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EP1331361A1 - Aube de turbine et dispositif de moulage pour la fabrication d' une aube de turbine - Google Patents

Aube de turbine et dispositif de moulage pour la fabrication d' une aube de turbine Download PDF

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Publication number
EP1331361A1
EP1331361A1 EP02001265A EP02001265A EP1331361A1 EP 1331361 A1 EP1331361 A1 EP 1331361A1 EP 02001265 A EP02001265 A EP 02001265A EP 02001265 A EP02001265 A EP 02001265A EP 1331361 A1 EP1331361 A1 EP 1331361A1
Authority
EP
European Patent Office
Prior art keywords
platform
blade
turbine blade
turbine
casting
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
EP02001265A
Other languages
German (de)
English (en)
Other versions
EP1331361B1 (fr
Inventor
Peter Tiemann
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP02001265A priority Critical patent/EP1331361B1/fr
Priority to AT02001265T priority patent/ATE467749T1/de
Priority to DE50214427T priority patent/DE50214427D1/de
Priority to JP2003005500A priority patent/JP4303480B2/ja
Priority to CNB031075010A priority patent/CN100447374C/zh
Priority to US10/345,947 priority patent/US6923620B2/en
Publication of EP1331361A1 publication Critical patent/EP1331361A1/fr
Application granted granted Critical
Publication of EP1331361B1 publication Critical patent/EP1331361B1/fr
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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/22—Moulds for peculiarly-shaped castings
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/915—Pump or portion thereof by casting or molding
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making

Definitions

  • the invention relates to a turbine blade with a profiled, along a blade axis extended Airfoil, to the end one transverse to the blade axis extending platform is formed. It concerns Furthermore, a casting system for producing such a turbine blade.
  • Gas turbines are used in many areas to drive generators or used by work machines. It is the Energy content of a fuel for generating a rotational movement used a turbine shaft.
  • the fuel will burned in a combustion chamber, being used by an air compressor compressed air is supplied. That in the combustion chamber produced by the combustion of the fuel, under high Pressure and high temperature working medium is doing via a turbine downstream of the combustion unit led, where it relaxes work.
  • For guiding the flow medium in the turbine unit are also usually between adjacent blade rows with the turbine housing connected Leitschaufelhalln arranged.
  • the turbine blades, in particular the guide vanes usually have for the suitable guidance of the working medium a profiled, along a blade axis extended blade on, at the end for attachment of the turbine blade on the respective support body a transverse to Blade axis extending, in at least one end as Hook base trained platform is formed.
  • Such gas turbines for thermodynamic reasons usually for particularly high outlet temperatures of the Combustion off and in the flowing into the turbine unit Working medium from about 1200 ° C to about 1300 ° C. designed.
  • the components are the gas turbine, in particular the turbine blades, comparatively exposed to high thermal loads.
  • a high reliability and a long life of the respective components to ensure the affected components are common cooled formed.
  • the turbine blades are common in modern gas turbines designed as a so-called hollow profile.
  • the profiled Airfoil features in its interior too referred to as vane core cavities in which a Cooling medium can be performed.
  • Coolant channels By the thus formed Coolant channels is thus an admission of the thermally stressed areas of the respective Blade with coolant allowed.
  • a particularly cheap Cooling effect and thus a particularly high level of operational safety is achievable by the coolant channels a comparatively large spatial area inside the respective Occupy the airfoil, and by the coolant as possible close to the respective, the hot gas exposed surface is guided.
  • sufficient mechanical stability and resilience can ensure the particular turbine blade flowed through several channels, wherein inside the blade profile a plurality of coolant, each other by comparatively thin partitions separate coolant channels are provided.
  • Such turbine blades are usually by casting manufactured.
  • a first casting step an in its contour adapted to the desired blade profile mold poured out with wax.
  • core elements for example made of ceramic material arranged after the casting from the Wax model can be removed for the blade body, so that the desired for the coolant channels cavities arise.
  • the wax model obtained in the first casting step subsequently becomes by repeated immersion with a ceramic coating Provided. Once this, if necessary after several Dipping operations, has a sufficient thickness is burned out the ceramic model provided with the wax model, where the ceramic solidifies and the wax burned out becomes.
  • this ceramic casting mold becomes poured out with blade material.
  • Mask elements or slider such in the mold arranged for the first casting step that during the casting process one of the blade shape to be produced corresponding Cavity for receiving the wax remains.
  • the invention is based on the object, a turbine blade of the abovementioned type, on the one hand for a designed especially high thermal and mechanical strength is, and on the other hand, a reliable cooling with comparatively low demand for coolant is. Furthermore, a for the production of the turbine blade suitable casting system can be specified.
  • this object is achieved according to the invention solved by the platform one compared to Platform bottom has thickened outer edge, whose the Airfoil facing side wall based on the blade axis is guided bevelled.
  • the invention is based on the consideration that the turbine blade for a particularly favorable manufacturability in should be configured monocrystalline construction.
  • a turbine blade in single-crystal construction is already due to the material properties comparatively high load capacity.
  • a monocrystalline construction is in particular by the use of also referred to as a slider mask elements cheaper for casting, especially as an alternative usable so-called lost inserts for nucleation polycrystalline material would contribute and thus for monocrystalline blades are not usable.
  • the turbine blade should thus be designed in their contouring be that in a relatively simple manner positioning and after casting a removal of the formation of Platform recesses used masking elements or slides is possible. Even with compliance with these boundary conditions However, the turbine blade should be for a comparatively be designed low demand for coolant.
  • the turbine blade is advantageously a function separation between the for the recording of the mechanical Load on the one hand and for absorbing the thermal load on the other hand provided for components.
  • a hook base formed in an advantageous embodiment of the blade of the Turbine bucket in the end area above the platform.
  • turbine blades at more reliable mechanical suspension a particularly high stability to allow for thermal stress, are advantageously in the area of entanglement of the turbine blade the platform and the hook base from each other structurally decoupled trained. It serves to the Airfoil molded platform for compensation only the thermal load of that in the interior the gas turbine guided hot working medium without it a mechanical load would be connected.
  • the Platform preferably comparatively thin-walled, which is particularly made possible by the fact that the platform is not exposed to any mechanical stress.
  • the mechanical load is carried out via a above the Platform arranged hook base, which is in a corresponding Structural part hung on the turbine wall or the turbine shaft is.
  • the hook base is expediently for the assumption of mechanical stress sufficiently dimensioned designed, with an impact on the hook base avoided by thermal stress through the platform is. The cooling requirement for the hook base is thus comparatively low.
  • the outer edge of the platform can in particular one with regard to guided on the blade axis substantially rectilinear, so aligned in cross section parallel to this have outer side wall.
  • the outer edge is thus in its platform floor facing area performed comparatively thick and Tapered in cross-section steadily up to his Platform floor facing away from the end.
  • To be reliable in this case To ensure cooling of all room areas of the outer edge, should be special funds for an admission the comparatively thick lower space of the outer edge be provided.
  • the cooling holes are in further advantageous Design on the output side in a common Cooling gap led.
  • the turbine blade can act as a blade for a turbine be provided.
  • the turbine blade as a guide vane for a gas turbine, in particular for a stationary gas turbine trained.
  • the casting system for producing such a turbine blade directed task is solved with one in one Mold positionable first mask element having a an interface of the platform floor predetermining recess has, and in which a substantially flat trained second mask element in one at an angle of more as 10 ° and less than 80 °, preferably less than 60 ° tilted against the boundary surface predetermining recess Directed displaced.
  • the first mask element as a circumferential slide and the second mask element also referred to as a pocket slide is to make a platform bag with bevelled side walls even without using a "lost Use.
  • the casting system is thus suitable in particular for the production of single-crystalline turbine blades, especially because of the conscious renunciation of the use of "lost missions” a nucleation for polycrystalline Areas is kept very low.
  • a substantially planar formed platform floor has the second mask element advantageously one compared to its base by an adapted Angle of more than 10 ° and less than 80 ° tilted Face on, which together with the recess of the first Mask element forms a casting mask for the platform floor.
  • the advantages achieved by the invention are in particular in that through the obliquely guided side wall of Platform bag, which by the in the first mask element or the circumferential slide arranged, obliquely in the circumferential direction sitting second mask element or the separate slide produced is an undercut of the ribbing of the profile can be avoided for entanglement.
  • This is both Mask elements removable after completion of the casting process, so that the use of a "lost mission" is not required.
  • cooling holes is also a reliable Cooling of all room areas of the platform with comparatively low coolant requirement allows, in particular by the comparatively broad base of the outer edge of the Platform the significant for coolant consumption impact-cooled Surface can be kept comparatively small. Due to the widening of the outer edge in the area of the platform floor is also comparatively in the operation of the turbine blade warm proportion compared to the colder part especially large, so that by impaired thermal expansions in the blade material induced voltages comparatively are kept low.
  • the turbine blade 1 according to the figure has a profiled Airfoil 2, which extends along a blade axis. 4 extends.
  • the blade 2 is suitable for influencing a flowing in an associated turbine unit Fluid medium curved and / or curved.
  • the turbine blade 1 in the embodiment is as a guide vane designed for a gas turbine; after the following but could also be a blade be designed. This is the end in the presentation after the figure upper end of the airfoil 2 at this is a transverse to the blade axis 4 extending platform 6 molded. In the sense of the representation after the figure is arranged above the platform 6 or overlying
  • a hook base 8 is formed, which is not shown in detail Way is attachable to a turbine housing.
  • the Hook base 8 is connected to an adjacent structural element in Intervention brought, so that in a particularly simple way a Attachment of the turbine blade 1 to a support body allows is.
  • the turbine blade 1 is for use seen in the direction of flow of the working medium second guide vane row of the gas turbine provided so that the hook base 8 both front and back for a suspension is configured in a structural element.
  • the turbine blade 1 is for use in a thermal comparatively highly loaded space area of the gas turbine educated. On the one hand, this is a consistent functional Separation of the absorption of thermal loads and mechanical Loads of the turbine blade 1 by different Structural parts provided. This is through the separate Arrangement of the platform 6 and the hook base 8 guaranteed.
  • the platform 6 is in fact the exclusive Recording of the gas turbine flowing through the hot Working fluid outgoing thermal load without the Platform 6 would be exposed to mechanical stress.
  • the platform 6 has a comparatively thin-walled design Platform bottom 12, in its planar design essentially as a radiation shield for those of the Turbines flowing through working fluid output heat output acts.
  • Platform bottom 12 For a possible connection with surrounding Structural elements, for example by entanglement, and / or for a stiffening with regard to a self-supporting mechanical Stability is the platform 6 with a thickened Edge or a ribbing executed and points to it a thickened compared to the platform bottom 12 outer edge 14 on.
  • By the outer edge 14 and the platform floor 12 is formed thus in the manner of a depression a so-called Platform pocket.
  • the turbine blade 1 designed such that even under Avoiding an undercut with the in the respective Spatial area protruding hook base 8 and thus underpassure the respective hook base 8, the reversible introduction a molding in the space area of the outer edge 14 recess formed together with the platform bottom 12 is possible.
  • the Blade axis 4 facing side wall 16 of the outer edge 14th With reference to the blade axis 4 seen chamfered out.
  • the angle ⁇ characterizing this bevel is too more than 10 ° and less than 80 °, namely in the embodiment to about 45 °, chosen.
  • the outer edge 14 thus has in its platform bottom 12th facing bottom region a comparatively wide cross-section moving towards his from the platform ground 12 facing away from end 18 towards increasingly tapered.
  • This upper end region of the outer edge 14 is thus due the comparatively small amount of material with comparatively simple means and in particular using a limited amount of coolant reliable cooled.
  • the platform bottom 12 facing lower area the outer edge 14 is in this Area with a number of acted upon by a coolant Cooling holes 20 provided. These flow into theirs Outlet area in a common cooling gap 22nd
  • the turbine blade 1 is for a high thermal capacity designed for high mechanical strength. Is to the turbine blade 1 carried out in a single-crystal construction. In compliance with the intended boundary conditions is the turbine blade 1 thereto using a in the figure only partially illustrated casting system 30 produced by casting.
  • the casting system 30, which is essentially when creating a wax model for the turbine blade 1 is used, comprises as a basic element a non-illustrated mold. In this mold a number of mask elements are positionable in their entirety one of the contour of the turbine blade to be produced 1 corresponding cavity release, in a subsequent step fillable with pourable wax is.
  • required elements includes the casting system 30, in particular a first mask element 32, which in the Art a circumferential slide can be used.
  • the first mask element 32 includes besides other structure defining features one predetermining the interface of the platform floor 12 Recess 34.
  • the first mask element 32 is for final shaping for the platform 6 is supplemented by a second mask element 36, formed substantially flat and in the first mask element 32 is slidably guided.
  • casting position protrudes the second mask member 36 so into the recess 34 of the first mask element 32, that only one to the final shape of the platform 6 adapted space area is released. This gives thus both the platform floor 12 and the outer edge 14 of the Platform 6 in front.
  • the second mask element 36 in one to one Angle ⁇ of about 45 ° with respect to the interface of the Platform floor 12 vor accommodateden recess. 34 tipped, displaced by the double arrow 38 direction indicated arranged. In this way is a distance of the second Mask element 36 from the wax model of the turbine blade 1 after its casting by simply moving in the direction of Double Arrow 38 allows without passing through the hook base 8 would be impaired.
  • the hook base 8 is for in its lateral extent dimensioned so that he indicated by the line 40 space area for the second Mask element 36 is not affected.
  • the second mask member 36 also has an opposite its base 42 by an angle ⁇ of the embodiment about 45 ° tilted end face 44, the together with the recess 34 of the first mask element forms a casting mask for the platform floor 12.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
EP02001265A 2002-01-17 2002-01-17 Aube statorique de turbine coulée ayant un crochet de fixation Expired - Lifetime EP1331361B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP02001265A EP1331361B1 (fr) 2002-01-17 2002-01-17 Aube statorique de turbine coulée ayant un crochet de fixation
AT02001265T ATE467749T1 (de) 2002-01-17 2002-01-17 Gegossene turbinenleitschaufel mit hakensockel
DE50214427T DE50214427D1 (de) 2002-01-17 2002-01-17 Gegossene Turbinenleitschaufel mit Hakensockel
JP2003005500A JP4303480B2 (ja) 2002-01-17 2003-01-14 タービン翼とその鋳造装置
CNB031075010A CN100447374C (zh) 2002-01-17 2003-01-17 透平机叶片以及制造透平机叶片的铸造组件
US10/345,947 US6923620B2 (en) 2002-01-17 2003-04-30 Turbine blade/vane and casting system for manufacturing a turbine blade/vane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02001265A EP1331361B1 (fr) 2002-01-17 2002-01-17 Aube statorique de turbine coulée ayant un crochet de fixation

Publications (2)

Publication Number Publication Date
EP1331361A1 true EP1331361A1 (fr) 2003-07-30
EP1331361B1 EP1331361B1 (fr) 2010-05-12

Family

ID=8185294

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02001265A Expired - Lifetime EP1331361B1 (fr) 2002-01-17 2002-01-17 Aube statorique de turbine coulée ayant un crochet de fixation

Country Status (6)

Country Link
US (1) US6923620B2 (fr)
EP (1) EP1331361B1 (fr)
JP (1) JP4303480B2 (fr)
CN (1) CN100447374C (fr)
AT (1) ATE467749T1 (fr)
DE (1) DE50214427D1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7628587B2 (en) * 2004-04-30 2009-12-08 Alstom Technology Ltd Gas turbine blade shroud
US7652960B2 (en) 2003-08-14 2010-01-26 Lg Electronics, Inc. Recording medium, method of configuring control information thereof, recording and reproducing method using the same, and apparatus thereof
CN113560544A (zh) * 2021-06-28 2021-10-29 深圳市万泽中南研究院有限公司 一种定向叶片及其柱状晶组织优化方法
CN118917015A (zh) * 2024-08-20 2024-11-08 中国船舶集团有限公司第七〇三研究所 涡轮导叶缘板双排圆形微细管阵冷却结构设计方法

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7819629B2 (en) * 2007-02-15 2010-10-26 Siemens Energy, Inc. Blade for a gas turbine
US8356975B2 (en) * 2010-03-23 2013-01-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured vane platform
US9976433B2 (en) 2010-04-02 2018-05-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured rotor blade platform
US8739404B2 (en) 2010-11-23 2014-06-03 General Electric Company Turbine components with cooling features and methods of manufacturing the same
EP3147452B1 (fr) * 2015-09-22 2018-07-25 Ansaldo Energia IP UK Limited Élément d'aubage de turbomachine
CN107755637A (zh) * 2017-09-18 2018-03-06 东方电气集团东方汽轮机有限公司 一种消除定向凝固铸件缺陷的方法
US10544699B2 (en) * 2017-12-19 2020-01-28 Rolls-Royce Corporation System and method for minimizing the turbine blade to vane platform overlap gap
CN115055645B (zh) * 2022-06-07 2023-10-17 中国航发航空科技股份有限公司 导向器叶片毛坯的浇注系统

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2488875A (en) 1947-05-07 1949-11-22 Rolls Royce Gas turbine engine
EP0357984A1 (fr) 1988-08-31 1990-03-14 Westinghouse Electric Corporation Turbine à gaz à refroidissement pelliculaire de frettes de distributeur
WO1996013653A1 (fr) * 1994-10-31 1996-05-09 Westinghouse Electric Corporation Pale de turbine a gaz avec plateforme refroidie
EP0937863A2 (fr) * 1998-02-23 1999-08-25 Mitsubishi Heavy Industries, Ltd. Plateforme pour une aube mobile d'une turbine à gaz
DE10004714A1 (de) * 2000-02-03 2001-08-16 Karl Walter Formen Formen & Ko Vorrichtung zum Gießen eines Formteils
EP1145784A1 (fr) * 2000-04-12 2001-10-17 Siemens Aktiengesellschaft Appareil de coulage, notamment pour la fabrication d'aubes de turbine
DE10024278A1 (de) * 2000-05-17 2001-11-22 Weidmueller Interface Kunststoffgehäuse mit einer Aufnahme sowie Verfahren zu dessen Herstellung
WO2002027147A1 (fr) * 2000-09-28 2002-04-04 Siemens Westinghouse Power Corporation Aube de turbine refroidie pourvue de couvercles d'extremite

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US3494709A (en) * 1965-05-27 1970-02-10 United Aircraft Corp Single crystal metallic part
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
US5344283A (en) * 1993-01-21 1994-09-06 United Technologies Corporation Turbine vane having dedicated inner platform cooling
JP2002512334A (ja) * 1998-04-21 2002-04-23 シーメンス アクチエンゲゼルシヤフト タービン翼
DE10060141A1 (de) * 2000-12-04 2002-06-06 Alstom Switzerland Ltd Verfahren zur Herstellung eines Gussteils, Modellform und keramischer Einsatz zum Gebrauch in diesem Verfahren

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2488875A (en) 1947-05-07 1949-11-22 Rolls Royce Gas turbine engine
EP0357984A1 (fr) 1988-08-31 1990-03-14 Westinghouse Electric Corporation Turbine à gaz à refroidissement pelliculaire de frettes de distributeur
WO1996013653A1 (fr) * 1994-10-31 1996-05-09 Westinghouse Electric Corporation Pale de turbine a gaz avec plateforme refroidie
EP0937863A2 (fr) * 1998-02-23 1999-08-25 Mitsubishi Heavy Industries, Ltd. Plateforme pour une aube mobile d'une turbine à gaz
DE10004714A1 (de) * 2000-02-03 2001-08-16 Karl Walter Formen Formen & Ko Vorrichtung zum Gießen eines Formteils
EP1145784A1 (fr) * 2000-04-12 2001-10-17 Siemens Aktiengesellschaft Appareil de coulage, notamment pour la fabrication d'aubes de turbine
DE10024278A1 (de) * 2000-05-17 2001-11-22 Weidmueller Interface Kunststoffgehäuse mit einer Aufnahme sowie Verfahren zu dessen Herstellung
WO2002027147A1 (fr) * 2000-09-28 2002-04-04 Siemens Westinghouse Power Corporation Aube de turbine refroidie pourvue de couvercles d'extremite

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7652960B2 (en) 2003-08-14 2010-01-26 Lg Electronics, Inc. Recording medium, method of configuring control information thereof, recording and reproducing method using the same, and apparatus thereof
US7628587B2 (en) * 2004-04-30 2009-12-08 Alstom Technology Ltd Gas turbine blade shroud
EP1759089B1 (fr) * 2004-04-30 2018-08-08 Ansaldo Energia IP UK Limited Virole pour aube de turbine à gaz
CN113560544A (zh) * 2021-06-28 2021-10-29 深圳市万泽中南研究院有限公司 一种定向叶片及其柱状晶组织优化方法
CN118917015A (zh) * 2024-08-20 2024-11-08 中国船舶集团有限公司第七〇三研究所 涡轮导叶缘板双排圆形微细管阵冷却结构设计方法

Also Published As

Publication number Publication date
JP2003232205A (ja) 2003-08-22
DE50214427D1 (de) 2010-06-24
EP1331361B1 (fr) 2010-05-12
ATE467749T1 (de) 2010-05-15
CN100447374C (zh) 2008-12-31
US6923620B2 (en) 2005-08-02
CN1451846A (zh) 2003-10-29
JP4303480B2 (ja) 2009-07-29
US20050111963A1 (en) 2005-05-26

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