US20110236223A1 - Blade for a gas turbine - Google Patents

Blade for a gas turbine Download PDF

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Publication number
US20110236223A1
US20110236223A1 US13/075,234 US201113075234A US2011236223A1 US 20110236223 A1 US20110236223 A1 US 20110236223A1 US 201113075234 A US201113075234 A US 201113075234A US 2011236223 A1 US2011236223 A1 US 2011236223A1
Authority
US
United States
Prior art keywords
platform
blade
airfoil
transition
cooling medium
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.)
Abandoned
Application number
US13/075,234
Other languages
English (en)
Inventor
Christoph Nagler
Erich Kreiselmaier
Jose McFeat Anguisola
Sergei Riazantsev
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 Technology 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 Technology AG filed Critical Alstom Technology AG
Assigned to ALSTOM TECHNOLOGY LTD reassignment ALSTOM TECHNOLOGY LTD ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: NAGLER, CHRISTOPH, ANGUISOLA, JOSE MCFEAT, KREISELMAIER, ERICH, RIAZANTSEV, SERGEI
Publication of US20110236223A1 publication Critical patent/US20110236223A1/en
Abandoned 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
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2250/24—Three-dimensional ellipsoidal
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to the field of gas turbines, and particularly relates to a blade for a gas turbine.
  • the requirements for increasing the efficiency of gas turbines leads to the thickness at the trailing edges of the blade airfoils of the blades which are fitted in the gas turbines having to be continuously reduced. This results in a geometry of the blade as is exemplarily shown in cross section in FIG. 1 .
  • the blade 10 of FIG. 1 extends in the manner of an airfoil profile transversely to its longitudinal direction between a rounded leading edge 15 and a comparatively sharply tapering trailing edge 16 .
  • the blade 10 has a (concave) pressure side 13 and a (convex) suction side 14 with corresponding walls 13 ′ and 14 ′.
  • a gaseous cooling medium or coolant is fed in the hollow inner space 17 and discharged into the environment inter alia through a cooling medium outlet which is formed at the trailing edge 16 .
  • a particularly sharply tapering, slender trailing edge 16 in this case is achieved by the cooling medium outlet 18 being arranged entirely on the pressure side 13 of the blade 10 , and by the two walls 13 ′ and 14 ′ being constructed especially thin in the region of the trailing edge 16 .
  • the transition of the blade airfoil 11 to this platform 12 in the region of the trailing edge 16 represents a typical factor which limits the service life of a gas turbine component because it is exposed to superposition of high thermal stress which is brought about by the thermo-mechanical mismatch between platform 12 and blade airfoil 11 , and to mechanical stress peaks which are brought about by loading of the blades as a result of the gas flow. Reducing the thickness of the trailing edge 16 causes an increase of the stress in this critical region so that when designing the blade measures have to be considered in order to achieve and to ensure a sufficiently long service life.
  • An aspect of the present invention is to further develop a blade for a gas turbine so that despite a low thickness at the trailing edge of the blade airfoil a satisfactory service life is achieved.
  • the present invention provides a blade for a gas turbine including an airfoil extending in a longitudinal direction and extending transversely to the longitudinal direction between a leading edge and a trailing edge.
  • the airfoil has a pressure side, a suction side, and a slot-like cooling medium outlet extending along the trailing edge.
  • the cooling medium outlet is configured to discharge cooling medium supplied from an inner space of the blade.
  • a platform extends transversely to the longitudinal direction.
  • An end of the airfoil merges into an underside of the platform and has a transition from the airfoil to the platform at the trailing edge of the airfoil that increases in thickness in a direction toward the underside of the platform.
  • the cooling medium outlet extends into the platform so as to reduce an operating temperature in a region of the transition from the blade airfoil to the platform.
  • FIG. 1 shows a simplified cross section through an gas turbine blade with a narrow trailing edge and a cooling medium outlet
  • FIG. 2 shows a sharp transition between blade airfoil and platform in a blade such as that shown in FIG. 1 ;
  • FIG. 3 shows a low-stress transition between blade airfoil and platform according to an exemplary embodiment of the invention.
  • the present invention provides a transition from the blade airfoil to the platform at the trailing edge that has a transition thickness profile in which the thickness increases above average the closer it gets to the underside of the platform, and that the cooling medium outlet is extended right into the platform for reducing the temperature in the region of the transition from the blade airfoil to the platform.
  • a transition thickness profile in which the thickness increases above average the closer it gets to the underside of the platform, and that the cooling medium outlet is extended right into the platform for reducing the temperature in the region of the transition from the blade airfoil to the platform.
  • the transition thickness profile has an essentially exponential shape which resembles an inverted, very slender, truncated pyramid or an inverted virtual pyramid. As a result of this an especially “smooth” transition between trailing edge and platform is achieved.
  • the transition from the blade airfoil to the platform has an approximately elliptical transition border profile which also reduces stresses.
  • the cooling medium outlet is formed between a pressure-side wall of the blade airfoil and a suction-side wall of the blade airfoil, and in that the pressure-side wall has a curvilinear transition edge profile in the transition from the blade airfoil to the platform in such a way that the wall thickness of the pressure-side wall in the region of the transition from the blade airfoil to the platform is approximately equal to the wall thickness in the remaining region of the blade airfoil.
  • a blade 20 for a gas turbine with a low-stress transition between blade airfoil 11 and platform 12 according to an exemplary embodiment of the invention is reproduced.
  • the blade 20 of the exemplary embodiment comprises a blade airfoil 11 which extends in a longitudinal direction and in the manner of a wing extends transversely to the longitudinal direction between a leading edge 15 and a trailing edge 16 , and has a pressure side 13 and a suction side 14 .
  • the blade airfoil 11 merges into a platform 12 which lies transversely to the longitudinal direction and projects laterally across the blade cross section.
  • a slot-like cooling medium outlet 18 which extends along the trailing edge 16 is provided at the trailing edge 16 of the blade airfoil 11 , through which a cooling medium, for example cooling air, which is fed via the (hollow) inner space 17 of the blade 20 , is discharged.
  • the trailing edge 16 with its thin walls 13 ′ and 14 ′ is very narrow in construction.
  • the transition has a transition thickness profile 21 in which the thickness D increases above average the closer it gets to the underside 12 ′ of the platform 12 .
  • the cooling medium outlet 18 is extended (extension 19 ) right into the platform 12 for reducing the local temperature in the region of the transition from the blade airfoil 11 to the platform 12 .
  • the transition thickness profile 21 has an essentially exponential shape and as a result resembles an inverted rampant pyramid. It is especially favorable in this case with regard to the stress distribution if the transition from the blade airfoil 11 to the platform 12 has an approximately elliptical transition border profile 22 . While in the case of the conventional blade according to FIG. 2 the trailing edge 16 of the blade airfoil 11 terminates inside the platform 12 and does not extend as far as the boundary of the platform 12 , in the case of the exemplary embodiment of FIG. 3 the trailing edge 16 at the transition from the blade airfoil 11 to the platform 12 is extended up to the edge 12 ′′ of the platform 12 .
  • the cooling medium outlet 18 is delimited by the pressure-side wall 13 ′ and the suction-side wall 14 ′ of the blade airfoil 11 .
  • the pressure-side wall 13 ′ in this case has a curvilinear transition edge profile 23 in the transition from the blade airfoil 11 to the platform 12 in such a way that the wall thickness of the pressure-side wall 13 ′ in the region of the transition from the blade airfoil 11 to the platform 12 is approximately equal to the wall thickness in the remaining region of the blade airfoil 11 .

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US13/075,234 2008-09-30 2011-03-30 Blade for a gas turbine Abandoned US20110236223A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH01548/08A CH699601A1 (de) 2008-09-30 2008-09-30 Schaufel für eine gasturbine.
CH01548/08 2008-09-30
PCT/EP2009/062213 WO2010037659A1 (de) 2008-09-30 2009-09-21 Schaufel für eine gasturbine

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2009/062213 Continuation WO2010037659A1 (de) 2008-09-30 2009-09-21 Schaufel für eine gasturbine

Publications (1)

Publication Number Publication Date
US20110236223A1 true US20110236223A1 (en) 2011-09-29

Family

ID=40130846

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/075,234 Abandoned US20110236223A1 (en) 2008-09-30 2011-03-30 Blade for a gas turbine

Country Status (4)

Country Link
US (1) US20110236223A1 (de)
CH (1) CH699601A1 (de)
DE (1) DE112009002628T5 (de)
WO (1) WO2010037659A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2868867A1 (de) * 2013-10-29 2015-05-06 Siemens Aktiengesellschaft Turbinenschaufel
US9045987B2 (en) 2012-06-15 2015-06-02 United Technologies Corporation Cooling for a turbine airfoil trailing edge
WO2018031032A1 (en) * 2016-08-12 2018-02-15 Siemens Aktiengesellschaft Blade for gas turbine engine

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6062817A (en) * 1998-11-06 2000-05-16 General Electric Company Apparatus and methods for cooling slot step elimination
US6190128B1 (en) * 1997-06-12 2001-02-20 Mitsubishi Heavy Industries, Ltd. Cooled moving blade for gas turbine
US6328531B1 (en) * 1998-08-05 2001-12-11 Societe Nationale d'Etude et de Construction de Moteurs d'Aviation “SNECMA” Cooled turbine blade
US20030138322A1 (en) * 2002-01-23 2003-07-24 Snecma Moteurs Moving blade for a high pressure turbine, the blade having a trailing edge of improved thermal behavior
US6851924B2 (en) * 2002-09-27 2005-02-08 Siemens Westinghouse Power Corporation Crack-resistance vane segment member
US20050249593A1 (en) * 2004-01-14 2005-11-10 Snecma Moteurs Cooling air evacuation slots of turbine blades
US7249933B2 (en) * 2005-01-10 2007-07-31 General Electric Company Funnel fillet turbine stage
US7371046B2 (en) * 2005-06-06 2008-05-13 General Electric Company Turbine airfoil with variable and compound fillet
US7581924B2 (en) * 2006-07-27 2009-09-01 Siemens Energy, Inc. Turbine vanes with airfoil-proximate cooling seam

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6190128B1 (en) * 1997-06-12 2001-02-20 Mitsubishi Heavy Industries, Ltd. Cooled moving blade for gas turbine
US6328531B1 (en) * 1998-08-05 2001-12-11 Societe Nationale d'Etude et de Construction de Moteurs d'Aviation “SNECMA” Cooled turbine blade
US6062817A (en) * 1998-11-06 2000-05-16 General Electric Company Apparatus and methods for cooling slot step elimination
US20030138322A1 (en) * 2002-01-23 2003-07-24 Snecma Moteurs Moving blade for a high pressure turbine, the blade having a trailing edge of improved thermal behavior
US6851924B2 (en) * 2002-09-27 2005-02-08 Siemens Westinghouse Power Corporation Crack-resistance vane segment member
US20050249593A1 (en) * 2004-01-14 2005-11-10 Snecma Moteurs Cooling air evacuation slots of turbine blades
US7249933B2 (en) * 2005-01-10 2007-07-31 General Electric Company Funnel fillet turbine stage
US7371046B2 (en) * 2005-06-06 2008-05-13 General Electric Company Turbine airfoil with variable and compound fillet
US7581924B2 (en) * 2006-07-27 2009-09-01 Siemens Energy, Inc. Turbine vanes with airfoil-proximate cooling seam

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9045987B2 (en) 2012-06-15 2015-06-02 United Technologies Corporation Cooling for a turbine airfoil trailing edge
EP2868867A1 (de) * 2013-10-29 2015-05-06 Siemens Aktiengesellschaft Turbinenschaufel
WO2015063021A1 (de) * 2013-10-29 2015-05-07 Siemens Aktiengesellschaft Turbinenschaufel mit einer mittigen ausblasung an der hinterkante
CN105683505A (zh) * 2013-10-29 2016-06-15 西门子股份公司 在后缘具有中央吹出部的涡轮叶片或轮叶
US10487669B2 (en) 2013-10-29 2019-11-26 Siemens Aktiengesellschaft Turbine blade with a central blowout at the trailing edge
WO2018031032A1 (en) * 2016-08-12 2018-02-15 Siemens Aktiengesellschaft Blade for gas turbine engine

Also Published As

Publication number Publication date
DE112009002628T5 (de) 2012-01-26
WO2010037659A1 (de) 2010-04-08
CH699601A1 (de) 2010-03-31

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AS Assignment

Owner name: ALSTOM TECHNOLOGY LTD, SWITZERLAND

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:NAGLER, CHRISTOPH;KREISELMAIER, ERICH;ANGUISOLA, JOSE MCFEAT;AND OTHERS;SIGNING DATES FROM 20110601 TO 20110606;REEL/FRAME:026423/0875

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION