US20110286851A1 - Guide blade arrangement for an axial turbo-machine - Google Patents

Guide blade arrangement for an axial turbo-machine Download PDF

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Publication number
US20110286851A1
US20110286851A1 US13/132,339 US200913132339A US2011286851A1 US 20110286851 A1 US20110286851 A1 US 20110286851A1 US 200913132339 A US200913132339 A US 200913132339A US 2011286851 A1 US2011286851 A1 US 2011286851A1
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US
United States
Prior art keywords
stator blade
inner ring
stator
turbomachine
spring element
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
US13/132,339
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English (en)
Inventor
Francois Benkler
Raoul Costamagna
Bernward Mertens
Uwe Sieber
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: MERTENS, BERNWARD, BENKLER, FRANCOIS, COSTAMAGNA, RAOUL, SIEBER, UWE
Publication of US20110286851A1 publication Critical patent/US20110286851A1/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
    • 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 refers to a stator blade arrangement for an axial turbomachine, comprising an annular stator blade carrier and an inner ring which is arranged concentrically to the stator blade carrier, between which a number of stator blades, with a blade airfoil, are arranged in a radial configuration, wherein each stator blade is fastened on the stator blade carrier.
  • stator blade arrangement which is referred to in the introduction is sufficiently known from the prior art.
  • This is known for example in the case of compressors of stationary gas turbines, in which stator blades of the compressor are fastened on a stator blade carrier or on a compressor casing.
  • stator blade carriers which in particular are mostly formed with a tubular shape, have retaining slots with undercuts which extend on their inner generated surfaces in the circumferential direction and in which stator blades or outer rings are inserted and fastened.
  • the stator blades in this case on the one hand can be formed as free-standing stator blades so that their blade airfoil tips lie opposite an inner boundary wall of the flow path of the compressor, forming a gap.
  • the inner boundary wall of the flow path is part of the stator blades or can be retained by the stator blades themselves.
  • the known stator blades either have shrouds which are arranged in each case on the tip side, which then form parts of the boundary wall, or the stator blades carry an inner ring on the tip side, the outer generated surface of which then constitutes the inner boundary for the flow path.
  • the fastening of the inner ring on the stator blades of the stator blade arrangement in this case can be carried out via a suitable bolted connection, by means of welding, or else by means of caulking.
  • the object of the invention is consequently the provision of a stator blade arrangement, which is referred to in the introduction, for an axial turbomachine, which enables a particularly simple, expansion-tolerant, low-wear and reliable fastening of stator blades on an inner ring.
  • the stator blade comprises a stator blade tip with a web and with a tip section which extends transversely to it, the stator blade tip projecting into an encompassing slot of the inner ring, and the slot is closed off in each case by a shroud in the section between two adjacent stator blades, that adjacent shrouds are at a distance from each other, forming recesses which accommodate the webs, and that the stator blade tip of at least one of the stator blades is spring-fastened on the inner ring by means of at least one spring element which is arranged in a side face of the recess which faces the web in question.
  • the invention is based on the knowledge that a rigid connection of stator blades on the inner ring is disadvantageous. It accordingly proposes a type of connection which to a small extent enables relative movements of stator blades to the inner ring in a wear-free manner, without damage to the connection. Consequently, the invention departs from the previous procedures in which a rigid, fixed connection between stator blades and inner ring was provided.
  • a simple spring element is now to be used for fixing the stator blade on the inner ring.
  • a uniform pressing of the stator blade in question on the inner ring can be carried out, which efficiently minimizes occurring stresses which are created as a result of thermal expansions and/or static and/or dynamic stresses.
  • the installation tolerances which are necessary for a simple installation, can be especially simply compensated.
  • Each stator blade in question on the inner ring side, comprises a stator blade tip, which is recessed in the inner ring, i.e. projects into a slot which is provided for it, and by means of which the stator blade is spring-fastened on the inner ring. So that the stator blade in question can be spring-fastened on the inner ring, it comprises at least one construction element, namely the stator blade tip, which can be connected to the inner ring and is suitable for carrying this.
  • the stator blade tip of each stator blade in question comprises a web which is arranged in each case in an outwardly open recess which is arranged on the inner ring and in which a spring element is arranged in at least one of the side faces of the recess which faces the web in question, and which spring element abuts in a pretensioned manner against the inner ring and against the web of the stator blade in question. Therefore, for spring-fastening of the stator blade on the inner ring provision is made for a further constructional component, that is to say the spring element, which on one side is supported on the inner ring and on the other side is supported on the web of the stator blade in question.
  • the stator blade arrangement is designed so that the spring element is preferably pretensioned and therefore presses the web of the stator blade in question either indirectly or directly onto the inner ring, in detail onto one of the two side faces of the recess.
  • the stator blade tip is formed in the shape of an inverted T by means of the web and a tip section which extends transversely to it, wherein the web connects the tip section to an aerodynamically curved blade airfoil of the stator blade in question, and wherein the inner ring has an encompassing slot, which is fanned corresponding to the stator blade tip, for accommodating the stator blade tips, which slot is closed off in each case by a shroud in the section between two adjacent stator blades, that is to say towards the blade airfoil.
  • stator blade arrangement can be disclosed in which the inner ring is especially reliably carried by the stator blades.
  • stator blade arrangement itself, the inner ring and/or the annular stator blade carrier, is not formed in one piece in each case but are faulted by means of at least two arc-shaped ring segments which during installation and/or removal are separated in each case from the other ring segments in a manageable manner.
  • the shroud on the one hand prevents displacement of the inner ring in relation to the stator blades along the circumference since the shroud is arranged in each case between two stator blades and therefore blocks the displacement path along the slot. On the other hand, the shroud also ensures a stepless boundary surface of the flow passage. Altogether, the components of the arrangement and the arrangement itself can then be easily produced.
  • each stator blade which is mounted in such a way indirectly, that is to say via the spring elements, is arranged on the inner ring in a pretensioned state.
  • the spring force of each spring element in this case is expediently oriented in the circumferential direction of the inner ring. If a tension sleeve is used as a spring element, there is only a linear contact between the web of each stator blade in question and the tension sleeve, as a result of which the static loading of the stator blade on the connecting point is lower than in the case of a two-dimensionally fixed stator blade.
  • the inner ring comprises two ring sections which can be installed after their assembly to form a one-piece inner ring.
  • stator blade arrangement is used especially in stationary turbomachines, it is advantageous if the stator blade arrangement itself comprises two or more ring segments, that is to say that the inner ring and/or the annular stator blade carrier are formed as arc-shaped ring segments. Since the stator blade arrangement and its components are part of the rotationally fixed component parts of a turbomachine, which, if used in the stationary region, have a parting plane, as a result of which the rotationally fixed component parts are split for an upper and a lower half, a stator blade arrangement which is split into two ring segments, each of 180°, is particularly suitable for stationary turbomachines. A simple installation of the individual components, forming an altogether annular stator blade arrangement, is then possible.
  • the stator blade arrangement is preferably used in a turbomachine which can be formed especially as an axial compressor or axial turbine. Moreover, the stator blade carrier can be arranged inside a separate casing or even itself can be formed as a casing.
  • FIG. 1 shows a segment 10 of a stator blade arrangement 12 of an axial turbomachine in a perspective view
  • FIG. 2 shows an exploded view of FIG. 1 ;
  • FIG. 3 shows a longitudinal section through a connection according to the invention of stator blade and inner ring
  • FIG. 4 shows a detail of the inner ring without stator blade
  • FIG. 5 shows a side view according to the section V-V
  • FIGS. 6 , 7 schematically show the twist of the stator blade as a result of load reaction and support reaction for a stator blade which is fastened according to the prior art and for a stator blade which is fastened according to the invention.
  • FIG. 1 shows a segment 10 of a stator blade arrangement 12 of an axial turbomachine in a perspective view.
  • the segment 10 is formed in the shape of an arc and spans an arc of 180°.
  • Two of the segments 10 which are shown in FIG. 1 can be assembled to form a stator blade arrangement 12 according to the invention, which is then formed in an annular configuration.
  • Slots 18 which extend in the axial direction and are for accommodating stator blades 20 are provided on an inner face 16 of the stator blade carrier 14 .
  • FIG. 2 the stator blades 20 which are to be inserted in the slots 18 are shown displaced to the stator blade carrier 14 on account of the exploded type of view.
  • stator blade root in each case and the radially inner part of the stator blade 20 is referred to as a stator blade tip.
  • stator blade tip Between stator blade root and stator blade tip the stator blade 20 has an aerodynamically curved blade airfoil.
  • An inner ring 22 is arranged on the stator blades 20 on the tip side. The inner ring 22 or its segments are assembled in this case from two ring sections 36 , 38 or ring section segments.
  • the stator blade arrangement 12 which is to be assembled from two segments 10 therefore comprises a ring of stator blades 20 which is also known as a stator blade ring and can be part of a compressor stage or turbine stage.
  • the stator blade carrier 14 is fastened on a casing, which is not additionally shown, of the axial turbomachine, for example of a compressor, or itself is formed as a casing.
  • the stator blade carrier 14 carries the stator blades 20 which are fastened on it on the inside and which in their turn carry the inner ring 22 inside on the tip side.
  • the outer generated surface of the inner ring 22 and the inner surface 16 of the stator blade carrier 14 in this case form the radial inner and outer boundary for a medium which flows through the axial turbomachine. If the axial turbomachine is formed as a compressor, the medium is compressed air, or air which is to be compressed.
  • FIG. 3 shows a longitudinal section (in the sense of the axial turbomachine) through a connection according to the invention of the stator blade 20 to the inner ring 22 .
  • the blade airfoil 28 which is part of the stator blade 20 is only partially shown.
  • a stator blade tip 30 which has a web 32 and also a tip section 34 which extends transversely to it, is provided on the blade airfoil 28 on the tip-side section of the stator blade 20 .
  • the stator blade tip 30 By means of the web 32 and the tip section 34 , the stator blade tip 30 altogether has an inverted T-shape, as seen in cross section.
  • the inner ring 22 is provided with an outwardly open slot 44 , the longitudinal sectional contour of which is formed corresponding to the stator blade tip 30 .
  • the inner ring 22 comprises the two ring sections 36 , 38 which in their turn according to FIG. 2 are also formed as 180° arc-shaped segments.
  • the ring sections 36 , 38 or their segments are interconnected in a fixed manner via a weld joint 40 .
  • the ring sections 36 , 38 have in each case projections 42 , 43 which are oriented towards each other, in each case for forming an undercut by means of which the inverted T-shaped stator blade tip 30 can be radially fixed.
  • FIG. 4 shows a perspective view of a section of the inner ring 22 , in which the ring sections 36 , 38 for reasons of clarity are not shown in their final constructional position but apart. In their final constructional position the two projections 42 , 43 , as far as possible, abut against each other without a gap.
  • a recess 46 In the projection 43 of the ring section 36 , a recess 46 , of which two are shown in FIG. 4 , is provided for each stator blade 20 .
  • the recesses 46 serve for accommodating the web 32 of the stator blade tip 30 of the stator blade 20 .
  • the projection 43 therefore forms a shroud 47 between the recesses which closes off the slot 44 between two stator blades 20 in order to provide a misalignment-free flow path.
  • each recess 46 has two side faces 48 which lie opposite each other.
  • a further pocket 50 is provided in which a spring element 52 , which is formed as a tension ring, is provided for spring-fastening of the stator blade 20 on the inner ring 22 .
  • a spring element 52 is schematically shown only in the recess 46 which is shown there further to the left.
  • FIG. 5 shows a side view of the portion of the ring section 36 which in FIG. 4 is shown further to the right.
  • This recess 46 is delimited by two side faces 48 in which a pocket 50 is provided in each case.
  • the pocket 50 is formed essentially in the shape of a circle segment and extends over the entire axial length of the recess 46 .
  • the pocket 50 in this case for example may have been produced by drilling or eroding before introducing the recess 46 .
  • the pocket 50 in this case is arranged so that the diameter of the pocket 50 , which lies in the radial plane of the axial turbomachine, is arranged in the projection 43 or in the shroud 47 so that only a comparatively small section of the hole circle is covered by the recess 46 .
  • the tension sleeve then has a diameter which is only slightly smaller than the diameter of the pocket 50 .
  • the spring element 52 which is formed as a tension sleeve can still project by such a distance into the recess 46 that the web 32 located there, which is not shown in FIG. 5 , is seated with spring effect on the inner ring 22 via the spring element 52 .
  • the force direction of the last-mentioned acts in the circumferential direction.
  • the spring element 52 could also be mounted in pockets which are arranged on the web 32 and not on the side faces 48 of the recess 46 .
  • FIG. 6 and FIG. 7 schematically show the twist of the stator blade 20 as a result of load reaction and support reaction for a stator blade which is fastened according to the prior art ( FIG. 6 ) and for a stator blade which is fastened according to the invention ( FIG. 7 ).
  • stator blade 20 which is fastened on the tip side according to the prior art is twisted to a particularly high degree, high loads and wear, which depending upon load can lead to crack emergence and crack propagation, could especially occur at their weakest point, namely on the stator blade tip 32 or else on the inner ring.
  • a spring-fastening of the stator blade tip 30 and therefore a fastening which is to be referred to as a flexible bearing, is now proposed which leads to significantly lower twist of the stator blade 20 as a result of load reaction and support reaction. As a result of this, the loading on the stator blade tip 32 can be reduced which delays or prevents the emergence of cracks and wear.
  • the invention refers to a stator blade arrangement 12 for an axial turbomachine and comprises at least one annular stator blade carrier 14 and an inner ring 22 which is arranged concentrically to the stator blade carrier 14 , between which a number of stator blades 20 are arranged in a radial configuration.
  • the stator blades 20 be spring-fastened on the inner ring 22 .
  • the fastening is carried out in this case by means of a spring element 52 .
  • the spring element 52 By means of the spring element 52 , a uniform pressing of the stator blade tip 30 onto the inner ring 22 , or possibly onto a further spring element 52 , can be ensured so that stresses and also wear which occur can be reduced.

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)
US13/132,339 2008-12-05 2009-11-02 Guide blade arrangement for an axial turbo-machine Abandoned US20110286851A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP080212152 2008-12-05
EP08021215A EP2194230A1 (de) 2008-12-05 2008-12-05 Leitschaufelanordnung für eine Axialturbomaschine
PCT/EP2009/064427 WO2010063525A1 (de) 2008-12-05 2009-11-02 Leitschaufelanordnung für eine axialturbomaschine

Publications (1)

Publication Number Publication Date
US20110286851A1 true US20110286851A1 (en) 2011-11-24

Family

ID=40591884

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/132,339 Abandoned US20110286851A1 (en) 2008-12-05 2009-11-02 Guide blade arrangement for an axial turbo-machine

Country Status (6)

Country Link
US (1) US20110286851A1 (de)
EP (2) EP2194230A1 (de)
JP (1) JP2012510582A (de)
CN (1) CN102239311A (de)
RU (1) RU2011127398A (de)
WO (1) WO2010063525A1 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USD732656S1 (en) * 2013-07-25 2015-06-23 Asustek Computer Inc. Fan blade
WO2016010554A1 (en) * 2014-07-18 2016-01-21 Siemens Energy, Inc. Turbine assembly with detachable struts
US20200088049A1 (en) * 2018-09-18 2020-03-19 General Electric Company Airfoil shroud assembly using tenon with externally threaded stud and nut
US11236615B1 (en) * 2020-09-01 2022-02-01 Solar Turbines Incorporated Stator assembly for compressor mid-plane rotor balancing and sealing in gas turbine engine
US11965432B2 (en) 2020-01-07 2024-04-23 Siemens Energy Global GmbH & Co. KG Guide vane ring with wear elements

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH704000A1 (de) * 2010-10-26 2012-04-30 Alstom Technology Ltd Leitschaufelanordnung einer Strömungsmaschine, insbesondere eines Axialkompressors.
EP3075961A1 (de) 2015-04-02 2016-10-05 Siemens Aktiengesellschaft Leitschaufelanordnung
EP3284919B1 (de) * 2016-08-16 2024-09-25 General Electric Technology GmbH Axialflussturbine mit einer in zwei hälften geteilten membran an einer anschlussebene
CN106988794B (zh) * 2017-06-02 2018-12-14 中国航发南方工业有限公司 静子组合件夹紧方法及静子组合件

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US2894318A (en) * 1952-10-08 1959-07-14 Gen Electric Turbomachine bucket-wheel fabricated by casting
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US5073084A (en) * 1989-10-04 1991-12-17 Rolls-Royce Plc Single-price labyrinth seal structure
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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USD732656S1 (en) * 2013-07-25 2015-06-23 Asustek Computer Inc. Fan blade
USD744085S1 (en) 2013-07-25 2015-11-24 Asustek Computer Inc. Fan blade
WO2016010554A1 (en) * 2014-07-18 2016-01-21 Siemens Energy, Inc. Turbine assembly with detachable struts
US9822669B2 (en) 2014-07-18 2017-11-21 Siemens Energy, Inc. Turbine assembly with detachable struts
US20200088049A1 (en) * 2018-09-18 2020-03-19 General Electric Company Airfoil shroud assembly using tenon with externally threaded stud and nut
US11028709B2 (en) * 2018-09-18 2021-06-08 General Electric Company Airfoil shroud assembly using tenon with externally threaded stud and nut
US11965432B2 (en) 2020-01-07 2024-04-23 Siemens Energy Global GmbH & Co. KG Guide vane ring with wear elements
US11236615B1 (en) * 2020-09-01 2022-02-01 Solar Turbines Incorporated Stator assembly for compressor mid-plane rotor balancing and sealing in gas turbine engine

Also Published As

Publication number Publication date
WO2010063525A1 (de) 2010-06-10
RU2011127398A (ru) 2013-01-10
EP2356319A1 (de) 2011-08-17
JP2012510582A (ja) 2012-05-10
EP2194230A1 (de) 2010-06-09
CN102239311A (zh) 2011-11-09

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Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BENKLER, FRANCOIS;COSTAMAGNA, RAOUL;MERTENS, BERNWARD;AND OTHERS;SIGNING DATES FROM 20110523 TO 20110524;REEL/FRAME:026732/0611

STCB Information on status: application discontinuation

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