WO2016156211A1 - Ensemble d'aubes directrices - Google Patents

Ensemble d'aubes directrices Download PDF

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Publication number
WO2016156211A1
WO2016156211A1 PCT/EP2016/056571 EP2016056571W WO2016156211A1 WO 2016156211 A1 WO2016156211 A1 WO 2016156211A1 EP 2016056571 W EP2016056571 W EP 2016056571W WO 2016156211 A1 WO2016156211 A1 WO 2016156211A1
Authority
WO
WIPO (PCT)
Prior art keywords
inner ring
blade
vane
ring element
vane arrangement
Prior art date
Application number
PCT/EP2016/056571
Other languages
German (de)
English (en)
Inventor
Marco Dreymann
Erik Porsch
Achim Schirrmacher
Dimitri Zelmer
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to CN201680020987.0A priority Critical patent/CN107438702A/zh
Priority to EP16713373.5A priority patent/EP3262282A1/fr
Publication of WO2016156211A1 publication Critical patent/WO2016156211A1/fr

Links

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 extending between the outer ring and the inner ring vanes, each having a fairfoot attached to the outer ring, extending between the outer ring and the inner ring and an airfoil via a blade web connected to the blade and having hook-like having formed ⁇ th blade head which is fixed to the inner ring,
  • the inner ring is composed of at least a first inner ring member and a second inner ring member having first inner ring member receiving grooves through which the blade webs extend therethrough, and 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 included.
  • FIG 16 shows a specific ⁇ matic perspective view of a known Leitschau ⁇ felan extract 100 with 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, is between the outer ring 101 and the inner ring 102 extending airfoil 105 and a connected via a blade web 106 with the airfoil 105 and hook-like fancy ⁇ th blade head 107 have.
  • the blade roots 104 of the vanes 103 are received from ⁇ formed Schaufelfußnuten 108 on the outer ring 101 in accordance with each and medium- attached by means of 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.
  • 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.
  • 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. First, the caulking causes a very rigid connection of the composite and is therefore vulnerable with respect to crack formation and wear ⁇ . The causes of this damage are vibrations, thermal stresses and gas forces that occur during operation with the turbomachine.
  • Verstemmgeometrien lie directly in the flow channel and can thus interfere with the flow of the medium, which is currency ⁇ rend the operation of the turbine engine passed through the Leitschaufelan ⁇ regulatory 100th This can result, for example, a reduction of the efficiency.
  • 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
  • a significant advantage of the guide vane arrangement according to the invention is that the guide vanes, thanks to the clamps, which are preferably made of spring steel, are fastened in a simple manner to the inner ring with resilient elastic elements. let wegungsspiel and a very high reproducibility Fixed To ⁇ gen. Just as easily, the guide vanes can also be exchanged again in case of service. In addition, due to the elastic attachment provided by the clamps, a damping effect occurs which is conducive to increasing the life of the vane assembly. Another advantage is that the stresses caused by the elastic fasteners are uniform over the component composite. In addition, the flow contour of the 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, so a reduction of the efficiency of the turbine engine is not to be ⁇ fear.
  • the clamps are substantially U-shaped and mountable by radially oriented movement on the blade heads, resulting in a simple and inexpensive to manufacture clamp assembly. Also prevents this configuration that legs of the brackets can get into the flow channel, for example, due to vibration.
  • Another important advantage of the preferred embodiment is the simplified shape of the receiving groove and the assembly of the brackets without special auxiliary tools, even with larger travel.
  • the second inner ring segment covers the radially inwardly facing side of the first inner ring segment. At the same time, the vane heads and brackets are also covered, so that
  • 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 in the form of grooves having formed ⁇ th and each provided a subregion of a clip essentially positively receiving recesses that prevent accidental loosening of the clamps preferably in axial direction are beneficial.
  • 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 present invention define ren the first inner ring member and the second inner Ringele ⁇ management support portions which engage existing recesses of the guide vanes in between the blades and the hook-type blade heads which are in particular 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 element and the second inner ring element are preferably provided with axial contact surfaces arranged opposite one another, which are provided 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 to produce a positive locking. Thanks to such a design of the contact surfaces, a defined relative positioning of the inner ring elements is achieved by the engaging projections and depressions.
  • the 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 is / are composed of individual mutually fastened ring segment sections.
  • ⁇ constricting invention also proposes an at least partially spring- ⁇ elasticated clamp for reducing a motion clearance between a blade ridge of a guide vane which is disposed between a blade head and a blade of the vane, and an inner ring to use a Leit ⁇ blade assembly , in particular a guide vane assembly according to the invention.
  • FIG. 1 shows a schematic front view of a half Leit ⁇ blade assembly according to an embodiment of the present invention
  • FIG. 2 is a schematic perspective sectional view showing a portion of the vane assembly shown in FIG. 1;
  • FIG 3 is an enlarged front view of the in FIG 2 with
  • FIG. 4 shows perspective views of 10, the individual items to show ⁇ during assembly of Darge ⁇ presented in FIG 1 vane assembly; 11 shows a perspective view of a clamp of the m FIG. 1 illustrated guide vane arrangement;
  • FIG 13 shows a cross-sectional view along the line XIII-XIII in FIG 12;
  • FIG. 15 shows a cross-sectional view along the line XV-XV in FIG.
  • 16 is a schematic perspective sectional view showing a portion of a known vane assembly.
  • FIGS 1 to 15 show a vane assembly 1 according to an embodiment of the present invention or components thereof.
  • 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.
  • Outer ring 2 and inner ring 3 are known to be arranged concentrically to a virtual machine axis 14, which is to serve as a reference axis for the terms "radial” and "axial”.
  • 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 of 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 consist of a plurality of ring segments.
  • the first inner ring member 10 has a T-shaped Wesentli ⁇ chen cross-section which a radially inwardly extending support legs 12 and located in
  • 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.
  • At its free end of the receiving leg 13 defines between the individual receiving grooves 14 axial contact surfaces 16 which are provided with circumferentially extending and axially projecting projections 17.
  • the second inner ring element 11 has a substantially L-shaped cross-section which defined an axially extending support leg 18 and a radially outwardly extending retaining limbs 19 defi ⁇ which is provided at its free end with a circumferentially encircling support portion 20 projecting axially and in the direction of the support leg 12 of the first inner ring element 10.
  • the support portion 20 forms an axial con ⁇ tact 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 in engagement therewith.
  • first inner ring element 10 and the second inner ring member 11 Defining the first inner ring element 10 and the second inner ring member 11 between them an annular receiving space 23, the radially inwardly at ⁇ joins the receiving grooves 14 of the first inner ring element 10 and in which the blade heads 8 of the guide vanes 4 are positively held, with the supporting portions 15 of the first inner ring element 10 and the support portion 20 of the second inner ring element 11 in between the Schaufelblät ⁇ tern 6 and the hook-like blade heads 8 existing training 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 is presently made of spring steel ⁇ made and U-shaped.
  • the brackets 25 umfas ⁇ sen a base leg 26 and two, which are nachfol ⁇ quietly referred to as the side legs of the base leg 26 outwardly extending leg 27 and 28th
  • 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 mounted from above on a blade head 8 that the Basisschen ⁇ angle substantially positively received in a groove-shaped recess 30 of the blade head 8 and the side legs 27 and 28 engage in the grooves 14, within which they produce a Pretension against both the blade webs 7 and against the first
  • Support inner ring element 10 resiliently.
  • the vane assembly 1 in a first step, the vanes 4 are fixed to the outer ring 2, in- which the blade roots are inserted into the associated Schaufelfußability ⁇ grooves 9 of the outer ring 2 and fastened by means of press fits.
  • the first inner ring element 10 of the inner ring 3 is pushed axially onto the guide vanes 4 in such a way 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 it engages the support sections 15 of the first inner ring element 10 anschla ⁇ gen, see FIG 4.
  • Receiving groove 14 are inserted and the base leg 26 of the clip 25 is received in the provided on the blade head 8 recess 30.
  • Figures 6 and 7 show a bracket 25 in the assembled state, in which the side legs 27 and 28 both against the vane 4 and against the opposite walls of the first
  • Inner ring member 10 is pushed until the support portion 20 of the second inner ring member 11 in the associated
  • Recess 24 of the guide vanes 4 is inserted and the projections 17 of the first inner ring member 10 with the formed on the second inner ring member 11 recess 22 in
  • a significant advantage associated with the described vane arrangement 1 is that the guide vanes 4, thanks to the clamps 25, can be fastened in a simple manner 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, which is why a reduction in the efficiency of the turbomachine is not to be feared.
  • Figures 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 elliptical in shape, the ellipse longitudinal axis being arranged transversely to the extension direction of the side legs 27 and 28.
  • the projections 34 are provided in a 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)

Abstract

La présente invention concerne un ensemble d'aubes directrices (1) comportant des brides de fixation (25; 31; 34) conçues au moins en partie à élasticité de ressort, qui réduisent un jeu de mouvement entre le talon (7) d'une aube directrice (4) disposé entre une tête d'aube (8) et une pale (6) de l'aube directrice (4), et une bague interne (3) de l'ensemble d'aubes directrices (1).
PCT/EP2016/056571 2015-04-02 2016-03-24 Ensemble d'aubes directrices WO2016156211A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CN201680020987.0A CN107438702A (zh) 2015-04-02 2016-03-24 导叶组件
EP16713373.5A EP3262282A1 (fr) 2015-04-02 2016-03-24 Ensemble d'aubes directrices

Applications Claiming Priority (2)

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

Publications (1)

Publication Number Publication Date
WO2016156211A1 true WO2016156211A1 (fr) 2016-10-06

Family

ID=52807704

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2016/056571 WO2016156211A1 (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
EP1520957B1 (fr) * 2003-10-03 2008-01-23 General Electric Company Dispositif et procédé pour amortir les vibrations entre des aubes turbocompresseur et le boîtier d'une turbine à gaz

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
EP3262282A1 (fr) 2018-01-03
CN107438702A (zh) 2017-12-05
EP3075961A1 (fr) 2016-10-05

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