EP2644834A1 - Turbinenschaufel sowie zugehöriges Verfahren zum Herstellen einer Turbinenschaufel - Google Patents

Turbinenschaufel sowie zugehöriges Verfahren zum Herstellen einer Turbinenschaufel Download PDF

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Publication number
EP2644834A1
EP2644834A1 EP12162103.1A EP12162103A EP2644834A1 EP 2644834 A1 EP2644834 A1 EP 2644834A1 EP 12162103 A EP12162103 A EP 12162103A EP 2644834 A1 EP2644834 A1 EP 2644834A1
Authority
EP
European Patent Office
Prior art keywords
platform
turbine blade
frame
platform frame
fuselage
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Withdrawn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
EP12162103.1A
Other languages
German (de)
English (en)
French (fr)
Inventor
Fathi Ahmad
Nihal Kurt
Hans-Thomas Bolms
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 EP12162103.1A priority Critical patent/EP2644834A1/de
Priority to CN201380017991.8A priority patent/CN104204417A/zh
Priority to PCT/EP2013/056594 priority patent/WO2013144245A1/de
Priority to JP2015502338A priority patent/JP2015517048A/ja
Priority to US14/388,411 priority patent/US20150064018A1/en
Priority to IN7295DEN2014 priority patent/IN2014DN07295A/en
Priority to RU2014143493A priority patent/RU2014143493A/ru
Priority to EP13713842.6A priority patent/EP2805023A1/de
Publication of EP2644834A1 publication Critical patent/EP2644834A1/de
Withdrawn legal-status Critical Current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
    • 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
    • F01D5/14—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
    • 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 mounting portion, a platform and an airfoil, which follow one another along a longitudinal axis of the turbine blade.
  • the invention further relates to a method of manufacturing a turbine blade, comprising the step of producing a monolithic fuselage blade comprising an airfoil, a platform and a mounting section.
  • Turbine blades and methods of making turbine blades are known in a variety of ways from the extensive prior art.
  • turbine blades for gas turbines are often produced in a casting process.
  • the blade root, platform and blade are formed from the casting material at the same time, so that such turbine blades are in one piece.
  • the surfaces exposed to the hot gas of the turbine are still provided with a corrosion protection layer and a thermal protection layer in order to increase the service life of the turbine blade.
  • the cast turbine blades are usually also hollow, 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 turbomachinery are subject to a variety of stresses during operation of the turbomachinery which cause the turbine blades to age and wear down in both predictable and unpredictable ways.
  • both low-cycle and higher cyclic fatigue loads as well as thermo-mechanical loads occur.
  • turbine blades are to be protected from oxidation and creep.
  • the above-mentioned loads relate in particular to the surfaces and components of the turbine blades which are directly exposed to the hot gas or superheated steam.
  • turbine blades are also exposed to so-called “bearing loads” and “friction loads”.
  • the material of integral turbine blades must be selected so that, if possible, a large number, if not all, loads are absorbed by the material without premature aging or premature end-of-life of the turbine blade being achieved.
  • the thermal load and with regard to the corrosion load it is known, for example, to equip turbine blades of gas turbines with a layer system which protects their material against corrosion as well as against excessive heat input.
  • the object of the invention is to provide a turbine blade with a fastening portion, a platform and an airfoil, which follow one another along a longitudinal axis of the turbine blade, which turbine blade with particularly low effort is reprocessed.
  • Another object of the invention is to provide a method of manufacturing turbine blades.
  • the task directed to the turbine blade is achieved with such according to the features of claim 1.
  • the object directed to the method for producing a turbine blade is achieved with the method steps according to claim 8.
  • Advantageous embodiments are specified in the respective subclaims.
  • the features of the respective subclaims with the features of other claims are readily combinable.
  • the invention is based on the finding that, in particular in the case of operationally stressed turbine blades, it is also possible for defects caused by oxidation to occur at the outer edge of the platform. These oxidation problems occur, in particular, when the thermal insulation layer, which is often provided there, locally flakes off. Such findings can lead to an increased operating risk in the turbine blade, which is why such turbine blades are replaced or processed.
  • the reprocessing of the turbine blade has been comparatively expensive.
  • the work-up rate i. the proportion of recycled blades that actually continue to qualify for use in the turbomachinery after reprocessing is likely to be low.
  • the platform comprises - in relation to a central longitudinal axis - an inner platform part and an outer platform part, the outer platform part being designed as an endless platform frame encompassing the outer edge of the inner platform part.
  • the flaws indicated above near the edge of the platform are to be removed, for example by passing the edge of the platform Milling or grinding is reset.
  • the platform edge is reset along the entire circulation so as to produce a monolithic fuselage bucket whose platform provides an abutment surface for a platform frame as an inner platform part of the turbine bucket to be produced. After attaching an endless platform frame to the inner platform portion, the turbine bucket thus produced then has a platform whose dimensions correspond to the original turbine bucket.
  • the method it is also possible to produce new components, ie turbine blades not subjected to operation, by first providing a so-called fuselage blade comprising an airfoil, a platform and a fastening section in a monolithic embodiment.
  • the monolithic fuselage bucket can be produced conventionally by casting and, for example, also be monocrystalline or directionally solidified.
  • the platform edge of the fuselage shovel may need to be brought to the predetermined, exact extent along the entire cycle by slight grinding or milling to provide the inner platform portion of the turbine bucket with a dimensionally bearing surface for the platform frame.
  • the platform frame Before, during or after the platform frame is to produce as a mostly rectangular structure. After attaching or mounting the platform frame to the dimensionally stable edge of the inner platform part, the turbine blade is then produced as a new component.
  • the platform frame may have different shapes in cross section. Preferably, however, such forms, which bring about a positive connection with the edge of the inner platform part.
  • the cross-sectional shape may be diamond-shaped or C-shaped.
  • the edge of the inner platform part is always executed corresponding to the cross-sectional shape.
  • a particular advantage of the turbine blade according to the invention and also of the method is that in particular also two different materials can be used for the fuselage bucket and for the platform frame. Thus, in addition to the different local loads consideration be taken, which possibly leads to an extended life of the turbine blade.
  • a further advantage of the turbine blade according to the invention is the higher precision with regard to the external dimensions of the platform, since these can be produced more easily when producing the platform frame than when casting a purely monolithic turbine blade.
  • Different methods can be used for permanently connecting the platform frame to the fuselage bucket. Since the platform frame is designed as an endless frame, it is preferable to shrink the platform frame to the peripheral edge of the inner platform part. Prior to shrinking, the platform frame may be heated and / or the fuselage shovel may be cooled. After assembly of the platform frame and fuselage bucket and subsequent temperature adjustment, the platform frame then sits firmly against the peripheral edge of the inner platform portion. Also soldering and welding - at points as well as along the connecting line from the edge of the inner platform part and platform frame - are possible.
  • the platform frame is flat against the inner platform part, wherein the contact surface at least partially encloses an angle with the longitudinal axis which is greater than 0 ° and less than 90 °.
  • Such an arrangement prevents at least in one direction a parallel displacement of the platform frame along the longitudinal axis, which is particularly advantageous when using the invention on turbine blades.
  • the centrifugal force acting on the platform frame during operation of the turbomachine is also transferred into the platform part by positive engagement due to the contact surface inclined with respect to the longitudinal axis. This reliably prevents the loss of the platform frame due to the centrifugal force.
  • the angle is a size between 15 ° and 35 °, for example, the angle is 20 °.
  • the turbine blade may be formed both as a vane or as a blade.
  • the turbine blade with the inner platform part and the outer platform part in the form of the endless platform frame enclosing the inner platform part can also be used in high-temperature applications, it is advantageous if the inner platform part and the platform frame are coated in a coating process. Thus, can a seamless protective layer can be applied to both platform parts.
  • FIG. 1 shows a perspective view of a turbine blade 10.
  • the turbine blade 10 is formed as a blade. However, it could also be designed as a guide vane.
  • the turbine blade 10 comprises, along its longitudinal axis 12, a fastening section 14, a platform 16 and an airfoil 18 in direct succession.
  • the mounting section 14 is contoured in a manner typical of a blade in the manner of a fir tree profile.
  • Guide vanes for turbines, instead of the fir-tree-shaped attachment portion 14 mostly a plurality of hooks, which are inserted into a not shown guide vane carrier of the turbomachine.
  • the attachment portion 14 merges into the platform 16.
  • the platform 16 has an upwardly facing platform surface 20, where the blade 18 settles.
  • the platform 16 includes an inner platform portion 22 and an outer platform portion 24 radially relative to the longitudinal axis 12, the outer platform portion 24 being formed as an endless platform frame 28 encompassing the outer edge 26 of the inner platform portion 22.
  • both attachment portion 14, the inner platform portion 22 and the blade 18 are monolithic - that is, in one piece - formed. This monolithic unit is also referred to as a fuselage bucket 19.
  • the surfaces 20 of the inner platform part 22 and of the outer platform part 24 pointing in this illustration to the blade leaf 18 are mutually offset so that they - when using the turbine blade 10 in a turbomachine - have an edge-free and boundary-free boundary wall for the working medium flowing in the turbomachine provide.
  • the turbine blade 10 may be formed internally cooled in any way by means of a cooling medium. Film cooling openings and trailing edge openings for coolant can also be provided. Of course, the turbine blade can also be uncooled.
  • FIG. 2 shows in perspective view the platform frame 28.
  • the platform frame 28 comprises two mutually parallel longitudinal struts 30 and two mutually parallel transverse struts 32.
  • the platform frame 28 may be made of a different material than those in FIG. 1 illustrated fuselage bucket 19.
  • the platform frame 28 may also be made of the same material.
  • the platform frame may also be made by welding the longitudinal struts 30 to the cross struts 32. It can also be cast or milled from solid.
  • FIG. 3 shows a section through the turbine blade 10 along the longitudinal axis 12.
  • the mounting portion according to FIG. 3 not fir-tree-shaped, but dovetail-shaped.
  • FIG. 3 shows FIG. 3 the platform frame 28 during assembly to the fuselage 19, just before the platform frame 28 reaches its final mounting position.
  • the platform frame 28 has a diamond shape in cross section. Other shapes are possible.
  • Each strut 30, 32 of the platform frame 28 has an inwardly directed first abutment surface 34 and a second abutment surface 36.
  • the outer edge 26 of the inner platform portion 22 has a laterally outwardly facing first abutment surface 38 and a second abutment surface 40.
  • FIG. 4 shows in perspective a corner of the inner platform part 22 and the platform frame 28 during assembly. In addition to the features already described is also in FIG. 4 on a laterally outwardly facing surface 42 of the platform frame 28, a slot 44 for receiving a sheet-like sealing element shown.
  • the invention thus relates to a turbine blade 10 having a mounting portion 14, a platform 16 and an airfoil 18, which follow one another along a longitudinal axis 12 of the turbine blade directly on each other.
  • the platform 16 in relation to the longitudinal axis 12 - an inner platform portion 22 and an outer platform portion 24, wherein the outer platform portion 24 as an outer edge 26 of the inner platform portion 22 encompassing endless Platform frame 28 is formed.

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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)
EP12162103.1A 2012-03-29 2012-03-29 Turbinenschaufel sowie zugehöriges Verfahren zum Herstellen einer Turbinenschaufel Withdrawn EP2644834A1 (de)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP12162103.1A EP2644834A1 (de) 2012-03-29 2012-03-29 Turbinenschaufel sowie zugehöriges Verfahren zum Herstellen einer Turbinenschaufel
CN201380017991.8A CN104204417A (zh) 2012-03-29 2013-03-27 涡轮叶片以及相关的用于制造涡轮叶片的方法
PCT/EP2013/056594 WO2013144245A1 (de) 2012-03-29 2013-03-27 Turbinenschaufel sowie zugehöriges verfahren zum herstellen einer turbinenschaufel
JP2015502338A JP2015517048A (ja) 2012-03-29 2013-03-27 タービンブレード、及び当該タービンブレードを製造するための方法
US14/388,411 US20150064018A1 (en) 2012-03-29 2013-03-27 Turbine blade and associated method for producing a turbine blade
IN7295DEN2014 IN2014DN07295A (OSRAM) 2012-03-29 2013-03-27
RU2014143493A RU2014143493A (ru) 2012-03-29 2013-03-27 Лопатка турбины, а также соответствующий способ изготовления лопатки турбины
EP13713842.6A EP2805023A1 (de) 2012-03-29 2013-03-27 Turbinenschaufel sowie zugehöriges verfahren zum herstellen einer turbinenschaufel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12162103.1A EP2644834A1 (de) 2012-03-29 2012-03-29 Turbinenschaufel sowie zugehöriges Verfahren zum Herstellen einer Turbinenschaufel

Publications (1)

Publication Number Publication Date
EP2644834A1 true EP2644834A1 (de) 2013-10-02

Family

ID=48045493

Family Applications (2)

Application Number Title Priority Date Filing Date
EP12162103.1A Withdrawn EP2644834A1 (de) 2012-03-29 2012-03-29 Turbinenschaufel sowie zugehöriges Verfahren zum Herstellen einer Turbinenschaufel
EP13713842.6A Withdrawn EP2805023A1 (de) 2012-03-29 2013-03-27 Turbinenschaufel sowie zugehöriges verfahren zum herstellen einer turbinenschaufel

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP13713842.6A Withdrawn EP2805023A1 (de) 2012-03-29 2013-03-27 Turbinenschaufel sowie zugehöriges verfahren zum herstellen einer turbinenschaufel

Country Status (7)

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

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Publication number Priority date Publication date Assignee Title
EP2644828A1 (de) * 2012-03-29 2013-10-02 Siemens Aktiengesellschaft Modulare Turbinenschaufel mit Plattform
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
EP3438410B1 (en) 2017-08-01 2021-09-29 General Electric Company Sealing system for a rotary machine
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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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
JPS6241902A (ja) * 1985-08-15 1987-02-23 Hitachi Ltd ガスタ−ビン用動翼構造
WO2000057032A1 (de) * 1999-03-24 2000-09-28 Siemens Aktiengesellschaft Leitschaufel und leitschaufelkranz für eine strömungsmaschine, sowie bauteil zur begrenzung eines strömungskanals
US20060245715A1 (en) * 2005-04-27 2006-11-02 Honda Motor Co., Ltd. Flow-guiding member unit and its production method
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
EP1992786A2 (en) * 2007-05-15 2008-11-19 General Electric Company Rotor blade platform and corresponding bladed rotor assembly

Also Published As

Publication number Publication date
RU2014143493A (ru) 2016-05-20
US20150064018A1 (en) 2015-03-05
EP2805023A1 (de) 2014-11-26
IN2014DN07295A (OSRAM) 2015-04-24
WO2013144245A1 (de) 2013-10-03
JP2015517048A (ja) 2015-06-18
CN104204417A (zh) 2014-12-10

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