EP3280879B1 - Anordnung für eine turbine - Google Patents

Anordnung für eine turbine Download PDF

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Publication number
EP3280879B1
EP3280879B1 EP16726577.6A EP16726577A EP3280879B1 EP 3280879 B1 EP3280879 B1 EP 3280879B1 EP 16726577 A EP16726577 A EP 16726577A EP 3280879 B1 EP3280879 B1 EP 3280879B1
Authority
EP
European Patent Office
Prior art keywords
arrangement
segments
support
support strut
segment
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.)
Active
Application number
EP16726577.6A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3280879A1 (de
Inventor
Bernd Burbaum
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 Energy Global GmbH and Co KG
Original Assignee
Siemens Energy Global GmbH and Co KG
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 Energy Global GmbH and Co KG filed Critical Siemens Energy Global GmbH and Co KG
Priority to PL16726577T priority Critical patent/PL3280879T3/pl
Publication of EP3280879A1 publication Critical patent/EP3280879A1/de
Application granted granted Critical
Publication of EP3280879B1 publication Critical patent/EP3280879B1/de
Active 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine 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
    • 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
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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
    • F01D5/284—Selection of ceramic materials
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/311—Layer deposition by torch or flame spraying
    • 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
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/51—Building or constructing in particular ways in a modular way, e.g. using several identical or complementary parts or features
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • 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
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6032—Metal matrix composites [MMC]
    • 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
    • F05D2300/614—Fibres or filaments

Definitions

  • the invention relates to an arrangement for a turbine according to claim 1.
  • the present invention also relates to a method for producing such an arrangement according to claim 12.
  • a blade arrangement with a blade which consists of a plurality of blade segments which are arranged one above the other in the radial direction are plate-shaped and made of a ceramic fiber composite material.
  • the individual airfoil segments each include aligned through openings through which support struts extend, for example in the form of metallic tie rods, which press the airfoil segments against each other, creating a force fit between the airfoil segments that holds them together.
  • the present invention creates an arrangement of the type mentioned at the outset, which is characterized in that at least one, for example some, support strut has at least one outwardly protruding, transversely to the radial direction extending projection which in at least one of the segments a correspondingly designed recess engages or can grip.
  • both a plurality of projections are provided on the support struts, and a plurality of cutouts, for example some cutouts, into which the projections are designed to be gripped.
  • the present invention can create a blade arrangement of the type mentioned at the beginning, which is characterized in that the at least one support strut has outwardly protruding, transversely to the radial direction extending projections which engage in correspondingly formed recesses on the blade segments.
  • segments are directly connected to the at least one support strut without the use of separate fastening means, whereby a Relative movement of the corresponding segments in a direction transverse to the radial direction is effectively prevented.
  • the support structure has a plurality of support struts, in particular three support struts, it being possible, of course, to provide a number of support struts that differs from this. Overall, a very stable arrangement is achieved by providing several support struts.
  • the at least one support strut preferably has a non-circular cross section, in particular a cross section which follows the circumferential contour of the arrangement. Such a choice of the cross section is also very beneficial to the stability of the arrangement.
  • the at least one support strut is advantageously designed to be hollow.
  • a cooling fluid can be passed through the support strut during the intended use of the arrangement, so that the at least one support strut defines a cooling channel.
  • the support structure has a platform which extends essentially parallel to the segments and from which the at least one support strut protrudes radially outward, the segments being stacked on the platform.
  • a platform connects the support struts to one another if several support struts are provided.
  • the platform defines a defined base on which the segments can be stacked.
  • such a platform can be provided with a blade root or formed in one piece with one which is used to fasten the arrangement to a turbine component.
  • a defined annular gap is preferably formed between the at least one support strut and those passage openings of the segments through which it extends.
  • the cutouts each extend starting from an upper side of the respective segment.
  • the projections can be manufactured easily, as will be explained in more detail below.
  • the at least one cutout or some or more cutouts are preferably designed in the form of chamfers which extend, for example, along the circumference of a through opening.
  • the at least one projection or the plurality of projections is advantageously received in the corresponding recess or recesses in an essentially form-fitting manner. In this way, a particularly good cohesion between the at least one support strut and the segments is achieved.
  • Each segment is preferably provided with at least one recess into which an assigned projection engages or can engage.
  • each segment is connected to the at least one support strut.
  • the outer surfaces of the at least one segment or segments are provided with a coating, in particular with a thermal barrier coating.
  • the arrangement is an arrangement for a turbine blade, in particular an airfoil, or an arrangement for a part for the turbine that is exposed to hot gas.
  • the arrangement can be an airfoil arrangement for a turbine, in particular a gas turbine.
  • the arrangement can furthermore be a ring segment arrangement for a turbine, in particular a gas turbine.
  • the arrangement can furthermore be an arrangement for another part in the gas and / or steam path of a turbine, for example a part of a gas turbine exposed to hot gas.
  • the present invention also creates a method for producing an arrangement according to the invention, the method being characterized in that at least the support struts of the support structure are produced using a generative method.
  • This can be, for example, an SLM process (Selective Laser Melting), a flame spraying process, a high-speed flame spraying process or even a build-up welding process, to name but a few examples.
  • the segments are preferably stacked using a robot. In this way, the entire manufacturing process of the arrangement can be carried out with a high degree of automation.
  • the outer surfaces of the segments are advantageously provided with a coating, in particular with a thermal barrier coating, the coating advantageously being provided subsequently.
  • the Figures 1 to 3 show an arrangement 1 according to an embodiment of the present invention or components thereof.
  • the arrangement 1 is one for a turbine, in particular a gas turbine, wherein the arrangement 1 can in principle be designed both as a rotor blade, as a guide vane and / or as a ring segment or some other part in the gas or steam path of a turbine, even if this is not shown in more detail here.
  • the arrangement 1 comprises as main components a metallic support structure with a platform 2 and three support struts 3, 4 and 5, which extend from the platform 2 in a radial direction R, and a plurality of plate-shaped segments 6 arranged one above the other on the support structure , which together define the circumferential contour of the arrangement.
  • the support structure which primarily serves to absorb and dissipate the forces acting on it during the intended use of the arrangement 1, is made of a metallic material, such as a nickel-based alloy, to name just one example.
  • the platform 2 has an essentially convexly curved suction side 7 and an essentially concavely curved pressure side 8, with fundamentally other geometries being possible.
  • the platform 2 can be a prefabricated component that was produced, for example, by means of casting and subsequent mechanical processing.
  • the platform 2 can also be manufactured using an additive manufacturing method, such as, for example, by means of an SLM method, with other additive manufacturing methods naturally also being possible.
  • the support struts 3, 4 and 5 are manufactured using an additive manufacturing process and are firmly connected to the platform 2, as will be explained in more detail below. Starting from the platform 2, they extend essentially parallel to one another, are hollow and in the present case each have a non-circular cross-section, which in the present case follows the circumferential contour of the arrangement. At the level of the upper edge of each segment 6, the support struts 3, 4 and 5 are each provided circumferentially with outwardly projecting projections 9 extending transversely to the radial direction.
  • the segments 6 are each made of a ceramic fiber composite material.
  • Al 2 O 3 2O 3 / Al 2 O 3 , C / SiC, SiC / SiC or the like can be used as the ceramic fiber composite material, to name just a few examples to call.
  • the segments 6 comprise a suction side 10 and a pressure side 11, the outer contours of adjacent segments 6 preferably being in alignment with one another, as is the outer contour of the platform 2 in the present case with the outer contour of the adjacent segment 6.
  • the segments 6 are each provided with three through openings 12 through which the respective support struts 3, 4 and 5 extend. A defined annular gap, which is only interrupted by the projections 9, can be left between the segments 6 and the support struts 3, 4 and 5.
  • annular gap can be advantageous during the intended use of the arrangement 1 in that, in the event of thermal expansion of the support struts 3, 4 and 5 and / or the segments 6, an appropriate escape space is created which reduces or prevents the occurrence of thermal stresses.
  • circumferential, chamfer-shaped recesses 13 are provided which extend along the edge regions of the respective through openings 12.
  • the projections 9 protruding from the support struts 3, 4 and 5 engage in these recesses 13 so that each segment 6 is firmly connected to the support struts 3, 4 and 5.
  • the arrangement 1 shown is, in a first step, as shown in FIG Figure 4 is shown schematically, the platform 2 of the support structure is arranged on the ground. A segment 6 is then positioned on the platform 2 in such a way that the outer contour of the segment 6 is aligned with the outer contour of the platform 2. The segment can be positioned using a robot, even if this is not shown here.
  • FIG. 4 shows schematically a nozzle arrangement 14 with which powdered metallic material is directed in the direction of the platform 2 and melted using a laser. It should be clear that, in principle, any generative LMD (laser metal deposition) process can be used.
  • LMD laser metal deposition
  • a further segment 6 is positioned on the segment 6 already attached to the platform 2, whereupon subregions of the support struts 3, 4 and 5 are again generated in layers, see Figure 7 .
  • the steps described above are repeated until the in Figure 1
  • the arrangement 1 shown is completed.
  • a stacking of the segments 6 and a step-by-step production of the support struts 3, 4 and 5 alternate, after arranging a segment 6 provided with a recess 13, a portion of the support struts 3, 4 and 5 including one in the recess 13 engaging projection 9 is generated.
  • An uppermost metallic cover layer which is provided with cooling fluid outlet bores and can be produced, for example, by means of build-up welding, can be arranged to form a blade tip.
  • a prefabricated cover layer can also be fixed to the metallic support structure by means of high-temperature soldering or the like.
  • the arrangement 1 shown can be provided with a coating, for example with a thermal barrier coating, if this is desired.
  • An essential advantage of the method according to the invention is that, during the production of a hybrid arrangement 1, the individual segments 6 are firmly and securely connected to the support structure in all spatial directions without the need for separate fastening means.
  • each segment can be provided with a recess in the representations of the figures, it is sufficient for the concept of the invention if this is only the case for at least one or some of the segments, for example two, three or four segments.
  • only at least one corresponding support strut or said plurality must have a corresponding projection.
  • the gripping connection through the projections and the recesses in the center of the arrangement or in every third or fourth stacked segment of the arrangement can be sufficient to utilize the advantages according to the invention.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Architecture (AREA)
  • Composite Materials (AREA)
  • Ceramic Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16726577.6A 2015-07-02 2016-06-02 Anordnung für eine turbine Active EP3280879B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL16726577T PL3280879T3 (pl) 2015-07-02 2016-06-02 Układ do turbiny

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102015212419.3A DE102015212419A1 (de) 2015-07-02 2015-07-02 Schaufelanordnung für eine Gasturbine
PCT/EP2016/062508 WO2017001139A1 (de) 2015-07-02 2016-06-02 Anordnung für eine turbine

Publications (2)

Publication Number Publication Date
EP3280879A1 EP3280879A1 (de) 2018-02-14
EP3280879B1 true EP3280879B1 (de) 2021-07-28

Family

ID=56097120

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16726577.6A Active EP3280879B1 (de) 2015-07-02 2016-06-02 Anordnung für eine turbine

Country Status (8)

Country Link
US (1) US10851654B2 (zh)
EP (1) EP3280879B1 (zh)
JP (1) JP6695363B2 (zh)
KR (1) KR102033653B1 (zh)
CN (1) CN107709705B (zh)
DE (1) DE102015212419A1 (zh)
PL (1) PL3280879T3 (zh)
WO (1) WO2017001139A1 (zh)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018213421A1 (de) * 2018-08-09 2020-02-13 Siemens Aktiengesellschaft CMC-Turbinenkomponente im StackWrap-Aufbau mit Kühlsystem
DE102018213417A1 (de) * 2018-08-09 2020-02-13 Siemens Aktiengesellschaft CMC-Turbinenkomponente
US11333022B2 (en) 2019-08-06 2022-05-17 General Electric Company Airfoil with thermally conductive pins

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016085654A1 (en) * 2014-11-24 2016-06-02 Siemens Aktiengesellschaft Hybrid ceramic matrix composite materials

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DE1476921U (zh)
US3301526A (en) 1964-12-22 1967-01-31 United Aircraft Corp Stacked-wafer turbine vane or blade
GB1075910A (en) * 1966-04-04 1967-07-19 Rolls Royce Improvements in or relating to blades for mounting in fluid flow ducts
JPS54102412A (en) 1978-01-31 1979-08-11 Denriyoku Chuo Kenkyusho Gas turbine vane
JPS58172406A (ja) 1982-04-05 1983-10-11 Hitachi Ltd ガスタ−ビン用の積層翼
US5820337A (en) * 1995-01-03 1998-10-13 General Electric Company Double wall turbine parts
US7247003B2 (en) 2004-12-02 2007-07-24 Siemens Power Generation, Inc. Stacked lamellate assembly
US7247002B2 (en) * 2004-12-02 2007-07-24 Siemens Power Generation, Inc. Lamellate CMC structure with interlock to metallic support structure
US7153096B2 (en) * 2004-12-02 2006-12-26 Siemens Power Generation, Inc. Stacked laminate CMC turbine vane
US7198458B2 (en) 2004-12-02 2007-04-03 Siemens Power Generation, Inc. Fail safe cooling system for turbine vanes
US7255535B2 (en) * 2004-12-02 2007-08-14 Albrecht Harry A Cooling systems for stacked laminate CMC vane
DE102006049216A1 (de) 2006-10-18 2008-04-24 Mtu Aero Engines Gmbh Hochdruckturbinen-Rotor und Verfahren zur Herstellung eines Hochdruckturbinen-Rotors
US9663404B2 (en) 2012-01-03 2017-05-30 General Electric Company Method of forming a ceramic matrix composite and a ceramic matrix component

Patent Citations (1)

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Publication number Priority date Publication date Assignee Title
WO2016085654A1 (en) * 2014-11-24 2016-06-02 Siemens Aktiengesellschaft Hybrid ceramic matrix composite materials

Also Published As

Publication number Publication date
CN107709705B (zh) 2019-12-24
KR20180021188A (ko) 2018-02-28
US20180156038A1 (en) 2018-06-07
DE102015212419A1 (de) 2017-01-05
EP3280879A1 (de) 2018-02-14
KR102033653B1 (ko) 2019-10-18
WO2017001139A1 (de) 2017-01-05
JP6695363B2 (ja) 2020-05-20
US10851654B2 (en) 2020-12-01
JP2018524510A (ja) 2018-08-30
CN107709705A (zh) 2018-02-16
PL3280879T3 (pl) 2021-12-27

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