EP1548232A1 - Turbomachine avec un stator et procédé de fixation d'aubes statoriques dans le stator - Google Patents

Turbomachine avec un stator et procédé de fixation d'aubes statoriques dans le stator Download PDF

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Publication number
EP1548232A1
EP1548232A1 EP03029771A EP03029771A EP1548232A1 EP 1548232 A1 EP1548232 A1 EP 1548232A1 EP 03029771 A EP03029771 A EP 03029771A EP 03029771 A EP03029771 A EP 03029771A EP 1548232 A1 EP1548232 A1 EP 1548232A1
Authority
EP
European Patent Office
Prior art keywords
vane
groove
feet
guide
press
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Withdrawn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
EP03029771A
Other languages
German (de)
English (en)
Inventor
Wilhelm Schulten
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 EP03029771A priority Critical patent/EP1548232A1/fr
Priority to PCT/EP2004/012553 priority patent/WO2005066463A1/fr
Priority to EP04797660A priority patent/EP1697618B1/fr
Publication of EP1548232A1 publication Critical patent/EP1548232A1/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Withdrawn legal-status Critical Current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

Definitions

  • the invention relates to a turbomachine, in particular a compressor, according to the preamble of claim 1, a Gas turbine according to the preamble of claim 11, a annular guide vane carrier for a turbomachine for fixing vanes according to the preamble of Claim 12 and a method for mounting vanes on an annular guide vane carrier of a turbomachine according to the preamble of claim 13.
  • Gas turbines coupled to generators become converters used by fossil energy in electrical energy.
  • a Gas turbine points to along its rotor shaft in the flow direction the gases a compressor, a combustion chamber and a Turbine unit on.
  • the compressor air is mixed with a fuel and the combustion chamber supplied.
  • the mixture burns too a hot gaseous working fluid and flows into the Buckets provided turbine unit.
  • the on the housing of Turbine unit attached vanes direct the working fluid on the rotor blades attached to the rotor so that these put the rotor in a rotary motion.
  • the so recorded Rotational energy of the rotor is through the rotor coupled generator converted into electrical energy. Furthermore, it is used to drive the compressor.
  • the object of the invention is to provide a turbomachine, in particular a compressor, with reduced flow losses specify. Furthermore, it is the object of the invention specify a gas turbine and a vane carrier. Another object of the invention is a method of mounting of vanes on an annular vane support a turbomachine.
  • the solution of the task directed at the turbomachine provides that the fastening means at least one in the groove bottom the circumferential groove extending along its circumference groove-shaped Recess and several arranged therein annular Press segments include, which under bias against the Press vane feet.
  • the invention is based on the knowledge that everyone Guide vane or each Leitschaufelfuß at least one press segment assigned.
  • a press segment is provided in the groove bottom of the circumferential groove a groove-shaped recess.
  • the pressing segments create one Preload, which the Leitschaufelfuß to the undercuts the circumferential groove presses, so that the vane one firm and secure fit without play.
  • the press segments will achieved by the press segments that no costly manual fitting required during assembly of the guide vanes is. Comparatively large tolerances of the circumferential groove and the Guide vanes are cost-reducing possible.
  • each press segment is located.
  • a vane or a Leitschaufelfuß of a pair of press segments pressed against the undercuts of the circumferential groove.
  • Only one press segment could the Leitschaufelfuß to one Contact surface on which the pressing segment bears against the guide blade root, tilt, or the guide blade foot unevenly to the press both undercuts.
  • each pressing segment in the circumferential direction at least two sections includes, wherein one of the sections in the radial direction has an excess to form the bias voltage.
  • the assembly is the Leitschaufelfuß already in the Recess provided press segment in an operating position postponed. Because the vane or its platform in the circumferential direction can be wider than the vane foot is It makes sense, the excess only in the section of the press segment to provide, in the operating position the Leitschaufelfuß contacted. Because the other sections only during the move process come into contact with the vane foot, an oversize provided here would be the initial move prevent. Furthermore serve the one or the other Sections of the press segment in the circumferential direction as a stop surface for subsequently installed press segments, the then be in the correct operating position.
  • the recess has an inner support wall as an abutment on which the press segment is supported.
  • the oversize is slightly larger than the distance from the vane root to the inner support wall.
  • a shift in the circumferential direction of the mounted vanes is prevented if at least in the vane ring a fuse element a vane against displacement secures in the circumferential direction.
  • the vane foot can be more compact and be made narrower, so that manufacturing processes like Forging or milling with little use of material per blank possible are.
  • the platform element can be additionally made a cheaper material, e.g. ST37 as the vane.
  • the turbomachine is a compressor.
  • the task directed to the gas turbine is by the Features of claim 11 and on the vane carrier directed object solved by the features of claim 12.
  • the task directed to the method is characterized by the features of claim 13 solved.
  • turbomachine applies mutatis mutandis also for the gas turbine, the vane carrier and for the Method.
  • FIG. 5 shows a gas turbine 1 in a longitudinal partial section. It has a rotatably mounted about an axis of rotation 2 inside Rotor 3, which also referred to as turbine rotor or rotor shaft becomes. Along the rotor 3 follow one another Intake housing 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of coaxially arranged burners 7, a turbine 8 and the exhaust housing 9.
  • annular compressor passage 10 is provided, in the direction of the annular combustion chamber 6 in cross section rejuvenated.
  • a diffuser 11 is arranged, which communicates with the annular combustion chamber 6 is in fluid communication.
  • the annular combustion chamber 6 forms a combustion chamber 12 for a mixture of a Fuel and compressed air.
  • An arranged in the turbine 8 Hot gas duct 13 is connected to the combustion chamber 12 in Flow connection, wherein the hot gas duct 13, the exhaust housing 9 is subordinate.
  • each alternating Shovel rings In the compressor duct 10 and in the hot gas duct 13 are each alternating Shovel rings arranged. It follows one from vanes 14 formed Leitschaufelring 15 each one out Blades 16 formed blade ring 17.
  • the fixed Guide vanes 14 are in this case with a guide vane carrier 18 connected, whereas where the blades 16 on the rotor. 3 are connected by a disc 19.
  • the gas turbine 1 During operation of the gas turbine 1 is from the compressor. 5 sucked air through the intake housing 4 and in the compressor duct 10 compacted. One at the burner end of the compressor 5 provided air L is through the diffuser 11th led to the burners 7 and mixed there with a fuel. The mixture is then made to form a working fluid 20 burned in the combustion chamber 12. From there flows the working fluid 20 in the hot gas duct 13. At the in the Turbine 8 arranged vanes 14 and on the blades 16 the working fluid 20 relaxes momentum, so that the rotor 3 is driven and with it one on it coupled machine (not shown).
  • Fig. 1 shows a section through a vane carrier 18 and a freestanding vane 14.
  • the annular Guide vane 18 has at its the compressor passage 10th facing wall on an inner circumferential groove 21. On whose Side walls 22 are each formed by a projection 23 Undercuts 24 provided.
  • the groove base 25 are further arranged two groove-shaped recesses 26, the may also be formed as further circumferential grooves.
  • the recesses 26 protrude with a radial depth in the vane support 18 in, which is larger than that Width B of its opening in the groove base 25.
  • the vane 14 extends with its vane root 27 in the circumferential groove 21 inside.
  • the Leitschaufelfuß 27 complementary to the undercuts 24 of the circumferential groove 21, that is T-shaped, formed, so that the guide vane 14th is held in the circumferential groove 21.
  • a compressor passage 10 radially outwardly limiting Platform 29 provided from which the freestanding Airfoil profile 28 extends into the compressor passage 10 inside.
  • each pressing segments 30 are arranged, the Leitschaufelfuß 27 with a bias to the Projections 23 of the circumferential groove 21 presses.
  • Fig. 2 shows the vane support 18 and the vane 14 according to the section II-II of Fig. 1.
  • a Platform element 32 is provided, which the compressor duct 10 limited radially outward.
  • the platform element 32 analogous to a Leitschaufelfußes 27 in the circumferential groove 21st hooked.
  • the pressing segment 30 Radially viewed from outside to inside is the pressing segment 30 with a support surface 40 on the support wall 31 at.
  • the Pressing segment 30 points into a first section 34 (FIG. 4) his Leitschaufelfuß 27 side facing a contact surface 33, which rests on the guide blade foot 27 and this pressed against the projections 23.
  • a second section 35 is a surface 36 which springs back against the contact surface 33, facing the platform element 32.
  • In the operating position is the surface 36 of the back of a to the vane 14 adjacent the platform member 32 without contact or with only comparatively low bias towards.
  • Fig. 3 shows a section through Fig. 1 according to the sectional plane III-III.
  • the platform element 32 Between two vanes 14 is the platform element 32 arranged.
  • the circumferential groove 21 extends in the circumferential direction U, wherein on the side walls 22, the undercuts 24 are shown.
  • In the groove base 25 are two recesses 26 with Abstütz alloyn 31.
  • In the in Fig. 3 left recess 26 is a press segment 30 is arranged, whose surface 36 is shown.
  • the platform element 32 has at one of the vane 14 facing end side a recess 37, in which a tool with a Lever is introduced to the vane 14 for disassembly from the contact surface 33 in the direction of the surface 36 to push and thus solve them.
  • vanes 14 and the platform elements 32 themselves due to tolerances and transient thermal expansions in Can not move the circumferential direction U, for example, each third platform element 32 by a securing element 38, which in a further recess 39 of the flow away Side of the vane 14 is introduced, fixed become.
  • the pressing segments 30 and securing elements 38 are located between vane support 18 and the guide vanes 14 and the platform elements 32 so that they do not enter the compressor duct 10 can get into it.
  • FIG 4 shows the pressing segment 30 with the first section 34 and the second section 35.
  • the contact surface 33 is spaced from the opposing supporting surface 40 at a distance B 1 .
  • the surface 36 is spaced from the opposite Abstützflache 40 at a further distance B 2 .
  • the distance B 1 is greater than the distance B 2 .
  • the distance B 1 corresponds to a distance S ( Figure 1), which is measured between the support wall 31 and the Leitschaufelfuß, plus an oversize of about 0.3 mm.
  • the section 35 without oversize has a distance B 2 which can correspond approximately to the distance S.
  • a Press segment 30 introduced for mounting a vane 14 on the vane carrier 18 is first in each groove-shaped recess 26 a Press segment 30 introduced. Either then can the vane 14 by radially inwardly moving into the circumferential groove 21st be introduced with subsequent twisting, so that the on the guide blade foot 27 provided T-shaped projections the Behind undercut 24. Or they are in the circumferential groove 21 inserted, if this one suitable Has opening, such as the parting line of the housing. Subsequently the vane 14 is in the direction of the free Press segments 30 shifted until the Leitschaufelfuß 27 the Surface 36 of the pressing segments 30 covered and on the protruding Contact surface 33 abuts.
  • a construction without platform elements 32 is also conceivable, when the platforms 29 of the guide vanes 14 in the circumferential direction U are made so wide that they are the one of the Platform elements 32 filled space bridged.
  • the pressing segments 30 remain unchanged.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP03029771A 2003-12-23 2003-12-23 Turbomachine avec un stator et procédé de fixation d'aubes statoriques dans le stator Withdrawn EP1548232A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP03029771A EP1548232A1 (fr) 2003-12-23 2003-12-23 Turbomachine avec un stator et procédé de fixation d'aubes statoriques dans le stator
PCT/EP2004/012553 WO2005066463A1 (fr) 2003-12-23 2004-11-05 Turbomachine comportant un support a aubes directrices et procede de montage d'aubes directrices sur un support a aubes directrices
EP04797660A EP1697618B1 (fr) 2003-12-23 2004-11-05 Stator et une pluralite d'aubes statoriques et procede de fixation d'aubes statoriques dans le stator

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03029771A EP1548232A1 (fr) 2003-12-23 2003-12-23 Turbomachine avec un stator et procédé de fixation d'aubes statoriques dans le stator

Publications (1)

Publication Number Publication Date
EP1548232A1 true EP1548232A1 (fr) 2005-06-29

Family

ID=34530723

Family Applications (2)

Application Number Title Priority Date Filing Date
EP03029771A Withdrawn EP1548232A1 (fr) 2003-12-23 2003-12-23 Turbomachine avec un stator et procédé de fixation d'aubes statoriques dans le stator
EP04797660A Not-in-force EP1697618B1 (fr) 2003-12-23 2004-11-05 Stator et une pluralite d'aubes statoriques et procede de fixation d'aubes statoriques dans le stator

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP04797660A Not-in-force EP1697618B1 (fr) 2003-12-23 2004-11-05 Stator et une pluralite d'aubes statoriques et procede de fixation d'aubes statoriques dans le stator

Country Status (2)

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EP (2) EP1548232A1 (fr)
WO (1) WO2005066463A1 (fr)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1965028A3 (fr) * 2007-02-27 2010-11-24 General Electric Company Appareil pour assembler des cales d' aubes
CH703997A1 (de) * 2010-10-27 2012-04-30 Alstom Technology Ltd Schaufelanordnung, insbesondere Leitschaufelanordnung.
RU2472975C2 (ru) * 2009-01-06 2013-01-20 Дженерал Электрик Компани Способ и устройство для обеспечения правильной установки статоров в корпусе компрессора
EP2679776A1 (fr) * 2012-06-28 2014-01-01 Alstom Technology Ltd Système de refroidissement et procédé pour turbine à flux axial
EP2211025A3 (fr) * 2009-01-21 2014-01-22 General Electric Company Ailettes de charge discrètes pour aubes de stator individuelles
WO2015073214A1 (fr) * 2013-11-13 2015-05-21 Siemens Energy, Inc. Ensemble d'aubes à plateformes non intégrées
EP2995775A1 (fr) * 2014-09-15 2016-03-16 Siemens Aktiengesellschaft Dispositif destiné à enfoncer une aube directrice dans une rainure d'aube
FR3048719A1 (fr) * 2016-03-14 2017-09-15 Snecma Redresseur de flux pour turbomachine avec plateformes integrees et rapportees
EP3611347A1 (fr) * 2018-08-14 2020-02-19 United Technologies Corporation Moteur à turbine à gaz doté de segments de stator

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2851515A1 (fr) * 2013-09-24 2015-03-25 Siemens Aktiengesellschaft Agencement de fixation d'aubes de turbine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US998820A (en) * 1908-05-13 1911-07-25 George Westinghouse Turbine-blading.
GB216737A (en) * 1923-08-02 1924-06-05 Karl Baumann Improvements relating to elastic fluid turbines
DE518106C (de) * 1924-02-18 1931-02-24 Jan Kieswetter Einrichtung zum Ausgleich verschiedener Waermeausdehnungen zwischen einer aeusseren Gehaeusewand und einer Zwischenwand des gleichen Gehaeuses, insbesondere bei Dampf- oder Gasturbinen
US3532437A (en) * 1967-11-03 1970-10-06 Sulzer Ag Stator blade assembly for axial-flow turbines
US4142827A (en) * 1976-06-15 1979-03-06 Nuovo Pignone S.P.A. System for locking the blades in position on the stator case of an axial compressor
EP0555082A1 (fr) * 1992-02-07 1993-08-11 General Electric Company Composants de turbine à haute pression à ajustement par serrage
DE4436731A1 (de) * 1994-10-14 1996-04-18 Abb Management Ag Verdichter

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US998820A (en) * 1908-05-13 1911-07-25 George Westinghouse Turbine-blading.
GB216737A (en) * 1923-08-02 1924-06-05 Karl Baumann Improvements relating to elastic fluid turbines
DE518106C (de) * 1924-02-18 1931-02-24 Jan Kieswetter Einrichtung zum Ausgleich verschiedener Waermeausdehnungen zwischen einer aeusseren Gehaeusewand und einer Zwischenwand des gleichen Gehaeuses, insbesondere bei Dampf- oder Gasturbinen
US3532437A (en) * 1967-11-03 1970-10-06 Sulzer Ag Stator blade assembly for axial-flow turbines
US4142827A (en) * 1976-06-15 1979-03-06 Nuovo Pignone S.P.A. System for locking the blades in position on the stator case of an axial compressor
EP0555082A1 (fr) * 1992-02-07 1993-08-11 General Electric Company Composants de turbine à haute pression à ajustement par serrage
DE4436731A1 (de) * 1994-10-14 1996-04-18 Abb Management Ag Verdichter

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1965028A3 (fr) * 2007-02-27 2010-11-24 General Electric Company Appareil pour assembler des cales d' aubes
RU2472975C2 (ru) * 2009-01-06 2013-01-20 Дженерал Электрик Компани Способ и устройство для обеспечения правильной установки статоров в корпусе компрессора
EP2211025A3 (fr) * 2009-01-21 2014-01-22 General Electric Company Ailettes de charge discrètes pour aubes de stator individuelles
CH703997A1 (de) * 2010-10-27 2012-04-30 Alstom Technology Ltd Schaufelanordnung, insbesondere Leitschaufelanordnung.
EP2447474A1 (fr) 2010-10-27 2012-05-02 Alstom Technology Ltd Agencement d'aube, notamment agencement d'aube directrice
US8979497B2 (en) 2010-10-27 2015-03-17 Alstom Technology Ltd. Blade arrangement, especially stator blade arrangement
CN103527258B (zh) * 2012-06-28 2016-12-28 通用电器技术有限公司 轴流式涡轮及冷却轴流式涡轮叶片的方法
CN103527258A (zh) * 2012-06-28 2014-01-22 阿尔斯通技术有限公司 用于轴流式涡轮的冷却系统及方法
EP2679776A1 (fr) * 2012-06-28 2014-01-01 Alstom Technology Ltd Système de refroidissement et procédé pour turbine à flux axial
WO2015073214A1 (fr) * 2013-11-13 2015-05-21 Siemens Energy, Inc. Ensemble d'aubes à plateformes non intégrées
US9388704B2 (en) 2013-11-13 2016-07-12 Siemens Energy, Inc. Vane array with one or more non-integral platforms
EP2995775A1 (fr) * 2014-09-15 2016-03-16 Siemens Aktiengesellschaft Dispositif destiné à enfoncer une aube directrice dans une rainure d'aube
WO2016041799A1 (fr) * 2014-09-15 2016-03-24 Siemens Aktiengesellschaft Dispositif pour insérer une aube directrice dans une rainure à aube
FR3048719A1 (fr) * 2016-03-14 2017-09-15 Snecma Redresseur de flux pour turbomachine avec plateformes integrees et rapportees
WO2017158266A1 (fr) * 2016-03-14 2017-09-21 Safran Aircraft Engines Redresseur de flux pour turbomachine avec plateformes intégrées et rapportées
GB2563796A (en) * 2016-03-14 2018-12-26 Safran Aircraft Engines Flow stator for turbomachine with integrated and attached platforms
GB2563796B (en) * 2016-03-14 2021-08-11 Safran Aircraft Engines Flow stator for turbomachine with integrated and attached platforms
EP3611347A1 (fr) * 2018-08-14 2020-02-19 United Technologies Corporation Moteur à turbine à gaz doté de segments de stator
US11125092B2 (en) 2018-08-14 2021-09-21 Raytheon Technologies Corporation Gas turbine engine having cantilevered stators

Also Published As

Publication number Publication date
EP1697618A1 (fr) 2006-09-06
EP1697618B1 (fr) 2012-12-26
WO2005066463A1 (fr) 2005-07-21

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