EP3421733B1 - Support d'aubes pour turbine à gaz et turbine à gaz comprenant ledit support d'aubes - Google Patents

Support d'aubes pour turbine à gaz et turbine à gaz comprenant ledit support d'aubes Download PDF

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Publication number
EP3421733B1
EP3421733B1 EP17179199.9A EP17179199A EP3421733B1 EP 3421733 B1 EP3421733 B1 EP 3421733B1 EP 17179199 A EP17179199 A EP 17179199A EP 3421733 B1 EP3421733 B1 EP 3421733B1
Authority
EP
European Patent Office
Prior art keywords
vane carrier
clearance control
control cavity
gas turbine
insert
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.)
Active
Application number
EP17179199.9A
Other languages
German (de)
English (en)
Other versions
EP3421733A1 (fr
Inventor
Johannes Richter
Giovanni Cataldi
Nikolas Wiedemann
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.)
Ansaldo Energia IP UK Ltd
Original Assignee
Ansaldo Energia IP UK Ltd
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 Ansaldo Energia IP UK Ltd filed Critical Ansaldo Energia IP UK Ltd
Priority to EP17179199.9A priority Critical patent/EP3421733B1/fr
Priority to CN201810699600.XA priority patent/CN109209515B/zh
Publication of EP3421733A1 publication Critical patent/EP3421733A1/fr
Application granted granted Critical
Publication of EP3421733B1 publication Critical patent/EP3421733B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • 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
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/125—Fluid guiding means, e.g. vanes related to the tip of a stator vane
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes

Definitions

  • It is a further object of the present invention to provide a gas turbine plant for the production of electrical power energy comprising a compressor, a combustor and a gas turbine; the compressor comprising a vane carrier according to the present invention.
  • reference numeral 1 indicates a gas turbine plant for electrical energy production extending along a longitudinal axis A (for the sake of simplicity only an half of the plant is illustrated in figure 1 as the plant being symmetrical with respect to axis A).
  • the plant 1 comprises a combustor 2, a compressor 3 and a gas turbine 5.
  • the angular position of the axis B of the clearance control cavity 29 can vary from radially to axially (axially excluded) depending on the available space in the vane carrier 10 wherein a clearance control is needed.
  • the vane carrier comprises more than one plurality of circumferentially arranged clearance control cavities at different axial positions of the vane carrier in order to influence the thermo-mechanical behaviour of the vane carrier in different zones of the vane carrier.
  • the feeding conduits 31 are supported by the outer casing 9 and are preferably connected to a common manifold (not illustrated for sake of simplicity) supplied with the control fluid.
  • the discharge conduits 34a connected to the outlets 33a of the clearance control cavities 29a which are closer to the split plane S of the vane carrier 10 connect the clearance control cavities 29a with the adjacent clearance control cavities 29b in order to create a sequential discharge configuration. In this way, at the split plane, a minimized space occupation is obtained.
  • clearance control cavities 29b have the outlets connected to respective discharge conduits extending substantially axially or are inclined at an angle with respect to the axis A and flowing into the expansion channel 7 (said discharge conduits are specifically not visible in the attached figures).
  • Discharge conduits 34a are preferably realized by drilling the vane carrier 10 at the split plane S.
  • said solution implies the presence of undesired service channels 39 which can be plugged up or joined.
  • Said insert 41 can furthermore enhance the heat transfer between the control fluid flowing in the clearance control cavity 29 and the material of the vane carrier 10 in order to influence the temperature of the vane carrier 10.
  • the insert 41 in fact, allow to operate with moderate flow quantities.
  • the gap defined between the insert 41 and the respective inner surface of the clearance control cavity 29 has a thickness T (intended as the measure along a direction perpendicular to the axis B) which is a function of the diameter of the clearance control cavity 29.
  • the ratio between the diameter of the clearance control cavity 29 and the thickness T is comprised between 1:200 to 1:2.
  • said turbulators may be helicoidally bended ribs protruding from the outer surface of the insert 41.
  • the insert is provided with damping means configured to resist vibrations.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (11)

  1. Support de pale pour une installation de turbine à gaz s'étendant le long d'un axe longitudinal (A) et comprenant une pluralité de cavités de contrôle de jeu (29) réparties le long d'une direction circonférentielle, chacune s'étendant de manière transversale par rapport à l'axe longitudinal (A) et ayant une première entrée (30) raccordée à une source de fluide de commande (31, 16, 3) ;
    au moins une cavité de contrôle de jeu (29a) de la pluralité de cavités de contrôle de jeu (29) ayant au moins une sortie (33a) raccordée à un conduit de décharge (34a) respectif ;
    caractérisé en ce que :
    le au moins un conduit de décharge (34a) raccorde la sortie (33a) de la cavité de contrôle de jeu (29a) à une autre entrée d'une autre cavité de contrôle de jeu (29b) adjacente.
  2. Support de pale selon la revendication 1, dans lequel la cavité de contrôle de jeu (29) s'étendant radialement par rapport à l'axe longitudinal (A).
  3. Support de pale selon l'une quelconque des revendications précédentes, dans lequel la pluralité de cavités de contrôle de jeu (29) sont régulièrement réparties le long de la direction circonférentielle.
  4. Support de pale selon l'une quelconque des revendications précédentes, ayant une surface interne (32b) faisant face à un canal de fluide de travail (7 ; 8) prévu avec des pales (11 ; 21) et une surface externe (32a) opposée à la surface interne (32b) ; dans lequel la cavité de contrôle de jeu (29) est un trou aveugle réalisé dans la surface externe (32a) du support de pale (10 ; 20).
  5. Support de pale selon l'une quelconque des revendications précédentes, dans lequel un autre conduit de décharge (34) s'écoule dans un canal de fluide de travail (7 ; 8) prévu avec des pales (11 ; 21).
  6. Support de pale selon l'une quelconque des revendications précédentes, comprenant au moins un insert (41) qui est agencé à l'intérieur d'au moins une cavité de contrôle de jeu (29).
  7. Support de pale selon la revendication 6, dans lequel l'insert (41) est creux afin de permettre le passage de fluide de commande à travers ce dernier.
  8. Support de pale selon la revendication 6 ou 7, dans lequel l'insert (41) est formé afin de définir un espace (42) entre l'insert (4) et la surface interne de la cavité de contrôle de jeu (29).
  9. Installation pour la production d'énergie électrique comprenant un compresseur (3), une chambre de combustion (4) et une turbine à gaz (5) ; la turbine à gaz (5) comprend au moins un support de pale (7) selon l'une quelconque des revendications précédentes.
  10. Installation selon la revendication 9, dans laquelle la cavité de contrôle de jeu (29) est raccordée à une ligne d'extraction (36) qui est configurée pour extraire l'air du compresseur (3) et l'amener dans la cavité de contrôle de jeu (29).
  11. Installation pour la production d'énergie électrique comprenant un compresseur (3), une chambre de combustion (4) et une turbine à gaz (5) ; le compresseur (3) comprend au moins un support de pale (8) selon l'une quelconque des revendications 1 à 8.
EP17179199.9A 2017-06-30 2017-06-30 Support d'aubes pour turbine à gaz et turbine à gaz comprenant ledit support d'aubes Active EP3421733B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP17179199.9A EP3421733B1 (fr) 2017-06-30 2017-06-30 Support d'aubes pour turbine à gaz et turbine à gaz comprenant ledit support d'aubes
CN201810699600.XA CN109209515B (zh) 2017-06-30 2018-06-29 用于燃气涡轮装置的导叶载体和包括所述导叶载体的燃气涡轮装置

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17179199.9A EP3421733B1 (fr) 2017-06-30 2017-06-30 Support d'aubes pour turbine à gaz et turbine à gaz comprenant ledit support d'aubes

Publications (2)

Publication Number Publication Date
EP3421733A1 EP3421733A1 (fr) 2019-01-02
EP3421733B1 true EP3421733B1 (fr) 2020-02-26

Family

ID=59269962

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Application Number Title Priority Date Filing Date
EP17179199.9A Active EP3421733B1 (fr) 2017-06-30 2017-06-30 Support d'aubes pour turbine à gaz et turbine à gaz comprenant ledit support d'aubes

Country Status (2)

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EP (1) EP3421733B1 (fr)
CN (1) CN109209515B (fr)

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19546722B4 (de) * 1995-12-14 2005-03-31 Alstom Leitschaufelträger für eine Gasturbine
US7434402B2 (en) 2005-03-29 2008-10-14 Siemens Power Generation, Inc. System for actively controlling compressor clearances
DE102005045255A1 (de) * 2005-09-22 2007-03-29 Mtu Aero Engines Gmbh Verbesserter Verdichter in Axialbauart
EP2023600A1 (fr) 2007-07-27 2009-02-11 Thomson Licensing Procédé de cartographie couleur d'une gamme de couleurs source non convexe en gamme de couleurs cible non convexe
US20100054911A1 (en) * 2008-08-29 2010-03-04 General Electric Company System and method for adjusting clearance in a gas turbine
US8342798B2 (en) * 2009-07-28 2013-01-01 General Electric Company System and method for clearance control in a rotary machine
US9157331B2 (en) * 2011-12-08 2015-10-13 Siemens Aktiengesellschaft Radial active clearance control for a gas turbine engine
EP2754859A1 (fr) * 2013-01-10 2014-07-16 Alstom Technology Ltd Turbomachine avec pilotage électrique actif de jeu et procédé associé
JP6223774B2 (ja) * 2013-10-15 2017-11-01 三菱日立パワーシステムズ株式会社 ガスタービン
EP3023600B1 (fr) 2014-11-24 2018-01-03 Ansaldo Energia IP UK Limited Élément de carter de moteur
CN106382136B (zh) * 2016-11-18 2017-07-25 中国科学院工程热物理研究所 一种跨音速动叶叶顶间隙主动控制装置

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
CN109209515A (zh) 2019-01-15
CN109209515B (zh) 2022-07-08
EP3421733A1 (fr) 2019-01-02

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