EP0043300A2 - Cooling system for turbine blades and discs - Google Patents

Cooling system for turbine blades and discs Download PDF

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Publication number
EP0043300A2
EP0043300A2 EP81400931A EP81400931A EP0043300A2 EP 0043300 A2 EP0043300 A2 EP 0043300A2 EP 81400931 A EP81400931 A EP 81400931A EP 81400931 A EP81400931 A EP 81400931A EP 0043300 A2 EP0043300 A2 EP 0043300A2
Authority
EP
European Patent Office
Prior art keywords
blade
disc
blades
foot
improvement
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
EP81400931A
Other languages
German (de)
French (fr)
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EP0043300B1 (en
EP0043300A3 (en
Inventor
André Alexandre Morlon
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0043300A2 publication Critical patent/EP0043300A2/en
Publication of EP0043300A3 publication Critical patent/EP0043300A3/en
Application granted granted Critical
Publication of EP0043300B1 publication Critical patent/EP0043300B1/en
Expired legal-status Critical Current

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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
    • 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
    • F01D5/12—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
    • F01D5/30—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 an improvement to the ventilation systems of blades and discs of turbines.
  • the supply of cooling air to the base of the turbine blades and to the walls of the disc cavities is generally ensured, from a capacity comprised between the flange and the front face of the disc.
  • the flange is bolted to the lower part of the disc and also comes to bear, either on the front face of the disc teeth and on the blade root, or only on the front edge of the blade platforms.
  • the foot of the blade has at its lower front part a tab or spoiler ensuring axial locking towards the rear, abutting against the upstream face of the turbine disc, said tab having an opening for the passage of the cooling air in an enclosure formed between the bottom of the cell and the underside of the foot, the axial locking towards the front being ensured by a flange fixed on the disc and against which comes to bear part of the dawn.
  • the present invention therefore allows a good seal between the flange, the blades and the disc by means of a very simple device ensuring both the supply of cooling air to the root of the blades and their axial locking towards the rear.
  • a rotor disc 1 in which are formed at its periphery axial cells 2 each receiving a foot 3 of a turbine blade 4 which comprises a platform 5 and a profiled part 6 extending radially from each platform.
  • the foot of the blade 3 has at its lower front part a tab or spoiler 7 abutting against the upstream face 1a of the turbine disc, said tab having an opening 8 for the passage of the cooling air in a chamber 9 formed . between the bottom of the cell 2 and the underside 3a of the foot 3.
  • the underside of the foot 3 of the blade also has a recess at the front 12 to facilitate the passage of air.
  • the enclosure 9 opens towards the downstream face of the disc through an orifice 10 so that the air escapes backwards in a deflected manner according to the arrow F where it joins the vein between the stage. and a rectifier stage 11.
  • the tab or spoiler 7 ensures the axial locking of the blade 4 towards the rear while the locking towards the front is obtained by means of a flange 13 which comes to bear on the platform 5 of the blades 4.
  • Locking forwards can also be obtained by means of the flange 13 which bears simultaneously on the front face of the foot 3 of the blade and on the teeth 1b of the disc 1.
  • FIGS 3 and 4 there is shown an alternative embodiment in which the enclosure 9 between the bottom of the cell 2 and the underside of the foot 3 of the blade is closed towards the downstream face of the disc by an elastic ring 14 engaged under a downstream spoiler 15 of the disc in which the ring 14 is held by elasticity on the one hand, but above all by centrifugal force.
  • conduit 16 connecting the enclosure 9 with the cavity 17 formed inside the profiled part 6 of the blade 4, said cavity 17 being in communication with the outside by conduits 18 and 19 provided respectively in the leading edge and in the trailing edge. In this way the air cools the profiled part 6 of the blade itself which is provided with well known means of air circulation.

Abstract

1. Improvement in systems of ventilation of blades and discs of a turbine, each blade comprising a root (3) engaged in one of the axial grooves (2) provided in the periphery of the disc, a platform (5) at the radial end of the extension of the root (3) and a profiled part (6) extending radially from the platform (5), a passage (9) being provided between the base of the groove (2) and the internal face (3a) of the root and the axial locking of the blade towards the front being effected by a flange (13) mounted on the disc and against which a part of the blade abuts, characterized in this that the root (3) of the blade (4) has at its lower front part a lug or protrusion (7) which includes an opening (8) for the flow of cooling air to the said passage (9), the said lug (7) providing axial rearwards locking by abutting against the upstream face (1a) of the turbine disc.

Description

La présente invention a pour objet un perfectionnement aux systèmes de ventilation des aubes et disques de turbines.The present invention relates to an improvement to the ventilation systems of blades and discs of turbines.

L'alimentation en air de refroidissement du pied des aubes de turbines et des parois des alvéoles du disque est en général assurée, à partir d'une capacité comprise entre le flasque et la face avant du disque. Le flasque est boulonné sur la partie basse du disque et vient par ailleurs en appui, soit sur la face avant des dents du disque et sur le pied des aubes, soit uniquement sur le bord avant des plateformes des aubes.The supply of cooling air to the base of the turbine blades and to the walls of the disc cavities is generally ensured, from a capacity comprised between the flange and the front face of the disc. The flange is bolted to the lower part of the disc and also comes to bear, either on the front face of the disc teeth and on the blade root, or only on the front edge of the blade platforms.

Il est également connu d'utiliser des plaques mantées dans des rainures circulaires prévues respectivement dans les plateformes des aubes et dans le disque, des orifices étant prévus dans les plaques pour le passage de l'air.It is also known to use plates manted in circular grooves provided respectively in the platforms of the blades and in the disc, orifices being provided in the plates for the passage of air.

Dans ces dispositifs connus, l'étanchéité entre flasque, aubes et disques n'est pas parfaite et les jeux créent de nombreuses sources de fuite.In these known devices, the seal between the flange, the blades and the discs is not perfect and the games create numerous sources of leakage.

Il est donc difficile d'apprécier avec exactitude le débit d'air de refroidissement, d'où il résulte un risque de surchauffe des dents du disque et des pieds d'aubes.It is therefore difficult to accurately assess the flow of cooling air, which results in a risk of overheating the disc teeth and blade roots.

Conformément à la présente invention, le pied de l'aube présente à sa partie inférieure frontale une patte ou becquet assurant le verrouillage axial vers l'arrière, venant en butée contre la face amont du disque de turbine, ladite patte présentant une ouverture pour le passage de l'air de refroidissement dans une enceinte ménagée entre le fond de l'alvéole et la face inférieure du pied, le verrouillage axial vers l'avant étant assuré par un flasque fixé sur le disque et contre lequel vient en appui une partie de l'aube.According to the present invention, the foot of the blade has at its lower front part a tab or spoiler ensuring axial locking towards the rear, abutting against the upstream face of the turbine disc, said tab having an opening for the passage of the cooling air in an enclosure formed between the bottom of the cell and the underside of the foot, the axial locking towards the front being ensured by a flange fixed on the disc and against which comes to bear part of the dawn.

La présente invention permet donc une bonne étanchéité entre le flasque, les aubes et le disque au moyen d'un dispositif très simple assurant à la fois l'alimentation en air de refroidissement du pied des aubes et leur verrouillage axial vers l'arrière.The present invention therefore allows a good seal between the flange, the blades and the disc by means of a very simple device ensuring both the supply of cooling air to the root of the blades and their axial locking towards the rear.

D'autres caractéristiques et avantages de l'invention seront mieux compris à la lecture de la description qui va suivre de plusieurs modes de réalisation et en se référant aux dessins annexés, sur lesquels :

  • La figure 1 est une vue en coupe axiale d'une aube de turbine perfectionnée suivant l'invention.
  • La figure 2 est une vue de la face avant de l'aube représentée à la figure 1.
  • La figure 3 est une vue en coupe axiale d'un autre mode de réalisation d'une aube de turbine.
  • La figure 4 est une vue de la face avant de l'aube représentée à la figure 3.
Other characteristics and advantages of the invention will be better understood on reading the following description of several embodiments and with reference to the appended drawings, in which:
  • Figure 1 is an axial sectional view of an improved turbine blade according to the invention.
  • FIG. 2 is a view of the front face of the blade shown in FIG. 1.
  • Figure 3 is an axial sectional view of another embodiment of a turbine blade.
  • FIG. 4 is a view of the front face of the blade shown in FIG. 3.

Aux figures 1 et 2, on a représenté un disque de rotor 1 dans lequel sont ménagées à sa périphérie des alvéoles axiales 2 recevant chacune un pied 3 d'une aube de turbine 4 qui comporte une plateforme 5 et une partie profilée 6 s'étendant radialement à partir de chaque plateforme.In Figures 1 and 2, there is shown a rotor disc 1 in which are formed at its periphery axial cells 2 each receiving a foot 3 of a turbine blade 4 which comprises a platform 5 and a profiled part 6 extending radially from each platform.

Le pied de l'aube 3 présente à sa partie inférieure frontale une patte ou becquet 7 en butée contre la face amont la du disque de turbine, ladite patte présentant une ouverture 8 pour le passage de l'air de refroidissement dans une enceinte 9 ménagée. entre le fond de l'alvéole 2 et la face inférieure 3a du pied 3.The foot of the blade 3 has at its lower front part a tab or spoiler 7 abutting against the upstream face 1a of the turbine disc, said tab having an opening 8 for the passage of the cooling air in a chamber 9 formed . between the bottom of the cell 2 and the underside 3a of the foot 3.

La face inférieure du pied 3 de l'aube comporte également à l'avant un décrochement 12 pour faciliter le passage de l'air.The underside of the foot 3 of the blade also has a recess at the front 12 to facilitate the passage of air.

L'enceinte 9 débouche vers la face aval du disque par un orifice 10 de telle sorte que l'air s'échappe vers l'arrière de manière défléchie suivant la flèche F où il rejoint la veine entre l'étage.mobile des aubes 4 et un étage redresseur 11.The enclosure 9 opens towards the downstream face of the disc through an orifice 10 so that the air escapes backwards in a deflected manner according to the arrow F where it joins the vein between the stage. and a rectifier stage 11.

La patte ou becquet 7 assure le verrouillage axial de l'aube 4 vers l'arrière alors que le verrouillage vers l'avant est obtenu au moyen d'un flasque 13 qui vient porter sur la plateforme 5 des aubes 4.The tab or spoiler 7 ensures the axial locking of the blade 4 towards the rear while the locking towards the front is obtained by means of a flange 13 which comes to bear on the platform 5 of the blades 4.

Le verrouillage vers l'avant peut être obtenu également au moyen du flasque 13 qui vient porter simultanément sur la face avant du pied 3 de l'aube et sur les dents 1b du disque 1.Locking forwards can also be obtained by means of the flange 13 which bears simultaneously on the front face of the foot 3 of the blade and on the teeth 1b of the disc 1.

Aux figures 3 et 4, on a représenté une variante de réalisation dans laquelle l'enceinte 9 entre le fond de l'alvéole 2 et la face inférieure du pied 3 de l'aube est obturée vers la face aval du disque par une bague élastique 14 engagée sous un becquet aval 15 du disque dans lequel la bague 14 est maintenue par élasticité d'une part, mais surtout par la force centrifuge.In Figures 3 and 4, there is shown an alternative embodiment in which the enclosure 9 between the bottom of the cell 2 and the underside of the foot 3 of the blade is closed towards the downstream face of the disc by an elastic ring 14 engaged under a downstream spoiler 15 of the disc in which the ring 14 is held by elasticity on the one hand, but above all by centrifugal force.

Dans la partie médiane du pied 3, il est prévu un conduit 16 reliant l'enceinte 9 avec la cavité 17 ménagée à l'intérieur de la partie profilée 6 de l'aube 4, ladite cavité 17 étant en communication avec l'extérieur par des conduits 18 et 19 prévus respectivement dans le bord d'attaque et dans le bord de fuite. De cette manière l'air refroidit la partie profilée 6 de l'aube elle-même qui est munie de moyens bien connus de circulation de l'air.In the middle part of the foot 3, there is provided a conduit 16 connecting the enclosure 9 with the cavity 17 formed inside the profiled part 6 of the blade 4, said cavity 17 being in communication with the outside by conduits 18 and 19 provided respectively in the leading edge and in the trailing edge. In this way the air cools the profiled part 6 of the blade itself which is provided with well known means of air circulation.

Bien entendu diverses modifications peuvent être apportées par l'homme de l'art aux dispositifs ou procédés qui viennent d'être décrits uniquement à titre d'exemples non limitatifs sans sortir du cadre de l'invention.Of course, various modifications can be made by those skilled in the art to the devices or methods which have just been described only by way of nonlimiting examples without departing from the scope of the invention.

Claims (7)

1. Perfectionnement aux systèmes de ventilation des aubes et disques de turbines, chaque aube comprenant un pied (3) engagé dans l'une des alvéoles axiales (2) ménagées à la périphérie du disque et une partie profilée s'étendant radialement à partir de chaque plateforme, caractérisé en ce que le pied (3) de l'aube (4) présente à sa partie inférieure frontale une patte ou becquet (7) assurant le verrouillage axial vers l'arrière venant en butée contre la face amont (1a) du disque de turbine, ladite patte présentant une ouverture (8) pour le passage de l'air de refroidissement dans une enceinte (9) ménagée entre le fond de l'alvéole (2) et la face inférieure (3a) du pied, le verrouillage axial vers l'avant étant assuré par un flasque (13) fixé sur le disque et contre lequel vient en appui une partie de l'aube.1. Improvement of the ventilation systems of the blades and discs of turbines, each blade comprising a foot (3) engaged in one of the axial cells (2) formed at the periphery of the disc and a profiled part extending radially from each platform, characterized in that the foot (3) of the blade (4) has at its lower front part a tab or spoiler (7) ensuring axial locking towards the rear coming into abutment against the upstream face (1a) of the turbine disc, said tab having an opening (8) for the passage of the cooling air in an enclosure (9) formed between the bottom of the cell (2) and the underside (3a) of the foot, the axial locking towards the front being ensured by a flange (13) fixed on the disc and against which comes to bear part of the blade. 2. Perfectionnement aux systèmes de ventilation des aubes et disques de turbines suivant la revendication 1, caractérisé en ce que l'enceinte (9) ménagée entre le fond de l'alvéole (2) et la face inférieure (3a) du pied de l'aube débouche vers la face aval du disque, de telle sorte que l'air s'échappe vers l'arrière de manière défléchie dans la veine d'air entre un étage mobile et un étage redresseur (11).2. Improvement to the ventilation systems of the blades and discs of turbines according to claim 1, characterized in that the enclosure (9) formed between the bottom of the cell (2) and the underside (3a) of the foot of the the blade opens towards the downstream face of the disc, so that the air escapes backwards in a deflected manner in the air stream between a movable stage and a rectifier stage (11). 3. Perfectionnement aux systèmes de ventilation des aubes et disques de turbines suivant la revendication 1, caractérisé en ce que l'enceinte (9) ménagée entre le fond de l'alvéole (2) et la face inférieure du pied (3) de l'aube est obturée vers la face aval du disque et débouche dans une cavité (17) de la partie profilée (6) de l'aube (4) par un conduit (16) ménagé dans le pied de l'aube, ladite cavité (17) de la partie profilée (6) de l'aube comportant des orifices (18, 19) débouchant à l'extérieur.3. Improvement to the ventilation systems of the blades and discs of turbines according to claim 1, characterized in that the enclosure (9) formed between the bottom of the cell (2) and the underside of the foot (3) of the the blade is closed towards the downstream face of the disc and opens into a cavity (17) of the profiled part (6) of the blade (4) by a conduit (16) formed in the foot of the blade, said cavity ( 17) of the profiled part (6) of the blade having orifices (18, 19) opening to the outside. 4. Perfectionnement aux systèmes de ventilation des aubes et disques de turbines suivant la revendication 3, caractérisé en ce que l'enceinte (9) ménagée entre le fond de l'alvéole et la face inférieure du pied de l'aube est obturée vers la face aval du disque par une bague élastique (14) engagée sous une dent (15) de l'aube (4).4. Improvement to the ventilation systems of the blades and turbine disks according to claim 3, characterized in that the enclosure (9) formed between the bottom of the cell and the underside of the blade root is closed towards the downstream face of the disc by an elastic ring (14) engaged under a tooth (15) of the blade (4). 5. Perfectionnement aux systèmes de ventilation des aubes et disques de turbines suivant la revendication 1, caractérisé en ce que la face inférieure du pied (3) des aubes (4) comporte à l'avant un décrochement (12) pour faciliter le passage de l'air.5. Improvement to the ventilation systems of the blades and turbine disks according to claim 1, characterized in that the underside of the base (3) of the blades (4) has at the front a recess (12) to facilitate the passage of the air. 6. Perfectionnement aux systèmes de ventilation des aubes et disques de turbines suivant la revendication 1, caractérisé en ce que le verrouillage vers l'avant est assuré par le flasque (13) contre lequel vient en appui le bord avant de la plateforme (5) de l'aube (4).6. Improvement to the ventilation systems of the blades and discs of turbines according to claim 1, characterized in that the locking towards the front is ensured by the flange (13) against which abuts the front edge of the platform (5) of dawn (4). 7. Perfectionnement aux systèmes de ventilation des aubes et disques de turbines suivant la revendication 1, caractérisé en ce que le verrouillage vers l'avant est assuré par le flasque (13) contre lequel vient en appui la face avant (5) du pied (3) de l'aube (4) et les dents (1b) du disque (1).7. Improvement to the ventilation systems of the blades and discs of turbines according to claim 1, characterized in that the locking towards the front is ensured by the flange (13) against which abuts the front face (5) of the foot ( 3) of the blade (4) and the teeth (1b) of the disc (1).
EP19810400931 1980-06-30 1981-06-12 Cooling system for turbine blades and discs Expired EP0043300B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8014498 1980-06-30
FR8014498A FR2485632B1 (en) 1980-06-30 1980-06-30 IMPROVEMENT IN VENTILATION SYSTEMS OF BLADES AND TURBINE DISCS

Publications (3)

Publication Number Publication Date
EP0043300A2 true EP0043300A2 (en) 1982-01-06
EP0043300A3 EP0043300A3 (en) 1982-01-13
EP0043300B1 EP0043300B1 (en) 1984-05-16

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EP19810400931 Expired EP0043300B1 (en) 1980-06-30 1981-06-12 Cooling system for turbine blades and discs

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EP (1) EP0043300B1 (en)
DE (1) DE3163609D1 (en)
FR (1) FR2485632B1 (en)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3835932A1 (en) * 1988-10-21 1990-04-26 Mtu Muenchen Gmbh DEVICE FOR COOLING AIR SUPPLY FOR GAS TURBINE ROTOR BLADES
EP0649975A1 (en) * 1993-10-26 1995-04-26 United Technologies Corporation Metering of cooling air in turbine blades
EP0709547A1 (en) * 1994-10-31 1996-05-01 Solar Turbines Incorporated Cooling of the rim of a gas turbine rotor disk
US5759012A (en) * 1996-12-13 1998-06-02 Caterpillar Inc. Turbine disc ingress prevention method and apparatus
EP1094199A1 (en) * 1999-10-18 2001-04-25 ABB (Schweiz) AG Rotor for a gas turbine
WO2010088881A1 (en) * 2009-02-05 2010-08-12 Mtu Aero Engines Gmbh Sealing apparatus at the blade shaft of a rotor stage of an axial turbomachine
FR2969209A1 (en) * 2010-12-21 2012-06-22 Snecma Element e.g. downstream wall, for use in blade of rotor of turbine stage of e.g. twin spool turbine engine of aircraft, has multiperforation part for passage of flow of cooling air to upstream face of downstream flange
US8622702B1 (en) * 2010-04-21 2014-01-07 Florida Turbine Technologies, Inc. Turbine blade with cooling air inlet holes
EP2896786A1 (en) * 2014-01-20 2015-07-22 Honeywell International Inc. Turbine rotor assemblies with improved slot cavities
EP3556996A1 (en) * 2018-04-20 2019-10-23 United Technologies Corporation Blade with inlet orifice on forward face of root
EP3680451A1 (en) * 2019-01-11 2020-07-15 Safran Aircraft Engines Rotor, turbine provided with such a rotor and turbine engine equipped with such a turbine
FR3095234A1 (en) * 2019-04-19 2020-10-23 Safran Aircraft Engines TURBOMACHINE ASSEMBLY INCLUDING A TEMPERATURE LIMITATION DEVICE FOR UNCOOLED ALVEOLE BOTTOM
CN112196628A (en) * 2020-09-25 2021-01-08 中国航发沈阳发动机研究所 Low-pressure turbine air cooling blade

Families Citing this family (2)

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Publication number Priority date Publication date Assignee Title
FR2695161B1 (en) * 1992-08-26 1994-11-04 Snecma Cooling system for a turbomachine compressor and clearance control.
FR3127255A1 (en) * 2021-09-23 2023-03-24 Safran Aircraft Engines Rotary assembly for turbomachine

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FR2323007A1 (en) * 1975-09-08 1977-04-01 Gen Electric Turbine blade cooling by fluid leakage through void by blade root - has void wall, with inclined coutlet bore, radial to blade platform
GB2001708A (en) * 1977-07-22 1979-02-07 Rolls Royce Bladed rotor for a gas turbine engine

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Publication number Priority date Publication date Assignee Title
GB701263A (en) * 1950-08-03 1953-12-23 Rolls Royce Improvements in or relating to turbo-machines
CH322022A (en) * 1953-04-13 1957-05-31 Rolls Royce Hollow blade for turbo machines
US3034763A (en) * 1959-08-20 1962-05-15 United Aircraft Corp Rotor construction
FR2323007A1 (en) * 1975-09-08 1977-04-01 Gen Electric Turbine blade cooling by fluid leakage through void by blade root - has void wall, with inclined coutlet bore, radial to blade platform
GB2001708A (en) * 1977-07-22 1979-02-07 Rolls Royce Bladed rotor for a gas turbine engine

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3835932A1 (en) * 1988-10-21 1990-04-26 Mtu Muenchen Gmbh DEVICE FOR COOLING AIR SUPPLY FOR GAS TURBINE ROTOR BLADES
EP0649975A1 (en) * 1993-10-26 1995-04-26 United Technologies Corporation Metering of cooling air in turbine blades
EP0709547A1 (en) * 1994-10-31 1996-05-01 Solar Turbines Incorporated Cooling of the rim of a gas turbine rotor disk
US5759012A (en) * 1996-12-13 1998-06-02 Caterpillar Inc. Turbine disc ingress prevention method and apparatus
EP1094199A1 (en) * 1999-10-18 2001-04-25 ABB (Schweiz) AG Rotor for a gas turbine
US6416282B1 (en) 1999-10-18 2002-07-09 Alstom Rotor for a gas turbine
WO2010088881A1 (en) * 2009-02-05 2010-08-12 Mtu Aero Engines Gmbh Sealing apparatus at the blade shaft of a rotor stage of an axial turbomachine
US8870542B2 (en) 2009-02-05 2014-10-28 Mtu Aero Engines Gmbh Sealing apparatus at the blade shaft of a rotor stage of an axial turbomachine
US8622702B1 (en) * 2010-04-21 2014-01-07 Florida Turbine Technologies, Inc. Turbine blade with cooling air inlet holes
FR2969209A1 (en) * 2010-12-21 2012-06-22 Snecma Element e.g. downstream wall, for use in blade of rotor of turbine stage of e.g. twin spool turbine engine of aircraft, has multiperforation part for passage of flow of cooling air to upstream face of downstream flange
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EP3556996A1 (en) * 2018-04-20 2019-10-23 United Technologies Corporation Blade with inlet orifice on forward face of root
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FR3091722A1 (en) * 2019-01-11 2020-07-17 Safran Aircraft Engines Rotor, turbine equipped with such a rotor and turbomachine equipped with such a turbine
US11261745B2 (en) 2019-01-11 2022-03-01 Safran Aircraft Engines Rotor, turbine equipped with such a rotor and turbomachine equipped with such a turbine
FR3095234A1 (en) * 2019-04-19 2020-10-23 Safran Aircraft Engines TURBOMACHINE ASSEMBLY INCLUDING A TEMPERATURE LIMITATION DEVICE FOR UNCOOLED ALVEOLE BOTTOM
CN112196628A (en) * 2020-09-25 2021-01-08 中国航发沈阳发动机研究所 Low-pressure turbine air cooling blade
CN112196628B (en) * 2020-09-25 2022-06-07 中国航发沈阳发动机研究所 Low-pressure turbine air cooling blade

Also Published As

Publication number Publication date
DE3163609D1 (en) 1984-06-20
FR2485632B1 (en) 1985-07-05
FR2485632A1 (en) 1981-12-31
EP0043300B1 (en) 1984-05-16
EP0043300A3 (en) 1982-01-13

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