EP1557536A1 - Turbine à gaz avec rotor axialement déplaçable - Google Patents

Turbine à gaz avec rotor axialement déplaçable Download PDF

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Publication number
EP1557536A1
EP1557536A1 EP04001335A EP04001335A EP1557536A1 EP 1557536 A1 EP1557536 A1 EP 1557536A1 EP 04001335 A EP04001335 A EP 04001335A EP 04001335 A EP04001335 A EP 04001335A EP 1557536 A1 EP1557536 A1 EP 1557536A1
Authority
EP
European Patent Office
Prior art keywords
rotor
guide
radial gap
platforms
turbomachine according
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Withdrawn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
EP04001335A
Other languages
German (de)
English (en)
Inventor
Arnd Dr. Reichert
Bernd Dr. Stöcker
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP04001335A priority Critical patent/EP1557536A1/fr
Priority to PCT/EP2005/000498 priority patent/WO2005071229A1/fr
Priority to EP05701049A priority patent/EP1706597B1/fr
Priority to US10/586,795 priority patent/US7559741B2/en
Priority to DE502005006804T priority patent/DE502005006804D1/de
Publication of EP1557536A1 publication Critical patent/EP1557536A1/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Withdrawn legal-status Critical Current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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • 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
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/052—Axially shiftable rotors
    • 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
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/312—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being parallel to each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other

Definitions

  • the invention relates to a turbomachine, in particular an axial flow compressor for a gas turbine, according to the preamble of claim 1.
  • Gas turbines coupled to generators become converters used by fossil energy in electrical energy.
  • a Gas turbine has to along its rotor shaft a compressor, a combustion chamber and a turbine unit. During operation the gas turbine sucks in the compressor ambient air and compacts them. Subsequently, the compressed air mixed with a fuel and fed to the combustion chamber. There, the mixture burns to a hot working medium and then flows into the turbine unit, in the blades are provided.
  • the attached to the housing of the turbine unit Guide vanes direct the working fluid onto the Rotor attached blades so that these are the rotor in make a rotary motion. The thus recorded rotational energy is then through the generator coupled to the rotor converted into electrical energy. Furthermore, it becomes the drive used the compressor.
  • WO 00/28190 is a gas turbine with a compressor known whose rotor for adjusting the radial gap, which between the tips of the turbine blades and the Inner housing is formed, against the flow direction of the Work medium is moved. This will be the radial column the turbine unit reduced, resulting in a significant Reduction of flow losses in the turbine unit and thus to an increase in efficiency of the gas turbine leads. At the same time, however, the radial gaps in the compressor increases what the flow losses in the compressor elevated. Despite the losses in the compressor, the shift leads of the rotor to a power increase of the gas turbine.
  • the object of the present invention is a turbomachine specify with an axially displaceable rotor whose Flow losses at an axial displacement of the rotor at least not be enlarged.
  • the solution of the task provides that the measure of each radial gap between the end of each blade or vane and the opposite axial portion of the boundary surface constant at least over the displacement of the rotor is and the radial gap parallel to the axis of rotation of the rotor runs.
  • the solution is based on the knowledge that the flow losses are not increased when the radial gap between fixed and rotating components remains constant over the displacement of the rotor.
  • the radial gap forming components such as the end of a Runner or vane and the opposite Limiting or guide surface, parallel to the rotor axis of rotation educated. With a displacement of the rotor in the axial direction Thus, the dimension of each radial gap remains constant.
  • the blade is a freestanding blade educated.
  • the end of the blade be designed as squeal, which a guide surface the ring channel opposite, the same time the boundary surface of the annular channel is formed.
  • the vane is a freestanding vane educated.
  • the rotor-facing end of the vane forms the radial gap with the boundary surface.
  • a parallel radial gap is formed when the Vanes of a wreath each at their end more Having platforms which, adjacent one another in the circumferential direction, an outer peripheral surface having the guide surface forms and when facing away from the guide surface Back of the platforms extending in the axial direction Section of the inner boundary surface opposite.
  • the Radial gap is then outside of the tapered flow channel shaped. In this radial gap can then labyrinth seals be arranged, the further pressure losses prevent in the flow medium. A flow around the platforms can thus be avoided.
  • turbomachine as an axial flowed through compressor of a gas turbine.
  • the Axial displacement of the rotor against the flow direction the flow medium leads in the turbine unit to itself decreasing and efficiency-increasing radial gaps, whereas the radial gaps in the compressor remain constant. Flow losses in the compressor are thus despite the shift kept constant of the rotor. Generally this leads to a further increased power output compared to that of the prior art.
  • Fig. 1 shows a gas turbine 1 in a longitudinal partial section. It has a rotatably mounted about an axis of rotation 2 inside Rotor 3 on, also called turbine rotor or rotor shaft referred to as. 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 unit 8 and the exhaust housing 9.
  • annular compressor passage 10 is present Seen 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.
  • One in the turbine unit 8 arranged hot gas duct 13 is connected to the combustion chamber 12 in flow communication, the hot gas duct 13, the exhaust housing 9 is subordinate.
  • vanes 14 formed Leitschaufelkranz 15 each one out Blades 16 formed blade ring 17.
  • the fixed Guide vanes 14 are one or more Guide vanes 18 connected, whereas the blades 16 are fixed by means of a disc 19 on the rotor 3.
  • the turbine unit 8 has a conically widening Hot gas duct 13, whose outer guide surface 21 itself extended concentrically in the flow direction of the working fluid 20.
  • the inner guide surface 22, however, is substantially aligned parallel to the axis of rotation 2 of the rotor 3.
  • the Blades 16 have at their free ends squint edges 29 on, with the opposite outer guide surfaces 21 forms a radial gap 23.
  • An inlet-side compressor bearing 32 is used in addition to the Axial and radial bearing as adjusting for a Displacement of the rotor. This is to increase performance the gas turbine 1, the rotor 2 in the stationary state of a Starting position in a stationary operating position against the Flow direction of the working fluid 20, in Fig. 1 to the left, postponed. As a result, in the turbine unit 8 of Blades 16 and the outer guide surface 21 formed Radial gap 23 reduced. This leads to a reduction the flow losses in the turbine unit 8 and thus to an increase in efficiency of the gas turbine 1.
  • Fig. 2 is a portion of the annular channel of the compressor fifth with two blade rings 17 and with an intermediate one Guide vane 15 shown.
  • the ring channel is as air flow channel 24 for the flow medium 26 air educated.
  • the outer guide surface 21 is in Fig. 2 and Fig. 3 with the outer boundary surface 37 and the inner Guide surface 22 with the inner boundary surface 36 identical.
  • each blade 16 has at its fixed end respectively a platform 25, the surfaces of which the compressor channel Limit 10 to the inside.
  • each vane 14 indicates their fixed end a platform 25, which the compressor duct 10 limit to the outside.
  • From the platform 25 of the Blade 16 (or the vane 14) extends from a running profile 27 (or a guide profile 28) in the compressor passage 10 in which, during operation of the compressor 5, the Compressed air L.
  • the free ends of the running or guide profiles 27, 28 which are opposite the platform-side ends, are designed as squashing edges 29 and are below Forming the radial gap 23 each guide rings 30 opposite.
  • Seen in the axial direction of the radial gap 23 is parallel aligned with axis of rotation 2, i. the guide ring 30 and the squealer 29 are cylindrical to the rotation axis. 2
  • the platforms 25, however, are each to the axis of rotation 2 of the Rotor 3 inclined so that viewed in the axial direction a taper of the flow channel 24 results. It turns out a cylindrical contour of the flow channel 24 in the areas the radially opposite fixed and rotating components, viewed in axial direction in sections and radial direction inside or outside of the Guiding or running profiles lie.
  • Fig. 4 shows a section of the flow channel 26 of the Compressor 3, in which each vane 14 at its the Rotor 3 each end facing a second platform 31st having.
  • the further platforms 31 of the guide vanes 14 of the vane ring 15 form a rotor 3 encompassing Ring.
  • the guide profile 28 facing surfaces the other platforms 31 form for the flow medium 26th the inner guide surface 22.
  • One of the guide surfaces 22 facing away Rear side 34 of the platform 31, 34 is located on a boundary surface 36 opposite. Between the back 34 of Platform 31 and the boundary surface 36 is the axis of rotation 2 parallel radial gap 23 formed.
  • the blades 16 are attached to the discs 19 of the rotor 3.
  • Each profile 27 has other platforms 31 at their free ends, whose run profile 27th facing surface as inner guide surfaces 22 the flow channel 24 shapes.
  • the other platforms 31 indicate their the guide surface 21, 22 opposite back 34 each have a peripheral surface, the boundary surface 36 of the annular channel 10 is opposite. This will between here the inner boundary surface 36 and the inner guide surface 22 of the radial gap 23 formed in the axial direction seen parallel to the axis of rotation 2 of the rotor 3 extends.
  • a labyrinth seal 38 is arranged, prevents the flow losses in the flow medium 26.
  • a flow channel 24 is conceivable, in the guide vanes 16 with other platforms 31 a vane ring Form 15, which is a blade ring 17 with freestanding Blades 16 follows.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP04001335A 2004-01-22 2004-01-22 Turbine à gaz avec rotor axialement déplaçable Withdrawn EP1557536A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP04001335A EP1557536A1 (fr) 2004-01-22 2004-01-22 Turbine à gaz avec rotor axialement déplaçable
PCT/EP2005/000498 WO2005071229A1 (fr) 2004-01-22 2005-01-19 Turbomachine a rotor a deplacement axial
EP05701049A EP1706597B1 (fr) 2004-01-22 2005-01-19 Turbine a gaz avec rotor axialement deplacable
US10/586,795 US7559741B2 (en) 2004-01-22 2005-01-19 Turbomachine having an axially displaceable rotor
DE502005006804T DE502005006804D1 (de) 2004-01-22 2005-01-19 Strömungsmaschine mit einem axial verschiebbaren rotor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04001335A EP1557536A1 (fr) 2004-01-22 2004-01-22 Turbine à gaz avec rotor axialement déplaçable

Publications (1)

Publication Number Publication Date
EP1557536A1 true EP1557536A1 (fr) 2005-07-27

Family

ID=34626485

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04001335A Withdrawn EP1557536A1 (fr) 2004-01-22 2004-01-22 Turbine à gaz avec rotor axialement déplaçable
EP05701049A Expired - Lifetime EP1706597B1 (fr) 2004-01-22 2005-01-19 Turbine a gaz avec rotor axialement deplacable

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP05701049A Expired - Lifetime EP1706597B1 (fr) 2004-01-22 2005-01-19 Turbine a gaz avec rotor axialement deplacable

Country Status (4)

Country Link
US (1) US7559741B2 (fr)
EP (2) EP1557536A1 (fr)
DE (1) DE502005006804D1 (fr)
WO (1) WO2005071229A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009042857A1 (de) * 2009-09-24 2011-03-31 Rolls-Royce Deutschland Ltd & Co Kg Gasturbine mit Deckband-Labyrinthdichtung
CN102121480A (zh) * 2009-12-31 2011-07-13 通用电气公司 关于涡轮发动机的压缩机定子叶片和扩散器的系统和设备
EP3222824A1 (fr) 2016-03-24 2017-09-27 Siemens Aktiengesellschaft Segment statorique, membre d'accouplage et aube directrice associés
EP3244022A1 (fr) * 2016-05-10 2017-11-15 General Electric Company Ensemble de turbine, ensemble de paroi interne de turbine et procédé d'ensemble de turbine

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8016553B1 (en) * 2007-12-12 2011-09-13 Florida Turbine Technologies, Inc. Turbine vane with rim cavity seal
DE102009021384A1 (de) * 2009-05-14 2010-11-18 Mtu Aero Engines Gmbh Strömungsvorrichtung mit Kavitätenkühlung
US20110088379A1 (en) * 2009-10-15 2011-04-21 General Electric Company Exhaust gas diffuser
US8388313B2 (en) * 2009-11-05 2013-03-05 General Electric Company Extraction cavity wing seal
US8939715B2 (en) * 2010-03-22 2015-01-27 General Electric Company Active tip clearance control for shrouded gas turbine blades and related method
US9249687B2 (en) 2010-10-27 2016-02-02 General Electric Company Turbine exhaust diffusion system and method
DE102012213016A1 (de) * 2012-07-25 2014-01-30 Siemens Aktiengesellschaft Verfahren zur Minimierung des Spalts zwischen einem Läufer und einem Gehäuse
WO2014175936A2 (fr) * 2013-02-05 2014-10-30 United Technologies Corporation Pièce de turbine à gaz présentant une fonction de création de tourbillon marginal
US9441499B2 (en) 2013-07-31 2016-09-13 General Electric Company System and method relating to axial positioning turbine casings and blade tip clearance in gas turbine engines
US9435218B2 (en) 2013-07-31 2016-09-06 General Electric Company Systems relating to axial positioning turbine casings and blade tip clearance in gas turbine engines
US20160160875A1 (en) * 2013-08-26 2016-06-09 United Technologies Corporation Gas turbine engine with fan clearance control
US9593589B2 (en) 2014-02-28 2017-03-14 General Electric Company System and method for thrust bearing actuation to actively control clearance in a turbo machine
EP3023600B1 (fr) 2014-11-24 2018-01-03 Ansaldo Energia IP UK Limited Élément de carter de moteur
DE102016115868A1 (de) 2016-08-26 2018-03-01 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit hohem Ausnutzungsgrad
CN109751131A (zh) * 2019-03-29 2019-05-14 国电环境保护研究院有限公司 一种提升燃气轮机效率和功率的调整方法

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5056986A (en) * 1989-11-22 1991-10-15 Westinghouse Electric Corp. Inner cylinder axial positioning system
WO2000028190A1 (fr) * 1998-11-11 2000-05-18 Siemens Aktiengesellschaft Palier d'arbre pour turbomachine, turbomachine correspondante et procede de fonctionnement d'une turbomachine
US20030223863A1 (en) * 2002-05-31 2003-12-04 Mitsubishi Heavy Industries, Ltd. Gas turbine compressor and clearance controlling method therefor

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3775023A (en) * 1971-02-17 1973-11-27 Teledyne Ind Multistage axial flow compressor
US4371311A (en) * 1980-04-28 1983-02-01 United Technologies Corporation Compression section for an axial flow rotary machine
US4606699A (en) * 1984-02-06 1986-08-19 General Electric Company Compressor casing recess

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5056986A (en) * 1989-11-22 1991-10-15 Westinghouse Electric Corp. Inner cylinder axial positioning system
WO2000028190A1 (fr) * 1998-11-11 2000-05-18 Siemens Aktiengesellschaft Palier d'arbre pour turbomachine, turbomachine correspondante et procede de fonctionnement d'une turbomachine
US20030223863A1 (en) * 2002-05-31 2003-12-04 Mitsubishi Heavy Industries, Ltd. Gas turbine compressor and clearance controlling method therefor

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009042857A1 (de) * 2009-09-24 2011-03-31 Rolls-Royce Deutschland Ltd & Co Kg Gasturbine mit Deckband-Labyrinthdichtung
CN102121480A (zh) * 2009-12-31 2011-07-13 通用电气公司 关于涡轮发动机的压缩机定子叶片和扩散器的系统和设备
EP3222824A1 (fr) 2016-03-24 2017-09-27 Siemens Aktiengesellschaft Segment statorique, membre d'accouplage et aube directrice associés
EP3244022A1 (fr) * 2016-05-10 2017-11-15 General Electric Company Ensemble de turbine, ensemble de paroi interne de turbine et procédé d'ensemble de turbine

Also Published As

Publication number Publication date
EP1706597A1 (fr) 2006-10-04
DE502005006804D1 (de) 2009-04-23
US20080232949A1 (en) 2008-09-25
US7559741B2 (en) 2009-07-14
WO2005071229A1 (fr) 2005-08-04
EP1706597B1 (fr) 2009-03-11

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