EP2532834A2 - Éléments de contrôle de l'écoulement de refroidissement pour aubes de turbomachine et procédé de contrôle - Google Patents

Éléments de contrôle de l'écoulement de refroidissement pour aubes de turbomachine et procédé de contrôle Download PDF

Info

Publication number
EP2532834A2
EP2532834A2 EP12170429A EP12170429A EP2532834A2 EP 2532834 A2 EP2532834 A2 EP 2532834A2 EP 12170429 A EP12170429 A EP 12170429A EP 12170429 A EP12170429 A EP 12170429A EP 2532834 A2 EP2532834 A2 EP 2532834A2
Authority
EP
European Patent Office
Prior art keywords
cooling
turbomachine
bucket
flow control
control member
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Withdrawn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
EP12170429A
Other languages
German (de)
English (en)
Inventor
Rohit Pruthi
Krishnakumar Pallikkara Gopalan
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 Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2532834A2 publication Critical patent/EP2532834A2/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • 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
    • F01D5/187—Convection cooling

Definitions

  • the subject matter disclosed herein relates to the art of turbomachines and, more particularly to cooling flow control members for turbomachine buckets.
  • Turbomachines typically include a compressor portion operationally linked to a turbine portion. Turbomachines also include a combustor that receives fuel and air which is mixed and combusted to form a high energy fluid or hot gases. The hot gases are directed into a hot gas path toward turbine blades or buckets. The turbine buckets convert thermal energy from the hot gases to mechanical, rotational energy that provides power to, for example, generators, pumps etc. During operation, compressor discharge air is passed through the turbine buckets to provide cooling that may extend an overall operational life of turbine portion components.
  • the compressor discharge air is passed into a turbine rotor that supports a plurality of turbine buckets.
  • the compressor discharge air passes through the turbine rotor into each of the plurality of buckets to provide internal cooling.
  • the compressor discharge air enters each of the turbine bucket through a dovetail member, and passes through an airfoil portion before exiting toward a shroud member mounted to a housing of the turbine portion. While effective at providing cooling, diverting compressor discharge air into the buckets reduces an overall operational efficiency of the turbomachine.
  • a turbomachine bucket including a base portion having a first end that extends to a second end, and an airfoil portion extending from the first end of the base portion.
  • the airfoil portion includes a first end section that extends to a tip section.
  • a plurality of cooling channels extend through the turbomachine bucket from the first end of the base portion to the tip portion, and a cooling flow control member is arranged in one of the plurality of cooling channels.
  • the cooling flow control member creates at least a partial flow restriction in the one of the plurality of cooling channels to modify cooling flow passing through the turbomachine bucket.
  • a method of controlling cooling flow passing through a plurality of cooling passages formed in a turbomachine bucket includes exposing the plurality of cooling passages formed in the turbomachine bucket, inserting a cooling flow control member into at least one of the cooling passages and controlling a cooling fluid flow passing through the turbomachine bucket with the cooling flow control member.
  • Turbomachine 2 includes a housing 4 that surrounds a compressor portion 6 operatively connected to a turbine portion 8.
  • Compressor portion 6 includes a plurality of rotor or wheel members, three of which are indicated at 20-22. Each wheel member 20-22 is operatively connected to corresponding pluralities of vanes or buckets 23-25 that establish various stages of compressor portion 6.
  • turbine portion 8 includes a plurality of rotor or wheel members, three of which are indicated at 26-28. Each wheel member 26-28 is operatively connected to corresponding pluralities of vanes or buckets 31-33 that establish various stages of turbine section 8.
  • Bucket 31 includes a bucket body 54 having a base portion 56 and an airfoil portion 58.
  • Base portion 56 includes a first or dovetail end 61 that extends to a second end 62 through an intermediate portion 63.
  • Airfoil portion 58 includes a first end section 68 that extends from second end 62 of base portion 56 to a second or tip end section 69 through an intermediate section 70.
  • Bucket 31 includes a plurality of cooling channels, one of which is indicated at 80, that extend from dovetail end 61 of base portion 56 to tip end section 69 of airfoil portion 58 within bucket body 54. As best shown in FIG.
  • each cooling channel 80 includes a first cooling channel section 83 that extends within base portion 56 and a second cooling channel section 84 that extends within airfoil portion 58.
  • First cooling channel section 83 includes a first diameter and second cooling channel section 84 includes a second diameter that is smaller than the first diameter.
  • First cooling channel section 83 includes an inlet end 85 that extends to a second end 86 through an intermediate section 87.
  • FIGs. 7-9 illustrate a cooling flow control member 104 in accordance with another aspect of the exemplary embodiment.
  • Cooling flow control member 104 includes a first end portion 106 that extends to a second end portion 107 through an intermediate portion 108.
  • Cooling flow control member 104 includes a passage 110 that extend between first and second end portions 106 and 107. Passage 110 creates a flow restriction within the corresponding one of cooling channels 80.
  • passage 110 includes a tapered profile 113 having a circular cross-section 115. By restricting cooling air passing though cooling channel(s) 80, additional compressor flow is directed to other portions of turbomachine 2 to enhance operability.
  • FIG. 10 illustrates a cooling flow control member 119 having a passage 121 including a non-circular cross-section 123. The non-circular cross-section provides another restriction to the cooling flow passing through cooling channel(s) 80.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12170429A 2011-06-10 2012-06-01 Éléments de contrôle de l'écoulement de refroidissement pour aubes de turbomachine et procédé de contrôle Withdrawn EP2532834A2 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/157,423 US20120315139A1 (en) 2011-06-10 2011-06-10 Cooling flow control members for turbomachine buckets and method

Publications (1)

Publication Number Publication Date
EP2532834A2 true EP2532834A2 (fr) 2012-12-12

Family

ID=46201451

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12170429A Withdrawn EP2532834A2 (fr) 2011-06-10 2012-06-01 Éléments de contrôle de l'écoulement de refroidissement pour aubes de turbomachine et procédé de contrôle

Country Status (3)

Country Link
US (1) US20120315139A1 (fr)
EP (1) EP2532834A2 (fr)
CN (1) CN102817638A (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2994044B1 (fr) 2013-05-08 2020-05-06 CardioInsight Technologies, Inc. Analyse et détection pour entrainements arythmiques

Family Cites Families (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2010022A (en) * 1931-06-27 1935-08-06 Holzwarth Gas Turbine Co Cooling of gas turbine blades
US2763427A (en) * 1949-10-13 1956-09-18 Armstrong Siddeley Motors Ltd Axial-flow machines
US2991973A (en) * 1954-10-18 1961-07-11 Parsons & Marine Eng Turbine Cooling of bodies subject to a hot gas stream
US2977090A (en) * 1956-06-12 1961-03-28 Daniel J Mccarty Heat responsive means for blade cooling
US3623825A (en) * 1969-11-13 1971-11-30 Avco Corp Liquid-metal-filled rotor blade
US3834831A (en) * 1973-01-23 1974-09-10 Westinghouse Electric Corp Blade shank cooling arrangement
US3902820A (en) * 1973-07-02 1975-09-02 Westinghouse Electric Corp Fluid cooled turbine rotor blade
US3994622A (en) * 1975-11-24 1976-11-30 United Technologies Corporation Coolable turbine blade
US4242045A (en) * 1979-06-01 1980-12-30 General Electric Company Trap seal for open circuit liquid cooled turbines
US4519745A (en) * 1980-09-19 1985-05-28 Rockwell International Corporation Rotor blade and stator vane using ceramic shell
US4668162A (en) * 1985-09-16 1987-05-26 Solar Turbines Incorporated Changeable cooling control system for a turbine shroud and rotor
US4820123A (en) * 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades
US5318404A (en) * 1992-12-30 1994-06-07 General Electric Company Steam transfer arrangement for turbine bucket cooling
US6059529A (en) * 1998-03-16 2000-05-09 Siemens Westinghouse Power Corporation Turbine blade assembly with cooling air handling device
DE69940948D1 (de) * 1999-01-25 2009-07-16 Gen Electric Interner Kühlkreislauf für eine Gasturbinenschaufel
GB9906450D0 (en) * 1999-03-19 1999-05-12 Rolls Royce Plc Aerofoil blade damper
US6176677B1 (en) * 1999-05-19 2001-01-23 Pratt & Whitney Canada Corp. Device for controlling air flow in a turbine blade
GB2354290B (en) * 1999-09-18 2004-02-25 Rolls Royce Plc A cooling air flow control device for a gas turbine engine
US6413041B1 (en) * 2000-08-02 2002-07-02 Siemens Westinghouse Power Corporation Method and apparatus for closing holes in superalloy gas turbine blades
EP1223308B1 (fr) * 2000-12-16 2007-01-24 ALSTOM Technology Ltd Composante d'une turbomachine
FR2823794B1 (fr) * 2001-04-19 2003-07-11 Snecma Moteurs Aube rapportee et refroidie pour turbine
US6589010B2 (en) * 2001-08-27 2003-07-08 General Electric Company Method for controlling coolant flow in airfoil, flow control structure and airfoil incorporating the same
FR2858352B1 (fr) * 2003-08-01 2006-01-20 Snecma Moteurs Circuit de refroidissement pour aube de turbine
US6997679B2 (en) * 2003-12-12 2006-02-14 General Electric Company Airfoil cooling holes
US7270517B2 (en) * 2005-10-06 2007-09-18 Siemens Power Generation, Inc. Turbine blade with vibration damper
US7413406B2 (en) * 2006-02-15 2008-08-19 United Technologies Corporation Turbine blade with radial cooling channels
US7819629B2 (en) * 2007-02-15 2010-10-26 Siemens Energy, Inc. Blade for a gas turbine
EP2003291B1 (fr) * 2007-06-15 2017-08-09 Ansaldo Energia Switzerland AG Aube de turbine à gaz moulée et procédé de production
US20090226327A1 (en) * 2008-03-07 2009-09-10 Siemens Power Generation, Inc. Gas Turbine Engine Including Temperature Control Device and Method Using Memory Metal
EP2252771A1 (fr) * 2008-03-07 2010-11-24 ALSTOM Technology Ltd Pale pour turbine à gaz
US8070421B2 (en) * 2008-03-26 2011-12-06 Siemens Energy, Inc. Mechanically affixed turbine shroud plug
US20100054915A1 (en) * 2008-08-28 2010-03-04 United Technologies Corporation Airfoil insert
US20100068066A1 (en) * 2008-09-12 2010-03-18 General Electric Company System and method for generating modulated pulsed flow
US8888455B2 (en) * 2010-11-10 2014-11-18 Rolls-Royce Corporation Gas turbine engine and blade for gas turbine engine

Non-Patent Citations (1)

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

Also Published As

Publication number Publication date
US20120315139A1 (en) 2012-12-13
CN102817638A (zh) 2012-12-12

Similar Documents

Publication Publication Date Title
US8087249B2 (en) Turbine cooling air from a centrifugal compressor
EP2660431B1 (fr) Turbomachine à gaz comprenant un système de refroidissement à contre-courant et procédé
EP2206882A2 (fr) Appareil pour fournier de poussée d'avance de compresseur centrifuge et de refroidissement de turbine
US8444372B2 (en) Passive cooling system for a turbomachine
EP2626600A2 (fr) Ensemble d'étanchéité de pièce de transition pour turbomachine
JP2009108861A (ja) 非対称流れ抽出システム
US20160305281A1 (en) Gas turbomachine including a counter-flow cooling system and method
US10066488B2 (en) Turbomachine blade with generally radial cooling conduit to wheel space
EP1930552A2 (fr) Ensemble de turbine pour faciliter la réduction de pertes dans des moteurs de turbines
CN101845997A (zh) 用于涡轮发动机冷却空气管理的装置
US8235652B2 (en) Turbine nozzle segment
US10704406B2 (en) Turbomachine blade cooling structure and related methods
US11549377B2 (en) Airfoil with cooling hole
US10408075B2 (en) Turbine engine with a rim seal between the rotor and stator
JP2013249835A (ja) タービンシステムのバケット用冷却組立体及び冷却方法
EP2484866B1 (fr) Système de flux de purge de transition pour un élément de roue de turbomachine
WO2014022620A1 (fr) Turbomachine comprenant un chauffage de joint horizontal et procédé de commande du jeu à l'extrémité dans une turbomachine à gaz
US20130318982A1 (en) Turbine cooling apparatus
EP2532834A2 (fr) Éléments de contrôle de l'écoulement de refroidissement pour aubes de turbomachine et procédé de contrôle
US11802493B2 (en) Outlet guide vane assembly in gas turbine engine
WO2014175936A2 (fr) Pièce de turbine à gaz présentant une fonction de création de tourbillon marginal
US9551353B2 (en) Compressor blade mounting arrangement
US10738638B2 (en) Rotor blade with wheel space swirlers and method for forming a rotor blade with wheel space swirlers
JP2014037831A (ja) タービンシステムの温度勾配管理装置およびタービンシステムの温度勾配管理方法

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20150106