EP1917419A2 - Dispositif d'aube directrice d'une turbomachine - Google Patents

Dispositif d'aube directrice d'une turbomachine

Info

Publication number
EP1917419A2
EP1917419A2 EP06792762A EP06792762A EP1917419A2 EP 1917419 A2 EP1917419 A2 EP 1917419A2 EP 06792762 A EP06792762 A EP 06792762A EP 06792762 A EP06792762 A EP 06792762A EP 1917419 A2 EP1917419 A2 EP 1917419A2
Authority
EP
European Patent Office
Prior art keywords
vane
circumferentially
axially
support
vanes
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.)
Granted
Application number
EP06792762A
Other languages
German (de)
English (en)
Other versions
EP1917419B1 (fr
Inventor
Alexander Chekanov
Alexander Khanin
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to SI200630367T priority Critical patent/SI1917419T1/sl
Publication of EP1917419A2 publication Critical patent/EP1917419A2/fr
Application granted granted Critical
Publication of EP1917419B1 publication Critical patent/EP1917419B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades

Definitions

  • the present invention relates to a guide vane arrangement of a turbomachine, in particular a gas turbine.
  • a typical vane assembly includes at least one vane support attached to a housing of a turbomachine. Such a vane assembly also includes a plurality of vanes mounted on the vane support and circumferentially juxtaposed.
  • each vane has a platform having at least two latch portions circumferentially spaced from one another.
  • Each latch portion has a tongue which projects circumferentially from the platform and extends in the axial direction.
  • the vane support has at least two support portions which are circumferentially spaced from each other.
  • Each support portion has a groove which is open in the circumferential direction and extends in the axial direction. The tongues of the locking portions and the grooves of the support portions are so 2 B05 / 049-0
  • a vane arrangement of this type provides the ability to assemble and disassemble individual vanes without disassembly of the entire vane support.
  • the invention is based on the general idea to arrange the locking portions and the complementary support portions with axial offset.
  • the assembly and disassembly of the vanes is simplified because the axial movement of the vanes, which must be performed in order to establish the positive locking, is significantly reduced. Problems such as distortion, jamming and jamming along the axial contact are reduced. Since the cooperating support sections and latch sections extend in the circumferential direction, the guide blade arrangement according to the invention allows the guide vanes to be adjusted in the circumferential direction.
  • the platform has a cavity bounded radially inwardly by a base and bounded axially and circumferentially by walls projecting outwardly from the base.
  • the vane carrier has a common collection channel, 3 B05 / 049-0
  • the housing has at least one cooling gas supply channel, which is fluidically connected to the common collection channel.
  • the vane carrier has a plurality of connection openings, each fluidically connecting the common collection channel with one of the cavities. Due to this feature, the vane support comprises an important part of a cooling gas supply path. Said common common rail significantly simplifies the cooling gas supply through the casing of the turbomachine, since the cooling gas supply passage of the casing can be disposed in a suitable portion of the casing and because the arrangement of the cooling gas supply passage is independent of the arrangement of the vanes.
  • the vane arrangement allows circumferentially adjacent vanes to be provided with a gap seal arrangement.
  • Said gap seal arrangement is designed to seal a gap extending axially between each two circumferentially adjacent vanes.
  • Fig. 1 shows a simplified, schematic axial section of a
  • FIG. 2 shows a detail view according to arrow II in Fig. 1,
  • FIG. 3 shows a circumferential section corresponding to sectional lines IM in FIG. 1, FIG.
  • FIG. 4 shows an exploded view of the vane arrangement according to FIG. 1.
  • a vane arrangement 1 has at least one guide vane carrier 2 and a plurality of stator vanes 3.
  • the vane arrangement 1 is part of a turbomachine 4.
  • Said turbomachine 4 is in particular a gas turbine.
  • the turbomachine can also be a steam turbine or a compressor.
  • the vane arrangement 1 has the guide vanes 3 of a row of guide vanes of the turbomachine 4.
  • the turbomachine 4 is equipped with a plurality of vane rows. 5 B05 / 049-0
  • each of these vane rows may comprise the vane arrangement 1 according to the invention.
  • the guide blade carrier 2 is attached to a housing 5 of the turbomachine 4.
  • the vanes 3 are attached to the vane carrier 2. In order to form the guide blade row, the guide vanes 3 are arranged next to one another in the circumferential direction.
  • Each vane 3 has a platform 6 and a flow profile 7 which projects radially and inwardly from the platform 6.
  • the platform 6 has a first latch portion 8, which is shown on the left side of Fig. 1, and a second latch portion 9, which is shown on the right side of Fig. 1.
  • the locking portions 8, 9 are arranged at an axial distance from each other.
  • the first locking portion 8 is arranged in the region of a downstream side 10 of the profile 7, while the second locking portion 9 is arranged in the region of an inflow side 11 of the profile 7.
  • the guide blade carrier 2 has a first support section 12 and a second support section 13.
  • the two support portions 12, 13 are also axially spaced apart from each other.
  • Each latch section 8, 9 and the associated support section 12, 13 are designed such that they provide an axially pluggable and radially positive fastening between the guide blade carrier 2 and the respective vane 3.
  • the cooperating latch sections 8, 9 and support sections 12, 13 open an axial push-in or push-in movement for mounting and an axial pull-out or pull-down motion for disassembling the respective guide blade 3.
  • the cooperating latch sections 8 constitute , 9 and support sections 12, 13 a 6 B05 / 049-0
  • the vane arrangement 1 has at least one securing element 14 which is fastened to the guide vane carrier 2.
  • Said securing element 14 is designed such that it provides an axial fixation of at least one of the guide vanes 3.
  • the vane 3 is axially fixed or secured in its assembled state by means of said securing element 14.
  • each vane 3 is basically adjustable in the circumferential direction. Such adjustment may be advantageous to eliminate or reduce backlash between adjacent vanes 3.
  • the first latch portion 8 and the second latch portion 9 are arranged at a radial distance from each other. This feature results in an axially compact structure of the vane assembly 1. This feature also reduces manufacturing costs.
  • the first support portion 12 and the second support portion 13 may be radially spaced from each other.
  • the first support portion 12 has an inner collar 15 which projects radially inwardly from the vane support 2 and extends in the circumferential direction.
  • Said inner collar 15 is provided with an inner tongue 16 which extends axially and circumferentially.
  • the first locking portion 8 has an inner groove 17.
  • Said inner groove 17 is axially open and extends circumferentially.
  • Said inner tongue 16 and said inner groove 17 are configured to provide a first tongue-and-groove joint 18 between the vane support 2 and the respective vane 3.
  • the inner tongue 16 projects axially into the inner groove 17 and engages radially on the platform 6.
  • the second latch portion 9 has an outer collar 19 which projects radially outward from the platform 6 and extends in the circumferential direction.
  • Said outer collar 19 is provided with an outer tongue 20 which extends in the axial direction and in the circumferential direction.
  • the second support portion 13 is provided with an outer groove 21 which is axially open and extends circumferentially.
  • Said outer tongue 20 and said outer groove 21 are configured to provide a second tongue-and-groove joint 22 between the vane support 2 and the respective vane 3. In the assembled state, the outer tongue 20 extends into the outer groove 21 and engages radially on the guide vane carrier 2.
  • the vane 3 is circumferentially adjustable during assembly.
  • a locking pin 23 is provided in order to fix a set position between the vane support 2 and the respective vane 3 circumferentially.
  • Said locking pin 23 penetrates into a recess 24, which is recessed in the outer collar 19.
  • Said locking pin 23 is screwed into a complementary threaded opening 25 which is provided in the guide blade carrier 2.
  • the vane 3 is preferably provided with at least one pullout opening 26, which is a threaded opening, which is provided for cooperation with a pullout device, not shown.
  • a pullout device not shown.
  • the platform 6 has a cavity 27 which is open towards the guide blade carrier 2. Said cavity 27 is bounded radially inwardly by a base 28 of the platform 6.
  • the airfoil 7 projects radially inwardly from said base 28.
  • the cavity 27 is axially and circumferentially bounded by walls 29. Said walls 29 are radially outwardly of the base 28.
  • the cavity 27 forms a cooling gas distribution chamber.
  • the airfoil 7 includes a cooling gas path 30 that is fluidically connected by the base 28 to the cavity 27.
  • the vane support 2 is equipped with a common collection channel 31.
  • Said common collecting channel 31 extends circumferentially and preferably extends along the entire guide plate carrier 2.
  • the housing 5 is equipped with at least one cooling gas supply channel 32, which is fluidly connected to a not shown cooling gas supply device.
  • Said cooling gas supply channel 32 is also fluidly connected to the common collection channel 31 and thus supplies the common collecting channel 31 with cooling gas.
  • the cooling gas flow is symbolized by arrows 33.
  • the vane support 2 is additionally equipped with a plurality of connection openings 34. Each connection opening 34 fluidly connects the common collection channel 31 with one of the cavities 27. Accordingly, the cavities 27 of the guide vanes 3 are supplied with cooling gas from the common collection channel 31 via the respective connection opening 34.
  • a baffle plate 43 may be arranged.
  • a common collecting channel 31 for supplying a plurality or all of the guide vanes 3 with cooling gas which is preferably air or steam, has the advantage that the cooling gas supply of the respective vane 3 due to approximately the samedegaspfadkonfigurationen between the 9 B05 / 049-0
  • the at least one cooling gas supply passage 32 can be disposed within the housing 5 regardless of the position of the respective guide blade 3. Also, the number of cooling gas supply passages 32 may be smaller than the number of guide vanes 3 to be supplied with cooling gas. The flexibility for designing the housing 5 is increased, thereby reducing the manufacturing cost of the housing 5.
  • the other wall 29, which axially delimits the cavity 27 in the region of the inflow side 11 of the airfoil 7, is equipped with the second latch portion 9. Accordingly, the cavity 27 extends axially from the downstream side 10 to the inflow side 11. In the circumferential direction, said cavity 27 extends over the entire circumferential extent of the base 28th
  • circumferentially adjacent vanes 3 are provided with a gap seal arrangement 35.
  • Said gap sealing arrangement 35 is designed to seal a gap 36, which is formed in each case between two circumferentially adjacent guide vanes 3.
  • Said gap 36 extends axially between the two adjacent vanes 3.
  • the gap 36 extends between two walls 29 which define the cavities 27 of said vanes 3 circumferentially.
  • Said gap seal arrangement 35 has a radial sealing plate 37 which extends circumferentially and axially. Perpendicular to its extension, the radial sealing plate 37 has a relatively small thickness, since the radial sealing plate 37 as 10 B05 / 049-0
  • the platforms 6 of the two adjacent guide vanes 3 are provided with two radial sealing slots 38. Said pair of radial sealing slots 38 are arranged circumferentially opposite one another and extend axially and circumferentially. The radial sealing plate 37 is inserted into the radial sealing slot 38 to achieve a radial sealing effect.
  • the gap seal arrangement 35 can also have a first axial sealing plate 39, which is arranged in the region of the first locking portion 8. Said first axial sealing plate 39 extends circumferentially and radially. Perpendicular to its extension, the first axial sealing plate 39 has a relatively small thickness.
  • the platforms 6 of the two adjacent guide vanes 3 are provided with two circumferentially opposite first axial sealing slots 40. Said first axial sealing slots 40 extend circumferentially and radially. The first axial sealing plate 39 is inserted into said pair of first axial sealing slots 40 to achieve an axial sealing effect.
  • the gap seal arrangement 35 also has a second axial sealing plate 41, which extends parallel to the first axial sealing plate 39. Said second axial sealing plate 41 is arranged in the region of the second locking portion 9.
  • the platforms 6 of the two adjacent vanes 3 are also provided with two circumferentially opposite second axial sealing slots 42 into which the second axial sealing plate 41 is inserted to achieve an axial sealing effect.
  • each individual vane 3 can be mounted and dismounted independently of other vanes 3.
  • the guide blade carrier 2 does not have to be dismantled for the assembly and disassembly of the guide vanes 3. 11 B05 / 049-0
  • the respective vane 3 is moved axially according to an arrow 44.
  • the two tongue and groove connections 18, 22 are produced by axial insertion of the tongues 16, 20 into the respective grooves 17, 21.
  • the respective guide blade 3 is fastened radially to the guide blade carrier 2 by means of the positive connection provided by the tongue and groove connections 18, 22.
  • the locking pin 23 is mounted.
  • the securing element 14 is mounted on the guide blade carrier 2.
  • the securing member 14 and the vane carrier 2 are provided with two tongue and groove connections 45 which are similar to the tongue and groove joints 18, 22 between the vane 3 and the vane carrier 2.
  • the securing element 14 is fastened to the guide blade carrier 2 by means of at least one locking bolt 46 in connection with at least one inlet segment 47.
  • Said inlet segment 24 is equipped with an external step 48.
  • the platform 6 is provided with an inner step 49, which is arranged with respect to the mounting direction 44 at the rear end of the platform 6.
  • the outer stage 48 of the inlet segment 47 engages with the inner stage 49 of the guide vane 3.
  • the inlet segment 47 is carried by the vane 3.
  • the inlet segment 47 can additionally be fastened to the guide blade carrier 2 by further fastening means (not shown).
  • the locking bolt 46 penetrates the securing element 14 within a passage opening 50 and projects into a blind hole 51 which is formed on the guide blade carrier 2. When assembled, said locking bolt 46 is supported radially inwardly by the inlet segment 47. Radial 12 B05 / 049-0
  • the locking bolt 46 is supported by the guide blade carrier 2 by means of a compression spring 52.
  • the locking bolt 46 secures the axial position of the securing element 14 and the support between the two stages 48 and 49.

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)
  • Control Of Turbines (AREA)
  • Vessels And Coating Films For Discharge Lamps (AREA)
  • Rotary Pumps (AREA)
  • Motor Or Generator Frames (AREA)
EP06792762A 2005-08-17 2006-08-09 Dispositif d'aube directrice d'une turbomachine Not-in-force EP1917419B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SI200630367T SI1917419T1 (sl) 2005-08-17 2006-08-09 Razporeditev vodilnih lopatic tokovnega stroja

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH13482005 2005-08-17
PCT/EP2006/065188 WO2007020217A2 (fr) 2005-08-17 2006-08-09 Dispositif d'aube directrice d'une turbomachine

Publications (2)

Publication Number Publication Date
EP1917419A2 true EP1917419A2 (fr) 2008-05-07
EP1917419B1 EP1917419B1 (fr) 2009-05-06

Family

ID=34975062

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06792762A Not-in-force EP1917419B1 (fr) 2005-08-17 2006-08-09 Dispositif d'aube directrice d'une turbomachine

Country Status (10)

Country Link
US (1) US7677867B2 (fr)
EP (1) EP1917419B1 (fr)
AT (1) ATE430874T1 (fr)
BR (1) BRPI0614795A8 (fr)
CA (1) CA2617826C (fr)
DE (1) DE502006003679D1 (fr)
MX (1) MX2008002013A (fr)
SI (1) SI1917419T1 (fr)
TW (1) TWI324217B (fr)
WO (1) WO2007020217A2 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007015669A1 (de) * 2007-03-31 2008-10-02 Mtu Aero Engines Gmbh Turbomaschine
US9133732B2 (en) 2010-05-27 2015-09-15 Siemens Energy, Inc. Anti-rotation pin retention system
US20120321454A1 (en) * 2011-06-14 2012-12-20 Yu Zhi-Xuan Wind power generation apparatus
US10526921B2 (en) * 2017-06-15 2020-01-07 General Electric Company Anti-rotation shroud dampening pin and turbine shroud assembly
US11346252B2 (en) 2019-07-01 2022-05-31 Raytheon Technologies Corporation Multi-purpose anti-rotation lock pin
CN113605994B (zh) * 2021-07-26 2023-10-03 中国船舶重工集团公司第七0三研究所 一种新型船用燃气轮机低泄露损失双联冷却导叶结构

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GB804010A (en) * 1956-02-13 1958-11-05 Rolls Royce Improvements in or relating to stator vane assemblies such as are used in axial-flowfluid machines
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JPS5872606A (ja) 1981-10-24 1983-04-30 Hitachi Zosen Corp ピストン制御孔型排気制御装置
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EP0943785A1 (fr) * 1998-03-18 1999-09-22 Asea Brown Boveri AG Fixation d'une aube à un stator
JP2000213301A (ja) 1999-01-19 2000-08-02 Takeshi Hatanaka 高効率タ―ビン
JP2002201913A (ja) * 2001-01-09 2002-07-19 Mitsubishi Heavy Ind Ltd ガスタービンの分割壁およびシュラウド
DE10210866C5 (de) * 2002-03-12 2008-04-10 Mtu Aero Engines Gmbh Leitschaufelbefestigung in einem Strömungskanal einer Fluggasturbine
GB0228748D0 (en) * 2002-12-10 2003-01-15 Alstom Switzerland Ltd Sealing arrangement
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Also Published As

Publication number Publication date
US20080199312A1 (en) 2008-08-21
MX2008002013A (es) 2008-03-27
WO2007020217A2 (fr) 2007-02-22
BRPI0614795A2 (pt) 2011-04-12
CA2617826A1 (fr) 2007-02-22
WO2007020217A3 (fr) 2007-04-12
DE502006003679D1 (de) 2009-06-18
EP1917419B1 (fr) 2009-05-06
ATE430874T1 (de) 2009-05-15
US7677867B2 (en) 2010-03-16
BRPI0614795A8 (pt) 2017-07-25
TWI324217B (en) 2010-05-01
CA2617826C (fr) 2014-04-01
SI1917419T1 (sl) 2009-10-31
TW200712309A (en) 2007-04-01

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