EP0943785A1 - Fixation d'une aube à un stator - Google Patents

Fixation d'une aube à un stator Download PDF

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Publication number
EP0943785A1
EP0943785A1 EP98810226A EP98810226A EP0943785A1 EP 0943785 A1 EP0943785 A1 EP 0943785A1 EP 98810226 A EP98810226 A EP 98810226A EP 98810226 A EP98810226 A EP 98810226A EP 0943785 A1 EP0943785 A1 EP 0943785A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
receiving structure
blade root
arrangement according
turbine
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Withdrawn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
EP98810226A
Other languages
German (de)
English (en)
Inventor
Gordon Anderson
Michael Hock
Erhard Kreis
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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Priority to EP98810226A priority Critical patent/EP0943785A1/fr
Publication of EP0943785A1 publication Critical patent/EP0943785A1/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Withdrawn legal-status Critical Current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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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

Definitions

  • the invention relates to an arrangement for connecting a turbine blade, which provides a turbine blade root with a turbine blade carrier, which has a ring-shaped receiving structure into which the turbine blade root can be used and firmly against the turbine blade carrier using a locking aid available both radially, axially and in the circumferential direction to the receiving structure is.
  • Turbines as well as compressor stages of gas turbine plants known per se have a large number of staggered turbine blades that are used for compression or relaxation of gaseous media and ultimately for energy generation be used.
  • Turbine blades are both on the peripheral peripheral edge a rotor shaft in staggered rows and are arranged referred to as turbine blades, as well as on the inner contour of the rotor shaft
  • turbine blades In addition to the turbine blades surrounding the housing provided that the turbine blades provided with the inner contour of the housing, for example. each protrude between two adjacent rows of turbine blades. Due to the fixed arrangement of the turbine blades on the inner contour of the rotor housing these turbine blades are also referred to as turbine guide vanes.
  • FIG. 1a a perspective view of FIG. 1a is shown that guide vanes 1 for Installation in a correspondingly designed receiving structure 2, which is in the inner contour of the turbine guide vane carrier 3 is incorporated peripherally.
  • the receiving structure 2 of the turbine guide vane carrier 3 sees two opposing ones Insertion grooves 4 before, in which the appropriately trained guide blade root 31 can be threaded in the circumferential direction of the receiving structure 2.
  • the turbine guide vane carrier 3 is interrupted at at least one parting plane 32, on which the individual guide vanes can be inserted one after the other into the receiving structure 2 are.
  • a fixed positioning of each individual guide vane 1 relative to the receiving structure is usually carried out with spring-loaded locking piston 5, which is spring-loaded sit in blind holes 6, which are circumferentially in the receiving structure 2 of the turbine guide vane carrier 3 are provided.
  • spring-loaded locking piston 5 protrudes into a Guide blade root area provided bore 10.
  • the provision of such spring-loaded locking piston is, however, during assembly or disassembly of the individual guide blades 1 in or out of the turbine guide blade carrier 3 associated with the handling of many small parts, which can be seen in such work as has proven very cumbersome.
  • the invention has for its object an arrangement for connecting a Turbine blade with a turbine blade carrier according to the generic Develop the preamble of claim 1 such that the above Disadvantages can be avoided.
  • the guide vane root responsible for a secure seat of the guide vanes and the receiving structure within the guide vane carrier one on top of the other be coordinated that misalignments occurring during the operation of such devices individual guide vanes can be avoided.
  • the inventive arrangement for connecting a turbine blade, the one Turbine blade base provides, with a turbine blade carrier, which is an annular has trained receiving structure into which the turbine blade root can be inserted and by means of a locking aid firmly against the turbine blade carrier both radially, is available axially and circumferentially to the receiving structure, is designed such that the receiving structure at least one in the circumferential direction has circumferential groove into which a correspondingly formed on the turbine blade root Counter contour can be used with a precise fit that the receiving structure and the Turbine blade root are designed such that a precise fit of the Turbine blade root with the turbine blade carrier only by radial and the turbine blade root is inserted axially into the receiving structure, that the mounting structure and the turbine blade root each have an area, which in the disposition state a space extending in the circumferential direction include, and that the locking aid is a spacer whose Shape is adapted to the space and that in the circumferential direction in the space can be introduced.
  • the receiving structure of the turbine guide vane carrier sees the configuration according to the invention the receiving structure and the turbine guide blade foot that the individual turbine guide vanes largely directly at the location, based on the Turbine guide vane carrier on which the turbine guide vanes are positioned, directly into the mounting structure by radial and axial fitting of the guide blade root can be inserted into the receiving structure.
  • dismantling the individual guide vanes are removed in the reverse order.
  • the peculiarity of the coordinated contours of the receiving structure within the guide vane carrier and that of a guide vane root exists in particular in that two receiving grooves in the receiving structure of the guide vane carrier are incorporated, which are preferably designed as hollow phases open on one side are whose open sides are oriented in the same direction.
  • the guide blade root is placed radially on the receiving structure can and by axially shifting the counter contours of the guide blade root a precise fit in the corresponding grooves of the receiving structure Influence is achieved.
  • an intermediate space in which a kind of spacer ring can be introduced, which counteracts the guide blade root the receiving structure at least axially, but preferably additionally in radial direction secures against slipping.
  • Guide vane feet have individual recesses, for example in the extra pins or projections provided in the receiving structure of the guide vane carrier can intervene to prevent slipping in the circumferential direction.
  • the recesses provided in the guide vane feet serve small lugs or protrusions on the guide blade feet, which in corresponding Engage recesses within the receiving structure of the guide vane carrier can, additionally as a protection against slipping in the circumferential direction.
  • FIG. 2a is a cross-sectional view through an arrangement according to the invention, consisting of a turbine guide vane carrier 3 and a guide vane 1, shown.
  • the guide vane carrier 3 has a receiving structure on its peripheral circumferential surface 2, which provides two grooves 4, 41 formed as hollow phases also have a rectangular inner contour.
  • Corresponding protrude into the grooves 4, 41 Counter contours 7, 71 fit exactly into that part of the turbine guide blade root 31 are.
  • the groove 41 in the example shown Fig. 2 b formed as a pin 11, which also in a corresponding recess 11 'within the guide vane root for radial and circumferential positioning the guide vane contributes within the receiving structure 2 of the guide vane carrier 3.
  • the essential aspect of the invention shown in the sub-figures 2a and 2b Arrangement is that the guide vanes 1 substantially radially from can be lowered on the inside of the receiving structure 2 and by mere axial Move a precisely fitting joint connection into the corresponding slot openings between vane root 31 and receiving structure 2 is obtained. After this axial displacement of the guide vane root 31 within the receiving structure 2 An intermediate space 12 is formed, into which a spacer ring 13 can be inserted in the circumferential direction is (see Fig. 2a and 2b). The spacer ring 13 can be segmented or in one piece in the space after all guide vanes have been inserted into the receiving structure be introduced.
  • the spacer ring 13 has both radial and axially in the unloaded state enough play within the space 12 to on the one hand, it can be easily inserted into the gap or for disassembly pull out accordingly, but it offers sufficient hold for a precise fit Joining between the guide vane foot and the receiving structure. Especially in operation the axial play is canceled by the prevailing axial gas force, whereby there is good mutual alignment of the individual blades.
  • Turbine guide vanes with a circumferential direction of the support structure are also common provide facing sealing grooves and sealing strips.
  • One with these sealing arrangements equipped guide vane is shown in Fig. 3.
  • a peculiarity of such Guide vanes consist of being in the receiving structure prior to insertion of the corresponding guide vane carrier via sealing strips and / or inner segments are connected to each other and thus connected in groups in the Recording structure must be used and inserted.
  • the insertion is preferably carried out in the sequences A shown in FIG. 3 to C.
  • the connected guide vanes 1 in the radial direction r is moved towards the receiving structure 2 of the guide vane carrier 3 (see sequence A, left cross-sectional representation, which is a sectional drawing according to the Section A-A through the top view depicted on the left onto a guide vane carrier 3 used guide vanes 1 corresponds).
  • the surface sections arrive 34 and 35 of the guide vane root 31 in contact with the surface sections 21 and 22 of the receiving structure 2
  • Heavy guide vanes are an advantage because the load on the vane can be lowered appropriately is carried by the guide vane carrier 3. (See drawing B, which at the same time corresponds to the cross section through the left representation along the section line B). In this lowered position can also be spaced apart Guide vanes 1 are positioned relative to one another in the circumferential direction, so that their opposite sealing grooves 13 are aligned so that the corresponding provided sealing strip 14 seals both guide vanes against each other.
  • step C the guide vanes connected via the sealing strips 14 1 by axial displacement in the corresponding grooves 4, 41 the receiving structure 2 shifted positively.
  • Field C corresponds again the cross section through the section line at point C.
  • FIG. 4a Another design option for a form-fitting arrangement between Guide vane root and guide vane carrier is the function of circumferential positioning to be transferred to a two-part spacer ring.
  • Figure 4a is one Shown cross-sectional view, in which a guide vane root 31 in the receiving structure 2 of a guide vane carrier 3 is positively fitted. Like everyone else Embodiments here also engage the counter groove 7 in the corresponding groove 4 the receiving structure 2.
  • a counter contour 71 on the guide blade root can also be used 31 may be provided which engages in the corresponding groove 41, but is it is also possible to do without them, as it is for example from the perspective Representation of a guide blade root 31 emerges from FIG. 4b.
  • the thrust ring 16 shown in FIG. 4c has protruding molded parts 17 and 18 on, which are referred to as springs and for circumferential positioning of a guide vane root serve within the receiving structure 2.
  • the molded parts 17 come into corresponding Recesses 19 which are provided in each blade root 31 (see Fig. 4b).
  • the molded parts 18 oriented upward of the thrust ring 16 accordingly arrive in corresponding recesses within the receiving structure 2 of the guide vane carrier 3.
  • a spacer ring 13 introduced subsequently in the circumferential direction provides ensure that the thrust ring 16 both against the inner contour of the blade root 31st as well as pressed against the corresponding recess of the receiving structure 2 becomes.
  • the thrust rings can be individually for each guide vane root (see left detail) or for several guide vane feet (e.g. Positioning for 3 guide vane feet, see right detail in Fig.4b) become.
  • the arrangement according to the invention leads to smaller radial clearances of the guide vane feet within the guide vane foot support, so that possible leaks with regard to the escape of cooling medium Tilting can be reduced. Because in particular the expansion path of the individual Guide vanes can take place axially or radially from the guide vane carrier to the carrier, the disassembly is considerably simplified and the disassembly time significantly reduced. Especially with regard to the use of multiple bucket segments with increasing circumferential length, as is the case, for example, in the exemplary embodiment 3, the arrangement according to the invention offers a comfortable handling of several connected guide vanes at the Assembly and disassembly.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP98810226A 1998-03-18 1998-03-18 Fixation d'une aube à un stator Withdrawn EP0943785A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP98810226A EP0943785A1 (fr) 1998-03-18 1998-03-18 Fixation d'une aube à un stator

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98810226A EP0943785A1 (fr) 1998-03-18 1998-03-18 Fixation d'une aube à un stator

Publications (1)

Publication Number Publication Date
EP0943785A1 true EP0943785A1 (fr) 1999-09-22

Family

ID=8235990

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98810226A Withdrawn EP0943785A1 (fr) 1998-03-18 1998-03-18 Fixation d'une aube à un stator

Country Status (1)

Country Link
EP (1) EP0943785A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1310633A1 (fr) * 2001-11-07 2003-05-14 Techspace Aero S.A. Etage redresseur d'un compresseur et turbocompresseur comprenant tel etage redresseur
WO2007020217A2 (fr) * 2005-08-17 2007-02-22 Alstom Technology Ltd Dispositif d'aube directrice d'une turbomachine
WO2007039396A1 (fr) * 2005-10-06 2007-04-12 Alstom Technology Ltd Systeme d'aubes directrices d'une turbomachine
CN101403320B (zh) * 2001-07-19 2012-09-19 株式会社东芝 装配型喷嘴隔板
WO2021155992A1 (fr) * 2020-02-06 2021-08-12 Siemens Aktiengesellschaft Aube de turbine de fabrication additive avec mécanisme de prévention de rotation, et procédé de réglage
CN114945733A (zh) * 2020-01-07 2022-08-26 西门子能源全球有限两合公司 具有磨损元件的导向叶片环
DE102021119780A1 (de) 2021-07-29 2023-02-02 Man Energy Solutions Se Leitapparat eines Turboladers und Turbolader

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB666911A (en) * 1949-06-07 1952-02-20 Henry George Yates Improvements in or relating to diaphragms for impulse turbines
US2982519A (en) * 1956-02-13 1961-05-02 Rolls Royce Stator vane assembly for axial-flow fluid machine
DE2030380A1 (de) * 1969-07-08 1971-03-25 Stal Laval Turbin Ab Einrichtung zur Halterung von Leit schaufeln bei Dampf oder Gasturbinen
EP0334794A2 (fr) * 1988-03-23 1989-09-27 United Technologies Corporation Assemblage d'un stator pour une machine rotative à flux axiale
FR2660362A1 (fr) * 1990-04-03 1991-10-04 Gen Electric Structure de fixation des extremites exterieures des aubes d'une turbine.

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB666911A (en) * 1949-06-07 1952-02-20 Henry George Yates Improvements in or relating to diaphragms for impulse turbines
US2982519A (en) * 1956-02-13 1961-05-02 Rolls Royce Stator vane assembly for axial-flow fluid machine
DE2030380A1 (de) * 1969-07-08 1971-03-25 Stal Laval Turbin Ab Einrichtung zur Halterung von Leit schaufeln bei Dampf oder Gasturbinen
EP0334794A2 (fr) * 1988-03-23 1989-09-27 United Technologies Corporation Assemblage d'un stator pour une machine rotative à flux axiale
FR2660362A1 (fr) * 1990-04-03 1991-10-04 Gen Electric Structure de fixation des extremites exterieures des aubes d'une turbine.

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101403320B (zh) * 2001-07-19 2012-09-19 株式会社东芝 装配型喷嘴隔板
EP1310633A1 (fr) * 2001-11-07 2003-05-14 Techspace Aero S.A. Etage redresseur d'un compresseur et turbocompresseur comprenant tel etage redresseur
US7677867B2 (en) 2005-08-17 2010-03-16 Alstom Technology Ltd Guide vane arrangement of a turbomachine
WO2007020217A2 (fr) * 2005-08-17 2007-02-22 Alstom Technology Ltd Dispositif d'aube directrice d'une turbomachine
WO2007020217A3 (fr) * 2005-08-17 2007-04-12 Alstom Technology Ltd Dispositif d'aube directrice d'une turbomachine
WO2007039396A1 (fr) * 2005-10-06 2007-04-12 Alstom Technology Ltd Systeme d'aubes directrices d'une turbomachine
US7674088B2 (en) 2005-10-06 2010-03-09 Alstom Technology Ltd. Vane arrangement of a turbo machine
CN114945733A (zh) * 2020-01-07 2022-08-26 西门子能源全球有限两合公司 具有磨损元件的导向叶片环
CN114945733B (zh) * 2020-01-07 2023-10-20 西门子能源全球有限两合公司 具有磨损元件的导向叶片环
US11965432B2 (en) 2020-01-07 2024-04-23 Siemens Energy Global GmbH & Co. KG Guide vane ring with wear elements
WO2021155992A1 (fr) * 2020-02-06 2021-08-12 Siemens Aktiengesellschaft Aube de turbine de fabrication additive avec mécanisme de prévention de rotation, et procédé de réglage
DE102021119780A1 (de) 2021-07-29 2023-02-02 Man Energy Solutions Se Leitapparat eines Turboladers und Turbolader
DE102021119780B4 (de) 2021-07-29 2023-02-16 Man Energy Solutions Se Leitapparat eines Turboladers und Turbolader

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