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EP1251243A1 - Turbine blade with cooling air baffle - Google Patents

Turbine blade with cooling air baffle Download PDF

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Publication number
EP1251243A1
EP1251243A1 EP02290964A EP02290964A EP1251243A1 EP 1251243 A1 EP1251243 A1 EP 1251243A1 EP 02290964 A EP02290964 A EP 02290964A EP 02290964 A EP02290964 A EP 02290964A EP 1251243 A1 EP1251243 A1 EP 1251243A1
Authority
EP
European Patent Office
Prior art keywords
blade
air
deflector
turbine
cell
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
EP02290964A
Other languages
German (de)
French (fr)
Other versions
EP1251243B8 (en
EP1251243B1 (en
Inventor
Morgan Lionel Balland
Sylvie Coulon
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
SNECMA Moteurs SA
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Publication date
Application filed by SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1251243A1 publication Critical patent/EP1251243A1/en
Application granted granted Critical
Publication of EP1251243B1 publication Critical patent/EP1251243B1/en
Publication of EP1251243B8 publication Critical patent/EP1251243B8/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • the present invention relates to a dawn for turbine, the blade being attached to a disc of the turbine and being cooled by a circulation internal air.
  • An axial turbine stage is composed a grid of fixed vanes called distributor and a grid of movable blades called a wheel. It exists monobloc wheels where blades and disc form a unique piece. There are also impellers reported where blades and disc are assembled mechanically, usually by fir tree feet.
  • Figure 1A is a partial view of a blade 1 mounted on a disc 2, the view being represented in a plane perpendicular to the axis of the turbine. It shows more precisely the foot 3 of dawn 1 in position in a cell 4 of the disc 2. The foot is shown in section along the axis of a channel 5 bringing air cooling from the bottom of cell 4 to the internal cooling circuit and not depicted from dawn.
  • the cooling air circulates in cell 4 in a direction perpendicular to the plan of the figure.
  • the air is introduced by one end of the cell, corresponding to a face of the disc called the upstream face, and goes up in channel (or channels) 5, the other end of the socket, corresponding to the other face of the disc or downstream face, being closed.
  • the cooling air taken from the compressor output is injected through a flange pressed against the upstream face of the disc to seal the air circuit.
  • the flange is often held on the disc by a hook system called dogs.
  • the hooks also provide another function. They give the cooling air directing towards the alveoli a speed of rotation equal to that of the turbine rotor. Looks like cooling then arrives in front of the cell in turning at the same speed as it and entering inside the socket without side effects.
  • WO-A-99 47792 discloses a dawn for turbine, the blade having a foot allowing bring it back into a cell of a disk of the turbine.
  • Dawn has an internal circuit of air cooling comprising inlet means of air located at the foot of dawn and opposite the cell, and air outlet means.
  • the foot of dawn is provided with a device for channel the dawn cooling air. This device also allows the evacuation of air from cooling after passing inside dawn. The device ensures the separation of the circuits cooling air entering and leaving dawn from dawn.
  • GB-A-1 605 282 discloses a blade for turbine, the blade having a foot allowing to bring it back in a cell of a disc of the turbine.
  • Dawn has an internal circuit of air cooling constituted by channels, comprising air intake means located on the foot of dawn and facing the cell, and means of air outlet located at the blade tip.
  • the foot of the blade is provided with a cooling tube allowing the cooling air to be brought in from the suction air manifold to the air inlets.
  • US-A-4,348,157 discloses a dawn for turbine, attached to a disc by means of a foot.
  • Dawn has an internal circuit of air-cooled including an inlet air.
  • the air inlet port is not located on the at the foot of dawn and opposite the receiving cell of this foot but in the connecting part between the foot and dawn, that is to say in the leg.
  • Passages are provided to supply cooling air up to the air intakes of the blades. These passages can include deflectors.
  • US-A-4,178,129 discloses a system cooling of turbine blades by circulation air. Each blade has a foot allowing the return to a cell of a turbine disc. The blade has an internal cooling circuit by air comprising air inlet means located on the foot of dawn. Cooling air is sent either in an air supply chamber of cooling in which the channels of cooling, either directly in the edge channel attack through a Pitot receiver.
  • the incoming cooling air is supplied by a tube-shaped device communicating with the orifices of the cooling channels.
  • the device tube-shaped can have size holes suitable for channel orifice openings practically corresponding to the width of the cell. In both cases, the formation of a whirlwind.
  • an air cooling tube is provided adapted to the width of the cell. So we cannot avoid the formation of a vortex.
  • Figure 1B illustrates the phenomenon causing a loss of effectiveness of the blade cooling.
  • This figure is a view of the underside of foot 3 and bearing the reference 6 in Figure 1A.
  • Channel (or channels) 5 has not been pictured.
  • the flange pressed against the upstream face of the disc is shown under the reference 7.
  • Under the reference 8 has been shown a sealing flange of the alveolus, downstream side of the disc.
  • the present invention overcomes this problem whenever it arises in a turbine.
  • a turbine blade the dawn presenting a foot allowing to bring it back in a cavity of a turbine disc, the dawn having an internal air cooling circuit comprising air inlet means located on a facing the foot of the dawn and facing said cell, and air outlet means, characterized in that said face of the foot of dawn is equipped with a deflector comprising at least one fin allowing channel the cooling air circulating in the bottom of the cell to regulate the air flow towards the air intake means.
  • the deflector can be an integral part from dawn.
  • the deflector can be an added element at the foot of dawn and provided with means of access to air intake means.
  • the means of access can include at least one calibrated hole.
  • the fin can be straight or tilted by relation to the general axis of dawn.
  • the deflector includes at least one fin allowing to channel the cooling air entering the socket and at least one fin allowing channel exhaust air to the center of the cell.
  • Figure 2A is a view of a blade 11 according to the invention and mounted on a disc 12, the view being represented in a plane perpendicular to the axis of the turbine as in FIG. 1A.
  • Foot 13 of the blade 11 is in position in a cell 14 of the disc 12.
  • the foot is shown in section along the axis of a channel 15 bringing the cooling air from the bottom of cell 14 to the cooling circuit internal and not shown from dawn.
  • the circulation of the air in the socket is made as described previously for Figure 1A.
  • the blade of Figure 2A is equipped with a deflector 20 secured to the underside 16 of the dawn foot.
  • the deflector 20 has fins to channel the cooling air circulating in the bottom of the cell 14.
  • FIG. 2A shows that the deflector has a hole 18 in correspondence with channel 15 and serving as means access to the cooling air channel. This hole can be a calibrated hole whose realization is easy to be obtained on a part such as a deflector reported.
  • FIG 2B corresponding to Figure 1B for the prior art, shows by arrows from which way is channeled the cooling air at the bottom of the socket, between the flanges 17 and 18 of the disc 12.
  • the deflector is equipped with two fins 22 and 23 located on either side of the axis for aligning the holes 21.
  • the fins are arranged so as to form a baffle species.
  • the deflector shown has four holes for the passage of air from cooling.
  • the deflector can be an insert by welding or soldering on the blade root. Alternatively, the deflector can be an integral part of the dawn.
  • Figure 3 is a perspective view of the deflector 20 mentioned previously. This figure allows to better see the fins 22 and 23 as well as the holes 21.
  • Figure 4 is a partial sectional view a turbine equipped with a blade according to the invention.
  • the Figure 4 shows a blade 11 equipped with a deflector 20 and mounted in a cell 14 of the disk 12. This figure also shows the flange 17 plated against the upstream face of the disc 12 and the flange 18 obturation of the alveolus.
  • the cooling air is taken in chamber background and accelerated through a series injectors such as injector 31. This air passes then through holes, such as hole 32, drilled on the flange 17 and goes up towards the bottoms of the alveoli as indicated by arrows on the Figure 4.
  • holes such as hole 32, drilled on the flange 17 and goes up towards the bottoms of the alveoli as indicated by arrows on the Figure 4.
  • the hooks or dogs that the invention allows remove In dashed lines, the hooks or dogs that the invention allows remove.
  • Figures 5 and 6 show, in position on the underside of a blade root, others forms of deflectors usable by the present invention.
  • the deflector 40 comprises two fins 41 and 42 present over the entire length of the deflector. Holes 43 for access to the canals of blades are also shown.
  • the deflector 50 comprises a first series of fins 51 and 53, located in a side of the deflector, and a second series of fins 52 and 54, located on the other side of the deflector.
  • the fins are arranged to form baffles. of the 55 access holes to the blade channels are also represented.
  • the deflector may also include one or more several fins of curved shape and allowing a cooling air guidance along a path more scalable.
  • Figures 7 to 10 give, by way of examples, other forms of deflectors that can be used by the present invention. All of these views are cross-sectional representations made according to a cooling air passage hole.
  • the deflector 60 of FIG. 7 is in rail shape. It has fins 61 and 62 arranged at right angles to the bearing face 63 of the deflector on the blade root.
  • the fins 61 and 62 can run the entire length of the deflector or be interrupted to form baffles.
  • the deflector 70 has fins 71 and 72 which are flared relative to the bearing face 73 of the deflector on the blade root.
  • Deflector 80 has fins 81 and 82 which extend closer to the bearing face 83 of the deflector on the blade root.
  • the deflector 90 includes four parallel fins 91, 92, 93 and 94 arranged at right angles to the bearing face 95 of the deflector on the blade root.
  • the invention provides a gain of static pressure in the center of the cell which fills in approximately 75% of the existing pressure drop without the arrangement made. This improvement in cooling air supply to the blade reduces the average dawn temperature according to the operating conditions and to increase consequently its lifespan.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The turbine blade (11), made with a root (13) that fits into a socket (14) of a disc (12) with internal air cooling, has a deflector (20) on the blade root comprising one or more fins to channel the air circulating in the lower part of the socket to regulate the air flow towards the intake (15). The deflector can be made as part of the blade, or a separate component attached to the root of the blade and having an access port (21) for the air intake in the form of a calibrated hole. The deflector fins can lie perpendicular or at an oblique angle to the general axis of the blade.

Description

Domaine techniqueTechnical area

La présente invention concerne une aube pour turbine, l'aube étant rapportée sur un disque de la turbine et étant refroidie par une circulation interne d'air.The present invention relates to a dawn for turbine, the blade being attached to a disc of the turbine and being cooled by a circulation internal air.

Etat de la technique antérieureState of the art

Un étage de turbine axiale est composé d'une grille d'aubes fixes appelée distributeur et d'une grille d'aubes mobiles appelée roue. Il existe des roues monoblocs où aubes et disque forment une pièce unique. Il existe aussi des roues à aubes rapportées où aubes et disque sont assemblés mécaniquement, généralement par pieds de sapin.An axial turbine stage is composed a grid of fixed vanes called distributor and a grid of movable blades called a wheel. It exists monobloc wheels where blades and disc form a unique piece. There are also impellers reported where blades and disc are assembled mechanically, usually by fir tree feet.

Lorsque les roues fonctionnent sous une température élevée, il est nécessaire de refroidir les aubes. Ce refroidissement peut être effectué par de l'air prélevé par exemple à la sortie du compresseur et acheminé à l'intérieur des aubes à travers leur fixation au disque. L'air de refroidissement pénètre par le pied d'une aube pour ressortir par exemple par l'extrémité opposée et par l'une de ses faces.When the wheels are operating under a high temperature, it is necessary to cool the blades. This cooling can be done by the air taken for example from the compressor outlet and routed inside the vanes through their attachment to disc. Cooling air enters by the foot of a dawn to stand out for example by the opposite end and by one of its faces.

La figure 1A est une vue partielle d'une aube 1 montée sur un disque 2, la vue étant représentée dans un plan perpendiculaire à l'axe de la turbine. Elle montre plus précisément le pied 3 de l'aube 1 en position dans une alvéole 4 du disque 2. Le pied est montré en coupe selon l'axe d'un canal 5 amenant l'air de refroidissement depuis le fond de l'alvéole 4 jusqu'au circuit de refroidissement interne et non représenté de l'aube. L'air de refroidissement circule dans l'alvéole 4 dans une direction perpendiculaire au plan de la figure. Dans l'exemple représenté, l'air est introduit par une extrémité de l'alvéole, correspondant à une face du disque dite face amont, et remonte dans le canal (ou les canaux) 5, l'autre extrémité de l'alvéole, correspondant à l'autre face du disque ou face aval, étant obturée.Figure 1A is a partial view of a blade 1 mounted on a disc 2, the view being represented in a plane perpendicular to the axis of the turbine. It shows more precisely the foot 3 of dawn 1 in position in a cell 4 of the disc 2. The foot is shown in section along the axis of a channel 5 bringing air cooling from the bottom of cell 4 to the internal cooling circuit and not depicted from dawn. The cooling air circulates in cell 4 in a direction perpendicular to the plan of the figure. In the example shown, the air is introduced by one end of the cell, corresponding to a face of the disc called the upstream face, and goes up in channel (or channels) 5, the other end of the socket, corresponding to the other face of the disc or downstream face, being closed.

L'air de refroidissement prélevé à la sortie du compresseur est injecté au travers d'un flasque plaqué contre la face amont du disque pour assurer l'étanchéité du circuit d'air. Pour ce faire, le flasque est souvent maintenu sur le disque par un système de crochets appelés crabots.The cooling air taken from the compressor output is injected through a flange pressed against the upstream face of the disc to seal the air circuit. To do this, the flange is often held on the disc by a hook system called dogs.

Les crochets assurent également une autre fonction. Ils donnent à l'air de refroidissement se dirigeant vers les alvéoles une vitesse de rotation égale à celle du rotor de la turbine. L'air de refroidissement arrive alors devant l'alvéole en tournant à la même vitesse qu'elle et entre à l'intérieur de l'alvéole sans effets secondaires.The hooks also provide another function. They give the cooling air directing towards the alveoli a speed of rotation equal to that of the turbine rotor. Looks like cooling then arrives in front of the cell in turning at the same speed as it and entering inside the socket without side effects.

Ces crochets ont cependant l'inconvénient d'être coûteux et d'avoir une relativement faible durée de vie. Il serait donc intéressant de pouvoir les supprimer. Cependant, des essais ont montré que le refroidissement des aubes de turbines est moins assuré lorsque ces crochets sont supprimés. However, these hooks have the disadvantage to be expensive and to have a relatively short duration of life. It would therefore be interesting to be able to remove. However, tests have shown that the less cooling of the turbine blades when these square brackets are removed.

Le document WO-A-99 47792 divulgue une aube pour turbine, l'aube présentant un pied permettant de la rapporter dans une alvéole d'un disque de la turbine. L'aube possède un circuit interne de refroidissement par air comprenant des moyens d'entrée d'air situés sur le pied de l'aube et en regard de l'alvéole, et des moyens de sortie d'air. Le pied de l'aube est pourvu d'un dispositif permettant de canaliser l'air de refroidissement de l'aube. Ce dispositif permet également l'évacuation de l'air de refroidissement après son passage à l'intérieur de l'aube. Le dispositif assure la séparation des circuits d'air de refroidissement entrant dans l'aube et sortant de l'aube.WO-A-99 47792 discloses a dawn for turbine, the blade having a foot allowing bring it back into a cell of a disk of the turbine. Dawn has an internal circuit of air cooling comprising inlet means of air located at the foot of dawn and opposite the cell, and air outlet means. The foot of dawn is provided with a device for channel the dawn cooling air. This device also allows the evacuation of air from cooling after passing inside dawn. The device ensures the separation of the circuits cooling air entering and leaving dawn from dawn.

Le document GB-A-1 605 282 divulgue une aube pour turbine, l'aube présentant un pied permettant de la rapporter dans une alvéole d'un disque de la turbine. L'aube possède un circuit interne de refroidissement par air constitué par des canaux, comprenant des moyens d'entrée d'air situés sur le pied de l'aube et en regard de l'alvéole, et des moyens de sortie d'air situés en extrémité d'aube. Le pied de l'aube est pourvu d'un tube de refroidissement permettant d'amener l'air de refroidissement depuis le collecteur d'air d'aspiration jusqu'aux entrées d'air.GB-A-1 605 282 discloses a blade for turbine, the blade having a foot allowing to bring it back in a cell of a disc of the turbine. Dawn has an internal circuit of air cooling constituted by channels, comprising air intake means located on the foot of dawn and facing the cell, and means of air outlet located at the blade tip. The foot of the blade is provided with a cooling tube allowing the cooling air to be brought in from the suction air manifold to the air inlets.

Le document US-A-4 348 157 divulgue une aube pour turbine, rapportée sur un disque au moyen d'un pied. L'aube possède un circuit interne de refroidissement par air comprenant un orifice d'entrée d'air. L'orifice d'entrée d'air n'est pas situé sur le pied de l'aube et en regard de l'alvéole de réception de ce pied mais dans la partie de liaison entre le pied et l'aube, c'est-à-dire dans la jambe. Des passages sont prévus pour amener l'air de refroidissement jusqu'aux entrées d'air des aubes. Ces passages peuvent comprendre des déflecteurs.US-A-4,348,157 discloses a dawn for turbine, attached to a disc by means of a foot. Dawn has an internal circuit of air-cooled including an inlet air. The air inlet port is not located on the at the foot of dawn and opposite the receiving cell of this foot but in the connecting part between the foot and dawn, that is to say in the leg. Passages are provided to supply cooling air up to the air intakes of the blades. These passages can include deflectors.

Le document US-A-4 178 129 divulgue un système de refroidissement d'aubes de turbine par circulation d'air. Chaque aube présente un pied permettant de la rapporter dans une alvéole d'un disque de la turbine. L'aube possède un circuit interne de refroidissement par air comprenant des moyens d'entrée d'air situés sur le pied de l'aube. L'air de refroidissement est envoyé soit dans une chambre d'alimentation en air de refroidissement dans laquelle débouche les canaux de refroidissement, soit directement dans le canal de bord d'attaque par l'intermédiaire d'un receveur de Pitot.US-A-4,178,129 discloses a system cooling of turbine blades by circulation air. Each blade has a foot allowing the return to a cell of a turbine disc. The blade has an internal cooling circuit by air comprising air inlet means located on the foot of dawn. Cooling air is sent either in an air supply chamber of cooling in which the channels of cooling, either directly in the edge channel attack through a Pitot receiver.

Concernant le document WO-A-99 47792 cité ci-dessus, l'air de refroidissement arrivant est amené par un dispositif en forme de tube communiquant avec les orifices des canaux de refroidissement. Le dispositif en forme de tube peut avoir des orifices de taille adaptée aux orifices des canaux ou des orifices correspondant pratiquement à la largeur de l'alvéole. Dans les deux cas, on ne peut éviter la formation d'un tourbillon.Regarding document WO-A-99 47792 cited above, the incoming cooling air is supplied by a tube-shaped device communicating with the orifices of the cooling channels. The device tube-shaped can have size holes suitable for channel orifice openings practically corresponding to the width of the cell. In both cases, the formation of a whirlwind.

Concernant le document GB-A-1 605 282 cité ci-dessus, il est prévu un tube de refroidissement d'air adapté à la largeur de l'alvéole. On ne peut donc éviter la formation d'un tourbillon. Concerning the document GB-A-1 605 282 cited above, an air cooling tube is provided adapted to the width of the cell. So we cannot avoid the formation of a vortex.

Concernant le document US-A-4 348 157 cité ci-dessus, l'air arrive directement sur une face percée d'un trou, ce qui conduit à la même conclusion.Concerning the document US-A-4 348 157 cited above, the air arrives directly on a pierced face of a hole, which leads to the same conclusion.

Concernant le document US-A-4 178 129 cité ci-dessus, l'air arrive soit directement dans un trou (par un receveur de Pitot), soit directement sur une face percée de trous, ce qui conduit à la même conclusion.Regarding document US-A-4,178,129 cited above, the air arrives either directly in a hole (by a Pitot receiver), either directly on one side pierced with holes, which leads to the same conclusion.

Exposé de l'inventionStatement of the invention

Il revient aux inventeurs de la présente invention d'avoir découvert la raison d'une moins grande efficacité du refroidissement lorsque les crochets ou crabots sont supprimés et d'avoir apporté une solution à ce problème.It is up to the inventors of this invention to have discovered the reason for a less high cooling efficiency when hooks or dogs are removed and to have brought a solution to this problem.

La figure 1B permet d'illustrer le phénomène provoquant une perte d'efficacité du refroidissement des aubes. Cette figure est une vue de la face inférieure du pied 3 et portant la référence 6 sur la figure 1A. Le canal (ou les canaux) 5 n'a pas été représenté. Le flasque plaqué contre la face amont du disque est figuré sous la référence 7. Sous la référence 8 a été figuré un flasque d'obturation de l'alvéole, côté face aval du disque.Figure 1B illustrates the phenomenon causing a loss of effectiveness of the blade cooling. This figure is a view of the underside of foot 3 and bearing the reference 6 in Figure 1A. Channel (or channels) 5 has not been pictured. The flange pressed against the upstream face of the disc is shown under the reference 7. Under the reference 8 has been shown a sealing flange of the alveolus, downstream side of the disc.

Les inventeurs sont arrivés à la conclusion que, quand l'air n'est plus guidé jusqu'à l'alvéole, l'air de refroidissement arrive dans l'alvéole avec une vitesse de rotation plus faible que lorsqu'il est guidé. L'air est alors écopé et tournoie dans l'alvéole en formant un tourbillon comme cela est figuré sur la figure 1B. Le centre de ce tourbillon (ou vortex) est un creux de pression très important qui est préjudiciable pour l'alimentation de l'aube en air de refroidissement.The inventors have come to the conclusion that when the air is no longer guided to the cell, the cooling air enters the cell with a lower rotational speed than when it is guided. The air is then scooped and swirls in the cell forming a vortex as shown on the Figure 1B. The center of this vortex (or vortex) is a very large pressure trough which is detrimental to the air supply of dawn to cooling.

La présente invention permet de remédier à ce problème chaque fois qu'il se présente dans une turbine.The present invention overcomes this problem whenever it arises in a turbine.

Elle a pour objet une aube pour turbine, l'aube présentant un pied permettant de la rapporter dans une alvéole d'un disque de la turbine, l'aube possédant un circuit interne de refroidissement par air comprenant des moyens d'entrée d'air situés sur une face du pied de l'aube et en regard de ladite alvéole, et des moyens de sortie d'air, caractérisée en ce que ladite face du pied de l'aube est équipée d'un déflecteur comportant au moins une ailette permettant de canaliser l'air de refroidissement circulant dans le fond de l'alvéole pour régulariser l'écoulement d'air vers les moyens d'entrée d'air.Its purpose is a turbine blade, the dawn presenting a foot allowing to bring it back in a cavity of a turbine disc, the dawn having an internal air cooling circuit comprising air inlet means located on a facing the foot of the dawn and facing said cell, and air outlet means, characterized in that said face of the foot of dawn is equipped with a deflector comprising at least one fin allowing channel the cooling air circulating in the bottom of the cell to regulate the air flow towards the air intake means.

La présence d'un tel déflecteur sur la face du pied de l'aube où sont situés les moyens d'entrée d'air permet d'éviter la formation d'un tourbillon.The presence of such a deflector on the face at the foot of dawn where the means of entry are located air prevents the formation of a vortex.

Le déflecteur peut faire partie intégrante de l'aube.The deflector can be an integral part from dawn.

Le déflecteur peut être un élément rapporté sur le pied de l'aube et pourvu de moyens d'accès aux moyens d'entrée d'air. Les moyens d'accès peuvent comprendre au moins un trou calibré.The deflector can be an added element at the foot of dawn and provided with means of access to air intake means. The means of access can include at least one calibrated hole.

L'ailette peut être droite ou inclinée par rapport à l'axe général de l'aube.The fin can be straight or tilted by relation to the general axis of dawn.

Selon un mode de réalisation avantageux, le déflecteur comprend au moins une ailette permettant de canaliser l'air de refroidissement pénétrant dans l'alvéole et au moins une ailette permettant de canaliser de l'air refoulé vers le centre de l'alvéole.According to an advantageous embodiment, the deflector includes at least one fin allowing to channel the cooling air entering the socket and at least one fin allowing channel exhaust air to the center of the cell.

Brève description des dessinsBrief description of the drawings

L'invention sera mieux comprise et d'autres avantages et particularités apparaítront à la lecture de la description qui va suivre, donnée à titre d'exemple non limitatif, accompagnée des dessins annexés parmi lesquels :

  • la figure 1A, déjà décrite, est une vue partielle d'une aube pour turbine, montée sur un disque, selon l'art connu,
  • la figure 1B, déjà décrite, est une vue de la face inférieure d'un pied d'aube pour turbine, selon l'art connu,
  • la figure 2A est une vue d'une aube pour turbine, montée sur un disque, selon l'invention,
  • la figure 2B est une vue de la face inférieure d'un pied d'aube pour turbine, selon l'invention,
  • la figure 3 est une vue en perspective d'un déflecteur utilisé par la présente invention,
  • la figure 4 est une vue partielle en coupe d'une turbine équipée d'une aube selon l'invention
  • les figures 5 et 6 sont des vues de dessous de déflecteurs utilisables par la présente invention,
  • les figures 7 à 10 sont des vues transversales et en coupe de différents déflecteurs utilisables par la présente invention.
The invention will be better understood and other advantages and features will appear on reading the description which follows, given by way of nonlimiting example, accompanied by the appended drawings among which:
  • FIG. 1A, already described, is a partial view of a turbine blade, mounted on a disc, according to known art,
  • FIG. 1B, already described, is a view of the underside of a blade root for a turbine, according to known art,
  • FIG. 2A is a view of a turbine blade, mounted on a disk, according to the invention,
  • FIG. 2B is a view of the underside of a blade root for a turbine, according to the invention,
  • FIG. 3 is a perspective view of a deflector used by the present invention,
  • Figure 4 is a partial sectional view of a turbine equipped with a blade according to the invention
  • FIGS. 5 and 6 are bottom views of deflectors usable by the present invention,
  • Figures 7 to 10 are cross-sectional views of different deflectors usable by the present invention.

Description détaillée de modes de réalisation de l'inventionDetailed description of embodiments of the invention

La figure 2A est une vue d'une aube 11 selon l'invention et montée sur un disque 12, la vue étant représentée dans un plan perpendiculaire à l'axe de la turbine comme pour la figure 1A. Le pied 13 de l'aube 11 est en position dans une alvéole 14 du disque 12. Le pied est montré en coupe selon l'axe d'un canal 15 amenant l'air de refroidissement depuis le fond de l'alvéole 14 jusqu'au circuit de refroidissement interne et non représenté de l'aube. La circulation de l'air dans l'alvéole se fait comme cela est décrit précédemment pour la figure 1A.Figure 2A is a view of a blade 11 according to the invention and mounted on a disc 12, the view being represented in a plane perpendicular to the axis of the turbine as in FIG. 1A. Foot 13 of the blade 11 is in position in a cell 14 of the disc 12. The foot is shown in section along the axis of a channel 15 bringing the cooling air from the bottom of cell 14 to the cooling circuit internal and not shown from dawn. The circulation of the air in the socket is made as described previously for Figure 1A.

A la différence de l'aube décrite dans la figure 1A, l'aube de la figure 2A est équipée d'un déflecteur 20 solidaire de la face inférieure 16 du pied d'aube. Le déflecteur 20 comporte des ailettes permettant de canaliser l'air de refroidissement circulant dans le fond de l'alvéole 14. La figure 2A montre que le déflecteur présente un trou 18 en correspondance avec le canal 15 et servant de moyens d'accès au canal pour l'air de refroidissement. Ce trou peut être un trou calibré dont la réalisation est aisée à obtenir sur une pièce telle qu'un déflecteur rapporté.Unlike the dawn described in the Figure 1A, the blade of Figure 2A is equipped with a deflector 20 secured to the underside 16 of the dawn foot. The deflector 20 has fins to channel the cooling air circulating in the bottom of the cell 14. FIG. 2A shows that the deflector has a hole 18 in correspondence with channel 15 and serving as means access to the cooling air channel. This hole can be a calibrated hole whose realization is easy to be obtained on a part such as a deflector reported.

La figure 2B, correspondant à la figure 1B pour l'art antérieur, montre par des flèches de quelle manière est canalisé l'air de refroidissement au fond de l'alvéole, entre les flasques 17 et 18 du disque 12. Sur cette figure, le déflecteur est équipé de deux ailettes 22 et 23 situées de part et d'autre de l'axe d'alignement des trous 21. Les ailettes sont agencées de façon à former une espèce de chicane. On peut remarquer également que le déflecteur représenté possède quatre trous pour le passage de l'air de refroidissement.Figure 2B, corresponding to Figure 1B for the prior art, shows by arrows from which way is channeled the cooling air at the bottom of the socket, between the flanges 17 and 18 of the disc 12. In this figure, the deflector is equipped with two fins 22 and 23 located on either side of the axis for aligning the holes 21. The fins are arranged so as to form a baffle species. We can also note that the deflector shown has four holes for the passage of air from cooling.

La présence d'un déflecteur en face inférieure du pied de l'aube permet d'éviter la formation d'un tourbillon et la manifestation d'un creux de pression.The presence of a deflector opposite lower of the dawn foot avoids the formation of a vortex and the manifestation of a pressure trough.

Le déflecteur peut être une pièce rapportée par soudage ou brasage sur le pied d'aube. En variante, le déflecteur peut faire partie intégrante de l'aube.The deflector can be an insert by welding or soldering on the blade root. Alternatively, the deflector can be an integral part of the dawn.

La figure 3 est une vue en perspective du déflecteur 20 mentionné précédemment. Cette figure permet de mieux voir les ailettes 22 et 23 ainsi que les trous 21.Figure 3 is a perspective view of the deflector 20 mentioned previously. This figure allows to better see the fins 22 and 23 as well as the holes 21.

La figure 4 est une vue partielle en coupe d'une turbine équipée d'une aube selon l'invention. La figure 4 montre une aube 11 équipée d'un déflecteur 20 et montée dans une alvéole 14 du disque 12. Cette figure permet de voir également le flasque 17 plaqué contre la face amont du disque 12 et le flasque 18 d'obturation de l'alvéole.Figure 4 is a partial sectional view a turbine equipped with a blade according to the invention. The Figure 4 shows a blade 11 equipped with a deflector 20 and mounted in a cell 14 of the disk 12. This figure also shows the flange 17 plated against the upstream face of the disc 12 and the flange 18 obturation of the alveolus.

L'air de refroidissement est prélevé en fond de chambre et accéléré à travers une série d'injecteurs tel que l'injecteur 31. Cet air passe ensuite au travers de trous, tels que le trou 32, percés sur le flasque 17 et remonte vers les fonds des alvéoles comme cela est indiqué par des flèches sur la figure 4. En traits interrompus, on a représenté les crochets ou crabots que l'invention permet de supprimer.The cooling air is taken in chamber background and accelerated through a series injectors such as injector 31. This air passes then through holes, such as hole 32, drilled on the flange 17 and goes up towards the bottoms of the alveoli as indicated by arrows on the Figure 4. In dashed lines, the hooks or dogs that the invention allows remove.

Les figures 5 et 6 montrent, en position sur la face inférieure d'un pied d'aube, d'autres formes de déflecteurs utilisables par la présente invention.Figures 5 and 6 show, in position on the underside of a blade root, others forms of deflectors usable by the present invention.

Sur la figure 5, le déflecteur 40 comporte deux ailettes 41 et 42 présentes sur toute la longueur du déflecteur. Des trous 43 d'accès aux canaux des aubes sont également représentés.In FIG. 5, the deflector 40 comprises two fins 41 and 42 present over the entire length of the deflector. Holes 43 for access to the canals of blades are also shown.

Sur la figure 6, le déflecteur 50 comporte une première série d'ailettes 51 et 53, situées d'un côté du déflecteur, et une deuxième série d'ailettes 52 et 54, situées de l'autre côté du déflecteur. Les ailettes sont agencées pour former des chicanes. Des trous 55 d'accès aux canaux des aubes sont également représentés.In FIG. 6, the deflector 50 comprises a first series of fins 51 and 53, located in a side of the deflector, and a second series of fins 52 and 54, located on the other side of the deflector. The fins are arranged to form baffles. of the 55 access holes to the blade channels are also represented.

Le déflecteur peut aussi comporter une ou plusieurs ailettes de forme incurvée et permettant un guidage de l'air de refroidissement selon un trajet plus évolutif.The deflector may also include one or more several fins of curved shape and allowing a cooling air guidance along a path more scalable.

Les figures 7 à 10 donnent, à titre d'exemples, d'autres formes de déflecteurs utilisables par la présente invention. Toutes ces vues sont des représentations en coupe transversale effectuée selon un trou de passage de l'air de refroidissement.Figures 7 to 10 give, by way of examples, other forms of deflectors that can be used by the present invention. All of these views are cross-sectional representations made according to a cooling air passage hole.

Le déflecteur 60 de la figure 7 est en forme de rail. Il comporte des ailettes 61 et 62 disposées à angle droit par rapport à la face d'appui 63 du déflecteur sur le pied d'aube. Les ailettes 61 et 62 peuvent courir toute la longueur du déflecteur ou être interrompues pour former des chicanes.The deflector 60 of FIG. 7 is in rail shape. It has fins 61 and 62 arranged at right angles to the bearing face 63 of the deflector on the blade root. The fins 61 and 62 can run the entire length of the deflector or be interrupted to form baffles.

Il en va de même pour les déflecteurs 70, 80 et 90 représentés respectivement aux figures 8, 9 et 10. Le déflecteur 70 comporte des ailettes 71 et 72 qui vont en s'évasant par rapport à la face d'appui 73 du déflecteur sur le pied d'aube. Le déflecteur 80 comporte des ailettes 81 et 82 qui vont en se rapprochant par rapport à la face d'appui 83 du déflecteur sur le pied d'aube. Le déflecteur 90 comprend quatre ailettes parallèles 91, 92, 93 et 94 disposées à angle droit par rapport à la face d'appui 95 du déflecteur sur le pied d'aube.The same goes for the deflectors 70, 80 and 90 shown respectively in Figures 8, 9 and 10. The deflector 70 has fins 71 and 72 which are flared relative to the bearing face 73 of the deflector on the blade root. Deflector 80 has fins 81 and 82 which extend closer to the bearing face 83 of the deflector on the blade root. The deflector 90 includes four parallel fins 91, 92, 93 and 94 arranged at right angles to the bearing face 95 of the deflector on the blade root.

L'invention permet d'obtenir un gain de pression statique au centre de l'alvéole qui comble à environ 75% le creux de pression existant sans l'aménagement apporté. Cette amélioration de l'alimentation de l'aube en air de refroidissement permet de réduire la température moyenne de l'aube suivant les conditions de fonctionnement et d'augmenter en conséquence sa durée de vie.The invention provides a gain of static pressure in the center of the cell which fills in approximately 75% of the existing pressure drop without the arrangement made. This improvement in cooling air supply to the blade reduces the average dawn temperature according to the operating conditions and to increase consequently its lifespan.

Claims (7)

Aube (11) pour turbine, l'aube présentant un pied (13) permettant de la rapporter dans une alvéole (14) d'un disque (12) de la turbine, l'aube possédant un circuit interne de refroidissement par air comprenant des moyens d'entrée d'air (15) situés sur une face du pied de l'aube et en regard de ladite alvéole, et des moyens de sortie d'air, caractérisée en ce que ladite face du pied de l'aube est équipée d'un déflecteur (20) comportant au moins une ailette (22, 23) permettant de canaliser l'air de refroidissement circulant dans le fond de l'alvéole pour régulariser l'écoulement d'air vers les moyens d'entrée d'air (15).Blade (11) for a turbine, the blade having a foot (13) enabling it to be brought into a cell (14) of a disc (12) of the turbine, the blade having an internal air cooling circuit comprising air inlet means (15) located on one face of the blade root and facing said cell, and air outlet means, characterized in that said face of the blade blade is equipped a deflector (20) comprising at least one fin (22, 23) for channeling the cooling air circulating in the bottom of the cell to regulate the flow of air to the air intake means (15). Aube pour turbine selon la revendication 1, caractérisée en ce que le déflecteur fait partie intégrante de l'aube.Impeller for turbine according to claim 1, characterized in that the deflector is an integral part of the blade. Aube pour turbine selon la revendication 1, caractérisée en ce que le déflecteur (20) est un élément rapporté sur le pied (13) de l'aube (11) et pourvu de moyens d'accès (21) aux moyens d'entrée d'air (15).Impeller for turbine according to claim 1, characterized in that the deflector (20) is an element attached to the foot (13) of the blade (11) and provided with access means (21) to the inlet means of 'air (15). Aube pour turbine selon la revendication 3, caractérisée en ce que les moyens d'accès (21) comprennent au moins un trou calibré. Impeller for turbine according to claim 3, characterized in that the access means (21) comprise at least one calibrated hole. Aube pour turbine selon l'une quelconque des revendications 1 à 4, caractérisée en ce que ladite ailette (22, 23) est droite ou inclinée par rapport à l'axe général de l'aube.Impeller for turbine according to any one of Claims 1 to 4, characterized in that the said fin (22, 23) is straight or inclined with respect to the general axis of the blade. Aube pour turbine selon l'une quelconque des revendications 1 à 5, caractérisée en ce que le déflecteur (20) comprend au moins une ailette (22) permettant de canaliser l'air de refroidissement pénétrant dans l'alvéole et au moins une ailette (23) permettant de canaliser de l'air refoulé vers le centre de l'alvéole.Impeller for turbine according to any one of Claims 1 to 5, characterized in that the deflector (20) comprises at least one fin (22) making it possible to channel the cooling air entering the alveolus and at least one fin ( 23) for channeling the discharged air towards the center of the cell. Aube pour turbine selon l'une quelconque des revendications 1 à 6, caractérisé en ce que le déflecteur comprend au moins une ailette incurvée.Impeller for turbine according to any one of Claims 1 to 6, characterized in that the deflector comprises at least one curved fin.
EP02290964A 2001-04-19 2002-04-17 Turbine blade with cooling air baffle Expired - Lifetime EP1251243B8 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0105289 2001-04-19
FR0105289A FR2823794B1 (en) 2001-04-19 2001-04-19 REPORTED AND COOLED DAWN FOR TURBINE

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EP1251243B1 EP1251243B1 (en) 2005-09-07
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CA (1) CA2444862C (en)
DE (1) DE60205977T2 (en)
ES (1) ES2244738T3 (en)
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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005012695A1 (en) * 2003-07-28 2005-02-10 Pratt & Whitney Canada Corp. Gas turbine blade inlet cooling flow deflector
FR2858829A1 (en) * 2003-08-12 2005-02-18 Snecma Moteurs Nozzle guide vane for gas turbine engine, has longitudinal sleeve folded in zone of its end portion to form throat for passage of air flow, where throat has dimension smaller than that of guide
EP1574670A3 (en) * 2004-03-13 2009-02-25 Rolls-Royce Plc A mounting arrangement for turbine blades
EP2436879A3 (en) * 2010-10-04 2014-01-08 Rolls-Royce plc Turbine disc cooling arrangement
EP1987903B1 (en) 2007-04-30 2015-11-11 United Technologies Corporation Method for manufacturing a turbine engine component
EP3093433A1 (en) * 2015-05-01 2016-11-16 General Electric Company Turbine dovetail slot heat shield

Families Citing this family (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0227745D0 (en) * 2002-11-28 2003-01-08 Rolls Royce Plc Blade cooling
ES2337800T3 (en) * 2004-03-30 2010-04-29 Alstom Technology Ltd DEVICE FOR THE PRESSURIZATION OF AIR REFRIGERATION IN A RODETE WIRE
US7578652B2 (en) 2006-10-03 2009-08-25 United Technologies Corporation Hybrid vapor and film cooled turbine blade
SG143087A1 (en) * 2006-11-21 2008-06-27 Turbine Overhaul Services Pte Laser fillet welding
US8128365B2 (en) 2007-07-09 2012-03-06 Siemens Energy, Inc. Turbine airfoil cooling system with rotor impingement cooling
FR2937372B1 (en) * 2008-10-22 2010-12-10 Snecma TURBINE BLADE EQUIPPED WITH MEANS FOR ADJUSTING ITS FLOW OF COOLING FLUID
US9249671B2 (en) 2009-09-04 2016-02-02 Siemens Aktiengesellschaft Method and a device of tangentially biasing internal cooling on nozzle guide vanes
US8622702B1 (en) * 2010-04-21 2014-01-07 Florida Turbine Technologies, Inc. Turbine blade with cooling air inlet holes
IT1403416B1 (en) * 2010-12-21 2013-10-17 Avio Spa BORED ROTOR OF A GAS TURBINE FOR AERONAUTICAL ENGINES AND METHOD FOR COOLING OF THE BORED ROTOR
DE102011121634B4 (en) * 2010-12-27 2019-08-14 Ansaldo Energia Ip Uk Limited turbine blade
US20120315139A1 (en) * 2011-06-10 2012-12-13 General Electric Company Cooling flow control members for turbomachine buckets and method
EP2639407A1 (en) * 2012-03-13 2013-09-18 Siemens Aktiengesellschaft Gas turbine arrangement alleviating stresses at turbine discs and corresponding gas turbine
US9435206B2 (en) * 2012-09-11 2016-09-06 General Electric Company Flow inducer for a gas turbine system
EP2725191B1 (en) * 2012-10-23 2016-03-16 Alstom Technology Ltd Gas turbine and turbine blade for such a gas turbine
US8926283B2 (en) * 2012-11-29 2015-01-06 Siemens Aktiengesellschaft Turbine blade angel wing with pumping features
US20160090841A1 (en) * 2014-09-29 2016-03-31 United Technologies Corporation Gas turbine engine blade slot heat shield
EP3320183B1 (en) * 2015-07-06 2021-11-10 Siemens Energy Global GmbH & Co. KG Turbine stator vane and/or turbine rotor vane with a cooling flow adjustment feature and corresponding method of adapting a vane
DE102015111746A1 (en) * 2015-07-20 2017-01-26 Rolls-Royce Deutschland Ltd & Co Kg Cooled turbine wheel, in particular for an aircraft engine
GB201516657D0 (en) 2015-09-21 2015-11-04 Rolls Royce Plc Seal-plate anti-rotation in a stage of a gas turbine engine
US20170234447A1 (en) * 2016-02-12 2017-08-17 United Technologies Corporation Methods and systems for modulating airflow
KR102025147B1 (en) * 2017-10-13 2019-09-27 두산중공업 주식회사 Structure for combining throttle plate of bucket, rotor and gas turbine
DE102019206432A1 (en) * 2019-05-06 2020-11-12 MTU Aero Engines AG Turbomachine Blade
KR102284507B1 (en) * 2020-02-25 2021-08-02 두산중공업 주식회사 rotor and turbo-machine comprising the same
US11560844B2 (en) * 2021-02-18 2023-01-24 Pratt & Whitney Canada Corp. Inertial particle separator for a turbine section of a gas turbine engine
US12398644B2 (en) * 2022-07-08 2025-08-26 Siemens Energy Global GmbH & Co. KG Manifold for turbine blade of gas turbine engine
US12018590B1 (en) 2023-04-04 2024-06-25 Ge Infrastructure Technology Llc Method for turbine blade and assembly with dovetail arrangement for enlarged rotor groove
US12110809B1 (en) 2023-04-04 2024-10-08 Ge Infrastructure Technology Llc Turbine blade and assembly with dovetail arrangement for enlarged rotor groove
US12410712B1 (en) 2024-09-24 2025-09-09 Pratt & Whitney Canada Corp. Rotor blade with apertured cooling air deflector

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4178129A (en) * 1977-02-18 1979-12-11 Rolls-Royce Limited Gas turbine engine cooling system
US4348157A (en) * 1978-10-26 1982-09-07 Rolls-Royce Limited Air cooled turbine for a gas turbine engine
US4626169A (en) * 1983-12-13 1986-12-02 United Technologies Corporation Seal means for a blade attachment slot of a rotor assembly
GB1605282A (en) * 1973-10-27 1987-12-23 Rolls Royce 1971 Ltd Bladed rotor for gas turbine engine
DE3835932A1 (en) * 1988-10-21 1990-04-26 Mtu Muenchen Gmbh DEVICE FOR COOLING AIR SUPPLY FOR GAS TURBINE ROTOR BLADES
US5403156A (en) * 1993-10-26 1995-04-04 United Technologies Corporation Integral meter plate for turbine blade and method
WO1999047792A1 (en) * 1998-03-16 1999-09-23 Siemens Westinghouse Power Corporation Turbine blade assembly with cooling air handling device

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB742477A (en) * 1952-10-31 1955-12-30 Rolls Royce Improvements in or relating to bladed stator or rotor constructions for fluid machines such as axial-flow turbines or compressors
SU1287678A2 (en) * 1984-09-11 1997-02-20 О.С. Чернилевский Cooled turbine blade
SU1369390A1 (en) * 1986-06-02 1996-12-20 Уфимский авиационный институт им.Серго Орджоникидзе Device for cooling rotor blades of gas turbine
US4820123A (en) * 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1605282A (en) * 1973-10-27 1987-12-23 Rolls Royce 1971 Ltd Bladed rotor for gas turbine engine
US4178129A (en) * 1977-02-18 1979-12-11 Rolls-Royce Limited Gas turbine engine cooling system
US4348157A (en) * 1978-10-26 1982-09-07 Rolls-Royce Limited Air cooled turbine for a gas turbine engine
US4626169A (en) * 1983-12-13 1986-12-02 United Technologies Corporation Seal means for a blade attachment slot of a rotor assembly
DE3835932A1 (en) * 1988-10-21 1990-04-26 Mtu Muenchen Gmbh DEVICE FOR COOLING AIR SUPPLY FOR GAS TURBINE ROTOR BLADES
US5403156A (en) * 1993-10-26 1995-04-04 United Technologies Corporation Integral meter plate for turbine blade and method
WO1999047792A1 (en) * 1998-03-16 1999-09-23 Siemens Westinghouse Power Corporation Turbine blade assembly with cooling air handling device

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6974306B2 (en) 2003-07-28 2005-12-13 Pratt & Whitney Canada Corp. Blade inlet cooling flow deflector apparatus and method
WO2005012695A1 (en) * 2003-07-28 2005-02-10 Pratt & Whitney Canada Corp. Gas turbine blade inlet cooling flow deflector
FR2858829A1 (en) * 2003-08-12 2005-02-18 Snecma Moteurs Nozzle guide vane for gas turbine engine, has longitudinal sleeve folded in zone of its end portion to form throat for passage of air flow, where throat has dimension smaller than that of guide
EP1508670A3 (en) * 2003-08-12 2005-03-09 Snecma Moteurs Cooled vane of a gas turbine
US7204675B2 (en) 2003-08-12 2007-04-17 Snecma Moteurs Cooled gas turbine engine vane
EP1574670A3 (en) * 2004-03-13 2009-02-25 Rolls-Royce Plc A mounting arrangement for turbine blades
EP1987903B1 (en) 2007-04-30 2015-11-11 United Technologies Corporation Method for manufacturing a turbine engine component
EP1987903B2 (en) † 2007-04-30 2022-07-27 Raytheon Technologies Corporation Method for manufacturing a turbine engine component
EP2436879A3 (en) * 2010-10-04 2014-01-08 Rolls-Royce plc Turbine disc cooling arrangement
US8807942B2 (en) 2010-10-04 2014-08-19 Rolls-Royce Plc Turbine disc cooling arrangement
EP3093433A1 (en) * 2015-05-01 2016-11-16 General Electric Company Turbine dovetail slot heat shield
CN106224011A (en) * 2015-05-01 2016-12-14 通用电气公司 Turbine dovetail groove heat shield
US10094228B2 (en) 2015-05-01 2018-10-09 General Electric Company Turbine dovetail slot heat shield
CN106224011B (en) * 2015-05-01 2019-02-19 通用电气公司 Turbine dovetail groove heat shield

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US6981845B2 (en) 2006-01-03
FR2823794B1 (en) 2003-07-11
JP2004522049A (en) 2004-07-22
FR2823794A1 (en) 2002-10-25
CA2444862C (en) 2009-11-24
DE60205977T2 (en) 2006-07-06
CA2444862A1 (en) 2002-10-31
RU2003133669A (en) 2005-04-20
US20040115054A1 (en) 2004-06-17
JP4112986B2 (en) 2008-07-02
RU2325537C2 (en) 2008-05-27
EP1251243B8 (en) 2005-11-02
WO2002086291A1 (en) 2002-10-31
UA73655C2 (en) 2005-08-15
DE60205977D1 (en) 2005-10-13
ES2244738T3 (en) 2005-12-16
EP1251243B1 (en) 2005-09-07

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