US20060216144A1 - First and second stage turbine airfoil shapes - Google Patents

First and second stage turbine airfoil shapes Download PDF

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Publication number
US20060216144A1
US20060216144A1 US11/090,300 US9030005A US2006216144A1 US 20060216144 A1 US20060216144 A1 US 20060216144A1 US 9030005 A US9030005 A US 9030005A US 2006216144 A1 US2006216144 A1 US 2006216144A1
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US
United States
Prior art keywords
airfoil
turbine
distances
radius
bucket
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
US11/090,300
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English (en)
Inventor
Michael Sullivan
Dale Ladoon
Ferruccio Candela
Adam Fredmonski
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
Priority to US11/090,300 priority Critical patent/US20060216144A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: FREDMONSKI, ADAM J., CANDELA, FERRUCCIO, LADOON, DALE W., SULLIVAN, MICHAEL A.
Priority to JP2006085756A priority patent/JP2006275049A/ja
Priority to KR1020060027665A priority patent/KR20060104916A/ko
Priority to CNA2006100715349A priority patent/CN1840863A/zh
Priority to EP06251688A priority patent/EP1707740A1/en
Publication of US20060216144A1 publication Critical patent/US20060216144A1/en
Priority to US11/648,906 priority patent/US7467920B2/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • 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
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F05D2250/70—Shape
    • 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
    • F05D2250/70—Shape
    • F05D2250/74—Shape given by a set or table of xyz-coordinates
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/02—Formulas of curves

Definitions

  • the present invention relates to airfoil shapes for a gas turbine and particularly relates to nozzle and bucket airfoil shapes for the first and second stages of the gas turbine.
  • nozzle and bucket airfoils for turbines, including optimized aerodynamic efficiency, aerodynamic and mechanical blade loading and the interaction between various stages of a gas turbine.
  • the airfoil shape of the nozzles provides guided turning of the hot gases for interactions along the hot gas path among the various stages of the turbine with substantial effect on the overall efficiency of the turbine. Accordingly, there is a need for airfoil shapes for each of the first and second stage nozzles and buckets for optimizing the efficiency of the gas turbine.
  • a turbine nozzle including an airfoil having an airfoil shape, the airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and R set forth in millimeters in Table I wherein R is a distance along a radius from an axis of rotation of the turbine and X and Y are distances which, when connected by smooth continuing arcs, define airfoil profile sections in planes normal to the radius and at each distance R, the profile sections at the R distances being joined smoothly with one another to form the airfoil shape.
  • a turbine bucket including an airfoil having an airfoil shape, the airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and R set forth in millimeters in Table II wherein R is a distance along a radius from an axis of rotation of the turbine and X and Y are distances which, when connected by smooth continuing arcs, define airfoil profile sections in planes normal to the radius and at each distance R, the profile sections at the R distances being joined smoothly with one another to form the airfoil shape.
  • a turbine nozzle including an airfoil having an airfoil shape, the airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and R set forth in millimeters in Table III wherein R is a distance along a radius from an axis of rotation of the turbine and X and Y are distances which, when connected by smooth continuous arcs, define airfoil profile sections in planes normal to the radius and at each distance R, the profile sections in planes normal to the radius and at the R distances being joined smoothly with one another to form the airfoil shape.
  • a turbine bucket including an airfoil having an airfoil shape, the airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and R set forth in millimeters in Table IV wherein R is a distance along a radius from an axis of rotation of the turbine and X and Y are distances which, when connected by smooth continuous arcs, define airfoil profile sections in planes normal to the radius and at each distance R, the profile sections at the R distances being joined smoothly with one another to form the airfoil shape.
  • a first stage of a turbine having a plurality of nozzles in a circumferential array thereof about a turbine axis and a plurality of buckets in a circumferential array thereof about the axis downstream of the nozzles, each the nozzle including an airfoil having an airfoil shape, the airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and R set forth in millimeters in Table I wherein R is a distance along a radius from the axis of rotation of the turbine and X and Y are distances which, when connected by smooth continuing arcs, define airfoil profile sections in planes normal to the radius and at each distance R, the profile sections at the R distances being joined smoothly with one another to form the airfoil shape, each the bucket including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal airfoil profile substantially in accordance with Cart
  • a second stage of a turbine having a plurality of nozzles in a circumferential array thereof about a turbine axis and a plurality of buckets in a circumferential array thereof about the axis downstream of the nozzles, each the nozzle each the nozzle including an airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and R set forth in millimeters in Table III wherein R is a distance along a radius from the axis of rotation of the turbine and X and y are distances which, when connected by smooth continuous arcs, define airfoil profile sections in planes normal to the radius and at each distance R, the profile sections at the R distances being joined smoothly with one another to form the airfoil shape, each the bucket including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate
  • FIG. 1 is a generalized schematic illustration of the hot gas path of a turbine having first and second stage nozzle and bucket airfoil shapes in accordance with a preferred aspect of the present invention
  • FIGS. 2 and 3 constitute plots of the first stage nozzle and bucket airfoil shapes, respectively, at the near root, near pitch and near tip sections;
  • FIGS. 4 and 5 constitute plots of the second stage nozzle and bucket airfoil shapes at the near root, near pitch and near tip sections.
  • Turbine 10 includes a rotor 12 and an outer casing 14 .
  • the first stage 11 of the gas turbine 10 includes a first stage nozzle having an array of circumferentially spaced nozzle airfoils 16 secured to casing 14 and an array of circumferentially spaced buckets 18 mounted on the rotor 12 .
  • the second stage 13 of the turbine includes an array of circumferentially spaced nozzle airfoils 20 secured to casing 14 and an array of circumferentially spaced buckets 22 mounted on the rotor 12 .
  • the turbine may include additional stages.
  • each of the nozzle and bucket airfoils have respective unique airfoil shapes for optimizing aerodynamic efficiency and aerodynamic and mechanical blade loading in the hot gas stream, generally indicated by the arrow 24 , flowing in the annular hot gas flowpath.
  • a Cartesian coordinate system of X, Y and R values given in millimeters in Tables I-IV define the profile of the airfoils 16 , 18 , 20 and 22 , respectively.
  • the coordinate values for the X, Y and R coordinates are set forth in millimeters in these tables although other units of dimensions may be used.
  • the Cartesian coordinate system has orthogonally related X, Y and R axes.
  • the R axis is a linear distance in millimeters from an axis of rotation of the turbine and along a radius to a plane normal thereto containing the X and Y values which define airfoil profile sections at each distance R from the axis of rotation.
  • the X axis extends in a direction parallel to the turbine rotor centerline, i.e. the axis of rotation, and the Y axis extends in a tangential direction
  • each profile section at each distance R given in the Tables is fixed.
  • the surface profiles at the various surface locations between the profile section planes at distances R are determined by smoothly connecting the adjacent profile sections to one another to form the airfoil shape.
  • Tables I-IV represent the airfoil profile sections at ambient non-operating or non-hot conditions.
  • the values provided in Tables I-IV are generated and shown to three decimal places for determining the profiles of the airfoils.
  • There are typical manufacturing tolerances as well as coatings which must be accounted for in the actual profile of each airfoil. Accordingly, the values for the profiles given in Tables I-IV are for nominal airfoils.
  • ⁇ typical manufacturing tolerances i.e., ⁇ values, including any coating thicknesses, are additive to or subtractive from the X, Y values given in the tables below. Accordingly, a distance of ⁇ 4.064 mm in a direction normal to any surface location along each airfoil surface defines an airfoil profile envelope for the particular airfoil shape.
  • the profile sections of the first stage nozzle airfoils 16 at each of near root, near pitch and near tip distances R are illustrated in FIG. 2 .
  • the profile sections of the first stage bucket airfoils 18 at each of the near root, near pitch and near tip distances R are illustrated in FIG. 3 .
  • the profile sections of the second stage nozzle airfoils 20 at each of the near root, near pitch and near tip distances R are illustrated in FIG. 4 .
  • the profile sections of the second stage bucket airfoils 22 at each of the near root, near pitch and near tip distances R are illustrated in FIG. 4 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Materials For Photolithography (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Developing Agents For Electrophotography (AREA)
US11/090,300 2005-03-28 2005-03-28 First and second stage turbine airfoil shapes Abandoned US20060216144A1 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
US11/090,300 US20060216144A1 (en) 2005-03-28 2005-03-28 First and second stage turbine airfoil shapes
JP2006085756A JP2006275049A (ja) 2005-03-28 2006-03-27 第１段および第２段のタービンエーロフォイル
KR1020060027665A KR20060104916A (ko) 2005-03-28 2006-03-27 터빈 노즐 및 터빈 버킷
CNA2006100715349A CN1840863A (zh) 2005-03-28 2006-03-28 第一和第二级涡轮机翼片形状
EP06251688A EP1707740A1 (en) 2005-03-28 2006-03-28 First and second stage turbine airfoil shapes
US11/648,906 US7467920B2 (en) 2005-03-28 2007-01-03 First and second stage turbine airfoil shapes

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/090,300 US20060216144A1 (en) 2005-03-28 2005-03-28 First and second stage turbine airfoil shapes

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US11/648,906 Continuation US7467920B2 (en) 2005-03-28 2007-01-03 First and second stage turbine airfoil shapes

Publications (1)

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US20060216144A1 true US20060216144A1 (en) 2006-09-28

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US11/090,300 Abandoned US20060216144A1 (en) 2005-03-28 2005-03-28 First and second stage turbine airfoil shapes
US11/648,906 Active 2025-05-06 US7467920B2 (en) 2005-03-28 2007-01-03 First and second stage turbine airfoil shapes

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US (2) US20060216144A1 (ja)
EP (1) EP1707740A1 (ja)
JP (1) JP2006275049A (ja)
KR (1) KR20060104916A (ja)
CN (1) CN1840863A (ja)

Cited By (5)

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US20070177980A1 (en) * 2006-01-27 2007-08-02 General Electric Company Stator blade airfoil profile for a compressor
US20070177981A1 (en) * 2006-01-27 2007-08-02 General Electric Company Nozzle blade airfoil profile for a turbine
US20070207035A1 (en) * 2006-03-02 2007-09-06 Pratt & Whitney Canada Corp. HP turbine blade airfoil profile
US10443393B2 (en) * 2016-07-13 2019-10-15 Safran Aircraft Engines Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the seventh stage of a turbine
US10443392B2 (en) * 2016-07-13 2019-10-15 Safran Aircraft Engines Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the second stage of a turbine

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US7527473B2 (en) * 2006-10-26 2009-05-05 General Electric Company Airfoil shape for a turbine nozzle
FR2913049A1 (fr) * 2007-02-22 2008-08-29 Snecma Sa Profil aerodynamique optimise pour une aube de turbine
US7887295B2 (en) * 2007-11-08 2011-02-15 General Electric Company Z-Notch shape for a turbine blade
FR2935016A1 (fr) * 2008-08-13 2010-02-19 Snecma Profil aerodynamique optimise pour une aube de turbine
WO2012090269A1 (ja) * 2010-12-27 2012-07-05 三菱重工業株式会社 翼体および回転機械
US8573945B2 (en) * 2009-11-13 2013-11-05 Alstom Technology Ltd. Compressor stator vane
US8602740B2 (en) * 2010-09-08 2013-12-10 United Technologies Corporation Turbine vane airfoil
US8393870B2 (en) 2010-09-08 2013-03-12 United Technologies Corporation Turbine blade airfoil
US9011101B2 (en) 2011-11-28 2015-04-21 General Electric Company Turbine bucket airfoil profile
US8814526B2 (en) 2011-11-28 2014-08-26 General Electric Company Turbine nozzle airfoil profile
US8740570B2 (en) 2011-11-28 2014-06-03 General Electric Company Turbine bucket airfoil profile
US8734116B2 (en) 2011-11-28 2014-05-27 General Electric Company Turbine bucket airfoil profile
US8827641B2 (en) 2011-11-28 2014-09-09 General Electric Company Turbine nozzle airfoil profile
CN103510999B (zh) * 2013-09-29 2015-04-22 哈尔滨汽轮机厂有限责任公司 一种适用于重型燃气轮机的涡轮第二级动叶片
CN103557034B (zh) * 2013-09-30 2015-07-15 哈尔滨汽轮机厂有限责任公司 一种应用于重型中低热值燃机的涡轮第二级导叶片
CN105822432A (zh) * 2016-04-22 2016-08-03 山东元动力科技有限公司 一种微型涡喷发动机
US10288086B2 (en) * 2016-10-04 2019-05-14 General Electric Company Airfoil shape for third stage compressor stator vane
US11066934B1 (en) * 2020-03-20 2021-07-20 General Electric Company Turbine rotor blade airfoil profile
US11519273B1 (en) * 2021-04-30 2022-12-06 General Electric Company Compressor rotor blade airfoils
US11293454B1 (en) 2021-04-30 2022-04-05 General Electric Company Compressor stator vane airfoils
US11459892B1 (en) 2021-04-30 2022-10-04 General Electric Company Compressor stator vane airfoils
US11519272B2 (en) * 2021-04-30 2022-12-06 General Electric Company Compressor rotor blade airfoils
US11480062B1 (en) 2021-04-30 2022-10-25 General Electric Company Compressor stator vane airfoils
US11414996B1 (en) 2021-04-30 2022-08-16 General Electric Company Compressor rotor blade airfoils
US11401816B1 (en) * 2021-04-30 2022-08-02 General Electric Company Compressor rotor blade airfoils
US11326620B1 (en) 2021-04-30 2022-05-10 General Electric Company Compressor stator vane airfoils
US11643932B2 (en) 2021-04-30 2023-05-09 General Electric Company Compressor rotor blade airfoils
US11441427B1 (en) 2021-04-30 2022-09-13 General Electric Company Compressor rotor blade airfoils
US11512595B1 (en) * 2022-02-04 2022-11-29 Pratt & Whitney Canada Corp. Turbine blade airfoil profile
US11867081B1 (en) * 2023-01-26 2024-01-09 Pratt & Whitney Canada Corp. Turbine blade airfoil profile

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US20070177980A1 (en) * 2006-01-27 2007-08-02 General Electric Company Stator blade airfoil profile for a compressor
US20070177981A1 (en) * 2006-01-27 2007-08-02 General Electric Company Nozzle blade airfoil profile for a turbine
US7329092B2 (en) * 2006-01-27 2008-02-12 General Electric Company Stator blade airfoil profile for a compressor
US7329093B2 (en) * 2006-01-27 2008-02-12 General Electric Company Nozzle blade airfoil profile for a turbine
US20070207035A1 (en) * 2006-03-02 2007-09-06 Pratt & Whitney Canada Corp. HP turbine blade airfoil profile
US7306436B2 (en) * 2006-03-02 2007-12-11 Pratt & Whitney Canada Corp. HP turbine blade airfoil profile
US10443393B2 (en) * 2016-07-13 2019-10-15 Safran Aircraft Engines Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the seventh stage of a turbine
US10443392B2 (en) * 2016-07-13 2019-10-15 Safran Aircraft Engines Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the second stage of a turbine

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US20080175707A1 (en) 2008-07-24
KR20060104916A (ko) 2006-10-09
EP1707740A1 (en) 2006-10-04
US7467920B2 (en) 2008-12-23
CN1840863A (zh) 2006-10-04

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