EP2607624B1 - Leitschaufel für eine Turbomaschine - Google Patents

Leitschaufel für eine Turbomaschine Download PDF

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Publication number
EP2607624B1
EP2607624B1 EP20110194338 EP11194338A EP2607624B1 EP 2607624 B1 EP2607624 B1 EP 2607624B1 EP 20110194338 EP20110194338 EP 20110194338 EP 11194338 A EP11194338 A EP 11194338A EP 2607624 B1 EP2607624 B1 EP 2607624B1
Authority
EP
European Patent Office
Prior art keywords
wall
vane
cooling fluid
openings
cooling
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.)
Not-in-force
Application number
EP20110194338
Other languages
English (en)
French (fr)
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EP2607624A1 (de
Inventor
Janos Szijarto
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.)
Siemens AG
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Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to ES11194338T priority Critical patent/ES2531065T3/es
Priority to EP20110194338 priority patent/EP2607624B1/de
Publication of EP2607624A1 publication Critical patent/EP2607624A1/de
Application granted granted Critical
Publication of EP2607624B1 publication Critical patent/EP2607624B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/186—Film cooling
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
    • F01D5/187—Convection cooling
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles

Definitions

  • the present invention relates to an airfoil for a turbomachine and more particularly to a vane for a turbomachine.
  • TMF Thermo-mechanical fatigue
  • An airfoil such as a vane has a leading edge and a trailing edge.
  • the leading edge of the airfoil portion of the vane is cooled by impingement cooling or by film cooling e.g. DE 4328401 and the trailing edge by matrix arrangement of ribs, pin-fins and so forth e.g. FR 2943380 .
  • film cooling e.g. DE 4328401
  • matrix arrangement of ribs, pin-fins and so forth e.g. FR 2943380 e.g. FR 2943380
  • the object is achieved by providing a vane for turbomachine according to claim 1 and a method according to claim 14.
  • the vane for a turbomachine includes atleast one inner cavity defined by an inner wall having a plurality of impingement holes, and an outer wall surrounding the inner wall forming a passageway therebetween for a cooling fluid to pass through the impingement holes from the inner cavity towards the passageway, wherein the outer wall comprises a plurality of openings for exit of the cooling fluid such that the outer wall is divided into a plurality of portions disconnected from each other by openings allowing independent thermal expansion of said portions.
  • the passageway improves cooling of the vane at both the inner wall and outer wall.
  • the opening in the outer wall provides the exit of the cooling fluid which results in film cooling at the outer wall thereby reducing the temperature. Additionally, by having the openings formed in the outer wall as a result of plurality of portions of the outer wall which are disconnected with each other ensures sufficient amount of thermal expansion without causing stress over the other portion of the outer wall. This arrangement obviates the strain caused due to thermo-mechanical fatigue in the vane.
  • the openings extend in a direction radial to an axis of rotation of a rotor of the turbomachine.
  • the openings form channels by a first front face of the first portion of the outer wall and a second front face of the second portion of the outer wall for cooling fluid, wherein atleast one of the front faces is provided with protrusions extending into said channel's width, wherein said protrusions are provided with contact surfaces and are designed such that said contact surfaces contact said respective opposite front face under full temperature conditions due to the thermal expansion of said outer wall portions. Due to the presence of such an arrangement, exit of the cooling fluid is achieved even when the portions of the outer wall are in contact with each other, thus allowing cooling of the outer wall of the vane.
  • the inner wall defines the structure of the vane including the inner cavities and the matrix arrangement of ribs at the trailing edge.
  • the vane in another embodiment, includes a trailing section and the leading section, the cooling fluid is directed to the trailing edge through the passageway in the trailing section. Such an arrangement ensures cooling fluid to move to the trailing edge and provide a cooling therein.
  • the opening for exit of cooling fluid is a slot. Slot ensures that only a limited amount cooling fluid passes through thereby ensuring film cooling. Additionally during thermal expansion, slots allow the cooling fluid to exit the outer wall of the vane thereby aiding in film cooling.
  • the openings are configured to partially exit the cooling fluid. This ensures cooling fluid to cool internal structures and some of the fluid to be directed to other parts of the vane including the trailing edge.
  • the openings extend through the outer wall inclined to a surface normal to the outer wall so as to prevent the entire cooling fluid to exit through the openings.
  • the outer wall is connected to the inner wall at a plurality of locations to ensure a strong attachment between the outer wall and the inner wall.
  • the outer wall and the inner wall are formed using laser sintering technique. This ensures forming a desired three dimensional shape with an outer wall and inner wall and passageway with channels to ensure cooling effectiveness.
  • the outer wall and the inner wall are formed of same material so that the thermal expansion is similar throughout the component and also the cooling rate is same at all the portions of the component.
  • Embodiments of the present invention relate to an airfoil in a turbomachine, more particularly to an airfoil of a vane component for the turbomachine.
  • the turbomachine may include a gas turbine, a steam turbine, a turbofan and the like.
  • FIG. 1 is a schematic diagram depicting an exemplary vane 10 of a turbomachine, such as a gas turbine, in accordance with aspects of the present technique.
  • the vane 10 includes an airfoil portion 12 formed from an outer wall 14 and having a leading edge 16 and a trailing edge 18 enclosed between a first end wall 20 and a second end wall 22 opposite each other as depicted in FIG. 1 .
  • the exemplary vane 10 includes one or more inner cavities 28 for a supply of cooling fluid, which may include cooling air for cooling the vane 10 during operation.
  • Reference numeral 26 is indicative of a flow of cooling fluid inside the vane of the turbomachine.
  • the outer wall 14 includes one or more openings 24 extending from the first end wall 20 to the second end wall 22 for exiting the cooling fluid from the vane 10 thereby providing film cooling at the outer wall 14 of the vane 10.
  • the openings 24 extend in a radial direction to an axis of rotation of a rotor (not shown) of the turbomachine which is enclosed by a stator securing the vanes, such as the vane 10.
  • the airfoil portion 12 of the vane 10 may be cast as a single component or may alternatively be assembled from multiple components.
  • the multiple component vane may include a leading edge component, a trailing edge component and core region components.
  • the components may be cast separately and thereafter joined together by bonding or brazing for example.
  • the vane 10 may be formed by a technique, such as but not limited to laser sintering, which enables forming multiple layers in the vane 10.
  • the vane 10 may be formed by using an investment casting technique.
  • An inner wall 30 defines the internal structure of the vane.
  • the vane includes one or more inner cavities 28 for supply of cooling fluid or cooling air.
  • the inner cavities 28 are defined by the inner wall 30 which extends from a pressure side 32 to a suction side 34 present on opposing sides of the airfoil 12.
  • the inner wall 30 includes one or more impingement holes 40 extending from the leading edge 16 to the trailing edge 18 of the airfoil 12.
  • the cooling fluid entering the one or more inner cavities 28 exits through the impingement holes 40, resulting in impingement cooling of the inner wall 30.
  • the airfoil 12 of the vane 10 includes the outer wall 14 which surrounds the inner wall 30 forming a passageway 36 therebetween for circulating the cooling air in the one or more sections 42, 44, 46, 48 of the vane 10.
  • the internal structure of vane 10 is defined by the inner wall 30.
  • the inner wall 30 extends from the leading edge 16 to the trailing edge 18 and further extends from the pressure side 32 to the suction side 34 forming one or more inner cavities 28 therein.
  • the airfoil 12 includes the outer wall 14 surrounding the inner wall 30, which also extends from the leading edge 16 to the trailing edge 18.
  • the outer wall 14 and the inner wall 30 are attached to each other at one or more locations over the extent of the airfoil 12.
  • the inner wall 30 and the outer wall 12 may be attached with each other by using laser sintering technique.
  • the outer wall 14 and the inner wall 30 are formed by use of laser sintering technique.
  • the laser sintering technique uses high power laser to fuse small particles of metals for example to form a desired three dimensional shape.
  • the outer wall 14 is formed from a plurality of portions, such as a first portion 15 and a second portion 17 such that an opening 24 is formed between the portions.
  • the outer wall 14 also includes a plurality of film cooling holes 50 at a portion forming the leading edge 16, as depicted in FIG. 2 .
  • the openings 24 in the outer wall 14 extend from the first end wall 20 to a second end wall 22 (see FIG. 1 ).
  • a cooling fluid such as, but not limited to cooling air enters the inner cavities 28 in the airfoil 12 of the vane 10, thereafter the cooling fluid is directed to the passageway 36 between the inner wall 30 and the outer wall 14 through impingement holes 40 present in the inner wall 30.
  • the cooling fluid cools the outer wall portions and exits through the openings 24.
  • the cooling fluid may also include a coolant, oil or steam for example.
  • openings 24 extend through the outer wall 14 inclined to a surface normal to the outer wall 14. It may be noted that the angle of inclination may be greater than 0 degree and less than 90 degrees.
  • the openings 24 in the outer wall 14 allow a portion of the cooling fluid to exit the outer wall 14 thereby providing film cooling at the surface of the vane 10.
  • the vane 10 gets heated resulting in thermal expansion.
  • the openings 24 in the outer wall 14 are disconnected with each other.
  • the openings 24 in the outer wall 14 thus obviate the stress caused due to thermal expansion.
  • the inner wall 30 and the outer wall 14 may be formed from a same material. More particularly, the inner wall 30 and the outer wall 14 may be formed of metal or metal alloy capable of withstanding high temperatures, which may sometimes reach about 800 degree centigrade. Such high temperatures result in thermal expansion which may damage the vane component.
  • the openings 24 in the outer wall 14 allow for thermal expansion and thus reduce stress on the vane 10.
  • the opening 24 in the outer wall 14 may include a plurality of slots to allow a portion of cooling air to exit even when the opening is closed due to the expansion of the first portion 15 and the second portion 17 of the outer wall 15, for example.
  • Such an arrangement provides escape of cooling fluid and hence aids in film cooling.
  • the rest of the air cools the internal structure of the vane 10.
  • the inner wall 30 and the outer wall 14 are cooled resulting in an increase in the temperature of cooling fluid.
  • the hot air is then convectively circulated in the passageway 36 between the inner wall 30 and the outer wall 14 and directed out of the vane through the opening 24 thus dissipating the heat from the vane 10.
  • FIG. 3 is a cross sectional view of vane 10 of FIG. 1 .
  • the vane 10 is divided into a plurality of sections formed by the inner wall 30.
  • the leading section 42, the middle sections 44, 46 and the trailing section 48 each have an inner cavity 28 for receiving a cooling fluid, such as cooling air.
  • the vane 10 includes the outer wall 14 surrounding the inner wall 30 as depicted in FIG. 3 .
  • the outer wall 14 is attached to the inner wall 30 at one or more locations 52, 54 and forms a passageway 36 for cooling fluid for each section 42, 44, 46, 48. Specifically, atleast a portion of the outer wall 14 is attached to the inner wall 30 at the one or more locations 52, 54.
  • the inner wall 30 and outer wall 14 may be connected to each other by connecting-pins or connecting-ribs such that the connecting-ribs or connecting-pins allow thermal expansion of the portions in circumferential direction of a profile of the vane.
  • the inner wall 30 of the vane 10 includes a plurality of holes 40 to allow the cooling air to pass through.
  • the cooling fluid from each of the section 42, 44, 46, 48 passes through the holes 40 into the passageway 36 between the outer wall 14 and the inner wall 30.
  • the outer wall 14 includes openings 24 to allow the cooling fluid to exit.
  • the cooling fluid is directed to the passageway 36 through the holes 40 in the inner wall 30.
  • a portion of the cooling air is supplied to a matrix arrangement of ribs 60 and pins or fins (not shown) to cool the trailing section 48 and directed out of the vane 10 through the trailing edge 18.
  • the remaining portion of the cooling fluid is exited outside the vane 10 through the opening 24 in the outer wall 14, thereby providing film cooling.
  • cooling fluid in the passageway 36 is opposite to the flow of hot gas in the airfoil 12 of the vane 10. In other words, cooling fluid flows in counterflow to the hot gas in the airfoil 12.
  • the outer wall 14 portion at the leading section 42 includes a plurality of holes 50 to allow for film cooling. Furthermore, the leading section 42 also includes opening 24 in the outer wall 14 which is inclined with respect to a surface normal to the outer wall 14, which improves the cooling at the leading section 42 of the vane 10.
  • FIG. 4 is a blown up view 62 of the vane 10, depicting the outer wall 14 in accordance with aspects of the present technique.
  • the outer wall 14 includes a plurality of portions, such as the first portion 15 and the second portion 17 forming opening 24 which is formed due to a gap between the portions of the outer wall 14.
  • the first portion 15 of the outer wall 14 includes a plurality of protrusions 25 spaced apart forming a plurality of slots 27 in between as depicted in FIG. 4 .
  • the plurality of slots 27 are in the form of channels formed by a first front face of the first portion 15 and a second front face of the second portion of the outer wall for the cooling fluid to pass through the slots 27.
  • the vane 10 is exposed to high operating temperatures, which results in thermal expansion of outer wall 14, since the wall 14 is formed of the first portion 15 and the second portion 17, therefore the first portion 15 and the second portion 17 expand thereby getting in contact with each other. More particularly, the protrusions 25 on the first portion 15 get in contact with the second portion 17 of the outer wall 14.
  • the slots 27 allow the cooling fluid to exit the outer wall of the vane.
  • the protrusions 25 may be present on the front faces of the first portion 15 or the second portion 17, the protrusions 25 are provided with contact surfaces 29 which get in contact with the opposite front face under full operating temperature condition due to the thermal expansion of the portions of the outer wall 14.
  • the method 70 includes providing a plurality of impingement holes 40 in the inner wall 30 of the vane 10.
  • the impingement holes 40 may be formed during casting process, alternatively, the impingement holes 40 may be formed in the inner wall 30 by selective laser sintering technique.
  • the inner wall 30 is designed such that it forms one or more inner cavities 28 therein as at step 72.
  • the inner wall 30 is surrounded by an outer wall 14 by attaching at one or more locations 52, 54, such that a passageway 36 is formed between the inner wall 30 and the outer wall 14.
  • a cooling fluid entering the inner cavities 28 is directed towards the passageway 36 through the impingement holes 40 in the inner wall 30.
  • the cooling fluid is exited from the vane 10 through one or more openings 24 in the outer wall 14.
  • the openings 24 are formed by assembling the outer wall 14 as a plurality of portions, such as the first portion 15 and the second portion 17 (see FIG. 2 and FIG. 4 ).
  • the openings 24 are formed as slots 27 in the outer wall 14 for the exit of cooling fluid from the vane 10.
  • the exiting cooling fluid forms a film of cooling air over the outer wall 14 thereby dissipating the heat from the vane 10.

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

Claims (14)

  1. Leitschaufel (10) für eine Turbomaschine, umfassend:
    - mindestens einen Innenhohlraum (28), der durch eine Innenwand (30) definiert ist, die eine Vielzahl von Prallkühlbohrungen (40) aufweist, und
    - eine Außenwand (14), welche die Innenwand (30) umgibt und dazwischen einen Durchlasskanal (36) bildet, damit ein Kühlfluid durch die Prallkühlbohrungen (40) hindurch aus dem Innenhohlraum (28) zu dem Durchlasskanal (36) hin strömt, wobei die Außenwand (14) eine Vielzahl von Öffnungen (24) für den Austritt des Kühlfluids umfasst,
    dadurch gekennzeichnet, dass
    die Außenwand (14) in eine Vielzahl von Abschnitten (15, 17) aufgeteilt ist, die durch eine Öffnung (24) voneinander getrennt sind, wobei sich diese Öffnung in einer zu einer Drehachse eines Rotors der Turbomaschine radialen Richtung zwischen einem ersten und einem zweiten Abschnitt (15, 17) erstreckt, was eine unabhängige Wärmedehnung dieser Abschnitte (15, 17) ermöglicht.
  2. Leitschaufel (10) nach Anspruch 1, wobei die Öffnungen (24) durch eine erste Stirnseite des ersten Abschnitts (15) der Außenwand (14) und eine zweite Stirnseite des zweiten Abschnitts (17) der Außenwand (14) Kanäle für Kühlfluid bilden, wobei mindestens eine der Stirnseiten mit Vorsprüngen (25) versehen ist, die sich in die Breite des Kanals hinein erstrecken, wobei diese Vorsprünge (25) mit Kontaktflächen (29) versehen sind und derart ausgebildet sind, dass diese Kontaktflächen (29) unter Bedingungen der vollen Betriebstemperatur infolge der Wärmedehnung der Außenwandabschnitte (15, 17) mit der jeweiligen gegenüberliegenden Stirnseite in Kontakt kommen.
  3. Leitschaufel (10) nach Anspruch 1, welche ferner einen Vorderabschnitt (42) und einen Hinterabschnitt (48) umfasst, wobei das Kühlfluid an dem Hinterabschnitt (48) über den Durchlasskanal (36) zu einer Hinterkante (18) der Leitschaufel (10) geleitet wird.
  4. Leitschaufel (10) nach einem der Ansprüche 1 bis 3, wobei die Öffnungen (24) eine Vielzahl von Schlitzen (27) umfassen.
  5. Leitschaufel (10) nach einem der Ansprüche 1 bis 4, wobei sich die Öffnungen (24) zu einer zu der Außenwand (14) senkrechten Fläche geneigt durch die Außenwand (14) erstrecken.
  6. Leitschaufel (10) nach einem der Ansprüche 1 bis 5, wobei die Öffnungen (24) dafür ausgebildet sind, wenigstens teilweise das Kühlfluid auszuspeisen.
  7. Leitschaufel (10) nach einem der Ansprüche 1 bis 6, wobei die Außenwand (14) an der Innenwand (30) befestigt ist.
  8. Leitschaufel (10) nach Anspruch 7, wobei die Außenwand (14) an mehreren Stellen (52, 54) an der Innenwand (30) befestigt ist.
  9. Leitschaufel (10) nach Anspruch 7 und 8, wobei die Außenwand (14) an der Innenwand (30) durch Lasersintertechnologie befestigt ist.
  10. Leitschaufel (10) nach einem der Ansprüche 1 bis 9, wobei die Innenwand (30) und die Außenwand (14) durch Verbindungsbolzen oder Verbindungsrippen miteinander verbunden sind, wobei die Verbindungsrippen oder Verbindungsbolzen eine Wärmedehnung der Abschnitte in Umfangsrichtung eines Profils der Leitschaufel ermöglichen.
  11. Leitschaufel (10) nach einem der Ansprüche 1 bis 10, welche ferner eine Matrixanordnung von Rippen (60) zum Kühlen der Hinterkante (18) umfasst.
  12. Leitschaufel (10) nach einem der Ansprüche 1 bis 11, wobei das Kühlfluid in einer Richtung strömt, die zu einem Strom von Heißgas in dem Schaufelblatt (12) der Leitschaufel entgegengesetzt ist.
  13. Turbomaschine, welche die Leitschaufel (10) nach einem der vorhergehenden Ansprüche 1 bis 12 umfasst.
  14. Verfahren (70) zum Kühlen einer Leitschaufel (10) nach einem der Ansprüche 1 bis 13, welches umfasst:
    - Lenken (76) eines Kühlfluids aus dem Innenhohlraum der Leitschaufel (10) über die Prallkühlbohrungen der Leitschaufel (10) zu dem Durchlasskanal der Leitschaufel (10) hin, und
    - Ausspeisen (78) des Kühlfluids der Leitschaufel (10) aus der Leitschaufel (10) durch eine oder mehrere der Öffnungen in der Außenwand der Leitschaufel (10).
EP20110194338 2011-12-19 2011-12-19 Leitschaufel für eine Turbomaschine Not-in-force EP2607624B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
ES11194338T ES2531065T3 (es) 2011-12-19 2011-12-19 Alabe para una turbomáquina
EP20110194338 EP2607624B1 (de) 2011-12-19 2011-12-19 Leitschaufel für eine Turbomaschine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20110194338 EP2607624B1 (de) 2011-12-19 2011-12-19 Leitschaufel für eine Turbomaschine

Publications (2)

Publication Number Publication Date
EP2607624A1 EP2607624A1 (de) 2013-06-26
EP2607624B1 true EP2607624B1 (de) 2014-12-17

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EP20110194338 Not-in-force EP2607624B1 (de) 2011-12-19 2011-12-19 Leitschaufel für eine Turbomaschine

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EP (1) EP2607624B1 (de)
ES (1) ES2531065T3 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9850763B2 (en) 2015-07-29 2017-12-26 General Electric Company Article, airfoil component and method for forming article

Families Citing this family (13)

* Cited by examiner, † Cited by third party
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US20160222796A1 (en) * 2013-09-18 2016-08-04 United Technologies Corporation Manufacturing method for a baffle-containing blade
EP3002415A1 (de) 2014-09-30 2016-04-06 Siemens Aktiengesellschaft Turbomaschinenkomponente, insbesondere einer Gasturbinenkomponente mit gekühlter Wand und Verfahren zur Herstellung
EP3248727A1 (de) * 2016-05-23 2017-11-29 Siemens Aktiengesellschaft Turbinenschaufel und verfahren zur herstellung der turbinenschaufel
US10655477B2 (en) * 2016-07-26 2020-05-19 General Electric Company Turbine components and method for forming turbine components
US10364685B2 (en) 2016-08-12 2019-07-30 Gneral Electric Company Impingement system for an airfoil
US10436048B2 (en) 2016-08-12 2019-10-08 General Electric Comapny Systems for removing heat from turbine components
US10408062B2 (en) 2016-08-12 2019-09-10 General Electric Company Impingement system for an airfoil
US10443397B2 (en) 2016-08-12 2019-10-15 General Electric Company Impingement system for an airfoil
US10260363B2 (en) 2016-12-08 2019-04-16 General Electric Company Additive manufactured seal for insert compartmentalization
DE102017215371A1 (de) * 2017-09-01 2019-03-07 Siemens Aktiengesellschaft Hohlleitschaufel
CN112523812B (zh) * 2020-12-02 2021-09-03 北京南方斯奈克玛涡轮技术有限公司 一种有支撑结构的涡轮导向器叶片
CN113914938B (zh) * 2021-12-10 2022-02-22 中国航发燃气轮机有限公司 一种燃气轮机透平气冷叶片
CN114872909B (zh) * 2022-05-06 2023-03-24 中国航发四川燃气涡轮研究院 飞机型涡轮叶片冷却通道换热结构

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0663442B2 (ja) * 1989-09-04 1994-08-22 株式会社日立製作所 タービン翼
DE4328401A1 (de) * 1993-08-24 1995-03-02 Abb Management Ag Turbinenschaufel für eine Gasturbine
US6237344B1 (en) * 1998-07-20 2001-05-29 General Electric Company Dimpled impingement baffle
US6514046B1 (en) * 2000-09-29 2003-02-04 Siemens Westinghouse Power Corporation Ceramic composite vane with metallic substructure
FR2943380B1 (fr) * 2009-03-20 2011-04-15 Turbomeca Aube de distributeur comprenant au moins une fente
US8206109B2 (en) * 2009-03-30 2012-06-26 General Electric Company Turbine blade assemblies with thermal insulation
CA2696274A1 (en) * 2010-03-11 2011-09-11 General Electric Company Method for fabricating turbine airfoils and tip structures therefor

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9850763B2 (en) 2015-07-29 2017-12-26 General Electric Company Article, airfoil component and method for forming article

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Publication number Publication date
ES2531065T3 (es) 2015-03-10
EP2607624A1 (de) 2013-06-26

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