EP1318274A1 - High-pressure turbine blade with cooled trailing edge - Google Patents
High-pressure turbine blade with cooled trailing edge Download PDFInfo
- Publication number
- EP1318274A1 EP1318274A1 EP02292970A EP02292970A EP1318274A1 EP 1318274 A1 EP1318274 A1 EP 1318274A1 EP 02292970 A EP02292970 A EP 02292970A EP 02292970 A EP02292970 A EP 02292970A EP 1318274 A1 EP1318274 A1 EP 1318274A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- foot
- dawn
- pressure turbine
- slot
- 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
Links
Images
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
- F01D5/187—Convection cooling
Definitions
- the present invention relates to the general field of moving blades of a high-pressure turbine of a turbomachine, and more particularly to the cooling air exhaust slots located on the trailing edge of the moving blades of a high-pressure turbine.
- a turbomachine comprises a combustion chamber in which air and fuel are mixed before being burnt.
- the gases from this combustion flow downstream into the combustion chamber and then feed a high pressure turbine.
- the high-pressure turbine has one or more multiple rows of circumferentially spaced movable vanes while around the turbine rotor.
- the moving blades of the high-pressure turbine are thus subjected to the very high temperatures of the combustion. These temperatures reach values largely higher than those which the blades which can withstand without damage are in contact with these gases, which has the consequence of limiting their lifetime.
- cooling air which is generally introduced into the dawn by its foot, crosses it in following a path formed by cavities made in the dawn before being ejected through slits opening on the surface of the blade. More precisely, these cooling air exhaust slots are usually distributed along the trailing edge of the dawn, between the foot and the top of the latter, substantially perpendicular to a longitudinal axis of dawn.
- cooling circuits slots are conventionally reserved by cores arranged parallel to each other in the mold before casting the metal.
- the cooling air exhaust slot closest to the dawn foot is usually made in more dimensions larger than those of other slots.
- the present invention therefore aims to overcome such a drawback by proposing a moving blade of a high-pressure turbine having a new geometry of the cooling air exhaust slot the closer to the foot of dawn which does not generate a crack.
- the invention also aims not to degrade the general mechanical strength of the dawn, part subject to very high mechanical stresses. She aims finally a high-pressure turbine of a turbomachine equipped with such blades mobile.
- turbomachine comprising at least one circuit cooling composed of at least one cavity extending radially between a summit and a foot of dawn, at least one opening air intake at a radial end of the cavity (ies) for supply the cooling circuit (s) with cooling air, and a plurality of slots opening in the cavity or cavities and opening onto a trailing edge of the blade, the slots being arranged along the edge of flight, between the foot and the top of the dawn, substantially perpendicular to a longitudinal axis of the blade, characterized in that at minus the slit closest to the foot of the blade has an inclination towards the top of the dawn between 10 ° and 30 ° relative to an axis dawn rotation.
- the inclination of the slot closest to the dawn foot is about 20 °.
- connection zone To lower the temperature of a connection area between the foot of dawn and a platform defining the vein flow of combustion gases through the high-pressure turbine, the upstream end of the slit closest to the foot of the dawn is formed essentially in this connection zone.
- Figure 1 shows in perspective a movable blade 10, by example of a high-pressure turbine of a turbomachine. This dawn of longitudinal axis X-X is fixed on a rotor disc (not shown) of the high-pressure turbine via a fitting 12 usually in the shape of a fir tree. It typically comprises a foot 14, a top 16, a leading edge 18 and a trailing edge 20.
- the fitting 12 is connected to the foot 14 of the blade at the level of a platform 22 defining a wall for the gas flow stream combustion through the high-pressure turbine.
- the movable blade 10 comprises at least one circuit for internal cooling.
- This cooling circuit is composed by example of at least one cavity 24 extending radially between the foot 14 and the summit 16 of dawn.
- This cavity is supplied with air from cooling at one of its radial ends by an opening air intake (not shown).
- This air intake opening is generally provided at the dawn fitting 12.
- It is also provided a plurality of slots 26 opening into the cavity 24 and leading to the trailing edge 20 of the blade in order to evacuate the air from cooling flowing into the cavity.
- These slots 26 for evacuating cooling air is typically distributed along the trailing edge 20, between the foot 14 and the apex 16 of the dawn, substantially perpendicular to the longitudinal axis X-X of the blade.
- Figure 2 illustrates more precisely the geometry of the slot 28 closest to foot 14 of dawn 10.
- the slot 28 closest to the foot of the dawn has an inclination towards the vertex 16 of the dawn between 10 ° and 30 ° relative to an axis of dawn rotation (not shown).
- the inclination of this slit is about 20 °.
- This particular inclination of the most close to the foot of dawn allows to homogenize the temperature at the level of it and thus remove any hot spot.
- Air cooling evacuated through this slot covers in fact the entire surface of the slot 28 and lowers the local temperature by around 5%. So any risk of crack at the level of this slot closest to the foot of dawn disappears and the lifespan of dawn is extended.
- the end upstream 28a of the slot 28 closest to the foot 14 of the dawn is formed essentially in a connection zone 30 between the foot 14 of the blade and the platform 22 on the side of the gas flow stream of combustion so the air exhausted through that slit tends to come cool the connection area 30 by thermal conduction. temperature of the connection zone 30 between the foot 14 of the dawn and the platform 22 is thus lowered by about 1.5%.
- the sharp angles of the upstream end 28a of the slot 28 are ground to facilitate guiding air evacuated through the slit towards this zone 30.
- the downstream end 28b of the slot 28 closest to the foot of the blade is not not formed in the connection zone 30, the holding of the blade 10 to the different mechanical stress is not affected by this geometry particular of the slot.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
La présente invention se rapporte au domaine général des aubes mobiles de turbine haute-pression d'une turbomachine, et plus particulièrement aux fentes d'évacuation de l'air de refroidissement situées sur le bord de fuite des aubes mobiles d'une turbine haute-pression.The present invention relates to the general field of moving blades of a high-pressure turbine of a turbomachine, and more particularly to the cooling air exhaust slots located on the trailing edge of the moving blades of a high-pressure turbine.
De façon connue en soi, une turbomachine comporte une chambre de combustion dans laquelle de l'air et du carburant sont mélangés avant d'y être brûlés. Les gaz issus de cette combustion s'écoulent vers l'aval dans la chambre de combustion et alimentent ensuite une turbine haute-pression. La turbine haute-pression comporte une ou plusieurs rangées d'aubes mobiles espacées de façon circonférentielle tout autour du rotor de la turbine. Les aubes mobiles de la turbine haute-pression sont ainsi soumises aux températures très élevées des gaz de combustion. Ces températures atteignent des valeurs largement supérieures à celles que peuvent supporter sans dommages les aubes qui sont en contact avec ces gaz, ce qui a pour conséquence de limiter leur durée de vie.In a manner known per se, a turbomachine comprises a combustion chamber in which air and fuel are mixed before being burnt. The gases from this combustion flow downstream into the combustion chamber and then feed a high pressure turbine. The high-pressure turbine has one or more multiple rows of circumferentially spaced movable vanes while around the turbine rotor. The moving blades of the high-pressure turbine are thus subjected to the very high temperatures of the combustion. These temperatures reach values largely higher than those which the blades which can withstand without damage are in contact with these gases, which has the consequence of limiting their lifetime.
Afin de résoudre ce problème, il est connu de munir ces aubes de circuits de refroidissement internes visant à réduire la température de ces dernières. Grâce à de tels circuits, de l'air de refroidissement, qui est généralement introduit dans l'aube par son pied, traverse celle-ci en suivant un trajet formé par des cavités pratiquées dans l'aube avant d'être éjecté par des fentes s'ouvrant à la surface de l'aube. Plus précisément, ces fentes d'évacuation de l'air de refroidissement sont généralement réparties le long du bord de fuite de l'aube, entre le pied et le sommet de celle-ci, de façon sensiblement perpendiculaire à un axe longitudinal de l'aube.In order to solve this problem, it is known to provide these blades internal cooling circuits to reduce the temperature of these last. Thanks to such circuits, cooling air, which is generally introduced into the dawn by its foot, crosses it in following a path formed by cavities made in the dawn before being ejected through slits opening on the surface of the blade. More precisely, these cooling air exhaust slots are usually distributed along the trailing edge of the dawn, between the foot and the top of the latter, substantially perpendicular to a longitudinal axis of dawn.
Il est également connu que les aubes de turbine haute-pression équipées de circuits de refroidissement sont réalisées par moulage. Les emplacements des fentes des circuits de refroidissement sont classiquement réservés par des noyaux disposés parallèlement entre eux dans le moule avant la coulée du métal. Afin de faciliter cette coulée du métal, la fente d'évacuation de l'air de refroidissement la plus proche du pied de l'aube est généralement réalisée dans des dimensions plus importantes que celles des autres fentes.It is also known that high pressure turbine blades equipped with cooling circuits are produced by molding. The slots of the cooling circuits slots are conventionally reserved by cores arranged parallel to each other in the mold before casting the metal. In order to facilitate this pouring of metal, the cooling air exhaust slot closest to the dawn foot is usually made in more dimensions larger than those of other slots.
Or, dans la pratique, on constate que la fente la plus proche du pied de l'aube est mal refroidie. En effet, à cause des dimensions importantes de cette fente et en raison de la force centrifuge engendrée par la rotation de l'aube, l'air évacué par cette fente à tendance à être dévié vers le sommet de l'aube. Il en résulte des gradients thermiques importants au voisinage du bord de fuite qui génèrent, au niveau de cette fente, une crique particulièrement préjudiciable à la durée de vie de l'aube. Ces gradients thermiques importants ont également tendance à se propager par conduction vers une zone de raccordement entre le pied de l'aube et une plate-forme supportant celle-ci.However, in practice, it is found that the slot closest to the dawn foot is poorly cooled. Because of the dimensions due to this crack and due to the centrifugal force generated by the rotation of the blade, the air evacuated through this slot tends to be deflected to the top of dawn. This results in thermal gradients important in the vicinity of the trailing edge which generate, at this level slot, a crack particularly detrimental to the life of dawn. These large thermal gradients also tend to propagate by conduction to a connection zone between the foot of dawn and a platform supporting it.
La présente invention vise donc à pallier un tel inconvénient en proposant une aube mobile de turbine haute-pression présentant une nouvelle géométrie de la fente d'évacuation de l'air de refroidissement la plus proche du pied de l'aube qui n'engendre pas de crique. L'invention vise également à ne pas dégrader la tenue mécanique générale de l'aube, pièce soumise à des contraintes mécaniques très importantes. Elle vise enfin une turbine haute-pression de turbomachine équipée de telles aubes mobiles.The present invention therefore aims to overcome such a drawback by proposing a moving blade of a high-pressure turbine having a new geometry of the cooling air exhaust slot the closer to the foot of dawn which does not generate a crack. The invention also aims not to degrade the general mechanical strength of the dawn, part subject to very high mechanical stresses. She aims finally a high-pressure turbine of a turbomachine equipped with such blades mobile.
A cet effet, il est prévu une aube mobile de turbine haute-pression de turbomachine, comprenant au moins un circuit de refroidissement composé d'au moins une cavité s'étendant radialement entre un sommet et un pied de l'aube, d'au moins une ouverture d'admission d'air à une extrémité radiale de la ou les cavités pour alimenter le ou les circuits de refroidissement en air de refroidissement, et d'une pluralité de fentes s'ouvrant dans la ou les cavités et débouchant sur un bord de fuite de l'aube, les fentes étant aménagées le long du bord de fuite, entre le pied et le sommet de l'aube, de façon sensiblement perpendiculaire à un axe longitudinal de l'aube, caractérisée en ce qu'au moins la fente la plus proche du pied de l'aube présente une inclinaison vers le sommet de l'aube comprise entre 10° et 30° par rapport à un axe de rotation de l'aube.For this purpose, a movable blade of a high-pressure turbine is provided. turbomachine, comprising at least one circuit cooling composed of at least one cavity extending radially between a summit and a foot of dawn, at least one opening air intake at a radial end of the cavity (ies) for supply the cooling circuit (s) with cooling air, and a plurality of slots opening in the cavity or cavities and opening onto a trailing edge of the blade, the slots being arranged along the edge of flight, between the foot and the top of the dawn, substantially perpendicular to a longitudinal axis of the blade, characterized in that at minus the slit closest to the foot of the blade has an inclination towards the top of the dawn between 10 ° and 30 ° relative to an axis dawn rotation.
De la sorte, l'air de refroidissement évacué par la fente la plus proche du pied de l'aube est guidé sur toute la surface de la fente de façon à éviter que des criques n'apparaissent au niveau de celle-ci. Cette géométrie particulière de la fente permet d'abaisser de 5% environ la température locale au niveau de cette fente. En outre, la tenue de l'aube aux différentes contraintes mécaniques auxquelles elle est soumise n'est pas détériorée par cette géométrie de la fente.In this way, the cooling air evacuated through the most near the foot of dawn is guided over the entire surface of the slit so as to prevent cracks from appearing there. This special geometry of the slot allows to lower by about 5% the local temperature at this slot. In addition, holding the dawn to the various mechanical stresses to which it is subjected is not deteriorated by this geometry of the slot.
Avantageusement, l'inclinaison de la fente la plus proche du pied de l'aube est d'environ 20°.Advantageously, the inclination of the slot closest to the dawn foot is about 20 °.
Afin d'abaisser la température d'une zone de raccordement entre le pied de l'aube et une plate-forme définissant la veine d'écoulement des gaz de combustion au travers de la turbine haute-pression, l'extrémité amont de la fente la plus proche du pied de l'aube est formée essentiellement dans cette zone de raccordement.To lower the temperature of a connection area between the foot of dawn and a platform defining the vein flow of combustion gases through the high-pressure turbine, the upstream end of the slit closest to the foot of the dawn is formed essentially in this connection zone.
D'autres caractéristiques et avantages de la présente invention ressortiront de la description faite ci-dessous, en référence aux dessins annexés qui en illustrent un exemple de réalisation dépourvu de tout caractère limitatif. Sur les figures :
- la figure 1 est une vue en perspective d'une aube mobile de turbine haute-pression selon l'invention ; et
- la figure 2 est une vue agrandie et partielle de la figure 1 montrant la fente d'évacuation de l'air de refroidissement la plus proche du pied de l'aube.
- Figure 1 is a perspective view of a movable blade of a high-pressure turbine according to the invention; and
- Figure 2 is an enlarged and partial view of Figure 1 showing the cooling air discharge slot closest to the foot of the blade.
La figure 1 représente en perspective une aube mobile 10, par
exemple d'une turbine haute-pression d'une turbomachine. Cette aube
d'axe longitudinal X-X est fixée sur un disque rotor (non représenté) de la
turbine haute-pression par l'intermédiaire d'un emmanchement 12
généralement en forme de sapin. Elle comporte typiquement un pied 14,
un sommet 16, un bord d'attaque 18 et un bord de fuite 20.
L'emmanchement 12 se raccorde au pied 14 de l'aube au niveau d'une
plate-forme 22 définissant une paroi pour la veine d'écoulement des gaz
de combustion au travers de la turbine haute-pression.Figure 1 shows in perspective a
Une telle aube est soumise aux températures très élevées des
gaz de combustion et nécessite donc d'être refroidie. A cet effet, et de
façon connue en soi, l'aube mobile 10 comporte au moins un circuit de
refroidissement interne. Ce circuit de refroidissement se compose par
exemple d'au moins une cavité 24 s'étendant radialement entre le pied 14
et le sommet 16 de l'aube. Cette cavité est alimentée en air de
refroidissement à l'une de ses extrémités radiales par une ouverture
d'admission d'air (non représentée). Cette ouverture d'admission d'air est
généralement prévue au niveau de l'emmanchement 12 de l'aube. Il est
également prévu une pluralité de fentes 26 s'ouvrant dans la cavité 24 et
débouchant sur le bord de fuite 20 de l'aube afin d'évacuer l'air de
refroidissement s'écoulant dans la cavité. Ces fentes 26 d'évacuation de
l'air de refroidissement sont typiquement réparties le long du bord de fuite
20, entre le pied 14 et le sommet 16 de l'aube, de façon sensiblement
perpendiculaire à l'axe longitudinal X-X de l'aube.Such a dawn is subject to the very high temperatures of
combustion gas and therefore needs to be cooled. To this end, and
in known manner, the
La figure 2 illustre plus précisément la géométrie de la fente 28
la plus proche du pied 14 de l'aube 10. Conformément à l'invention, la
fente 28 la plus proche du pied de l'aube présente une inclinaison vers le
sommet 16 de l'aube comprise entre 10° et 30° par rapport à un axe de
rotation de l'aube (non représenté). De préférence, l'inclinaison de cette
fente est d'environ 20°. Cette inclinaison particulière de la fente 28 la plus
proche du pied de l'aube permet d'homogénéiser la température au niveau
de celle-ci et ainsi de supprimer tout point chaud. L'air de refroidissement
évacué par cette fente recouvre en effet toute la surface de la fente 28 et
en abaisse la température locale de 5% environ. Ainsi, tout risque de
crique au niveau de cette fente la plus proche du pied de l'aube disparaít
et la durée de vie de l'aube s'en trouve rallongée.Figure 2 illustrates more precisely the geometry of the
Selon une caractéristique avantageuse de l'invention, l'extrémité
amont 28a de la fente 28 la plus proche du pied 14 de l'aube est formée
essentiellement dans une zone de raccordement 30 entre le pied 14 de
l'aube et la plate-forme 22 du côté de la veine d'écoulement des gaz de
combustion de sorte que l'air évacué par celle fente a tendance à venir
refroidir par conduction thermique la zone de raccordement 30. La
température de la zone de raccordement 30 entre le pied 14 de l'aube et
la plate-forme 22 est ainsi abaissée d'environ 1,5%. Afin d'accentuer ce
refroidissement de la zone de raccordement 30, les angles vifs de
l'extrémité amont 28a de la fente 28 sont meulés pour faciliter le guidage
de l'air évacué par la fente vers cette zone 30. Par ailleurs, comme
l'extrémité aval 28b de la fente 28 la plus proche du pied de l'aube n'est
pas formée dans la zone de raccordement 30, la tenue de l'aube 10 aux
différentes contraintes mécaniques n'est pas affectée par cette géométrie
particulière de la fente.According to an advantageous characteristic of the invention, the end
upstream 28a of the
Claims (5)
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0115904 | 2001-12-05 | ||
| FR0115904A FR2833298B1 (en) | 2001-12-10 | 2001-12-10 | IMPROVEMENTS TO THE THERMAL BEHAVIOR OF THE TRAILING EDGE OF A HIGH-PRESSURE TURBINE BLADE |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1318274A1 true EP1318274A1 (en) | 2003-06-11 |
| EP1318274B1 EP1318274B1 (en) | 2004-09-22 |
Family
ID=8870271
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP02292970A Expired - Lifetime EP1318274B1 (en) | 2001-12-10 | 2002-12-03 | High-pressure turbine blade with cooled trailing edge |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US6830431B2 (en) |
| EP (1) | EP1318274B1 (en) |
| JP (1) | JP4012054B2 (en) |
| CA (1) | CA2412989C (en) |
| DE (1) | DE60201325T2 (en) |
| ES (1) | ES2225740T3 (en) |
| FR (1) | FR2833298B1 (en) |
| RU (1) | RU2297537C2 (en) |
| UA (1) | UA80246C2 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1726781A1 (en) * | 2005-04-01 | 2006-11-29 | The General Electric Company | Turbine airfoil with tapered trailing edge ribs |
| FR2924156A1 (en) * | 2007-11-26 | 2009-05-29 | Snecma Sa | Blade for use in high pressure turbine of e.g. turboprop engine, has ribs with ends formed closer to trailing edge in zone, and small ribs arranged closer to platform, where surfaces are connected at level of trailing and leading edges |
| WO2021259569A1 (en) * | 2020-06-22 | 2021-12-30 | Siemens Aktiengesellschaft | Turbine blade and method for machining same |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2864990B1 (en) * | 2004-01-14 | 2008-02-22 | Snecma Moteurs | IMPROVEMENTS IN THE HIGH-PRESSURE TURBINE AIR COOLING AIR EXHAUST DUCTING SLOTS |
| FR2887287B1 (en) * | 2005-06-21 | 2007-09-21 | Snecma Moteurs Sa | COOLING CIRCUITS FOR MOBILE TURBINE DRIVE |
| KR100847523B1 (en) * | 2006-12-29 | 2008-07-22 | 엘지전자 주식회사 | Turbo fan |
| US8002525B2 (en) * | 2007-11-16 | 2011-08-23 | Siemens Energy, Inc. | Turbine airfoil cooling system with recessed trailing edge cooling slot |
| US8157504B2 (en) * | 2009-04-17 | 2012-04-17 | General Electric Company | Rotor blades for turbine engines |
| FR2954798B1 (en) | 2009-12-31 | 2012-03-30 | Snecma | AUBE WITH INTERNAL VENTILATION |
| US8608429B2 (en) * | 2010-05-28 | 2013-12-17 | General Electric Company | System and method for enhanced turbine wake mixing via fluidic-generated vortices |
| US10107108B2 (en) | 2015-04-29 | 2018-10-23 | General Electric Company | Rotor blade having a flared tip |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3807892A (en) * | 1972-01-18 | 1974-04-30 | Bbc Sulzer Turbomaschinen | Cooled guide blade for a gas turbine |
| EP1128024A2 (en) * | 2000-02-23 | 2001-08-29 | Mitsubishi Heavy Industries, Ltd. | Gas turbine moving blade |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2121483B (en) * | 1982-06-08 | 1985-02-13 | Rolls Royce | Cooled turbine blade for a gas turbine engine |
| US4601638A (en) * | 1984-12-21 | 1986-07-22 | United Technologies Corporation | Airfoil trailing edge cooling arrangement |
| US5403158A (en) * | 1993-12-23 | 1995-04-04 | United Technologies Corporation | Aerodynamic tip sealing for rotor blades |
| WO1998000627A1 (en) * | 1996-06-28 | 1998-01-08 | United Technologies Corporation | Coolable airfoil for a gas turbine engine |
-
2001
- 2001-12-10 FR FR0115904A patent/FR2833298B1/en not_active Expired - Fee Related
-
2002
- 2002-11-25 US US10/303,012 patent/US6830431B2/en not_active Expired - Lifetime
- 2002-11-29 CA CA002412989A patent/CA2412989C/en not_active Expired - Lifetime
- 2002-12-03 EP EP02292970A patent/EP1318274B1/en not_active Expired - Lifetime
- 2002-12-03 ES ES02292970T patent/ES2225740T3/en not_active Expired - Lifetime
- 2002-12-03 DE DE60201325T patent/DE60201325T2/en not_active Expired - Lifetime
- 2002-12-04 JP JP2002352590A patent/JP4012054B2/en not_active Expired - Lifetime
- 2002-12-04 UA UA2002129702A patent/UA80246C2/en unknown
- 2002-12-09 RU RU2002132866/06A patent/RU2297537C2/en active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3807892A (en) * | 1972-01-18 | 1974-04-30 | Bbc Sulzer Turbomaschinen | Cooled guide blade for a gas turbine |
| EP1128024A2 (en) * | 2000-02-23 | 2001-08-29 | Mitsubishi Heavy Industries, Ltd. | Gas turbine moving blade |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1726781A1 (en) * | 2005-04-01 | 2006-11-29 | The General Electric Company | Turbine airfoil with tapered trailing edge ribs |
| CN1840859B (en) * | 2005-04-01 | 2012-08-08 | 通用电气公司 | Turbine airfoil with trailing edge convection |
| FR2924156A1 (en) * | 2007-11-26 | 2009-05-29 | Snecma Sa | Blade for use in high pressure turbine of e.g. turboprop engine, has ribs with ends formed closer to trailing edge in zone, and small ribs arranged closer to platform, where surfaces are connected at level of trailing and leading edges |
| WO2021259569A1 (en) * | 2020-06-22 | 2021-12-30 | Siemens Aktiengesellschaft | Turbine blade and method for machining same |
| US11867083B2 (en) | 2020-06-22 | 2024-01-09 | Siemens Energy Global GmbH & Co. KG | Turbine blade and method for machining same |
Also Published As
| Publication number | Publication date |
|---|---|
| CA2412989A1 (en) | 2003-06-05 |
| JP4012054B2 (en) | 2007-11-21 |
| JP2003193804A (en) | 2003-07-09 |
| US20030108425A1 (en) | 2003-06-12 |
| UA80246C2 (en) | 2007-09-10 |
| FR2833298B1 (en) | 2004-08-06 |
| ES2225740T3 (en) | 2005-03-16 |
| RU2297537C2 (en) | 2007-04-20 |
| DE60201325T2 (en) | 2005-03-17 |
| DE60201325D1 (en) | 2004-10-28 |
| FR2833298A1 (en) | 2003-06-13 |
| EP1318274B1 (en) | 2004-09-22 |
| US6830431B2 (en) | 2004-12-14 |
| CA2412989C (en) | 2008-09-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2652679C (en) | Blades for turbomachine impeller, with a groove for cooling | |
| EP1726783B1 (en) | Hollow rotor blade for the turbine of a gas turbine engine, provided with a tip cup | |
| FR2835015A1 (en) | HIGH-PRESSURE TURBINE MOBILE TURBINE WITH IMPROVED THERMAL BEHAVIOR LEAKAGE EDGE | |
| EP1612374B1 (en) | Turbine guide vane with improved cooling properties | |
| CA2493094C (en) | Improvements to turbine blade cooling air exhaust slots | |
| CA2550442C (en) | Cooling circuits for turbine moving blade | |
| CA2834213C (en) | Sealing device for a turbomachine turbine nozzle | |
| EP1318274B1 (en) | High-pressure turbine blade with cooled trailing edge | |
| CA2569563C (en) | Turbine blade with improved cooling characteristics and useful life | |
| FR2875262A1 (en) | METHODS AND DEVICES FOR ASSEMBLING ROTOR ASSEMBLIES OF GAS TURBINE ENGINES | |
| EP1790819A1 (en) | Cooling circuit for a turbine blade | |
| EP1598523A1 (en) | Wall structure for hollow gas turbine blades to increase the heat transfer | |
| EP1452695B1 (en) | Cooled turbine blade having reduced cooling air leakage | |
| EP1469165B1 (en) | Reduction of the blade tip clearance in a gas turbine | |
| EP1452691B1 (en) | Annular stator blade platform for low pressure turbine in a gas turbine engine | |
| FR3075869A1 (en) | MOBILE TURBINE WHEEL FOR AIRCRAFT TURBOMACHINE, COMPRISING A SEAL RING RADIALLY RETAINED BY INCREASES ON THE ECHASSE DES AUBES | |
| FR3066783B1 (en) | SHIRT FOR OPTIMIZED COOLING TURBINE BLADE | |
| EP3420198B1 (en) | Flow-straightener for aircraft turbomachine compressor, comprising air extraction openings having a stretched form in the peripheral direction | |
| EP3768949B1 (en) | Turbine vane comprising impingement cooling features | |
| FR3090032A1 (en) | BLADE FOR TURBOMACHINE WHEEL | |
| FR3080406A1 (en) | IMPROVED TURBINE DISPENSER FOR TURBOMACHINE | |
| FR2943380A1 (en) | Fixed vane for high pressure turbine distributor in turbomachine, has sleeve comprising slots extending from free end to secured end of sleeve, where free end is moved relative to internal edge of vane under thermal dilation effects | |
| FR3116857A1 (en) | turbomachine component comprising a wall provided with cooling means |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
| 17P | Request for examination filed |
Effective date: 20021207 |
|
| AK | Designated contracting states |
Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR IE IT LI LU MC NL PT SE SI SK TR |
|
| AX | Request for extension of the european patent |
Extension state: AL LT LV MK RO |
|
| AKX | Designation fees paid |
Designated state(s): DE ES FR GB IT SE |
|
| GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
| GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
| GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
| AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE ES FR GB IT SE |
|
| REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
| REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D Free format text: FRENCH |
|
| REF | Corresponds to: |
Ref document number: 60201325 Country of ref document: DE Date of ref document: 20041028 Kind code of ref document: P |
|
| REG | Reference to a national code |
Ref country code: SE Ref legal event code: TRGR |
|
| REG | Reference to a national code |
Ref country code: ES Ref legal event code: FG2A Ref document number: 2225740 Country of ref document: ES Kind code of ref document: T3 |
|
| REG | Reference to a national code |
Ref country code: IE Ref legal event code: FD4D |
|
| PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
| STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
| 26N | No opposition filed |
Effective date: 20050623 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: CD |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: ES Payment date: 20121205 Year of fee payment: 11 |
|
| REG | Reference to a national code |
Ref country code: ES Ref legal event code: FD2A Effective date: 20150407 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: ES Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20131204 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 14 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 15 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 16 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: CD Owner name: SAFRAN AIRCRAFT ENGINES Effective date: 20170719 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20211117 Year of fee payment: 20 Ref country code: SE Payment date: 20211119 Year of fee payment: 20 Ref country code: GB Payment date: 20211118 Year of fee payment: 20 Ref country code: FR Payment date: 20211118 Year of fee payment: 20 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20211117 Year of fee payment: 20 |
|
| REG | Reference to a national code |
Ref country code: DE Ref legal event code: R071 Ref document number: 60201325 Country of ref document: DE |
|
| REG | Reference to a national code |
Ref country code: GB Ref legal event code: PE20 Expiry date: 20221202 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION Effective date: 20221202 |
|
| REG | Reference to a national code |
Ref country code: SE Ref legal event code: EUG |