US20150071783A1 - Turbine blade - Google Patents

Turbine blade Download PDF

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Publication number
US20150071783A1
US20150071783A1 US14/388,458 US201314388458A US2015071783A1 US 20150071783 A1 US20150071783 A1 US 20150071783A1 US 201314388458 A US201314388458 A US 201314388458A US 2015071783 A1 US2015071783 A1 US 2015071783A1
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US
United States
Prior art keywords
platform
blade
turbine blade
turbine
elements
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US14/388,458
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English (en)
Inventor
Fathi Ahmad
Hans-Thomas Bolms
Nihal Kurt
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BOLMS, HANS-THOMAS, AHMAD, FATHI, Kurt, Nihal
Publication of US20150071783A1 publication Critical patent/US20150071783A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—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
    • 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 having a platform and a blade airfoil in direct succession along a longitudinal axis of the turbine blade.
  • turbine blades for gas turbines are often manufactured by casting.
  • the blade root, platform and blade airfoil are simultaneously formed from the casting material, such that turbine blades of this type are one-piece.
  • those surfaces which are exposed to the hot gas of the turbine are also provided with a corrosion protection layer and a thermal protection layer in order to increase the service life of the turbine blade.
  • Cast turbine blades are also generally hollow in order that a coolant for cooling the blade material can flow inside.
  • Turbine blades of steam machines are generally milled from solid or are forged.
  • Turbine blades used in static turbomachines are subjected, in operation, to a multiplicity of loads which cause the turbine blades to age and wear both in foreseeable and non-foreseeable ways.
  • a further disadvantage may for example reside in a service life which is shorter in comparison with a monolithic turbine blade, which arises on account of a construction and/or connection of the individual components which is only of limited reliability.
  • the turbine blade comprises at least one platform and a blade airfoil in direct succession along a longitudinal axis of the turbine blade—corresponding to the radial direction of a turbomachine—wherein the blade airfoil has a projection in the longitudinal direction and the platform comprises—in radial relation to the longitudinal axis—an outer platform part and an at least two-part inner platform part, wherein the inner platform part bears laterally against the projection of the blade airfoil and the outer platform part is formed as an endless platform frame which grips around the outer edge of the inner platform part.
  • the main components of the inner platform part are here respectively labeled as platform elements.
  • aspects of the invention are based on the knowledge that separately manufactured platform elements of a turbine blade can be particularly simply attached to a separately manufactured blade airfoil if these are placed laterally against and end-side extension of the blade airfoil, what is termed a projection, and the two platform elements are pressed against the projection of the blade airfoil with the aid of a clamp.
  • a first platform element can be arranged on the suction side of the projection of the blade airfoil
  • a second platform element can be arranged on the pressure side.
  • the clamp is configured as an endless circumferential platform frame.
  • the platform frame can, by virtue of its annular—endless—form, clamp around the platform elements in a shrink fit, such that it is no longer strictly necessary to further secure the platform frame against any losses.
  • the projection of the blade airfoil is set back with respect to the pressure-side and suction-side blade airfoil surface by means of a step, such that the platform elements bearing against the step cannot move parallel to the longitudinal axis of the turbine blade.
  • the cross section of the platform frame can have various shapes. Preference is given, however, to such shapes as bring about a form fit with the rim of the inner platform part.
  • the cross section may be lozenge-shaped or C-shaped.
  • the rim of the inner platform part is always embodied in corresponding fashion to the cross section shape.
  • a particular advantage of the turbine blade according to aspects of the invention is that, in particular, two different materials may also be used for the platform elements, the blade airfoil and for the platform frame. It is thus in addition possible to take into account the different local loads, which can lead to an extended service life of the turbine blade.
  • a further advantage of the turbine blade according to aspects of the invention is the increased precision with respect to the outer dimensions of the platform since these are easier to bring about when manufacturing the platform frame than when casting a purely monolithic turbine blade.
  • the platform frame is configured as an endless frame, shrink-fitting the platform frame onto the circumferential rim of the inner platform part is preferred. Before shrink-fitting, the platform frame may be heated and/or the platform elements may be cooled. After assembling the platform frame and the platform elements and after a subsequent temperature equalization, the platform frame is then seated securely on the circumferential rim of the inner platform part. Spot-welding and—soldering, and welding or soldering along the connection line from the rim of the inner platform part and platform frame, are also possible.
  • the particular feature of the proposed turbine blade is that the platform elements are placed against the projection by means of a movement perpendicular to the longitudinal axis, and their securing element against a return movement, in the form of the platform frame, is placed over the platform elements with a movement transverse thereto—that is to say parallel to the longitudinal axis. Thereafter, it is simply necessary to ensure that only the platform frame is secured against releasing. A displacement of the platform, comprising the platform elements and the platform frame, parallel to the longitudinal axis is also blocked on account of the step between the actual blade airfoil and the projection, and on account of the collar on the projection.
  • the inner platform part expediently comprises two platform elements, although more platform elements may also be provided.
  • the construction according to aspects of the invention permits the use of different materials for the various components of the turbine blade. It is thus possible, for example, for the blade airfoil and the platform elements to be made from different materials which are adapted to the respective local requirements and loads, as described in the introduction.
  • the platform frame may also be made of a material which is best suited to its purposes. It is thus possible for various alloys and casting materials to be used within one turbine blade.
  • the turbine blade may be equipped both at its first blade airfoil end and at a second end, opposite the first end, with an above-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 airfoil has on both sides in each case one above-described projection.
  • the plurality of platform elements may be coupled to one another and/or one platform element, a plurality of platform elements or all the platform elements may be coupled to the blade airfoil by means of bolts.
  • both platform elements may have mutually opposite aligned bores into 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 through holes and/or blind holes which extend parallel to the longitudinal axis and into which are inserted bolts that are also seated in openings extending through the collar of the projection.
  • Such a bolted connection of the projection of the blade airfoil to the platform elements prevents the platform elements detaching from the blade airfoil, even when the platform frame is not present. In addition to easier assembly, this measure also increases the strength of the turbine blade and the operational reliability of the turbine blade for the unlikely event of the platform frame tearing.
  • the inner platform part and the outer platform part may be coupled by means of a tongue-and-groove connection.
  • the platform frame bears areally against the inner platform part, wherein the contact surface at least partially encloses, with the longitudinal axis, an angle 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 of particular advantage if the invention is applied to turbine rotor blades.
  • the centrifugal force acting on the platform frame while the turbomachine is in operation is also transmitted into the inner platform part by a form fit on account of the contact surface which is inclined with respect to the longitudinal axis. This reliably prevents loss of the platform frame due to the centrifugal force.
  • the angle is preferably between 15° and 35°, for example the angle is 20°.
  • the platform frame has, on at least one laterally outward-facing surface, a slot for receiving a sealing element.
  • a slot for receiving a sealing element presents the advantage that, in the event of wear of slots present in the platform rim due to the sheet-like sealing elements seated therein, the invention presented here provides a simple and reliable possibility of also reconditioning such operationally loaded turbine blades.
  • such slots may be produced more cost-effectively than in the case of purely monolithic turbine blades.
  • the turbine blade may expediently be formed both as a guide vane and as a rotor blade.
  • the turbine blade may be inserted with the inner platform part and the outer platform part into the form of the endless platform frame gripping around the inner platform part, even in the case of high-temperature uses, it is advantageous if the inner platform part and the platform frame are coated in one coating procedure. It is thus possible to apply a seamless protective coating to both platform parts.
  • FIG. 1 shows a turbine blade in a type of exploded representation, comprising a blade airfoil having a projection, a two-part inner platform part and an outer platform part,
  • FIG. 2 shows, in cross section, the turbine blade from FIG. 1 in the assembled state
  • FIG. 3 shows, in perspective representation, the plan view of the turbine blade from FIG. 2 .
  • FIG. 4 shows the turbine blade from FIG. 1 with a modular platform arranged on the tip side.
  • FIG. 1 shows part of a turbine blade 10 in the manner of an exploded drawing.
  • the turbine blade 10 is of modular configuration and, according to this exemplary embodiment, therefore comprises as separately manufactured components a blade airfoil 12 , two platform elements 14 , 16 and a platform frame 18 and a plurality of bolts 20 connecting these to one another.
  • the turbine blade 10 comprises a virtual longitudinal axis 11 .
  • the blade airfoil 12 is curved aerodynamically and has, as is known, 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 .
  • a projection 26 which is formed in one piece with the profile of the blade airfoil 12 .
  • the projection 26 is curved aerodynamically in similar fashion to the pressure side 22 and the suction side 24 .
  • the projection 26 is formed substantially smaller in its dimensions than the profile of the blade airfoil 12 given by the blade airfoil walls 22 , 24 , such that the projection adjoins the blade airfoil 12 via a step 28 .
  • the projection 26 comprises, at its free end 30 , a collar 32 . This collar 32 extends perpendicular to the longitudinal axis 11 and along the entire circumference of the profile, whereby it forms, with the step 28 , a circumferential groove 34 .
  • three through holes 36 are provided in both the suction side and the pressure side of the collar 32 of the projection 26 , which holes open into one of the side walls of the groove 34 .
  • Two platform elements 14 , 16 are fastened to the side of the projection 26 , with it also being possible to provide a larger number of platform elements.
  • the platform elements 14 , 16 have a platform material thickness which substantially corresponds to the width of the groove 34 .
  • the platform elements 14 , 16 have, upstream of the leading edge 23 or, respectively, downstream of the trailing edge 25 , in each case one or more blind holes 38 into which bolts 20 are partially inserted.
  • the orientation of the blind holes 38 is on one hand perpendicular to the longitudinal axis 11 and on the other hand chosen such that, when the bolts are inserted, the two platform elements 14 , 16 can be pushed toward one another until both platform elements 14 , 16 , seated in the groove 34 , bear against the projection 26 .
  • the platform elements 14 , 16 have, on their side facing toward the working medium, hereafter called the rear side 40 , blind holes 42 which, once the platform elements 14 , 16 are seated in the groove 34 , are aligned with the relevant through holes 36 in the collar 32 . Accordingly, pin-like bolts may be pushed into the mutually aligned holes 36 , 42 , whereby the platform elements 14 , 16 are first securely connected to the blade airfoil 12 .
  • the platform frame 18 is pushed parallel to the longitudinal axis 11 of the turbine blade 10 until it clamps around the two platform elements 14 , 16 .
  • the two platform elements 14 , 16 are on one hand firmly pressed against one another and on the other hand pressed into the groove 34 such that, on account of the resulting form fit, they can no longer move along the longitudinal axis 11 .
  • the two platform elements 14 , 16 then form an inner platform part 13 of the turbine blade 10 and the platform frame 18 forms an outer platform part 15 of the turbine blade 10 .
  • the inner platform part 13 and the outer platform part 15 form the platform 17 ( FIG. 2 ).
  • one tongue-and-groove connection is formed on each of the two longitudinal edges 41 of the inner platform part 13 and on each of the two longitudinal struts 46 of the platform frame 18 .
  • a tongue 48 belonging to the longitudinal strut 46 is represented on an inner side of the latter and a groove 50 belonging to the platform element 14 is represented on the longitudinal edge of the latter.
  • a tongue-and-groove connection can in each case be provided on the transverse edges and/or transverse struts.
  • one or more hooks 52 are provided both on the leading edge side and on the trailing edge side, in order to push the turbine blade 10 into a turbine guide vane support and attach it thereto. Accordingly, the turbine blade 10 represented in FIG. 1 is formed as a guide vane.
  • turbine blade 10 is formed as a rotor blade
  • those means of the turbine blade 10 which are provided for attachment are preferably formed monolithically on the projection 26 such that the means designated as the blade root is then integrally connected to the projection 26 and to the blade airfoil 12 .
  • a circumferential groove 34 for the platform elements 14 , 16 is also provided in the case of the rotor blade.
  • FIG. 2 shows, schematically, a partial perspective section view of the turbine blade 10 from FIG. 1 in the assembled final state.
  • FIG. 2 shows neither the holes arranged in the collar 32 nor the bolts seated therein.
  • the division of the inner platform part 13 into the pressure-side platform element 14 and the suction-side platform element 16 can be seen.
  • FIG. 4 shows the turbine blade 10 with its tip-side end 55 , which can have, by analogy with the root-side end, a modular platform 17 comprising two platform elements 14 , 16 and the platform frame 18 .
  • the tip-side end 55 differs here from the root-side end only with respect to that side of the platform 17 which faces the working medium.
  • FIG. 4 shows a slot 54 on a lateral, outward-facing surface 53 of the platform frame 18 .
  • the slot 54 serves to accommodate sheet-like sealing elements which can be provided between mutually adjacent guide vanes in order to seal the gap present therebetween.
  • the invention relates to a turbine blade 10 comprising a blade airfoil 12 and a modular platform 17 therefor, in succession along a longitudinal axis 11 of the turbine blade 10 .
  • the blade airfoil 12 comprise a projection 26 and the platform 17 comprise an outer platform part 15 and an at least two-part—in radial relation to the longitudinal axis 11 —inner platform part 13 which bear laterally against the projection 26 of the blade airfoil 12 and wherein the outer platform part 15 is formed as an endless platform frame 18 which grips around the outer rim of the inner platform part 13 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US14/388,458 2012-03-29 2013-03-28 Turbine blade Abandoned US20150071783A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP12162106.4A EP2644828A1 (de) 2012-03-29 2012-03-29 Modulare Turbinenschaufel mit Plattform
EP12162106.4 2012-03-29
PCT/EP2013/056652 WO2013144270A1 (de) 2012-03-29 2013-03-28 Modulare turbinenschaufel mit plattform

Publications (1)

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US20150071783A1 true US20150071783A1 (en) 2015-03-12

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US14/388,458 Abandoned US20150071783A1 (en) 2012-03-29 2013-03-28 Turbine blade

Country Status (6)

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

Cited By (3)

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US20170298751A1 (en) * 2014-10-28 2017-10-19 Siemens Energy, Inc. Modular turbine vane
US10934870B2 (en) 2018-09-17 2021-03-02 Rolls Royce Plc Turbine vane assembly with reinforced end wall joints
US20240052748A1 (en) * 2022-02-18 2024-02-15 General Electric Company Methods and apparatus to reduce deflection of an airfoil

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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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WO2013144270A1 (de) 2013-10-03
EP2644828A1 (de) 2013-10-02
EP2807342A1 (de) 2014-12-03
IN2014DN07525A (enrdf_load_stackoverflow) 2015-04-24
JP2015512486A (ja) 2015-04-27
CN104220700A (zh) 2014-12-17

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