EP2644828A1 - Aube de turbine modulaire avec plateforme - Google Patents

Aube de turbine modulaire avec plateforme Download PDF

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Publication number
EP2644828A1
EP2644828A1 EP12162106.4A EP12162106A EP2644828A1 EP 2644828 A1 EP2644828 A1 EP 2644828A1 EP 12162106 A EP12162106 A EP 12162106A EP 2644828 A1 EP2644828 A1 EP 2644828A1
Authority
EP
European Patent Office
Prior art keywords
platform
turbine blade
blade
elements
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.)
Withdrawn
Application number
EP12162106.4A
Other languages
German (de)
English (en)
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
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 EP12162106.4A priority Critical patent/EP2644828A1/fr
Priority to CN201380017983.3A priority patent/CN104220700A/zh
Priority to US14/388,458 priority patent/US20150071783A1/en
Priority to IN7525DEN2014 priority patent/IN2014DN07525A/en
Priority to PCT/EP2013/056652 priority patent/WO2013144270A1/fr
Priority to JP2015502347A priority patent/JP2015512486A/ja
Priority to EP13713848.3A priority patent/EP2807342A1/fr
Publication of EP2644828A1 publication Critical patent/EP2644828A1/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Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/80—Platforms for stationary or moving blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the invention relates to a turbine blade with a platform and an airfoil, which follow one another directly along a longitudinal axis of the turbine blade.
  • 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.
  • the object of the invention is to provide a modular turbine blade which is constructed and assembled in a particularly simple yet highly reliable manner.
  • the turbine blade comprises at least one platform and an airfoil, which follow one another along a longitudinal axis of the turbine blade, corresponding to the radial direction of a turbomachine, wherein the airfoil has an extension in the longitudinal direction and the platform has an outer platform part and a radial reference to the longitudinal axis at least two-part inner platform part, wherein the inner platform part on the extension of the airfoil laterally abuts and the outer platform part is formed as a the outer edge of the inner platform part encompassing endless platform frame.
  • the main components of the inner platform part are here each referred to as a platform element.
  • the invention is based on the finding that separately produced platform elements of a turbine blade can be fastened in a particularly simple manner to a separately produced airfoil, if they are laterally applied to an end extension of the airfoil, a so-called extension, and the two platform elements Help a clip to be pressed against the extension of the airfoil.
  • a first platform element can be arranged on the suction side and a second platform element on the pressure side.
  • the clip is designed as an endlessly circulating platform frame. Due to the annular - endless - shape of the platform frame this can cling to the platform elements in a shrink fit, so that a further backup of the platform frame against any loss is no longer mandatory.
  • the extension of the airfoil is set back over a step with respect to the pressure-side and suction-side airfoil surfaces, so that one with respect to the longitudinal axis of the Turbine blade parallel displacement of the adjacent to the stage platform elements is not possible.
  • 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 is that, in particular, two different materials can also be used for the platform elements, the airfoil 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.
  • 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 platform elements may be cooled. After assembly of platform frame and platform elements and a subsequent temperature adjustment, the platform frame then sits firmly against the peripheral edge of the inner platform part. 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 special feature of the proposed turbine blade is that the platform elements are applied by means of a movement perpendicular to the longitudinal axis of the extension and their securing element against a return movement in the form of the platform frame with a movement transverse to it - ie parallel to the longitudinal axis - the platform elements is slipped over. Thereafter, only to ensure that only the platform frame is secured against loosening. A displacement of the platform comprising the platform elements and the platform frame parallel to the longitudinal axis is also blocked due to the step between the actual airfoil and the extension and the collar on the extension.
  • the inner platform part expediently comprises two platform elements, but it is also possible for more platform elements to be provided.
  • the construction according to the invention allows the use of different materials for the different components of the turbine blade.
  • the airfoil and the platform elements may be made of different materials, which are tuned to the respective local requirements and loads, as described in the introduction.
  • the platform frame may be made of a material most suitable for its purpose.
  • different alloys and cast materials can be used within a turbine blade.
  • the turbine blade can be equipped both at its first blade end and at a second end opposite the first end a previously described platform having an inner platform part with a plurality of platform elements and an outer platform part formed from a platform frame.
  • the blade at both ends each have a projection described above.
  • the plurality of platform elements can be coupled together with one another and / or a platform element, a plurality of platform elements or all platform elements with the airfoil via bolts.
  • both platform elements may have mutually opposite, aligned bores in which a bolt is inserted. This improves the mechanical coupling between the two platform elements and increases the strength of the turbine blade assembled from individual components.
  • the platform elements may have parallel to the longitudinal axis extending through holes and / or blind holes in which bolts are inserted, which also sit in extending through the collar of the extension openings.
  • Such bolting extension of the airfoil with the platform elements prevents the release of the platform elements from the airfoil even without the presence of the platform frame. In addition to facilitating assembly, this measure increases the strength of the turbine blade and the reliability of the turbine blade in the unlikely event that the platform frame on or even tears.
  • the inner platform part and the outer platform part be coupled via a tongue and groove connection.
  • the platform frame is flat against the inner platform part, wherein the contact surface at least partially with the longitudinal axis forms an angle which is greater than 0 ° and smaller 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 inner 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 platform frame on at least one laterally outwardly facing surface on a slot for receiving a sealing element.
  • 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 inner platform part encompassing endless platform frame 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.
  • a seamless protective layer can be applied to both platform parts.
  • FIG. 1 a part of a turbine blade 10 is shown in the manner of an exploded view.
  • the turbine blade 10 has a modular design and, according to this exemplary embodiment, thus comprises, as separately produced components, an airfoil 12, two platform elements 14, 16 as well as a platform frame 18 and a plurality of these interconnecting Bolt 20. Furthermore, the turbine blade 10 comprises a virtual longitudinal axis 11.
  • the airfoil 12 is aerodynamically curved and has a known manner on a pressure side 22 and a suction side 24.
  • the pressure side 22 and the suction side 24 connect at a leading edge 23 and at a trailing edge 25.
  • a working medium flows from the leading edge 23 to the trailing edge 25.
  • an extension 26 is provided which is formed integrally with the profile of the airfoil 12. Laterally, the extension 26 is curved in an analogous manner to the pressure side 22 and the suction side 24 aerodynamically. However, the extension 26 is formed substantially smaller by its profile dimensions than the profile of the blade 12 predetermined by the blade walls 22, 24, so that the extension connects to the blade 12 via a step 28.
  • the extension 26 comprises at its free end 30 a collar 32. This collar 32 extends transversely to the longitudinal axis 11 and along the entire circulation of the profile, whereby it forms a circumferential groove 34 with the step 28.
  • each of the suction side and the pressure side three through holes 36 are provided in the collar 32 of the extension 26, which open into one of the side walls of the groove 34. Laterally of the extension 26, two platform elements 14, 16 are located, whereby a larger number of platform elements can be provided.
  • the platform elements 14, 16 have a platform material thickness that substantially corresponds to the width of the groove 34.
  • the platform elements 14, 16 have upstream of the front edge 23 and downstream of the trailing edge 25 in each case one or more blind holes 38, in which bolts 20 are partially inserted.
  • the orientation of the blind holes 38 is on the one hand perpendicular to the longitudinal axis 11 and on the other hand so chosen that with two bolts inserted, the two platform elements 14, 16 can be pushed towards each other until both platform elements 14, 16 rest in the groove 34 sitting on the extension 26.
  • the platform elements 14, 16 on their side facing away from the working medium, hereinafter referred to as rear side 40, blind holes 42 which, after the platform elements 14, 16 sit in the groove 34, aligned with the respective through holes 36 of the collar 32. Sonach pin-like bolts can be inserted into the aligned holes 36, 42, whereby the platform elements 14, 16 are for the first time firmly connected to the blade 12.
  • the platform frame 18 is displaced parallel to the longitudinal axis 11 of the turbine blade 10 until it clasps the two platform elements 14, 16.
  • a shrink fit of the platform frame 18 is preferred.
  • the two platform elements 14, 16 are pressed against one another firmly against the other and pressed into the groove 34, so that they can not move along the longitudinal axis 11 due to the then resulting positive fit.
  • the two platform elements 14, 16 then form an inner platform part 13 of the turbine blade 10 and the platform frame 18 an outer platform part 15 of the turbine blade 10.
  • Inner platform part 13 and outer platform part 15 form the platform 17 (FIG. FIG. 2 ).
  • a tongue and groove connection is in each case formed on both longitudinal edges 41 of the inner platform part 13 and on both longitudinal struts 46 of the platform frame 18.
  • an associated spring 48 is shown on an inner side of the longitudinal strut 46 and an associated groove 50 on the longitudinal edge of the platform element 14.
  • a tongue and groove connection can also be provided on the transverse edges or transverse struts.
  • one or more entanglements 52 are provided on both the inflow and outflow sides in order to insert the turbine blade 10 into a turbine guide vane carrier and to fasten it thereto. Accordingly, the in FIG. 1 Turbine blade 10 shown formed as a vane.
  • the means for securing the turbine blade 10 are preferably monolithically formed on the extension 26, so that the means referred to as blade root is then integrally connected to the extension 26 and the blade 12.
  • a circumferential groove 34 for the platform elements 14, 16 is provided in any case also in the blade.
  • FIG. 2 schematically shows a partial perspective sectional view of the turbine blade 10 according to FIG. 1 in assembled final state.
  • FIG. 2 neither the holes arranged in the collar 32 nor the bolts seated therein are shown.
  • the division of the inner platform part 13 into the pressure-side platform element 14 and the suction-side platform element 16 according to the perspective illustration in FIG FIG. 3 recognizable.
  • FIG. 4 shows the turbine blade 10 with its head-side end 55, which in a similar manner to the foot-side end of a modular platform 17 comprising two platform elements 14, 16 and the platform frame 18 may have.
  • the head-side end 55 differs from the foot-side end only with respect to the side facing away from the working medium of the platform 17.
  • turbine vanes 10 which are used in stationary gas turbines, at the head end 55 so-called U-rings attached, which couple and connect the arranged in a ring vanes head side.
  • a slot 54 is shown on a side outwardly facing surface 53 of the platform frame 18. The slot 54 serves to receive sheet-like sealing elements, which may be provided between adjacent guide vanes for sealing the gap between them.
  • the invention relates to a turbine blade 10 comprising an airfoil 12 and a modular platform 17, which follow one another along a longitudinal axis 11 of the turbine blade 10.
  • a modular turbine blade 10 which on the one hand is particularly simple and simple in construction and on the other hand ensures a particularly reliable, durable and permanent connection of the individual components with each other, it is proposed that the blade 12 has an extension 26 and the platform 17 an outer Platform part 15 and an at least two-part - in radial relation to the longitudinal axis 11 - inner platform portion 13 which rest on the extension 26 of the airfoil 12 laterally and wherein the outer platform portion 15 formed as a the outer edge of the inner platform portion 13 encompassing endless platform frame 18 is.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12162106.4A 2012-03-29 2012-03-29 Aube de turbine modulaire avec plateforme Withdrawn EP2644828A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP12162106.4A EP2644828A1 (fr) 2012-03-29 2012-03-29 Aube de turbine modulaire avec plateforme
CN201380017983.3A CN104220700A (zh) 2012-03-29 2013-03-28 具有平台的模块化的涡轮叶片
US14/388,458 US20150071783A1 (en) 2012-03-29 2013-03-28 Turbine blade
IN7525DEN2014 IN2014DN07525A (fr) 2012-03-29 2013-03-28
PCT/EP2013/056652 WO2013144270A1 (fr) 2012-03-29 2013-03-28 Aube de turbine modulaire à plate-forme
JP2015502347A JP2015512486A (ja) 2012-03-29 2013-03-28 プラットフォームを有するモジュール式タービン翼
EP13713848.3A EP2807342A1 (fr) 2012-03-29 2013-03-28 Aube de turbine modulaire à plate-forme

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12162106.4A EP2644828A1 (fr) 2012-03-29 2012-03-29 Aube de turbine modulaire avec plateforme

Publications (1)

Publication Number Publication Date
EP2644828A1 true EP2644828A1 (fr) 2013-10-02

Family

ID=48045499

Family Applications (2)

Application Number Title Priority Date Filing Date
EP12162106.4A Withdrawn EP2644828A1 (fr) 2012-03-29 2012-03-29 Aube de turbine modulaire avec plateforme
EP13713848.3A Withdrawn EP2807342A1 (fr) 2012-03-29 2013-03-28 Aube de turbine modulaire à plate-forme

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP13713848.3A Withdrawn EP2807342A1 (fr) 2012-03-29 2013-03-28 Aube de turbine modulaire à plate-forme

Country Status (6)

Country Link
US (1) US20150071783A1 (fr)
EP (2) EP2644828A1 (fr)
JP (1) JP2015512486A (fr)
CN (1) CN104220700A (fr)
IN (1) IN2014DN07525A (fr)
WO (1) WO2013144270A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016068859A1 (fr) * 2014-10-28 2016-05-06 Siemens Energy, Inc. Aube de turbine modulaire

Families Citing this family (3)

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Publication number Priority date Publication date Assignee Title
US10934870B2 (en) 2018-09-17 2021-03-02 Rolls Royce Plc Turbine vane assembly with reinforced end wall joints
CN110132556B (zh) * 2019-04-30 2021-11-12 中国航发湖南动力机械研究所 模块化涡轮试验件及其试验方法
DE102020201448A1 (de) * 2020-02-06 2021-08-12 Siemens Aktiengesellschaft Additiv hergestellte Turbinenschaufel mit Verdrehsicherung und Justageverfahren

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US2727716A (en) * 1945-12-21 1955-12-20 Power Jets Res & Dev Ltd Bladed body
US3451654A (en) * 1967-08-25 1969-06-24 Gen Motors Corp Blade vibration damping
FR2463849A1 (fr) * 1979-08-23 1981-02-27 Onera (Off Nat Aerospatiale) Perfectionnements apportes aux aubes tournantes de turbines a gaz, et aux turbines a gaz equipees de ces aubes
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
EP0433111A1 (fr) * 1989-11-15 1991-06-19 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Elément de stator de turbomachine
JPH04252806A (ja) * 1990-08-15 1992-09-08 Tokyo Electric Power Co Inc:The ガスタービンの静翼
DE10346240A1 (de) * 2003-10-06 2005-04-21 Alstom Technology Ltd Baden Bauteil einer Gasturbine
US20060245715A1 (en) * 2005-04-27 2006-11-02 Honda Motor Co., Ltd. Flow-guiding member unit and its production method
US20100150703A1 (en) * 2006-09-22 2010-06-17 Siemens Power Generation, Inc. Stacked laminate bolted ring segment
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EP2213839A2 (fr) * 2009-01-28 2010-08-04 United Technologies Corporation Segment en céramique d'un moteur à turbine à gaz
US20110142639A1 (en) * 2009-12-15 2011-06-16 Campbell Christian X Modular turbine airfoil and platform assembly with independent root teeth

Cited By (3)

* Cited by examiner, † Cited by third party
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WO2016068859A1 (fr) * 2014-10-28 2016-05-06 Siemens Energy, Inc. Aube de turbine modulaire
CN107075952A (zh) * 2014-10-28 2017-08-18 西门子能源公司 模块化涡轮叶片
JP2017537255A (ja) * 2014-10-28 2017-12-14 シーメンス エナジー インコーポレイテッド モジュール式のタービンベーン

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EP2807342A1 (fr) 2014-12-03
WO2013144270A1 (fr) 2013-10-03
IN2014DN07525A (fr) 2015-04-24
JP2015512486A (ja) 2015-04-27
US20150071783A1 (en) 2015-03-12

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