EP2886799A1 - Couronne d'aubes de turbomachine et procédé de montage des aubes d'une couronne d'aubes de turbomachine - Google Patents

Couronne d'aubes de turbomachine et procédé de montage des aubes d'une couronne d'aubes de turbomachine Download PDF

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Publication number
EP2886799A1
EP2886799A1 EP13199052.5A EP13199052A EP2886799A1 EP 2886799 A1 EP2886799 A1 EP 2886799A1 EP 13199052 A EP13199052 A EP 13199052A EP 2886799 A1 EP2886799 A1 EP 2886799A1
Authority
EP
European Patent Office
Prior art keywords
blade
groove
blades
ring
blade ring
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Withdrawn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
EP13199052.5A
Other languages
German (de)
English (en)
Inventor
Marco Dreymann
Dimitri Zelmer
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 EP13199052.5A priority Critical patent/EP2886799A1/fr
Publication of EP2886799A1 publication Critical patent/EP2886799A1/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Withdrawn legal-status Critical Current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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • 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

Definitions

  • the invention relates to a blade ring for a turbomachine, comprising a circular blade carrier, along the circumference of which an endless circumferential groove with blades seated therein to form the blade ring, wherein in two mutually facing side surfaces of the circumferential groove is provided in each case an endless side groove and the feet of the Blades are attached indirectly by means of a positive connection in the circumferential groove.
  • Such blade rings are known in particular from compressors of gas turbines. These blade rings are usually arranged as rotor blade rings on rotors, which in turn have rotor disks as a blade carrier. In this case, extends along the peripheral surface of the rotor disk, the endless circumferential groove, which generally have axially extending projections on their mutually facing side surfaces, which thus form undercuts. In the undercuts then engage projections of blade roots, whereby the blades are held securely even under centrifugal force in the radial direction with respect to the machine axis of the compressor.
  • the projections forming the undercuts are endless in the circumferential direction.
  • the then used for use blades then have generally - seen in the circumferential direction - comparatively short platforms.
  • Such blades are inserted by a first, radial movement in the circumferential groove.
  • the blade must be about 90 ° along its longitudinal axis - which is perpendicular to the machine axis is - pivoted, after which the projections of the blade roots engage behind the projections of the circumferential groove.
  • so-called intermediate pieces are used, so that blades and spacers are lined up alternately.
  • the spacers are mounted in an analogous manner.
  • this first system is relatively complex, since several different components are required to form the blade ring.
  • the object of the invention is therefore to provide a blade ring for a turbomachine whose components are comparatively simple, quick and inexpensive to manufacture and that are low in number, in order to simplify the assembly and to accelerate.
  • Another object of the invention is to provide a method of mounting blades of a blade ring in an endless circumferential groove of a circular blade carrier in accordance with the aforementioned boundary condition.
  • the object underlying the invention is achieved with a blade ring according to the feature of claim 1 and the object directed to the method is achieved by a method according to the steps of claim 9.
  • each blade root has two beneficialnuten, each of which faces a portion of the two side grooves to form a Nutbinung and the side groove at least two each complementary to a ring Positive-locking elements are provided, which engage in the formation of the positive fit in the spaces bounded by Nutschreibept.
  • the positive locking elements engage simultaneously in both grooves - the northwestnut and the circumferentially opposite section of the side groove - a, so that a radial entanglement is ensured.
  • a pairing of grooves means that pair formation of a foot groove and a peripheral portion of one of the two side grooves, which are arranged in immediately opposite side surfaces and side walls, independently of their direct distance from each other.
  • side grooves and constitutionalnuten a Nutploung which are offset from each other so that they do not overlap radially.
  • the invention is based on the finding that the projection of the circumferential groove required for the radial form-locking of the blades in the circumferential groove, which are provided on the mutually facing side surfaces of the circumferential groove, does not necessarily have to be monolithically formed with the material of the blade carrier delimiting the circumferential groove. Rather, the inventors have recognized that a modular design is possible here. At the same time, the inventors have recognized that the replacement elements for the previously known projection - according to the invention the positive locking elements - per side groove can also be designed in several parts. This results in the possibility that an insertion opening for blades - as in the prior art - can be provided, which makes the use of spacers dispensable.
  • the blades of the blade ring according to the invention can be equipped with a comparatively wide-in the circumferential direction-extending platform.
  • the elimination of the spacers saves costs, both by a simpler manufacture of the components of the blade ring, by a simple storage as well as by the time savings because of the simplified assembly of the blade ring.
  • the circumferential groove with its two endless side grooves can be produced by turning.
  • the milling of an insertion opening in the blade carrier can be omitted.
  • fewer components are needed overall, resulting in savings in manufacturing, storage, and product management costs for these components.
  • the special assembly method since the blades no longer need to be supported by a substructure on the groove bottom of the circumferential groove by a closer fit on the form-fitting elements.
  • the elimination of the intermediate pieces also leads to a weight saving. This results in the saving of energy when starting, operating or decelerating the rotor.
  • the reduction of the rotor mass also leads to a lower load on the wheel discs and bearings, when the blade ring is designed as a blade ring.
  • the interlocking elements are designed in such a way that the spaces are at least largely or completely filled up by them. Usually means that they simultaneously bring about a radial entanglement with two grooves, so as to ensure a backlash-free attachment of the blades in the circumferential groove. This reduces wear on blades, especially when the blade ring is designed as a blade ring and the rotor of the turbomachine, which has this blade ring, is operated at a comparatively low speed.
  • each form-fitting element is designed either as a round profile, as a rectangular profile or as a flattened round profile and the cross-sectional contours of the Schwarznuten and side grooves correspond to the profile of the positive locking elements. In this way, a secure seat of the blade can be ensured in the circumferential groove by means of a particularly reliable positive connection.
  • At least three positive locking elements are provided per side groove, which complement each other to form a ring. More preferably, one of these three positive locking elements - hereinafter referred to as a tail pin - comparatively short and has a length in the circumferential direction of the circumferential groove, which is only slightly larger than the circumferential extent of the blade root of the last used blade.
  • the other two form-locking elements, which complement together with the end pin to the ring, may have an identical length.
  • the final pin could have a length of about 8 ° and the other two form-locking elements each have an arc length of 176 °.
  • a first half ring of the blade ring can be mounted as it were, after which the second half ring can be mounted on blades through the insertion, so that after the assembly of all blades only the two closing pins are to be arranged at the circumferential position of the insertion.
  • the locking pins are then pressed by a paddle lock into the respective side groove, so that at the same time the paddle lock and the locking pins are held securely.
  • the positive locking elements are secured against displacement in the circumferential direction.
  • the maximum number of form-fitting elements per side groove should be able to be determined by the number of blades of the blade ring.
  • Their arrangement in the circumferential direction with respect to the Schwarznut can be with or without offset.
  • the paddle lock comprises a plate-shaped clamping piece with a through thread, a platform piece with a stepped or chamfered through hole and a screw that spans these two pieces, wherein in the clamped state of the paddle lock in the circumferential groove, the clamping piece the two closing pins in the respective side groove and the Platform piece presses from the outside to the environment of the circumferential groove.
  • a comparatively simple paddle lock can be specified, which comprises only three components. This is a small number compared to the prior art paddle locks.
  • the screw should be secured in a conventional manner against loosening. Common methods for this are the caulking of the screw or surrounding the screw material of the platform piece. The use of other paddle locks and other screw locks are conceivable.
  • blades typically identical blades are used in the blade ring.
  • the last two blades to be mounted which are arranged on both sides of the lock, are so-called special blades. These are characterized by the fact that they have a shortened platform on the side facing the paddle lock - compared to the remaining blades of the ring - so that after their positioning in the circumferential groove, the insertion opening is still open and then can only be closed by the paddle lock.
  • the blade ring can be configured both as a vane ring or as a blade ring. If the blade ring is designed as a blade ring, the blade carrier is usually designed as a rotor disk or as a monolithic rotor, along the outer peripheral surface, the endless circumferential groove can extend. In contrast, if the blade ring according to the invention is designed as a vane ring, the blade carrier has as an annular structure an inwardly facing surface which is circular in cross-section and along the circumferential direction, the circumferential groove extends endlessly. Such arrangements are, for example, to be found in steam turbines with a pot housing.
  • the guide vane ring and / or blade ring according to the invention can be used, for example, in a gas turbine, in a steam turbine or in a compressor.
  • the invention thus relates to a blade ring for a turbomachine comprising a blade carrier, along the circumference of an endless circumferential groove with blades seated therein to form the blade ring, wherein in two mutually facing side surfaces of the circumferential groove is provided in each case an endless side groove, and the feet the blades are each secured by means of a positive connection in the circumferential groove. Furthermore, the invention relates to a method for producing such a blade ring.
  • each blade root has two therapeuticnuten, each of which is a section of one of two side grooves to form a Nutformung immediately opposite and that each side groove at least two each complementary to a ring form-locking elements are provided which extend to form the form-fitting through the limited spaces of the groove pairs.
  • the blade lock described in detail here in principle also in conventional blade carriers having an endless circumferential groove with blades seated therein to form the blade ring, wherein in two mutually facing side surfaces of the circumferential groove each extending along the circumferential groove projection to form a Undercut is provided at the circumferential position where the monolithic with the side walls of the circumferential groove projections are interrupted to form an insertion, can be applied, the side surfaces each identify a side groove according to the invention and there closing pins are used using the paddle lock described above.
  • the advantage of this lock is the simple construction, which, apart from the two closing pins, only comprises three components in order to close the insertion opening of the circumferential groove permanently and reliably.
  • FIG. 1 shows a blade ring 10 for a turbomachine.
  • a blade ring 10 for a turbomachine.
  • FIG. 1 only a portion of the circumference of the blade ring 10 is shown in perspective.
  • the axial compressor can be, for example, that of a gas turbine.
  • each blade 18 comprises an aerodynamically curved blade 20 and a platform 22 bounding the flow path of the compressor.
  • the blade carrier 12 is designed as a wheel disc 13. Radially within the platform 22, each blade 18 has a blade root for attachment of the blade 18 in the circumferential groove 16.
  • FIG. 2 shows the cross section through the blade carrier 12 according to the section line II-II FIG. 1 ,
  • the circumferential groove 16 has a groove base 24, which merges via rounded portions 26 into two side surfaces 28.
  • the two side surfaces 28 are parallel to each other and facing each other. Radially outward, the side surface 28 is followed by obliquely arranged surfaces 30 to provide clearance for the platform 22 of the blade 18.
  • the radially outwardly facing surface 14 of the blade carrier 12 and the upwardly facing surface 21 of the platform 22 define the flow channel 32 in the illustrated embodiment the compressor not shown on the hub side.
  • a side groove 34 with a semicircular contour is provided in each side face 28.
  • both side grooves 34 are arranged on an identical radius, relative to a machine axis 36.
  • the machine rotor 36 rotates about the rotor of the compressor.
  • the distances of the side grooves 34 to the machine axis 36 can also be different in size, contrary to the example shown.
  • the blade root 23 of the blade 18 Radially inwardly adjacent to the platform 22 of the blade root 23 of the blade 18 is arranged.
  • the blade root 23, platform 22 and blade 20 are mostly made as a monolithic unit by forging. But such blades can also be milled from the solid.
  • the use of a composed of modules blade is also conceivable.
  • the blade root 23 has on each of two opposite side walls 25 a respective foot groove 27 with a semi-circular contour. Each foot groove 27 is arranged on the blade root 23 so that it directly opposite one of the two side grooves 34 in the installed state.
  • the side grooves 34 extend along the entire circumference of the circumferential groove 16, these are just as endless as the circumferential groove 16, so that upon closer inspection of the blade root 23, which has only a limited extension in the circumferential direction, thus only a portion of the relevant side groove 34th can be opposite.
  • the relevant section of one of the two side grooves 34 and the foot groove 27 opposite this section are combined to form a groove pairing 29, said groove pairing 29 having a cross-section in FIG FIG. 2 quasi-circular space 31 limit coat side.
  • there may be a slight gap between the side wall 25 of the blade root 23 and the side surface 28 of the circumferential groove 16 it is negligible in determining the space 31.
  • Each space 31 thus extends over a length in the circumferential direction, which corresponds to the length of the foot groove 27 in the circumferential direction.
  • the space 31 is filled by so-called positive-locking elements 33.
  • positive-locking elements 33 Per side surface 28 at least two, preferably three positive locking elements 33 are provided, which complement each other to a ring. If the interlocking elements 33 complement each other to form a ring, they are arranged virtually free of play in the circumferential direction, which reduces wear. Since the form-fitting elements 33 fill each space 31 at least for the most part, if not completely, a positive connection results for fastening the blades 18 in the radial direction, relative to the machine axis 36, whereby the blades 18 are securely held in the circumferential groove 16.
  • FIG. 3 shows three complementary to the ring 35 form-fitting elements 33.
  • Two of these form-fitting elements 33 have the identical arc length and extend over an arc length of 176 °.
  • the shorter of the three interlocking elements 33 which is arranged in the illustrated embodiment at the 6 o'clock position and serves as a tail pin 37, has a comparatively short arc length, which is dimensioned so that it has a sufficient gap for insertion of the blade roots 23 in the Circumferential groove 16 provides.
  • the blades 18 are successively passed through the gap in the circumferential groove 16 (FIG. FIG. 4 ) and moved along the circumferential direction, so that visibly the circumferential groove 16 is fitted with blades 18.
  • FIG. 4 An assembled to the last two blades blade ring 10 is in FIG. 4 partial perspective shown.
  • FIG. 4 shows therefore the blade carrier 12, the circumferential groove 16, four positive locking elements 33 and an insertion 38 for radially inserting the blades 18 in the circumferential groove 16.
  • To complete the blade ring 10 are in the almost completely bladed circumferential groove 16 two blades to mount, which in FIG. 5 is shown.
  • FIG. 5 shows partially cut representation of the circumferential groove 16, the form-fitting elements 33, the blades 18 and two special blades 40, which are mounted last.
  • Both special blades 40 differ from the previously shown or assembled blades 18 only in that they have a shorter in the circumferential direction of platform 22 than the other blades 18, so that after assembly despite full blade ring 10, a free space 42 remains, with the aid of Closing pins 37 and a paddle lock 43 can be permanently closed.
  • the paddle lock 43 to be used for closing the clearance 42 is in FIG FIG. 6 and includes a platform piece 44, a clamping piece 46 and a screw 48 that screws these two pieces together.
  • the clamping piece 46 is first inserted into the circumferential groove 16 (FIG. FIG. 7 ), so that it initially rests on the groove base 24 of the circumferential groove 16. This is chamfered at the two narrow edges 50 of the clamping piece 46, so that the then inserted into the circumferential groove 16 closing pins 37 at least partially insert into the side grooves 34. Subsequently, the free space 42 is closed from above by the platform piece 44.
  • the platform piece 44 and the clamping piece 46 are provided with aligned holes, wherein the hole of the clamping piece 46 has an internal thread as a through thread. Subsequently, a screw 48 can be inserted from the outside through the through hole of the platform piece 48, which engages in the through thread of the clamping piece 46. With further screwing of the screw 48, the clamping piece 46 is visibly lifted from the groove base 24 and while on the one hand pushes the closing pins 37 in each associated side groove 34, on the other hand the platform piece 44 is simultaneously pressed against the surfaces 30 from the outside. With sufficient preload, closing pins 37 as well as clamping piece 46 and platform piece 44 are finally securely braced together on blade carrier 12. Thereafter, only the screw 48 is secured in a known manner against loosening, which avoids the loss of the paddle lock 43 safely.
  • FIGS. 8 and 9 show the cross section of the circumferential groove 16 analogous to FIG. 2 but with different contours for the side grooves 34 and foot grooves 27.
  • the contours of personallyuten 27 are curved in a platform-side section, to which a straight-line section 51 connects. This results in a dovetail-shaped contour for the blade root 23.
  • Die Side grooves 34 are in relation to the embodiment according to FIG. 2 unchanged and thus semicircular. With respect to the radial direction to the machine axis 36, the foot grooves 27 overlap, so that the form-locking elements 33 with a semicircular contour can bring about the positive locking for the radial securing of the blade 18.
  • the space 31 defined by the groove pairing 29 is only partially filled.
  • the cross section of the space 31 is in FIG. 8 represented by a dashed line.
  • This embodiment offers the advantage that due to the dovetail-shaped contour of the blade root 23, the blade 18, which tends outward under centrifugal force, presses the positive-locking elements 33 into the side grooves 34 with great force. This ensures a secure fit of the positive locking elements 33 in both grooves 34, 27th
  • FIG. 9 may instead of the half-round contours for the side grooves 34 and 27 foot grooves also completely opposite grooves 34, 27 (in FIG. 9 left) may be provided with a rectangular contour.
  • the form-locking elements 33 have a largely corresponding contour in the form.
  • the corners of the form-fitting element 33 chamfered. Since the transitions from the bottom of the side groove 34 and foot groove 27 into arcuate surfaces pass to avoid stress concentration, the space closed by the two grooves 27, 34 is only largely and not completely completely filled by the interlocking elements 33.
  • Fig. 9 shown on the right is a special form of Nutformung 29, in which the side groove 34 and the cancellednut - relative to the machine axis 36 does not overlap radially. Accordingly, the associated positive-locking element 33 is Z-shaped in cross-section in order to hook the two grooves 27, 34 together.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13199052.5A 2013-12-20 2013-12-20 Couronne d'aubes de turbomachine et procédé de montage des aubes d'une couronne d'aubes de turbomachine Withdrawn EP2886799A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13199052.5A EP2886799A1 (fr) 2013-12-20 2013-12-20 Couronne d'aubes de turbomachine et procédé de montage des aubes d'une couronne d'aubes de turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13199052.5A EP2886799A1 (fr) 2013-12-20 2013-12-20 Couronne d'aubes de turbomachine et procédé de montage des aubes d'une couronne d'aubes de turbomachine

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EP2886799A1 true EP2886799A1 (fr) 2015-06-24

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EP13199052.5A Withdrawn EP2886799A1 (fr) 2013-12-20 2013-12-20 Couronne d'aubes de turbomachine et procédé de montage des aubes d'une couronne d'aubes de turbomachine

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109931112A (zh) * 2019-04-28 2019-06-25 杭州汽轮机股份有限公司 一种汽轮机自由叶片结构及其装配方法
US20210254480A1 (en) * 2020-02-18 2021-08-19 United Technologies Corporation Tangential Rotor Blade Slot Spacer for a Gas Turbine Engine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2317338A (en) * 1942-02-07 1943-04-20 Westinghouse Electric & Mfg Co Turbine blade fastening apparatus
US2421855A (en) 1943-07-23 1947-06-10 United Aircraft Corp Turbine blade locking device
US2430140A (en) * 1945-04-06 1947-11-04 Northrop Hendy Company Turbine blade and mounting
US3088708A (en) 1961-12-29 1963-05-07 Seymour J Feinberg Compressor blade locking device
FR1484321A (fr) * 1966-06-22 1967-06-09 Ass Elect Ind Perfectionnements apportés aux rotors de turbines à vapeur
DE10346263A1 (de) * 2003-10-06 2005-04-28 Alstom Technology Ltd Baden Schaufelfußbefestigung
EP2022944A1 (fr) * 2007-07-27 2009-02-11 Siemens Aktiengesellschaft Fixation d'aube dans une rainure circonférentielle au moyen d'une masse céramique durcissable

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2317338A (en) * 1942-02-07 1943-04-20 Westinghouse Electric & Mfg Co Turbine blade fastening apparatus
US2421855A (en) 1943-07-23 1947-06-10 United Aircraft Corp Turbine blade locking device
US2430140A (en) * 1945-04-06 1947-11-04 Northrop Hendy Company Turbine blade and mounting
US3088708A (en) 1961-12-29 1963-05-07 Seymour J Feinberg Compressor blade locking device
FR1484321A (fr) * 1966-06-22 1967-06-09 Ass Elect Ind Perfectionnements apportés aux rotors de turbines à vapeur
DE10346263A1 (de) * 2003-10-06 2005-04-28 Alstom Technology Ltd Baden Schaufelfußbefestigung
EP2022944A1 (fr) * 2007-07-27 2009-02-11 Siemens Aktiengesellschaft Fixation d'aube dans une rainure circonférentielle au moyen d'une masse céramique durcissable

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109931112A (zh) * 2019-04-28 2019-06-25 杭州汽轮机股份有限公司 一种汽轮机自由叶片结构及其装配方法
US20210254480A1 (en) * 2020-02-18 2021-08-19 United Technologies Corporation Tangential Rotor Blade Slot Spacer for a Gas Turbine Engine
US11242761B2 (en) * 2020-02-18 2022-02-08 Raytheon Technologies Corporation Tangential rotor blade slot spacer for a gas turbine engine

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