EP1566519A1 - Composant à haute température d'une turbomachine et turbomachine - Google Patents

Composant à haute température d'une turbomachine et turbomachine Download PDF

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Publication number
EP1566519A1
EP1566519A1 EP04004021A EP04004021A EP1566519A1 EP 1566519 A1 EP1566519 A1 EP 1566519A1 EP 04004021 A EP04004021 A EP 04004021A EP 04004021 A EP04004021 A EP 04004021A EP 1566519 A1 EP1566519 A1 EP 1566519A1
Authority
EP
European Patent Office
Prior art keywords
temperature component
blade
porous material
viscous filler
turbomachine
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.)
Withdrawn
Application number
EP04004021A
Other languages
German (de)
English (en)
Inventor
Andreas Dr. Kayser
Ivo Dr. Wolter
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
Priority to EP04004021A priority Critical patent/EP1566519A1/fr
Priority to US11/062,303 priority patent/US7347664B2/en
Publication of EP1566519A1 publication Critical patent/EP1566519A1/fr
Withdrawn legal-status Critical Current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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/005—Selecting particular materials
    • 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
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/04—Heavy metals
    • F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
    • F05C2201/0463—Cobalt
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/04—Heavy metals
    • F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
    • F05C2201/0466—Nickel
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2102—Glass
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2112—Aluminium oxides
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2118—Zirconium oxides
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/222—Silicon
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/612—Foam
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/615—Filler
    • 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
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • the invention relates to a high-temperature component, in particular a shovel with an airfoil and a Blade root, for a turbomachine, z. B. for a gas turbine or a compressor. Furthermore, the invention relates a turbomachine with such a high-temperature component.
  • Conventional turbomachines, z. B. turbocharger, compressor, Gas turbines include high temperature components, e.g. B. Blades, such as guide vanes and rotor blades, carrier elements, ring elements, which is a high temperature and a corrosive one or oxidative atmosphere exposed by combustion gases are. In addition to such temperature stresses are in particular the blades also withstand high mechanical stresses, z. B. vibrations exposed.
  • high temperature components e.g. B. Blades, such as guide vanes and rotor blades, carrier elements, ring elements, which is a high temperature and a corrosive one or oxidative atmosphere exposed by combustion gases are.
  • the blades also withstand high mechanical stresses, z. B. vibrations exposed.
  • the blade is made of an airfoil, possibly a paddle platform and a blade root, formed.
  • the blade root is in a recess on a rotor or stator arranged a turbomachine.
  • a turbomachine When operating the Turbomachine can do it by different operating conditions to bending and torsional vibrations, especially in the transition region from the blade root to the blade, come, the to a material fatigue and thus to a shortened life being able to lead.
  • Shovel with damping elements to damp these vibrations to provide.
  • the blades provided with wires, friction elements or shrouds.
  • the invention is therefore based on the object, a high-temperature component indicate which ones are particularly easy to face Torsions and bending stresses is protected. Of Another is a particularly simple running turbomachine specify.
  • the first object is achieved by a high-temperature component for a turbomachine, in particular a blade with an airfoil and a Blade foot comprising at least partially as a base material porous material filled with a viscous filler and surrounded by a festival layer.
  • the invention is based on the consideration that a exposed to high temperature, torsional and bending stresses High-temperature component on elaborate damping elements should refrain from reducing the vibrations. Therefore, the high-temperature component itself should be appropriate be educated.
  • the high-temperature component is provided at least partially, especially in the areas with high vibration stress, as base material to form a porous material, which with a viscous Filled filler and surrounded by a solid layer is.
  • the porous material has the advantage of being particularly temperature-resistant and to be heat resistant. In addition, draws it has a high resistance to corrosion, Oxidation and other chemicals, such as combustion gases, out.
  • the viscous filler By a suitable choice of the viscous filler is the High-temperature component also particularly mechanically strong and sufficiently resistant to tension and damping. there occurs during a mechanical stress of the high-temperature component, z. B. by vibration movements, to a Relative movement between the porous material and the fluid Filler. The resulting friction causes a Damping and thus a vibration reduction and stress reduction.
  • a porous material is a raw material the base of silicon dioxide, a commodity based on Alumina, a zirconia based raw material, a raw material based on magnesium oxide or a raw material used on the basis of mica and aluminosilicates.
  • the material based on silicon carbide or on the basis of aluminum titanate another substance formed with carbide or nitrite structure or metal materials be.
  • These raw materials are characterized by a high temperature resistance and strength against thermal cycling out. In addition, these raw materials are especially against Corrosion and oxidation resistant.
  • the porous material has a porosity of not more than 20%, in particular from 5% to 15% or 10% up to 15%, up.
  • the porosity depends significantly on the use the high-temperature component, in particular of the load this by centrifugal forces and the resulting Bending and torsional stresses, from. Such is for example for a turbine blade a maximum porosity of 20% advantageous in which the vibrations occurring at the Turbine blade are sufficiently attenuated.
  • the porous material have a varying porosity. Especially can the high-temperature component in areas, in Dependence on the respective temperature load as well the vibration stress, made of a porous material with low porosity and high porosity. In areas with heavy use, z. B.
  • the porous material in the transition area between a blade root and an airfoil, is a porous material with a low porosity of maximum 20% provided.
  • a less stressed area of the High temperature component can be made of a porous material with a high porosity of greater than 20%, in particular from 40% to 60%, be formed.
  • the porous material has a variable pore size.
  • the porous material has an average Pore size from 20 microns to 70 microns, especially from 40 microns to 50 ⁇ m, on.
  • the base material is as granular Material formed whose grains by their surface shape Mutually abutting each other form of comparatively small cavities.
  • a viscous filler is a fluid, in particular a heat-resistant fluid used.
  • a viscous filler is a lubricant, in particular a polyalkylene glycol, a synthetic hydrocarbon, a dicarboxylic acid and polyol ester, a silicone Polyphenyl ether, a fluorocarbon, used.
  • a phosphoric acid ester may be used.
  • synthetic hydrocarbon is, for example, polyalphaolefins, Diakylbenzenes, polyisobutylenes used.
  • such viscous fillers are characterized by high temperature stability, Oxidation resistance, high pressure stability and viscosity-temperature behavior out.
  • a more viscous Filler is a wax or a liquid metal filling be used.
  • the porous material and the viscous filler in the ratio of 4 to 1, 3 to 1 or 2 to 1 mixed.
  • Other mixing ratios are also possible and depend significantly on the use of the high-temperature component and the operating conditions occurring.
  • the high-temperature component is as a surface layer a solid layer of a metal material, in particular of a heat-resistant alloy, provided substantially of at least one Ni-based material, one material Cr-based, a Co-based material, a material Fe-based and / or Ti-based material is.
  • this is alloy steel based on NiCr, based on CoCr, based on NiCrAl, NiCoCr or CoCrAl.
  • the solid layer of the high temperature component for a sufficient corrosion and wear protection a thickness of 100 microns to 1,000 microns, in particular from 180 ⁇ m to 300 ⁇ m or from 200 ⁇ m to 500 ⁇ m.
  • the high temperature component is complete from the porous material filled with the viscous filler and surrounded by the hard layer is formed.
  • a formed as a blade high-temperature component the airfoil and the blade root completely out of the porous Material formed.
  • the bucket in Seen in the longitudinal direction of the blade body partially from the porous material filled with the viscous filler and surrounded by the hard layer, be formed.
  • the blade can at least partially, especially over a length of 10%, 20%, 30% to 45% the total length of the airfoil, made of the porous material be formed.
  • the blade is at least a third to half of the porous Material filled with the viscous filler and from the Fixed layer is surrounded, formed.
  • a possible use of such a trained high-temperature component puts a stationary blade in one Turbomachine dar.
  • the high-temperature component as a movable shovel in a turbomachine be educated.
  • other uses as a carrier element, Bearing element or ring element in a turbomachine are possible.
  • the advantages achieved by the invention are in particular in that at a high temperature component, which at least partially as a base material a porous material having filled with viscous filler, a sufficient high protection against mechanical stress, the caused by vibrations, eg. B. bending and torsional stresses, given is.
  • a sufficient high protection against mechanical stress the caused by vibrations, eg. B. bending and torsional stresses, given is.
  • the by the Use of the porous material caused damping due the relative movement between the porous material and the viscous filler leads to a vibration reduction and thus reducing the stress on the high temperature component due to mechanical stresses, so that extends the life of the high-temperature component becomes.
  • the base material 1 shows a base material 1, which consists of a porous material 2 is formed.
  • the porous material 2 is with a viscous filler 4 filled and surrounded by a solid layer 6.
  • a raw material is used the base of silicon dioxide, a commodity based on Alumina, a zirconia based raw material, a raw material based on magnesium oxide, a raw material based on aluminum titanate, a commodity based of silicon carbide or a raw material based on Mica and aluminosilicates.
  • the porous Material has a porosity of at most 20%, in particular of 5% to 15% or from 10% to 15%.
  • the porous material 2 a varying porosity, z. B. from 10%, 20% to a maximum of 30%, or a variable pore size, z. B. an average pore size of 20 microns to 80 microns, in particular from 20 ⁇ m to 40 ⁇ m or 40 ⁇ m to 60 ⁇ m.
  • a viscous filler 4 is a fluid, in particular a heat resistant fluid.
  • a lubricant in particular Polyalkylene glycols, synthetic hydrocarbons, Dicarboxylic acid and polyol esters, silicones, polyphenyl ethers, Fluorocarbons, are used.
  • These viscous Fillers 4 are characterized by the fact that they are at do not flocculate such temperature loads and thus even with a vibration stress of the base material 1, for example, by centrifugal forces, a relative movement between the porous material 2 and the viscous filler. 4 cause. This relative movement then leads to a vibration reduction.
  • the porous material 2 and the viscous filler 4 in the ratio of 4 to 1, from 3 to 1 or from 2 to 1 or in any other Mixing ratio mixed.
  • a metal material made of a heat-resistant alloy provided, which consists essentially of at least one material Ni-based, a Co-based material, a material Fe base and / or a Ti-based material is formed.
  • the solid layer 6 has, for example, a thickness d of 100 microns to 1,000 microns, in particular from 180 microns to 350 microns or from 350 ⁇ m to 500 ⁇ m.
  • a high-temperature component 8 which, for example as a blade 10, z. B. as a guide or blade, as a stationary or as a movable shovel, for one not shown turbomachine is formed.
  • the high-temperature component 8 can also be used as a carrier element, Bearing element or ring element for a turbomachine be educated.
  • the blade 10 is in the embodiment of an airfoil 12, a paddle platform 14 and a blade root 16 formed. Alternatively, the blade 10 in not closer shown way, depending on the blade type and an upper and include lower blade platform. About the blade root 14 the blade 10 is arranged in the turbomachine.
  • the airfoil 12 can be at least one Third to half of the base material 1 and thus from the porous material 2 filled with the viscous filler 4 and surrounded by the solid layer 6, be formed.
  • FIG. 3 shows a cast rotor blade 20 with an airfoil 22, a platform 24 and a blade root 26 in a partial section.
  • the airfoil 22 and the blade root 26 is at least partially hollow.
  • a not shown Casting device which is used for pouring the blade 20 will, casting cores on, after pouring the blade 20 are removed, leaving the cavities 28.
  • the casting cores extend doing so from the blade root 26 through the blade 20 to the Blade tip 30, so that the casting cores outside the Blade 20 are attached to the casting device.
  • the Molded with this casting device blade 20 has the blade tip 30 and the blade root 26 through the core cores caused Kernhalteötechnisch 32.
  • porous materials and viscous fillers disposed through the blade root 26 Core holding openings 32 in the cavities 28 of the blade 20 are introduced.
  • a vibration-damping Material only a quartz sand or a Granules of visco-elastic substances in the hollow blade 20 are filled.
  • the cast walls 34 of the blade 20 then surrounded as a solid layer 6 that the vibrational energy dissipative filler.
  • a granular material 36 as a base material be used.
  • Fig. 3 is the granular Material indicated only in a cavity 28.
  • a suitable, in particular irregular, form of the grains 35 are these under formation of a variety of comparative small cavities 37 together, in which optionally the viscous filler can be filled.
  • Attaching the Cast Cores Outside of the Blade 20 has the further advantage that the usual fixing pins, which hold the casting cores with each other, can be omitted.
  • the better fixation of Cast cores more uniform wall thicknesses of the airfoil 22, which gives a better temperature distribution and stress distribution in the walls 34 of the airfoil 22 causes and thus to a further increase in the life of the Blade 20 leads.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04004021A 2004-02-23 2004-02-23 Composant à haute température d'une turbomachine et turbomachine Withdrawn EP1566519A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP04004021A EP1566519A1 (fr) 2004-02-23 2004-02-23 Composant à haute température d'une turbomachine et turbomachine
US11/062,303 US7347664B2 (en) 2004-02-23 2005-02-18 High-temperature component for a turbomachine, and a turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04004021A EP1566519A1 (fr) 2004-02-23 2004-02-23 Composant à haute température d'une turbomachine et turbomachine

Publications (1)

Publication Number Publication Date
EP1566519A1 true EP1566519A1 (fr) 2005-08-24

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Application Number Title Priority Date Filing Date
EP04004021A Withdrawn EP1566519A1 (fr) 2004-02-23 2004-02-23 Composant à haute température d'une turbomachine et turbomachine

Country Status (2)

Country Link
US (1) US7347664B2 (fr)
EP (1) EP1566519A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
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EP1980715A1 (fr) * 2007-04-13 2008-10-15 Siemens Aktiengesellschaft Amortissement de vibrations dans des aubes mobiles et fixes par granulat
DE102008058141A1 (de) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Verfahren zum Herstellen einer Schaufel für einen Rotor einer Strömungsmaschine
DE102008058142A1 (de) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Verfahren zum Herstellen und/oder Reparieren eines Rotors einer Strömungsmaschine und Rotor hierzu
EP2851510A1 (fr) * 2013-09-24 2015-03-25 Siemens Aktiengesellschaft Aube pour une turbomachine
EP2907973A3 (fr) * 2014-02-14 2015-11-18 United Technologies Corporation Procédé d'assemblage d'un composant amorti par particules d'un moteur à turbine à gaz et aube statorique structurelle associée
CN109083685A (zh) * 2017-06-13 2018-12-25 通用电气公司 冷却布置和创建冷却布置的方法

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US9004873B2 (en) * 2010-12-27 2015-04-14 Rolls-Royce Corporation Airfoil, turbomachine and gas turbine engine
US8734111B2 (en) 2011-06-27 2014-05-27 General Electric Company Platform cooling passages and methods for creating platform cooling passages in turbine rotor blades
US9925584B2 (en) * 2011-09-29 2018-03-27 United Technologies Corporation Method and system for die casting a hybrid component
US9181806B2 (en) * 2012-04-24 2015-11-10 United Technologies Corporation Airfoil with powder damper
GB201216343D0 (en) 2012-09-13 2012-10-24 Rolls Royce Plc Filled static structure for axial-flow machine
US9903434B2 (en) * 2013-08-21 2018-02-27 General Electric Company Components having vibration dampers enclosed therein and methods of forming such components
US10215029B2 (en) 2016-01-27 2019-02-26 Hanwha Power Systems Co., Ltd. Blade assembly
US10577940B2 (en) 2017-01-31 2020-03-03 General Electric Company Turbomachine rotor blade
US11365636B2 (en) 2020-05-25 2022-06-21 General Electric Company Fan blade with intrinsic damping characteristics
US11739645B2 (en) 2020-09-30 2023-08-29 General Electric Company Vibrational dampening elements
US11536144B2 (en) 2020-09-30 2022-12-27 General Electric Company Rotor blade damping structures
CN112610285B (zh) * 2020-12-18 2021-09-14 武汉大学 一种仿金刚石晶胞拓扑的汽轮机空心静叶强化除湿结构及汽轮机除湿装置
US11767765B2 (en) 2021-09-28 2023-09-26 General Electric Company Glass viscous damper
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CN109083685B (zh) * 2017-06-13 2023-08-29 通用电气公司 冷却布置和创建冷却布置的方法

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