AU2001233889A1 - Aerofoil for an axial flow turbomachine - Google Patents

Aerofoil for an axial flow turbomachine

Info

Publication number
AU2001233889A1
AU2001233889A1 AU2001233889A AU3388901A AU2001233889A1 AU 2001233889 A1 AU2001233889 A1 AU 2001233889A1 AU 2001233889 A AU2001233889 A AU 2001233889A AU 3388901 A AU3388901 A AU 3388901A AU 2001233889 A1 AU2001233889 A1 AU 2001233889A1
Authority
AU
Australia
Prior art keywords
aerofoil
platform
turbine
vane
sections
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
AU2001233889A
Inventor
Brian Robert Haller
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.)
Alstom NV
Original Assignee
Alstom Power NV
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 Power NV filed Critical Alstom Power NV
Publication of AU2001233889A1 publication Critical patent/AU2001233889A1/en
Abandoned 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
    • 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
    • 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
    • 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
    • Y10S416/05—Variable camber or chord length

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Preparation Of Compounds By Using Micro-Organisms (AREA)

Abstract

A turbine stator vane for use in an axial flow gas turbine. The vane has an aerofoil, the pressure face of which is convex between platform and tip regions in a plane which extends both radially of the turbine and transversely of the general working fluid flow direction between the vanes. The trailing edge of the aerofoil is straight from platform to tip, and the spanwise convex and concave curvatures of the aerofoil pressure and suction surfaces respectively are achieved by rotational displacement of the aerofoil sections about the straight trailing edge. However, the axial width of the aerofoil is substantially constant over substantially all of the aerofoil radial height and the chord line at mid-height aerofoil sections is shorter than the chord lines in aerofoil sections at platform or tip regions. Reducing chord length at the mid-height region in this way lowers aerodynamic profile losses without unduly affecting vane performance. Also disclosed is a turbine rotor blade designed to form a stage pair with the stator vane.
AU2001233889A 2000-02-17 2001-02-19 Aerofoil for an axial flow turbomachine Abandoned AU2001233889A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
GBGB0003676.4A GB0003676D0 (en) 2000-02-17 2000-02-17 Aerofoils
GB0003676 2000-02-17
PCT/GB2001/000682 WO2001061152A1 (en) 2000-02-17 2001-02-19 Aerofoil for an axial flow turbomachine

Publications (1)

Publication Number Publication Date
AU2001233889A1 true AU2001233889A1 (en) 2001-08-27

Family

ID=9885797

Family Applications (1)

Application Number Title Priority Date Filing Date
AU2001233889A Abandoned AU2001233889A1 (en) 2000-02-17 2001-02-19 Aerofoil for an axial flow turbomachine

Country Status (9)

Country Link
US (1) US6709233B2 (en)
EP (1) EP1259711B1 (en)
JP (1) JP2003522890A (en)
AT (1) ATE301767T1 (en)
AU (1) AU2001233889A1 (en)
DE (1) DE60112551T2 (en)
ES (1) ES2243448T3 (en)
GB (2) GB0003676D0 (en)
WO (1) WO2001061152A1 (en)

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US7559747B2 (en) * 2006-11-22 2009-07-14 Pratt & Whitney Canada Corp. Turbine exhaust strut airfoil profile
US7559746B2 (en) * 2006-11-22 2009-07-14 Pratt & Whitney Canada Corp. LP turbine blade airfoil profile
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US7794201B2 (en) * 2006-12-22 2010-09-14 General Electric Company Gas turbine engines including lean stator vanes and methods of assembling the same
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US8147207B2 (en) * 2008-09-04 2012-04-03 Siemens Energy, Inc. Compressor blade having a ratio of leading edge sweep to leading edge dihedral in a range of 1:1 to 3:1 along the radially outer portion
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US8105044B2 (en) * 2010-04-23 2012-01-31 Pratt & Whitney Canada Corp. Compressor turbine blade airfoil profile
US10287987B2 (en) * 2010-07-19 2019-05-14 United Technologies Corporation Noise reducing vane
ITMI20101447A1 (en) * 2010-07-30 2012-01-30 Alstom Technology Ltd "LOW PRESSURE STEAM TURBINE AND METHOD FOR THE FUNCTIONING OF THE SAME"
US8672620B2 (en) * 2010-08-17 2014-03-18 Hamilton Sundstrand Corporation Air turbine starter turbine nozzle airfoil
US8651806B2 (en) * 2010-08-17 2014-02-18 Hamilton Sundstrand Corporation Air turbine starter inlet housing assembly airflow path
EP2476862B1 (en) * 2011-01-13 2013-11-20 Alstom Technology Ltd Vane for an axial flow turbomachine and corresponding turbomachine
US9255480B2 (en) * 2011-10-28 2016-02-09 General Electric Company Turbine of a turbomachine
US8967959B2 (en) * 2011-10-28 2015-03-03 General Electric Company Turbine of a turbomachine
US8992179B2 (en) 2011-10-28 2015-03-31 General Electric Company Turbine of a turbomachine
US9051843B2 (en) 2011-10-28 2015-06-09 General Electric Company Turbomachine blade including a squeeler pocket
US8894376B2 (en) * 2011-10-28 2014-11-25 General Electric Company Turbomachine blade with tip flare
US9429069B2 (en) * 2012-01-10 2016-08-30 Starrotor Corporation Open brayton bottoming cycle and method of using the same
US8979487B2 (en) * 2012-04-11 2015-03-17 Pratt & Whitney Canada Corp. High pressure turbine vane airfoil profile
GB201217482D0 (en) * 2012-10-01 2012-11-14 Rolls Royce Plc Aerofoil for axial-flow machine
US10495106B2 (en) * 2014-02-19 2019-12-03 United Technologies Corporation Gas turbine engine airfoil
EP3163019B1 (en) 2015-10-26 2019-03-13 MTU Aero Engines GmbH Rotor blade
GB2544735B (en) * 2015-11-23 2018-02-07 Rolls Royce Plc Vanes of a gas turbine engine
US20170342839A1 (en) * 2016-05-25 2017-11-30 General Electric Company System for a low swirl low pressure turbine
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
CN109578085B (en) * 2018-12-26 2021-06-22 中国船舶重工集团公司第七0三研究所 Method for weakening unsteady acting force of turbine movable blade through guide blade inclination
JP7029181B2 (en) * 2019-04-22 2022-03-03 株式会社アテクト Nozzle vane
PL3816397T3 (en) * 2019-10-31 2023-06-19 General Electric Company Controlled flow turbine blades
US11566530B2 (en) 2019-11-26 2023-01-31 General Electric Company Turbomachine nozzle with an airfoil having a circular trailing edge
US11629599B2 (en) 2019-11-26 2023-04-18 General Electric Company Turbomachine nozzle with an airfoil having a curvilinear trailing edge
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Also Published As

Publication number Publication date
GB0104002D0 (en) 2001-04-04
ES2243448T3 (en) 2005-12-01
JP2003522890A (en) 2003-07-29
DE60112551T2 (en) 2006-06-08
ATE301767T1 (en) 2005-08-15
GB2359341A (en) 2001-08-22
US6709233B2 (en) 2004-03-23
WO2001061152A1 (en) 2001-08-23
EP1259711A1 (en) 2002-11-27
EP1259711B1 (en) 2005-08-10
DE60112551D1 (en) 2005-09-15
GB0003676D0 (en) 2000-04-05
US20020197156A1 (en) 2002-12-26

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