US20150064018A1 - Turbine blade and associated method for producing a turbine blade - Google Patents

Turbine blade and associated method for producing a turbine blade Download PDF

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Publication number
US20150064018A1
US20150064018A1 US14/388,411 US201314388411A US2015064018A1 US 20150064018 A1 US20150064018 A1 US 20150064018A1 US 201314388411 A US201314388411 A US 201314388411A US 2015064018 A1 US2015064018 A1 US 2015064018A1
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US
United States
Prior art keywords
platform
blade
turbine blade
platform part
frame
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.)
Abandoned
Application number
US14/388,411
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English (en)
Inventor
Fathi Ahmad
Hans-Thomas Bolms
Nihal Kurt
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
Original Assignee
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
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: AHMAD, FATHI, Kurt, Nihal, BOLMS, HANS-THOMAS
Publication of US20150064018A1 publication Critical patent/US20150064018A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • 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
    • 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
    • Y10T29/49339—Hollow blade

Definitions

  • the invention relates to a turbine blade with a fastening portion, with a platform for delimiting a flow duct and with a blade airfoil, which succeed one another along a longitudinal axis of the turbine blade.
  • the invention relates, furthermore, to a method for producing a turbine blade, comprising the step: production of a monolithic trunk blade comprising a blade airfoil, a platform for delimiting a flow duct and a fastening portion.
  • Turbine blades and methods for producing turbine blades are known in many different forms from the abundant prior art.
  • turbine blades for gas turbines are often produced by a casting method.
  • the blade foot, platform and blade airfoil are formed simultaneously from the casting material, and therefore turbine blades of this type are in one piece.
  • the surfaces, that it to say the platform and blade airfoil, which are exposed to the hot gas of the turbine are subsequently also provided with a corrosion protection layer and with a heat protection layer, in order to increase the service life of the turbine blade.
  • the cast turbine blades are mostly also of hollow form, so that a means for cooling the blade material can flow inside.
  • Turbine blades of steam engines are mostly milled from solid or forged.
  • the turbine blades used in stationary turbomachines are subjected, when the turbomachine is in operation, to a multiplicity of loads which cause the turbine blades to age and to become worn both in a predictable and in an unpredictable way.
  • U.S. Pat. No. 4,650,399 A1 discloses a moving blade with two platform halves which are arranged on both sides of a blade airfoil. In order to prevent the platform halves from being displaced along the blade airfoil, a positive connection is provided, the two platform halves being pinned to one another. However, the fastening of the platforms is classed as unsafe.
  • EP 1 905 950 A1 and US 4,019,832 A1 disclose likewise dividing platforms into two halves.
  • WO 2000/057032 A1 discloses a single platform element between two directly adjacent moving blades of a moving blade ring. The mounting of the components on the rotor seems to be a disadvantage here.
  • An object of the invention is to provide a turbine blade with a fastening portion, with a platform for delimiting a flow duct and with a blade airfoil, which succeed one another along a longitudinal axis of the turbine blade, which turbine blade can be regenerated at especially low outlay.
  • a further object of the invention is to provide a method for producing turbine blades.
  • the object aimed at the turbine blade is achieved by means of a turbine blade according to the features of the claims.
  • the object aimed at the method for producing a turbine blade is achieved by means of the method steps according to the claims.
  • Advantageous refinements are specified in the respective subclaims. In this case, the features of the respective subclaims can be readily combined with the features of other subclaims.
  • aspects of the invention are based on the recognition that, particularly in the case of operationally stressed turbine blades, defects caused by oxidation may occur even at the outer margin of the platform. These oxidation problems arise, in particular, when the heat insulation layer often also provided there flakes off locally. Such consequences may lead in the turbine blade to an increased operating risk, and therefore turbine blades of this type are exchanged or treated.
  • the retreatment of the turbine blade has hitherto been comparatively complicated.
  • the regeneration rate that is to say the fraction of retreated blades which, after retreatment, actually still qualify for use in the turbomachine, may be rather small.
  • the platform comprises radially with respect to a central longitudinal axis an inner platform part and an outer platform part, the outer platform part being designed as a continuous platform frame surrounding the outer margin of the inner platform part.
  • the platform frame is thus continuously peripheral and in one piece and could also be designated as closed.
  • the invention does not attempt to provide a design for modular turbine blades, and therefore that surface of the inner platform part over which the hot gas can flow is preferably substantially larger than that surface of the platform frame over which the hot gas can flow.
  • the defects specified further above in the vicinity of the platform margin must be removed by the margin of the platform being set back, for example, by milling or grinding. According to aspects of the invention, there is in this case provision whereby not only the local defect is removed when the platform margin is set back.
  • the platform margin is set back along the entire periphery in order thereby to produce a monolithic trunk blade, the platform of which, as an inner platform part of the turbine blade to be produced, provides a bearing surface for a platform frame.
  • a trunk blade comprising a blade airfoil, a platform and a fastening portion
  • the monolithic trunk blade can be produced conventionally by the casting method and, for example, can also be solidified in a monocrystalline or directional manner.
  • the platform margin of the trunk blade has to be brought to the predetermined exact dimension, if appropriate, also along the entire periphery, by minor grinding or milling, in order to provide the inner platform part of the turbine blade with a dimensionally accurate bearing surface for the platform frame.
  • the platform frame Before, during or after this, the platform frame must be produced as a mostly rectangular structure. After the attachment or mounting of the platform frame on the dimensionally accurate margin of the inner platform part, the turbine blade is then produced as a new component.
  • the platform frame may have various forms in cross section. However, those forms are preferred which bring about a positive connection to the margin of the inner platform part.
  • the cost-sectional form may be diamond-shaped or C-shaped.
  • the margin of the inner platform part is in this case always designed to match with the cross-sectional form.
  • a particular advantage of the turbine blade according to aspects of the invention and also of the method is that, in particular, even two different materials can be used for the trunk blade and for the platform frame.
  • the various local loads can additionally be taken into account, thereby leading, where appropriate, to a prolonged service life of the turbine blade.
  • a further advantage of the turbine blade according to aspects of the invention is the higher precision in terms of the outer dimensions of the platform, since these can be implemented more simply during the production of the platform frame than when a purely monolithic turbine blade is being cast.
  • the platform frame is configured as a continuous frame, it is preferably appropriate to shrink the platform frame onto the peripheral margin of the inner platform part. Before shrinking on, the platform frame can be heated and/or the trunk blade cooled. After the assembling of the platform frame and trunk blade and subsequent temperature equalization, the platform frame is then seated firmly on the peripheral margin of the inner platform part. Even soldering and welding, in spot form and also along the connecting line of the margin of the inner platform part and platform frame, are possible.
  • the platform frame bears against the inner platform part in a sheet-like manner, the contact area forming at least partially with the longitudinal axis at an angle which is larger than 0° and smaller than 90°.
  • Such an arrangement prevents a parallel displacement of the platform frame along the longitudinal axis, at least in one direction, this being advantageous particularly when the invention is used on turbine moving blades.
  • the centrifugal force acting upon the platform frame during the operation of the turbomachine is also transferred by positive connection into the platform part because the contact area is inclined with respect to the longitudinal axis. This reliably prevents the loss of the platform frame due to the centrifugal force.
  • the angle amounts to a size of between 15° and 35°, for example the angle lies at 20°.
  • the platform frame has, on at least one surface pointing laterally outward, a slot for the reception of a sealing element.
  • the turbine blade may expediently be designed both as a guide blade or as a moving blade.
  • the turbine blade with the inner platform part and the outer platform part in the form of the continuous platform frame surrounding the inner platform part, can be used even in high-temperature applications, it is advantageous if the inner platform part and the platform frame are coated in a coating operation.
  • a seamless protective layer can thus be applied to both platform parts.
  • FIG. 1 shows, in a perspective illustration, the side view of a turbine blade according to an embodiment of the invention
  • FIG. 2 shows, in a perspective illustration, the top view of a platform frame
  • FIG. 3 shows the cross section through a turbine blade according to FIG. 1 .
  • FIG. 4 shows a detail of the corner of a platform of the turbine blade according to FIG. 1 during the assembly of the trunk blade and platform frame.
  • FIG. 1 shows a perspective illustration of a turbine blade 10 .
  • the turbine blade 10 is designed as a moving blade. However, it may also be designed as a guide blade.
  • the turbine blade 10 comprises, succeeding one another directly along its longitudinal axis 12 , a fastening portion 14 , a platform 16 and a blade airfoil 18 .
  • the fastening portion 14 is contoured in a manner of a pine tree profile in a way typical of a moving blade.
  • Guide blades for turbines mostly have, instead of the pine tree-shaped fastening portion 14 , a plurality of hooks which are pushed into a guide blade carrier, not illustrated in any more detail, of the turbomachine.
  • the fastening portion 14 merges into the platform 16 .
  • the platform 16 has an upwardly pointing platform surface 20 on which the blade airfoil 18 is seated.
  • the platform 16 comprises radially with respect to the longitudinal axis 12 an inner platform part 22 and an outer platform part 24 , the outer platform part 24 being designed as a continuous platform frame 28 surrounding the outer margin 26 of the inner platform part 22 .
  • both the fastening portion 14 , the inner platform part 22 and the blade airfoil 18 are formed monolithically, that is to say in one piece. This monolithic unit is also designated as a trunk blade 19 .
  • the surfaces 20 of the inner platform part 22 and of the outer platform part 24 which point toward the blade airfoil 18 according to this illustration are offset-free with respect to one another, so that, when the turbine blade 10 is used in a turbomachine, they provide an edge-free and step-free boundary wall for the working medium flowing in the turbomachine.
  • that surface of the inner platform part 22 over which the hot gas can flow is substantially larger than that surface of the platform frame 28 over which the hot gas can flow.
  • the turbine blade 10 may be designed to be internally cooled with the aid of a cooling medium in any way. Even film cooling ports and trailing edge ports for coolant may be provided. The turbine blade may, of course, also be uncooled.
  • FIG. 2 shows a perspective illustration of the platform frame 28 .
  • the platform frame 28 comprises two longitudinal struts 30 parallel to one another and two transverse struts 32 parallel to one another.
  • the platform frame 28 may be produced from a material other than that of the trunk blade 19 illustrated in FIG. 1 . However, the platform frame 28 may also be produced from the same material.
  • the platform frame may also be produced by welding the longitudinal struts 30 to the transverse struts 32 . It may also be cast or be milled from solid.
  • FIG. 3 shows a section through the turbine blade 10 along the longitudinal axis 12 . In contrast to the turbine blade illustrated in FIG. 1 , the fastening portion according to FIG. 3 is not of pine tree-shaped form, but instead is dovetail-shaped.
  • FIG. 3 shows the platform frame 28 during mounting on the trunk blade 19 , shortly before the platform frame 28 reaches its ultimate mounting position.
  • the platform frame 28 is diamond-shaped in cross section. Other forms are also possible.
  • Each strut 30 , 32 of the platform frame 28 has an inwardly directed first bearing surface 34 and a second bearing surface 36 .
  • the outer margin 26 of the inner platform part 22 likewise has a laterally outward-pointing first bearing surface 38 and a second bearing surface 40 .
  • first bearing surface 34 bears in a sheet-like manner against the first bearing surface 38 of the inner platform part 22
  • second bearing surface 36 bears in a sheet-like manner against the second bearing surface of the inner platform part 22 .
  • the first contact areas and second contact areas thus formed are inclined differently with respect to the longitudinal axis 12 .
  • the first contact area is oriented parallel to the longitudinal axis 12 in cross section.
  • the second contact area is inclined in cross section at an acute angle ⁇ to the longitudinal axis 12 .
  • This embodiment also prevents, by positive connection, the release of the platform frame 28 from the trunk blade 19 under centrifugal forces acting upon the turbine blade 10 .
  • FIG. 4 shows a perspective illustration of a corner of the inner platform part 22 and of the platform frame 28 during mounting. In addition to the features already described, FIG. 4 also shows, on a laterally outward-pointing surface 42 of the platform frame 28 , a slot 44 for the reception of a sheet-like sealing element.
  • the invention relates to a turbine blade 10 with a fastening portion 14 , with a platform 16 and with a blade airfoil 18 , which directly succeed one another along a longitudinal axis 12 of the turbine blade.
  • the platform 16 comprises radially with respect to the longitudinal axis 12 an inner platform part 22 and an outer platform part 24 , the outer platform part 24 being designed as a continuous platform frame 28 surrounding the outer margin 26 of the inner platform part 22 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US14/388,411 2012-03-29 2013-03-27 Turbine blade and associated method for producing a turbine blade Abandoned US20150064018A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP12162103.1 2012-03-29
EP12162103.1A EP2644834A1 (de) 2012-03-29 2012-03-29 Turbinenschaufel sowie zugehöriges Verfahren zum Herstellen einer Turbinenschaufel
PCT/EP2013/056594 WO2013144245A1 (de) 2012-03-29 2013-03-27 Turbinenschaufel sowie zugehöriges verfahren zum herstellen einer turbinenschaufel

Publications (1)

Publication Number Publication Date
US20150064018A1 true US20150064018A1 (en) 2015-03-05

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US14/388,411 Abandoned US20150064018A1 (en) 2012-03-29 2013-03-27 Turbine blade and associated method for producing a turbine blade

Country Status (7)

Country Link
US (1) US20150064018A1 (de)
EP (2) EP2644834A1 (de)
JP (1) JP2015517048A (de)
CN (1) CN104204417A (de)
IN (1) IN2014DN07295A (de)
RU (1) RU2014143493A (de)
WO (1) WO2013144245A1 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150071783A1 (en) * 2012-03-29 2015-03-12 Siemens Aktiengesellschaft Turbine blade
US20170306774A1 (en) * 2016-04-21 2017-10-26 General Electric Company Article, component, and method of making a component
US10753212B2 (en) * 2017-08-23 2020-08-25 Doosan Heavy Industries & Construction Co., Ltd Turbine blade, turbine, and gas turbine having the same
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
US11111858B2 (en) * 2017-01-27 2021-09-07 General Electric Company Cool core gas turbine engine

Citations (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2727716A (en) * 1945-12-21 1955-12-20 Power Jets Res & Dev Ltd Bladed body
US3749518A (en) * 1972-03-15 1973-07-31 United Aircraft Corp Composite blade root configuration
US3778185A (en) * 1972-08-28 1973-12-11 United Aircraft Corp Composite strut joint construction
US4152816A (en) * 1977-06-06 1979-05-08 General Motors Corporation Method of manufacturing a hybrid turbine rotor
US4501053A (en) * 1982-06-14 1985-02-26 United Technologies Corporation Method of making rotor blade for a rotary machine
US4524980A (en) * 1983-12-05 1985-06-25 United Technologies Corporation Intersecting feather seals for interlocking gas turbine vanes
US4583914A (en) * 1982-06-14 1986-04-22 United Technologies Corp. Rotor blade for a rotary machine
US4875830A (en) * 1985-07-18 1989-10-24 United Technologies Corporation Flanged ladder seal
US5083900A (en) * 1989-11-15 1992-01-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbomachine stator element
US5318406A (en) * 1992-11-02 1994-06-07 General Electric Company Multipart gas turbine blade
US6648597B1 (en) * 2002-05-31 2003-11-18 Siemens Westinghouse Power Corporation Ceramic matrix composite turbine vane
US6652228B2 (en) * 2000-12-27 2003-11-25 Siemens Aktiengesellschaft Gas turbine blade and gas turbine
US20070237630A1 (en) * 2006-04-11 2007-10-11 Siemens Power Generation, Inc. Vane shroud through-flow platform cover
US7284958B2 (en) * 2003-03-22 2007-10-23 Allison Advanced Development Company Separable blade platform
US20080298973A1 (en) * 2007-05-29 2008-12-04 Siemens Power Generation, Inc. Turbine vane with divided turbine vane platform
US20090053037A1 (en) * 2006-07-27 2009-02-26 Siemens Power Generation, Inc. Turbine vanes with airfoil-proximate cooling seam
US20100080687A1 (en) * 2008-09-26 2010-04-01 Siemens Power Generation, Inc. Multiple Piece Turbine Engine Airfoil with a Structural Spar
US20100150703A1 (en) * 2006-09-22 2010-06-17 Siemens Power Generation, Inc. Stacked laminate bolted ring segment
US20100189556A1 (en) * 2009-01-28 2010-07-29 United Technologies Corporation Segmented ceramic matrix composite turbine airfoil component
US20110027098A1 (en) * 2008-12-31 2011-02-03 General Electric Company Ceramic matrix composite blade having integral platform structures and methods of fabrication
US20110142639A1 (en) * 2009-12-15 2011-06-16 Campbell Christian X Modular turbine airfoil and platform assembly with independent root teeth
US7972113B1 (en) * 2007-05-02 2011-07-05 Florida Turbine Technologies, Inc. Integral turbine blade and platform
US7976281B2 (en) * 2007-05-15 2011-07-12 General Electric Company Turbine rotor blade and method of assembling the same
US20110243746A1 (en) * 2010-04-06 2011-10-06 General Electric Company Composite turbine bucket assembly
US20110297344A1 (en) * 2010-04-01 2011-12-08 Campbell Christian X Turbine airfoil to shroud attachment method
US8162617B1 (en) * 2008-01-30 2012-04-24 Florida Turbine Technologies, Inc. Turbine blade with spar and shell
US8231354B2 (en) * 2009-12-15 2012-07-31 Siemens Energy, Inc. Turbine engine airfoil and platform assembly

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3451654A (en) * 1967-08-25 1969-06-24 Gen Motors Corp Blade vibration damping
US4019832A (en) * 1976-02-27 1977-04-26 General Electric Company Platform for a turbomachinery blade
US4650399A (en) * 1982-06-14 1987-03-17 United Technologies Corporation Rotor blade for a rotary machine
JP2743066B2 (ja) * 1985-08-15 1998-04-22 株式会社日立製作所 ガスタービン用動翼構造
EP1163428B1 (de) * 1999-03-24 2004-08-25 Siemens Aktiengesellschaft Leitschaufel und leitschaufelkranz für eine strömungsmaschine, sowie bauteil zur begrenzung eines strömungskanals
EP1128023A1 (de) * 2000-02-25 2001-08-29 Siemens Aktiengesellschaft Turbinenlaufschaufel
JP4860941B2 (ja) * 2005-04-27 2012-01-25 本田技研工業株式会社 整流部材ユニット及びその製造方法
US7467922B2 (en) * 2005-07-25 2008-12-23 Siemens Aktiengesellschaft Cooled turbine blade or vane for a gas turbine, and use of a turbine blade or vane of this type
EP1905950A1 (de) * 2006-09-21 2008-04-02 Siemens Aktiengesellschaft Laufschaufel für eine Turbine
US7762781B1 (en) * 2007-03-06 2010-07-27 Florida Turbine Technologies, Inc. Composite blade and platform assembly
US7874804B1 (en) * 2007-05-10 2011-01-25 Florida Turbine Technologies, Inc. Turbine blade with detached platform
US7878763B2 (en) * 2007-05-15 2011-02-01 General Electric Company Turbine rotor blade assembly and method of assembling the same
CH700001A1 (de) * 2008-11-20 2010-05-31 Alstom Technology Ltd Laufschaufelanordnung, insbesondere für eine gasturbine.

Patent Citations (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2727716A (en) * 1945-12-21 1955-12-20 Power Jets Res & Dev Ltd Bladed body
US3749518A (en) * 1972-03-15 1973-07-31 United Aircraft Corp Composite blade root configuration
US3778185A (en) * 1972-08-28 1973-12-11 United Aircraft Corp Composite strut joint construction
US4152816A (en) * 1977-06-06 1979-05-08 General Motors Corporation Method of manufacturing a hybrid turbine rotor
US4583914A (en) * 1982-06-14 1986-04-22 United Technologies Corp. Rotor blade for a rotary machine
US4501053A (en) * 1982-06-14 1985-02-26 United Technologies Corporation Method of making rotor blade for a rotary machine
US4524980A (en) * 1983-12-05 1985-06-25 United Technologies Corporation Intersecting feather seals for interlocking gas turbine vanes
US4875830A (en) * 1985-07-18 1989-10-24 United Technologies Corporation Flanged ladder seal
US5083900A (en) * 1989-11-15 1992-01-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbomachine stator element
US5318406A (en) * 1992-11-02 1994-06-07 General Electric Company Multipart gas turbine blade
US6652228B2 (en) * 2000-12-27 2003-11-25 Siemens Aktiengesellschaft Gas turbine blade and gas turbine
US6648597B1 (en) * 2002-05-31 2003-11-18 Siemens Westinghouse Power Corporation Ceramic matrix composite turbine vane
US7284958B2 (en) * 2003-03-22 2007-10-23 Allison Advanced Development Company Separable blade platform
US20070237630A1 (en) * 2006-04-11 2007-10-11 Siemens Power Generation, Inc. Vane shroud through-flow platform cover
US20090053037A1 (en) * 2006-07-27 2009-02-26 Siemens Power Generation, Inc. Turbine vanes with airfoil-proximate cooling seam
US20100150703A1 (en) * 2006-09-22 2010-06-17 Siemens Power Generation, Inc. Stacked laminate bolted ring segment
US7972113B1 (en) * 2007-05-02 2011-07-05 Florida Turbine Technologies, Inc. Integral turbine blade and platform
US7976281B2 (en) * 2007-05-15 2011-07-12 General Electric Company Turbine rotor blade and method of assembling the same
US20080298973A1 (en) * 2007-05-29 2008-12-04 Siemens Power Generation, Inc. Turbine vane with divided turbine vane platform
US8162617B1 (en) * 2008-01-30 2012-04-24 Florida Turbine Technologies, Inc. Turbine blade with spar and shell
US20100080687A1 (en) * 2008-09-26 2010-04-01 Siemens Power Generation, Inc. Multiple Piece Turbine Engine Airfoil with a Structural Spar
US20110027098A1 (en) * 2008-12-31 2011-02-03 General Electric Company Ceramic matrix composite blade having integral platform structures and methods of fabrication
US20100189556A1 (en) * 2009-01-28 2010-07-29 United Technologies Corporation Segmented ceramic matrix composite turbine airfoil component
US20110142639A1 (en) * 2009-12-15 2011-06-16 Campbell Christian X Modular turbine airfoil and platform assembly with independent root teeth
US8231354B2 (en) * 2009-12-15 2012-07-31 Siemens Energy, Inc. Turbine engine airfoil and platform assembly
US20110297344A1 (en) * 2010-04-01 2011-12-08 Campbell Christian X Turbine airfoil to shroud attachment method
US20110243746A1 (en) * 2010-04-06 2011-10-06 General Electric Company Composite turbine bucket assembly

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150071783A1 (en) * 2012-03-29 2015-03-12 Siemens Aktiengesellschaft Turbine blade
US20170306774A1 (en) * 2016-04-21 2017-10-26 General Electric Company Article, component, and method of making a component
US10767501B2 (en) * 2016-04-21 2020-09-08 General Electric Company Article, component, and method of making a component
US11111858B2 (en) * 2017-01-27 2021-09-07 General Electric Company Cool core gas turbine engine
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
US10753212B2 (en) * 2017-08-23 2020-08-25 Doosan Heavy Industries & Construction Co., Ltd Turbine blade, turbine, and gas turbine having the same

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WO2013144245A1 (de) 2013-10-03
IN2014DN07295A (de) 2015-04-24
RU2014143493A (ru) 2016-05-20
JP2015517048A (ja) 2015-06-18
EP2644834A1 (de) 2013-10-02
CN104204417A (zh) 2014-12-10
EP2805023A1 (de) 2014-11-26

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