EP2620593A1 - Turbinenschaufel und zugehöriges Kühlverfahren - Google Patents

Turbinenschaufel und zugehöriges Kühlverfahren Download PDF

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Publication number
EP2620593A1
EP2620593A1 EP13152580.0A EP13152580A EP2620593A1 EP 2620593 A1 EP2620593 A1 EP 2620593A1 EP 13152580 A EP13152580 A EP 13152580A EP 2620593 A1 EP2620593 A1 EP 2620593A1
Authority
EP
European Patent Office
Prior art keywords
film holes
film
turbine airfoil
cooling
helical
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Withdrawn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
EP13152580.0A
Other languages
English (en)
French (fr)
Inventor
Adebukola O. Benson
Xiuzhang James Zhang
Gary Michael Itzel
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 EP2620593A1 publication Critical patent/EP2620593A1/de
Withdrawn legal-status Critical Current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
    • 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
    • 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
    • F05D2240/303—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 leading 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical
    • 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
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • This application relates generally to gas turbine engines and, more particularly, to methods and apparatus for film cooling airfoils used within gas turbine engines.
  • Gas turbine engines typically include a compressor, a combustor, and a turbine. Airflow entering the compressor is compressed and directed to the combustor where it is mixed with fuel and ignited, producing hot combustion gases used to drive the turbine. Blades and vanes used in the turbine section of a gas turbine engine each have an airfoil section that extends radially across an engine flowpath. During engine operation, the turbine blades and vanes are exposed to elevated temperatures that can lead to mechanical failure and corrosion. Therefore, it is common practice to make the blades and vanes from a temperature tolerant alloy and to apply corrosion resistant and thermally insulating coatings to the airfoil and other flowpath exposed surfaces. It is also widespread practice to cool the airfoils by flowing a coolant through the interior of the airfoils.
  • a turbine vane or rotor blade typically includes a hollow airfoil, the outside of which is exposed to the hot combustion gases, and the inside of which is supplied with cooling fluid, which is typically compressed air.
  • the airfoil includes leading and trailing edges, a pressure side, and a suction side.
  • the pressure and suction sides connect at the airfoil leading and trailing edges, and span radially between an airfoil root and an airfoil tip.
  • Film cooling holes extend between an internal cooling circuit defined within the airfoil and an outer surface of the airfoil. The film cooling holes route cooling fluid from the internal cooling circuit to the outside of the airfoil for film cooling the airfoil.
  • Helical ribs in cooling holes have been used to generate a secondary flow pair of longitudinal vortices in the same direction as the turn of the rib. It may be desirable to utilize this known behavior in film holes to improve film cooling, increase coverage for film cooling and augment cooling efficiency.
  • a turbine airfoil in a first aspect, includes a blade with a pressure sidewall and a suction sidewall joined together at chordally opposite leading and trailing edges, and at least one cooling hole disposed between the pressure sidewall and the suction sidewall adjacent the leading edge.
  • a plurality of curved film holes extend between the at least one cooling hole and an exterior of the blade.
  • a turbine airfoil in another aspect, includes a blade having a leading and trailing edges and an internal cooling circuit, and a plurality of film holes extending between the internal cooling circuit and an exterior of the blade.
  • the plurality of film holes are shaped to generate a swirling flow exiting the film holes adjacent the leading edge to thereby enhance local convection and provide an insulating barrier to gaspath flow.
  • the invention resides in a method of film cooling a turbine airfoil includes the steps of delivering cooling air to the internal cooling circuit, and flowing the cooling air from the internal cooling circuit through a plurality of film holes extending between the internal cooling circuit and an exterior of the blade.
  • the flowing step comprises swirling the cooling air in the film holes and thereby providing an insulating barrier to gaspath flow.
  • Film-cooling holes or film holes are widely used in modem gas turbines to cool the turbine airfoils that are exposed to hot combustion gases during operation of the turbine.
  • the film-cooling holes provide cooling of the airfoil in several ways. Firstly, they provide film-cooling of the airfoil surface. Film-cooling is the cooling of a body or surface by maintaining a thin fluid layer over the affected area of a fluid that has a lower temperature than the operating environment. The fluid film insulates the film-cooled surface from the external operating environment, thereby reducing convective heat transfer from the external operating environment into the airfoil. Further, the film of the cooling fluid also removes heat from the airfoil surface.
  • film-cooling also provides convective heat transfer from and cooling of the airfoil sidewall surrounding the film-cooling hole as the cooling air flows through it along the length of the hole.
  • the film-cooling holes remove heat by providing an exhaust path for the cooling air that has been heated as it in turn cools the airfoil by passage through the airfoil cooling circuit.
  • FIG. 1 shows a blade section 10 of a turbine airfoil.
  • the blade includes a pressure sidewall 12 and a suction sidewall 14 joined together at chordally opposite leading 16 and trailing 18 edges.
  • a cooling circuit is defined by a plurality of cooling passages or holes 20 that are disposed between the pressure sidewall 12 and the suction sidewall 14. At least one cooling hole 21 is positioned adjacent the leading edge 16.
  • Film holes or film cooling holes are known that extend from one or more of the cooling holes 20 to an exterior of the blade.
  • the film cooling holes are typically straight and direct cooling air from the cooling holes 20 to the blade exterior.
  • the airfoil includes a plurality of curved film holes 22 that extend between the cooling hole 21 and the exterior of the blade 10. That is, a passage between the cooling hole 21 and the exterior of the blade 10 comprises a curved or twisted groove or the like such that air flowing through and exiting the film holes 22 is turning.
  • An exemplary shape for the film holes may be helical, although other shapes may be contemplated, and the invention is not necessarily meant to be limited to the arrangement shown in the drawings.
  • the film flow coming out of the holes no longer has a direct path, but rather exits in a swirling pattern, resulting in enhanced local convection with the holes as well as providing an insulating barrier to the gas path flow.
  • the helical film holes 22 are oriented in both clockwise and counter-clockwise directions. Adjacent ones of the plurality of helical film holes 22 may thus be oriented in opposite directions. As a consequence of such structure, the exiting flow swirls in opposite vortices, further enhancing the advantageous effects of the design.
  • a first group 24 of the helical film holes 22 may be oriented in one direction, while a second group 26 is oriented in an opposite direction. As shown, the first groups 24 and second groups 26 may alternate along a length of the blade 10.
  • each of the first and second groups 24, 26 comprises three helical film holes 22.
  • At least one of the helical film holes may comprise a double helical film hole 220. That is, the film hole 220 may comprise two (or more) interlaced helical grooves or passageways through which cooling air is passed.
  • the cooling circuit with helical film holes serves to improve film cooling, increase coverage for film cooling and generally augment cooling efficiency.
  • the swirling flow provides for enhanced local convection within the holes and also provides an insulating barrier to the gaspath flow.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13152580.0A 2012-01-27 2013-01-24 Turbinenschaufel und zugehöriges Kühlverfahren Withdrawn EP2620593A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/359,691 US20130195650A1 (en) 2012-01-27 2012-01-27 Gas Turbine Pattern Swirl Film Cooling

Publications (1)

Publication Number Publication Date
EP2620593A1 true EP2620593A1 (de) 2013-07-31

Family

ID=47631309

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13152580.0A Withdrawn EP2620593A1 (de) 2012-01-27 2013-01-24 Turbinenschaufel und zugehöriges Kühlverfahren

Country Status (5)

Country Link
US (1) US20130195650A1 (de)
EP (1) EP2620593A1 (de)
JP (1) JP2013155733A (de)
CN (1) CN103225517A (de)
RU (1) RU2013103432A (de)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10378362B2 (en) * 2013-03-15 2019-08-13 United Technologies Corporation Gas turbine engine component cooling channels
US20150260048A1 (en) * 2014-03-11 2015-09-17 United Technologies Corporation Component with cooling hole having helical groove
US20170101870A1 (en) * 2015-10-12 2017-04-13 United Technologies Corporation Cooling holes of turbine
FR3052183B1 (fr) * 2016-06-02 2020-03-06 Safran Aircraft Engines Aube de turbine comprenant une portion d'admission d'air de refroidissement incluant un element helicoidal pour faire tourbillonner l'air de refroidissement
US20190003316A1 (en) * 2017-06-29 2019-01-03 United Technologies Corporation Helical skin cooling passages for turbine airfoils
US10787932B2 (en) * 2018-07-13 2020-09-29 Honeywell International Inc. Turbine blade with dust tolerant cooling system
JP7224928B2 (ja) * 2019-01-17 2023-02-20 三菱重工業株式会社 タービン動翼及びガスタービン
CN111140287B (zh) * 2020-01-06 2021-06-04 大连理工大学 一种采用多边形扰流柱的层板冷却结构
CN111075510B (zh) * 2020-01-06 2021-08-20 大连理工大学 涡轮叶片蜂巢螺旋腔冷却结构
CN112983561B (zh) * 2021-05-11 2021-08-03 中国航发四川燃气涡轮研究院 梅花型气膜孔和形成方法、涡轮叶片和形成方法、燃气机
CN114876582B (zh) * 2022-06-28 2023-05-16 西北工业大学 一种涡轮叶片及航空发动机

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0641917A1 (de) * 1993-09-08 1995-03-08 United Technologies Corporation Kühlung der Vorderkante einer Schaufel
EP0971095A2 (de) * 1998-07-06 2000-01-12 United Technologies Corporation Kühlbare Schaufel für Gasturbinen
EP1013877A2 (de) * 1998-12-21 2000-06-28 United Technologies Corporation Hole Gasturbinenschaufel
EP1759788A2 (de) * 2005-09-01 2007-03-07 United Technologies Corporation Feingiessen von gekühlten Turbinenschaufeln
EP1790821A1 (de) * 2005-11-23 2007-05-30 United Technologies Corporation Refraktärmetallkernkühltechnologie für gebogene Anströmkantennuten
EP1847684A1 (de) * 2006-04-21 2007-10-24 Siemens Aktiengesellschaft Turbinenschaufel
US20100119377A1 (en) * 2008-11-12 2010-05-13 Rolls-Royce Plc Cooling arrangement
US7785071B1 (en) * 2007-05-31 2010-08-31 Florida Turbine Technologies, Inc. Turbine airfoil with spiral trailing edge cooling passages
US7789626B1 (en) * 2007-05-31 2010-09-07 Florida Turbine Technologies, Inc. Turbine blade with showerhead film cooling holes

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090304494A1 (en) * 2008-06-06 2009-12-10 United Technologies Corporation Counter-vortex paired film cooling hole design
US8201621B2 (en) * 2008-12-08 2012-06-19 General Electric Company Heat exchanging hollow passages with helicoidal grooves

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0641917A1 (de) * 1993-09-08 1995-03-08 United Technologies Corporation Kühlung der Vorderkante einer Schaufel
EP0971095A2 (de) * 1998-07-06 2000-01-12 United Technologies Corporation Kühlbare Schaufel für Gasturbinen
EP1013877A2 (de) * 1998-12-21 2000-06-28 United Technologies Corporation Hole Gasturbinenschaufel
EP1759788A2 (de) * 2005-09-01 2007-03-07 United Technologies Corporation Feingiessen von gekühlten Turbinenschaufeln
EP1790821A1 (de) * 2005-11-23 2007-05-30 United Technologies Corporation Refraktärmetallkernkühltechnologie für gebogene Anströmkantennuten
EP1847684A1 (de) * 2006-04-21 2007-10-24 Siemens Aktiengesellschaft Turbinenschaufel
US7785071B1 (en) * 2007-05-31 2010-08-31 Florida Turbine Technologies, Inc. Turbine airfoil with spiral trailing edge cooling passages
US7789626B1 (en) * 2007-05-31 2010-09-07 Florida Turbine Technologies, Inc. Turbine blade with showerhead film cooling holes
US20100119377A1 (en) * 2008-11-12 2010-05-13 Rolls-Royce Plc Cooling arrangement

Also Published As

Publication number Publication date
CN103225517A (zh) 2013-07-31
JP2013155733A (ja) 2013-08-15
US20130195650A1 (en) 2013-08-01
RU2013103432A (ru) 2014-07-27

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