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EP1223308A3 - Cooling of a turbo machine component - Google Patents

Cooling of a turbo machine component Download PDF

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Publication number
EP1223308A3
EP1223308A3 EP01129169A EP01129169A EP1223308A3 EP 1223308 A3 EP1223308 A3 EP 1223308A3 EP 01129169 A EP01129169 A EP 01129169A EP 01129169 A EP01129169 A EP 01129169A EP 1223308 A3 EP1223308 A3 EP 1223308A3
Authority
EP
European Patent Office
Prior art keywords
cooling
channel
flow
deflection
section
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
EP01129169A
Other languages
German (de)
French (fr)
Other versions
EP1223308B1 (en
EP1223308A2 (en
Inventor
Sacha Parneix
Martin Dr. Schnieder
Jens Prof. Dr. Von Wolfersdorf
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 Schweiz 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 Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP1223308A2 publication Critical patent/EP1223308A2/en
Publication of EP1223308A3 publication Critical patent/EP1223308A3/en
Application granted granted Critical
Publication of EP1223308B1 publication Critical patent/EP1223308B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Die vorliegende Erfindung betrifft eine Komponente einer Strömungsmaschine, insbesondere eine Turbinenschaufel, die einen von einem Kühlmedium durchströmbaren Kühlkanal (9, 10) mit zumindest einer durch die Wandung (11, 12) des Kühlkanals gebildeten Umlenkung aufweist, durch die die Strömung des Kühlmediums von einem ersten Kanalabschnitt (9) in einen stromab gelegenen zweiten Kanalabschnitt (10) umgelenkt wird. Im Bereich der Umlenkung ist zumindest ein Strömungsleitelement (8) im Kühlkanal angeordnet, durch das der Kühlkanal in einen inneren (13) und einen äußeren Strömungskanal (14) aufgeteilt wird. Der innere Strömungskanal (13) weist bei der vorliegenden Komponente eine Einschnürung im Strömungsquerschnitt auf. Durch die vorgeschlagene Ausgestaltung der Kühlkanalumlenkung wird der durch die Umlenkung hervorgerufene Druckverlust minimiert und gleichzeitig ein deutlich homogenerer Wärmeübergang auf das Kühlmedium ohne lokale Temperaturspitzen erreicht.

Figure 00000001
The invention relates to a component of a turbomachine, in particular a turbine blade, which has a cooling channel (9, 10) through which a cooling medium can flow, with at least one deflection formed by the wall (11, 12) of the cooling channel, through which the flow of the cooling medium is prevented by a first channel section (9) is deflected into a downstream second channel section (10). In the area of the deflection, at least one flow guide element (8) is arranged in the cooling channel, through which the cooling channel is divided into an inner (13) and an outer flow channel (14). The inner flow channel (13) has a constriction in the flow cross section in the present component. The proposed design of the cooling duct deflection minimizes the pressure loss caused by the deflection and at the same time achieves a significantly more homogeneous heat transfer to the cooling medium without local temperature peaks.
Figure 00000001
EP01129169A 2000-12-16 2001-12-08 Turbomachine component Expired - Lifetime EP1223308B1 (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
DE10062906 2000-12-16
DE10062906 2000-12-16
DE10126215 2001-05-30
DE10126215 2001-05-30

Publications (3)

Publication Number Publication Date
EP1223308A2 EP1223308A2 (en) 2002-07-17
EP1223308A3 true EP1223308A3 (en) 2004-01-02
EP1223308B1 EP1223308B1 (en) 2007-01-24

Family

ID=26007995

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01129169A Expired - Lifetime EP1223308B1 (en) 2000-12-16 2001-12-08 Turbomachine component

Country Status (3)

Country Link
US (1) US6595750B2 (en)
EP (1) EP1223308B1 (en)
DE (1) DE50111949D1 (en)

Families Citing this family (42)

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AU2002342500A1 (en) * 2001-12-10 2003-07-09 Alstom Technology Ltd Thermally loaded component
US6939102B2 (en) * 2003-09-25 2005-09-06 Siemens Westinghouse Power Corporation Flow guide component with enhanced cooling
US7118325B2 (en) 2004-06-14 2006-10-10 United Technologies Corporation Cooling passageway turn
US7377747B2 (en) * 2005-06-06 2008-05-27 General Electric Company Turbine airfoil with integrated impingement and serpentine cooling circuit
US20070227706A1 (en) * 2005-09-19 2007-10-04 United Technologies Corporation Compact heat exchanger
US7445432B2 (en) * 2006-03-28 2008-11-04 United Technologies Corporation Enhanced serpentine cooling with U-shaped divider rib
TWI448285B (en) * 2006-07-13 2014-08-11 Los Angeles Biomed Res Inst Compositions and methods for the treatment of mucormycosis and other fungal diseases
US7625178B2 (en) * 2006-08-30 2009-12-01 Honeywell International Inc. High effectiveness cooled turbine blade
US7967563B1 (en) * 2007-11-19 2011-06-28 Florida Turbine Technologies, Inc. Turbine blade with tip section cooling channel
WO2009118245A1 (en) * 2008-03-28 2009-10-01 Alstom Technology Ltd Guide vane for a gas turbine and gas turbine comprising such a guide vane
US20120093828A1 (en) * 2009-03-19 2012-04-19 Ibrahim Ashraf S Vaccine compositions and methods for treatment of mucormycosis and other fungal diseases
US8562286B2 (en) * 2010-04-06 2013-10-22 United Technologies Corporation Dead ended bulbed rib geometry for a gas turbine engine
GB201102719D0 (en) * 2011-02-17 2011-03-30 Rolls Royce Plc Cooled component for the turbine of a gas turbine engine
US20120315139A1 (en) * 2011-06-10 2012-12-13 General Electric Company Cooling flow control members for turbomachine buckets and method
US8807945B2 (en) 2011-06-22 2014-08-19 United Technologies Corporation Cooling system for turbine airfoil including ice-cream-cone-shaped pedestals
US8985940B2 (en) 2012-03-30 2015-03-24 Solar Turbines Incorporated Turbine cooling apparatus
US20140093388A1 (en) * 2012-09-28 2014-04-03 Solar Turbines Incorporated Cooled turbine blade with leading edge flow deflection and division
US9228439B2 (en) * 2012-09-28 2016-01-05 Solar Turbines Incorporated Cooled turbine blade with leading edge flow redirection and diffusion
US9638041B2 (en) 2013-10-23 2017-05-02 General Electric Company Turbine bucket having non-axisymmetric base contour
US9528379B2 (en) 2013-10-23 2016-12-27 General Electric Company Turbine bucket having serpentine core
US9797258B2 (en) * 2013-10-23 2017-10-24 General Electric Company Turbine bucket including cooling passage with turn
US9551226B2 (en) 2013-10-23 2017-01-24 General Electric Company Turbine bucket with endwall contour and airfoil profile
US9670784B2 (en) 2013-10-23 2017-06-06 General Electric Company Turbine bucket base having serpentine cooling passage with leading edge cooling
EP3271553A1 (en) * 2015-03-17 2018-01-24 Siemens Energy, Inc. Turbine blade with a non-constraint flow turning guide structure
US10704397B2 (en) 2015-04-03 2020-07-07 Siemens Aktiengesellschaft Turbine blade trailing edge with low flow framing channel
WO2016163980A1 (en) * 2015-04-06 2016-10-13 Siemens Energy, Inc. Turbine airfoil with flow splitter enhanced serpentine channel cooling system
US10107108B2 (en) 2015-04-29 2018-10-23 General Electric Company Rotor blade having a flared tip
DE102015112643A1 (en) * 2015-07-31 2017-02-02 Wobben Properties Gmbh Wind turbine rotor blade
US10119406B2 (en) * 2016-05-12 2018-11-06 General Electric Company Blade with stress-reducing bulbous projection at turn opening of coolant passages
WO2018143997A1 (en) * 2017-02-03 2018-08-09 Siemens Aktiengesellschaft Turbine blade
US11111795B2 (en) * 2017-08-24 2021-09-07 Siemens Energy Global GmbH & Co. KG Turbine rotor airfoil and corresponding method for reducing pressure loss in a cavity within a blade
US10641106B2 (en) 2017-11-13 2020-05-05 Honeywell International Inc. Gas turbine engines with improved airfoil dust removal
US11274569B2 (en) 2017-12-13 2022-03-15 Pratt & Whitney Canada Corp. Turbine shroud cooling
US10502093B2 (en) * 2017-12-13 2019-12-10 Pratt & Whitney Canada Corp. Turbine shroud cooling
US10570773B2 (en) * 2017-12-13 2020-02-25 Pratt & Whitney Canada Corp. Turbine shroud cooling
US10815791B2 (en) * 2017-12-13 2020-10-27 Solar Turbines Incorporated Turbine blade cooling system with upper turning vane bank
US10533454B2 (en) 2017-12-13 2020-01-14 Pratt & Whitney Canada Corp. Turbine shroud cooling
US10655476B2 (en) * 2017-12-14 2020-05-19 Honeywell International Inc. Gas turbine engines with airfoils having improved dust tolerance
DE102019125779B4 (en) * 2019-09-25 2024-03-21 Man Energy Solutions Se Blade of a turbomachine
US11319839B2 (en) * 2019-12-20 2022-05-03 Raytheon Technologies Corporation Component having a dirt tolerant passage turn
CN111852574A (en) * 2020-07-27 2020-10-30 北京全四维动力科技有限公司 Turbine blade and gas turbine comprising same
US11365645B2 (en) 2020-10-07 2022-06-21 Pratt & Whitney Canada Corp. Turbine shroud cooling

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4604031A (en) * 1984-10-04 1986-08-05 Rolls-Royce Limited Hollow fluid cooled turbine blades
US4775296A (en) * 1981-12-28 1988-10-04 United Technologies Corporation Coolable airfoil for a rotary machine
US5498126A (en) * 1994-04-28 1996-03-12 United Technologies Corporation Airfoil with dual source cooling

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4474532A (en) * 1981-12-28 1984-10-02 United Technologies Corporation Coolable airfoil for a rotary machine
GB9014762D0 (en) 1990-07-03 1990-10-17 Rolls Royce Plc Cooled aerofoil vane
GB9402442D0 (en) 1994-02-09 1994-04-20 Rolls Royce Plc Cooling air cooled gas turbine aerofoil
JP3137527B2 (en) 1994-04-21 2001-02-26 三菱重工業株式会社 Gas turbine blade tip cooling system
DE19921644B4 (en) * 1999-05-10 2012-01-05 Alstom Coolable blade for a gas turbine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4775296A (en) * 1981-12-28 1988-10-04 United Technologies Corporation Coolable airfoil for a rotary machine
US4604031A (en) * 1984-10-04 1986-08-05 Rolls-Royce Limited Hollow fluid cooled turbine blades
US5498126A (en) * 1994-04-28 1996-03-12 United Technologies Corporation Airfoil with dual source cooling

Also Published As

Publication number Publication date
EP1223308B1 (en) 2007-01-24
EP1223308A2 (en) 2002-07-17
US6595750B2 (en) 2003-07-22
US20020176776A1 (en) 2002-11-28
DE50111949D1 (en) 2007-03-15

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