EP3075961A1 - Ensemble d'aube directrice - Google Patents

Ensemble d'aube directrice Download PDF

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Publication number
EP3075961A1
EP3075961A1 EP15162353.5A EP15162353A EP3075961A1 EP 3075961 A1 EP3075961 A1 EP 3075961A1 EP 15162353 A EP15162353 A EP 15162353A EP 3075961 A1 EP3075961 A1 EP 3075961A1
Authority
EP
European Patent Office
Prior art keywords
inner ring
blade
vane assembly
ring element
guide vane
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Withdrawn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
EP15162353.5A
Other languages
German (de)
English (en)
Inventor
Marco Dreymann
Erik Porsch
Achim Schirrmacher
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 EP15162353.5A priority Critical patent/EP3075961A1/fr
Priority to EP16713373.5A priority patent/EP3262282A1/fr
Priority to CN201680020987.0A priority patent/CN107438702A/zh
Priority to PCT/EP2016/056571 priority patent/WO2016156211A1/fr
Publication of EP3075961A1 publication Critical patent/EP3075961A1/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Withdrawn legal-status Critical Current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
    • 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
    • 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
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps

Definitions

  • the present invention relates to a vane assembly comprising an outer ring, an inner ring and a plurality of vanes extending between the outer ring and the inner ring, each having a blade root attached to the outer ring, an airfoil extending between the outer ring and the inner ring, and a blade web having the airfoil connected and hook-like blade head, which is fixed to the inner ring, wherein the inner ring is composed of at least a first inner ring member and a second inner ring member having the first inner ring member receiving grooves through which blade webs extend therethrough, and the first inner ring member and the second inner ring member define at least one receiving space between them, which connects radially inwardly to the receiving grooves and in which the blade heads are received.
  • FIG. 16 shows a schematic perspective view of a known vane assembly 100 having an outer ring 101, an inner ring 102 and a plurality of between the outer ring 101 and the inner ring 102 extending vanes 103, each having a fixed to the outer ring 101 blade root 104, a between the outer ring 101 and Inner ring 102 extending airfoil 105 and a connected via a blade web 106 with the airfoil 105 and hook-like blade head 107 have.
  • the blade roots 104 of the guide vanes 103 are received on the outer ring 101 in correspondingly formed Schaufelfußnuten 108 and each means attached to a press fit.
  • the inner ring 102 accommodating the blade heads 107 of the guide vanes 103 is composed of a first inner ring element 109 and of a second inner ring element 110.
  • the first inner ring member 109 includes not shown receiving grooves through which the blade webs 106 extend therethrough, the blade heads 107 are disposed in an annular receiving space 111 which is defined between the first inner ring member 109 and the second inner ring member 110 and radially inwardly to the Connecting grooves connects.
  • the first inner ring element 109 and the second inner ring element 110 are screwed or welded together.
  • the blade heads 107 are caulked in the composite of the two inner ring elements 109 and 110 in order to compensate for manufacturing inaccuracies and to achieve a positive fit of the blade heads 107 within the receiving space 111. In this caulking, it comes to deformation of the inner ring 102 on the one hand and the blade heads 107 on the other.
  • the caulking described has a number of disadvantages.
  • On the one hand causes the caulking a very rigid connection of the composite and is therefore prone to cracking and wear.
  • the causes of this damage are vibrations, thermal stresses and gas forces that occur during operation with the turbomachine.
  • the caulking geometries lie directly in the flow channel and can thus disturb the flow of the medium, which is conducted through the guide vane assembly 100 during operation of the turbomachine. This can result, for example, a reduction of the efficiency.
  • Another disadvantage is that the caulking is performed partly manually or semi-manually. Accordingly, a uniform process control or process monitoring due to the strong dispersion of manufacturing parameters is possible only with great effort.
  • the present invention provides a vane assembly of the type mentioned, which is characterized in that brackets are provided which comprise the blade heads, and that the brackets have legs which engage in the receiving grooves and within the receiving grooves to produce a Support spring bias against both the corresponding vane and against the first inner ring element.
  • brackets are provided which comprise the blade heads, and that the brackets have legs which engage in the receiving grooves and within the receiving grooves to produce a Support spring bias against both the corresponding vane and against the first inner ring element.
  • Another advantage is that the stresses caused by the elastic fasteners are uniform over the component composite.
  • the flow contour of the guide vane assembly according to the invention is not affected by the recorded between the first inner ring member and the second inner ring member brackets, which is why a Reduction of the efficiency of the turbomachine is not to be feared.
  • the brackets are substantially U-shaped, resulting in a simple and inexpensive to produce stapling construction.
  • the legs of the brackets are provided with protruding projections, via which the spring elasticity of the brackets can be realized.
  • the projections formed in the form of beads can be finished with little effort.
  • the projections may be circular, elliptical, annular, rectilinear or wavy, to name just a few examples.
  • the blade heads are provided with groove-shaped and in each case a portion of a clamp substantially form-fitting receiving recesses, which prevent accidental release of the brackets preferably in the axial direction.
  • the depth of each recess is slightly greater than the thickness of the clip so that the portion of a clip received by a recess does not project outwardly beyond the clip.
  • the first inner ring member and the second inner ring member define support portions which engage in recesses of the vanes existing between the airfoils and the hook-like blade heads, defined by the hook-like shape of the blade heads. In this way, a secure hold of the blade heads between the inner ring elements is realized.
  • the first inner ring element and the second inner ring element are assembled in the axial direction, resulting in a simple mountability.
  • the first inner ring member and the second inner ring member are provided with opposing axial contact surfaces which are provided to produce a positive connection on the one hand with at least one projection and on the other hand with at least one corresponding recess which receives the at least one projection. Thanks to such a design of the contact surfaces, a defined relative positioning of the inner ring elements is achieved by the interlocking projections and depressions.
  • first inner ring element and the second inner ring element are welded together.
  • the first inner ring element and / or the second inner ring element are / is composed of individual ring segment sections attached to one another.
  • the present invention also proposes to use an at least partially resilient clip for reducing a play between a blade web of a vane, which is arranged between a blade head and a blade of the vane, and an inner ring of a vane assembly, in particular a guide vane assembly according to the invention.
  • FIGS. 1 to 15 show a vane assembly 1 according to an embodiment of the present invention and Components of the same.
  • the vane assembly 1 comprises as main components an outer ring 2, an inner ring 3 and a plurality of extending between the outer ring 2 and the inner ring 3 vanes 4, each having a fixed to the outer ring 2 blade root 5, extending between the outer ring 2 and the inner ring 3 airfoil 6 and have a connected via a blade web 7 with the blade 6 and hook-like design blade head 8, which is fixed to the inner ring 3.
  • the outer ring 2 is provided along its inner periphery with a plurality of Schaufelfußabilitynuten 9 in which the blade roots 5 of the guide vanes 4 are received and fixed by means of a press fit.
  • the inner ring 3 is composed of a first inner ring element 10 and a second inner ring element 11, wherein both the first inner ring element 10 and the second inner ring element 11 in the present case consists of a plurality of ring segments.
  • the first inner ring member 10 has a substantially T-shaped cross-section defining a radially inwardly extending support leg 12 and a substantially axially extending receiving leg 13.
  • the receiving leg 13 has a number of guide vanes 4 corresponding number of grooves 14, which are equally spaced in the circumferential direction and serve to accommodate the blade webs 7.
  • the groove bottom of each receiving groove 14 is spaced from the support leg 12 and forms a support portion 15.
  • the second inner ring member 11 has a substantially L-shaped cross-section defining an axially extending support leg 18 and a radially outwardly extending support leg 19 which is provided at its free end with a circumferential circumferential support portion 20 which projects axially and in the direction of the support leg 12 of the first inner ring element 10 has.
  • the support portion 20 forms an axial contact surface 21, which is provided with a circumferentially circumferential recess 22 which is formed corresponding to the projections 17 of the first inner ring member 10 and with these engaged.
  • the first inner ring member 10 and the second inner ring member 11 define therebetween an annular receiving space 23 which connects radially inwardly to the receiving grooves 14 of the first inner ring member 10 and in which the blade heads 8 of the vanes 4 are held positively, wherein the support portions 15 of the first inner ring element 10 and the support portion 20 of the second inner ring member 11 in between the blades 6 and the hook-like blade heads 8 existing recesses 24 of the vanes 4 engage.
  • the blade webs 7 are fixed in the associated receiving grooves 14 of the first inner ring element 10 in each case using a clamp 25, which in the present case is made of spring steel and is U-shaped.
  • the brackets 25 include a base leg 26 and two legs 27 and 28 extending outwardly from the base leg 26, hereafter referred to as side legs.
  • the side legs 27, 28 are each provided with inwardly projecting projections 29, which are designed as straight beads extending transversely to the extension direction of the side legs 27 and 28 over the entire length of the side legs 27 and 28.
  • the free ends of the side legs 27 and 28 are provided with bevels.
  • Each clip 25 is placed from above onto a blade head 8 such that the base leg is substantially positively received in a groove-shaped recess 30 of the blade head 8 and the side legs 27 and 28 engage in the receiving grooves 14, within which they both to produce a bias resiliently supported against the blade webs 7 and against the first inner ring member 10.
  • the guide vanes 4 are attached to the outer ring 2 in a first step by the blade roots are inserted into the associated Schaufelfußabilitynuten 9 of the outer ring 2 and secured by means of press fits.
  • the first inner ring element 10 of the inner ring 3 is pushed axially onto the guide vanes 4 such that the individual blade webs 7 of the guide vanes 4 are inserted into the receiving grooves 14 of the first inner ring element 10 until they abut the support sections 15 of the first inner ring element 10 , please refer FIG. 4 .
  • FIGS. 6 and 7 show a bracket 25 in the assembled state, in which the side legs 27 and 28 are supported against both the guide vane 4 and against the opposite walls of the first inner ring member 10. Thanks to the projections 29 while a resilient seat of the blade web 7 is achieved within the grooves 14 of the first inner ring member 10.
  • the second inner ring element 11 according to FIG.
  • FIG. 9 shows the second inner ring member 11 in the assembled state.
  • the first inner ring member 10 and the second inner ring member 11 are welded together, which is not shown in more detail in the figures.
  • a significant advantage associated with the illustrated vane assembly 1 is that the vanes 4, thanks to the brackets 25 in a simple way and Be attached to the inner ring with elastic movement play and a very high reproducibility. Likewise, the guide vanes 4 can also be replaced again in case of service. In addition, due to the elastic attachment achieved by the bracket 25, a damping effect occurs, which is conducive to an increase in the life of the vane assembly 1. Another advantage is that due to the brackets 25 of the composite component is evenly loaded. In addition, the flow contour of the guide vane assembly 1 according to the invention is not affected by the recorded between the first inner ring member 10 and the second inner ring member 11 brackets 25, so reducing the efficiency of the turbomachine is not to be feared.
  • FIGS. 12 to 15 show alternative embodiments of brackets 31 and 33, which differ only with respect to the projections 32 and 34 from the previously described bracket 25, for which reason the same component areas are designated by the same reference numerals.
  • the projections 32 are formed ellipse-shaped, wherein the ellipse longitudinal axis is arranged transversely to the extension direction of the side legs 27 and 28.
  • the projections 34 are provided in waveform.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP15162353.5A 2015-04-02 2015-04-02 Ensemble d'aube directrice Withdrawn EP3075961A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP15162353.5A EP3075961A1 (fr) 2015-04-02 2015-04-02 Ensemble d'aube directrice
EP16713373.5A EP3262282A1 (fr) 2015-04-02 2016-03-24 Ensemble d'aubes directrices
CN201680020987.0A CN107438702A (zh) 2015-04-02 2016-03-24 导叶组件
PCT/EP2016/056571 WO2016156211A1 (fr) 2015-04-02 2016-03-24 Ensemble d'aubes directrices

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15162353.5A EP3075961A1 (fr) 2015-04-02 2015-04-02 Ensemble d'aube directrice

Publications (1)

Publication Number Publication Date
EP3075961A1 true EP3075961A1 (fr) 2016-10-05

Family

ID=52807704

Family Applications (2)

Application Number Title Priority Date Filing Date
EP15162353.5A Withdrawn EP3075961A1 (fr) 2015-04-02 2015-04-02 Ensemble d'aube directrice
EP16713373.5A Withdrawn EP3262282A1 (fr) 2015-04-02 2016-03-24 Ensemble d'aubes directrices

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP16713373.5A Withdrawn EP3262282A1 (fr) 2015-04-02 2016-03-24 Ensemble d'aubes directrices

Country Status (3)

Country Link
EP (2) EP3075961A1 (fr)
CN (1) CN107438702A (fr)
WO (1) WO2016156211A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102020200073A1 (de) 2020-01-07 2021-07-08 Siemens Aktiengesellschaft Leitschaufelkranz
CN111561480B (zh) * 2020-05-14 2022-02-22 中国航发沈阳发动机研究所 一种静子结构
CN114810221B (zh) * 2021-01-27 2023-09-15 中国航发上海商用航空发动机制造有限责任公司 静子叶片与内环支撑机构

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0421596A2 (fr) * 1989-10-04 1991-04-10 ROLLS-ROYCE plc Support pour garniture d'étanchéité à labyrinthe
EP1079074A2 (fr) * 1999-08-09 2001-02-28 United Technologies Corporation Aube statorique et stator pour une turbomachine
US20040062652A1 (en) * 2002-09-30 2004-04-01 Carl Grant Apparatus and method for damping vibrations between a compressor stator vane and a casing of a gas turbine engine
EP2194230A1 (fr) * 2008-12-05 2010-06-09 Siemens Aktiengesellschaft Agencement d'aube directrice pour une turbomachine axiale
US20100226777A1 (en) * 2005-09-15 2010-09-09 Snecma Shim for a turbojet blade

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE60318852T2 (de) * 2003-10-03 2009-02-05 General Electric Co. Apparat und Methode zur Dämpfung von Vibrationen zwischen Kompressorleitschaufeln und dem Gehäuse einer Gasturbine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0421596A2 (fr) * 1989-10-04 1991-04-10 ROLLS-ROYCE plc Support pour garniture d'étanchéité à labyrinthe
EP1079074A2 (fr) * 1999-08-09 2001-02-28 United Technologies Corporation Aube statorique et stator pour une turbomachine
US20040062652A1 (en) * 2002-09-30 2004-04-01 Carl Grant Apparatus and method for damping vibrations between a compressor stator vane and a casing of a gas turbine engine
US20100226777A1 (en) * 2005-09-15 2010-09-09 Snecma Shim for a turbojet blade
EP2194230A1 (fr) * 2008-12-05 2010-06-09 Siemens Aktiengesellschaft Agencement d'aube directrice pour une turbomachine axiale

Also Published As

Publication number Publication date
CN107438702A (zh) 2017-12-05
WO2016156211A1 (fr) 2016-10-06
EP3262282A1 (fr) 2018-01-03

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