EP2565382A3 - Airfoil with array of cooling pins - Google Patents

Airfoil with array of cooling pins Download PDF

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Publication number
EP2565382A3
EP2565382A3 EP20120180753 EP12180753A EP2565382A3 EP 2565382 A3 EP2565382 A3 EP 2565382A3 EP 20120180753 EP20120180753 EP 20120180753 EP 12180753 A EP12180753 A EP 12180753A EP 2565382 A3 EP2565382 A3 EP 2565382A3
Authority
EP
European Patent Office
Prior art keywords
airfoil
cooling
array
cooling pins
fms
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Withdrawn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
EP20120180753
Other languages
German (de)
French (fr)
Other versions
EP2565382A2 (en
Inventor
Aaron Ezekiel Smith
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 EP2565382A2 publication Critical patent/EP2565382A2/en
Publication of EP2565382A3 publication Critical patent/EP2565382A3/en
Withdrawn legal-status Critical Current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
    • 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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface

Abstract

The present application provides an airfoil (100) with a cooling flow (130) therein. The airfoil (100) may include an internal cooling passage (110), a number of cooling holes (120) in communication with the internal cooling passage (110), and a number of pin-fms (150) positioned within the internal cooling passage (110). The pin-fms (150) are arranged with one or more turning openings (170) and one or more guiding openings (180) so as to direct the cooling flow (130) towards the cooling holes (120).
Figure imgaf001
EP20120180753 2011-08-30 2012-08-16 Airfoil with array of cooling pins Withdrawn EP2565382A3 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/221,009 US20130052036A1 (en) 2011-08-30 2011-08-30 Pin-fin array

Publications (2)

Publication Number Publication Date
EP2565382A2 EP2565382A2 (en) 2013-03-06
EP2565382A3 true EP2565382A3 (en) 2015-04-22

Family

ID=46679213

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20120180753 Withdrawn EP2565382A3 (en) 2011-08-30 2012-08-16 Airfoil with array of cooling pins

Country Status (3)

Country Link
US (1) US20130052036A1 (en)
EP (1) EP2565382A3 (en)
CN (1) CN102966380A (en)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB201217125D0 (en) * 2012-09-26 2012-11-07 Rolls Royce Plc Gas turbine engine component
US9732617B2 (en) 2013-11-26 2017-08-15 General Electric Company Cooled airfoil trailing edge and method of cooling the airfoil trailing edge
US9784123B2 (en) * 2014-01-10 2017-10-10 Genearl Electric Company Turbine components with bi-material adaptive cooling pathways
US9976425B2 (en) * 2015-12-21 2018-05-22 General Electric Company Cooling circuit for a multi-wall blade
CN105673089B (en) * 2016-03-31 2018-06-29 中国船舶重工集团公司第七�三研究所 A kind of Gas Turbine is without hat gaseous film control rotor blade
CN106014488A (en) * 2016-07-07 2016-10-12 周丽玲 Gas turbine blade with longitudinal intersection rib cooling structure
US10704399B2 (en) 2017-05-31 2020-07-07 General Electric Company Adaptively opening cooling pathway
US11041389B2 (en) 2017-05-31 2021-06-22 General Electric Company Adaptive cover for cooling pathway by additive manufacture
US10760430B2 (en) 2017-05-31 2020-09-01 General Electric Company Adaptively opening backup cooling pathway
US10927680B2 (en) 2017-05-31 2021-02-23 General Electric Company Adaptive cover for cooling pathway by additive manufacture
EP3862537A1 (en) * 2020-02-10 2021-08-11 General Electric Company Polska sp. z o.o. Cooled turbine nozzle and nozzle segment

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3858290A (en) * 1972-11-21 1975-01-07 Avco Corp Method of making inserts for cooled turbine blades
EP0034961A1 (en) * 1980-02-19 1981-09-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Cooled turbine blades
WO2001031171A1 (en) * 1999-10-22 2001-05-03 Pratt & Whitney Canada Corp. Cast airfoil structure with openings which do not require plugging
EP1113145A1 (en) * 1999-12-27 2001-07-04 ALSTOM POWER (Schweiz) AG Blade for gas turbines with metering section at the trailing edge

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5601399A (en) * 1996-05-08 1997-02-11 Alliedsignal Inc. Internally cooled gas turbine vane
US6254334B1 (en) * 1999-10-05 2001-07-03 United Technologies Corporation Method and apparatus for cooling a wall within a gas turbine engine
US6402470B1 (en) * 1999-10-05 2002-06-11 United Technologies Corporation Method and apparatus for cooling a wall within a gas turbine engine
US7014424B2 (en) * 2003-04-08 2006-03-21 United Technologies Corporation Turbine element
US6890154B2 (en) * 2003-08-08 2005-05-10 United Technologies Corporation Microcircuit cooling for a turbine blade
US6981840B2 (en) * 2003-10-24 2006-01-03 General Electric Company Converging pin cooled airfoil
US7125225B2 (en) * 2004-02-04 2006-10-24 United Technologies Corporation Cooled rotor blade with vibration damping device
EP2143883A1 (en) * 2008-07-10 2010-01-13 Siemens Aktiengesellschaft Turbine blade and corresponding casting core

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3858290A (en) * 1972-11-21 1975-01-07 Avco Corp Method of making inserts for cooled turbine blades
EP0034961A1 (en) * 1980-02-19 1981-09-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Cooled turbine blades
WO2001031171A1 (en) * 1999-10-22 2001-05-03 Pratt & Whitney Canada Corp. Cast airfoil structure with openings which do not require plugging
EP1113145A1 (en) * 1999-12-27 2001-07-04 ALSTOM POWER (Schweiz) AG Blade for gas turbines with metering section at the trailing edge

Also Published As

Publication number Publication date
CN102966380A (en) 2013-03-13
EP2565382A2 (en) 2013-03-06
US20130052036A1 (en) 2013-02-28

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