as to reduce the velocity of the air entering into the holes (14) relative to said rotating holes.
- A compressor according to claim 1, characterised by the fact that said air guide means in the groove comprise a plurality of guide profiles (21) regularly distributed around the axis of rotation (X) of said compressor and fixed to said inner platforms (11) by projecting from beneath them.
- A compressor according to claim 2, characterised by the fact that the leading edges (22) of the guide profiles (21) extend at least in part into the interstice (13).
- A compressor according to claim 3, characterised by the fact that the angle of incidence (α) of the profiles is determined as a function of the local tangential velocity and radial velocity of the air passing through the interstice.
- A compressor according to any one of claims 1 to 4, characterised by the fact that the bleed device (20) comprises bleed channels (15) formed in the upstream disk (3).
- A turbomachine including a compressor according to one of claims 1 to 5.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0200519 | 2002-01-17 | ||
| FR0200519A FR2834758B1 (en) | 2002-01-17 | 2002-01-17 | DEVICE FOR STRAIGHTENING THE SUPPLY AIR OF A CENTRIPETE SAMPLING IN A COMPRESSOR |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1329639A1 EP1329639A1 (en) | 2003-07-23 |
| EP1329639B1 true EP1329639B1 (en) | 2008-03-12 |
Family
ID=8871319
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP03290061A Expired - Lifetime EP1329639B1 (en) | 2002-01-17 | 2003-01-10 | Centripetal air bleed device |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US6908278B2 (en) |
| EP (1) | EP1329639B1 (en) |
| CA (1) | CA2416157C (en) |
| DE (1) | DE60319607T2 (en) |
| FR (1) | FR2834758B1 (en) |
| RU (1) | RU2295656C2 (en) |
Families Citing this family (13)
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|---|---|---|---|---|
| US7686576B2 (en) * | 2006-10-24 | 2010-03-30 | General Electric Company | Method and apparatus for assembling gas turbine engines |
| US7661924B2 (en) * | 2007-03-28 | 2010-02-16 | General Electric Company | Method and apparatus for assembling turbine engines |
| RU2451840C2 (en) * | 2010-06-21 | 2012-05-27 | Открытое акционерное общество "Авиадвигатель" | Compressor rotor of gas-turbine engine |
| DE102010063071A1 (en) | 2010-12-14 | 2012-06-14 | Rolls-Royce Deutschland Ltd & Co Kg | Cooling device for a jet engine |
| US20130177430A1 (en) * | 2012-01-05 | 2013-07-11 | General Electric Company | System and method for reducing stress in a rotor |
| US9121413B2 (en) * | 2012-03-22 | 2015-09-01 | General Electric Company | Variable length compressor rotor pumping vanes |
| US9091173B2 (en) * | 2012-05-31 | 2015-07-28 | United Technologies Corporation | Turbine coolant supply system |
| US9039357B2 (en) * | 2013-01-23 | 2015-05-26 | Siemens Aktiengesellschaft | Seal assembly including grooves in a radially outwardly facing side of a platform in a gas turbine engine |
| CN109209980B (en) * | 2017-06-30 | 2020-06-05 | 中国航发商用航空发动机有限责任公司 | Guide plate for axial flow compressor |
| RU189794U1 (en) * | 2017-08-29 | 2019-06-04 | Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") | ROTOR COMPRESSOR GAS TURBINE ENGINE |
| RU2728550C1 (en) * | 2019-09-05 | 2020-07-31 | Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") | Air bleeder in rotor of turbojet compressor |
| WO2022066471A1 (en) | 2020-09-22 | 2022-03-31 | General Electric Company | Turbomachine and system for compressor operation |
| CN113006880B (en) * | 2021-03-29 | 2022-02-22 | 南京航空航天大学 | Cooling device for end wall of turbine blade |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2618433A (en) * | 1948-06-23 | 1952-11-18 | Curtiss Wright Corp | Means for bleeding air from compressors |
| GB712051A (en) * | 1951-10-10 | 1954-07-14 | Rolls Royce | Improvements in or relating to axial-flow fluid machines |
| US3085400A (en) * | 1959-03-23 | 1963-04-16 | Gen Electric | Cooling fluid impeller for elastic fluid turbines |
| FR2609500B1 (en) | 1987-01-14 | 1991-04-12 | Snecma | TURBOMACHINE COMPRESSOR DISC WITH CENTRIPTIC ACCELERATOR FOR SUCTION OF TURBINE COOLING AIR |
| FR2614654B1 (en) | 1987-04-29 | 1992-02-21 | Snecma | TURBOMACHINE AXIAL COMPRESSOR DISC WITH CENTRIPTED AIR TAKE-OFF |
| US5475313A (en) | 1994-09-20 | 1995-12-12 | Dykes; Wallace E. | Primary charge roller evaluator |
-
2002
- 2002-01-17 FR FR0200519A patent/FR2834758B1/en not_active Expired - Fee Related
-
2003
- 2003-01-10 EP EP03290061A patent/EP1329639B1/en not_active Expired - Lifetime
- 2003-01-10 DE DE60319607T patent/DE60319607T2/en not_active Expired - Lifetime
- 2003-01-15 CA CA2416157A patent/CA2416157C/en not_active Expired - Lifetime
- 2003-01-16 US US10/345,184 patent/US6908278B2/en not_active Expired - Lifetime
- 2003-01-17 RU RU2003102223/06A patent/RU2295656C2/en active
Also Published As
| Publication number | Publication date |
|---|---|
| US6908278B2 (en) | 2005-06-21 |
| US20030133787A1 (en) | 2003-07-17 |
| CA2416157C (en) | 2011-05-17 |
| CA2416157A1 (en) | 2003-07-17 |
| EP1329639A1 (en) | 2003-07-23 |
| DE60319607D1 (en) | 2008-04-24 |
| FR2834758B1 (en) | 2004-04-02 |
| FR2834758A1 (en) | 2003-07-18 |
| DE60319607T2 (en) | 2009-04-02 |
| RU2295656C2 (en) | 2007-03-20 |
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