UA91191C2 - Blade of a guide vane or of a rotor blade of a fluid flow machine and fluid flow machine - Google Patents

Blade of a guide vane or of a rotor blade of a fluid flow machine and fluid flow machine

Info

Publication number
UA91191C2
UA91191C2 UAA200613524A UAA200613524A UA91191C2 UA 91191 C2 UA91191 C2 UA 91191C2 UA A200613524 A UAA200613524 A UA A200613524A UA A200613524 A UAA200613524 A UA A200613524A UA 91191 C2 UA91191 C2 UA 91191C2
Authority
UA
Ukraine
Prior art keywords
blade
vane
fluid flow
flow machine
blades
Prior art date
Application number
UAA200613524A
Other languages
Russian (ru)
Ukrainian (uk)
Inventor
Мартин Хегер
Original Assignee
Мту Аэро Энджинс Гмбх
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 Мту Аэро Энджинс Гмбх filed Critical Мту Аэро Энджинс Гмбх
Publication of UA91191C2 publication Critical patent/UA91191C2/en

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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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

Abstract

The invention relates to a vane of a guide vane or impeller blade of a turbo machine, particularly a gas turbine. The profile of said vane comprises at least one thickening that is advantageous for flow purposes in a radially inward final region and/or a radially outward final region of the vane. According to the invention, the thickening (11) is a cut in the area of a forward edge (12) of the vane so as to form a mirror surface (14, 17) or a basal plane. A fluid flow machine comprises at least one guide vane ring having a plurality of guide vanes and at least one rotor blade ring having a plurality of rotor blades, the guide vanes and the rotor blades each having blades that extend in the radial direction of a flow channel, and, at a radially inside end region and/or at a radially outside end region of the blade, the blades exhibiting a thickened portion of the blade profile that is beneficial from a standpoint of fluid mechanics, the thickened portion having a cut in an area of a leading edge of the blade forming a mirror surface or a basal plane.
UAA200613524A 2004-05-29 2005-04-29 Blade of a guide vane or of a rotor blade of a fluid flow machine and fluid flow machine UA91191C2 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102004026386A DE102004026386A1 (en) 2004-05-29 2004-05-29 Airfoil of a turbomachine and turbomachine

Publications (1)

Publication Number Publication Date
UA91191C2 true UA91191C2 (en) 2010-07-12

Family

ID=34969634

Family Applications (1)

Application Number Title Priority Date Filing Date
UAA200613524A UA91191C2 (en) 2004-05-29 2005-04-29 Blade of a guide vane or of a rotor blade of a fluid flow machine and fluid flow machine

Country Status (6)

Country Link
US (1) US20070177979A1 (en)
EP (1) EP1759090A1 (en)
DE (1) DE102004026386A1 (en)
RU (1) RU2383748C2 (en)
UA (1) UA91191C2 (en)
WO (1) WO2005116404A1 (en)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2899270A1 (en) * 2006-03-30 2007-10-05 Snecma Sa LOCALLY-SHAPED RECTIFIER RAM, RECTIFIER AREA, COMPRESSION STAGE, COMPRESSOR AND TURBOMACHINE COMPRISING SUCH A BLADE
FR2899269A1 (en) * 2006-03-30 2007-10-05 Snecma Sa OPTIMIZED RECTIFIER BLADE, RECTIFIER AREA, COMPRESSION FLOOR, COMPRESSOR AND TURBOMACHINE COMPRISING SUCH A BLADE
DE102008017624A1 (en) * 2008-04-04 2009-10-08 Rolls-Royce Deutschland Ltd & Co Kg Method for aerodynamically shaping the leading edge of blisk blades
DE102009036406A1 (en) 2009-08-06 2011-02-10 Mtu Aero Engines Gmbh airfoil
DE102010004854A1 (en) * 2010-01-16 2011-07-21 MTU Aero Engines GmbH, 80995 Blade for a turbomachine and turbomachine
US8944774B2 (en) * 2012-01-03 2015-02-03 General Electric Company Gas turbine nozzle with a flow fence
EP2811115A1 (en) 2013-06-05 2014-12-10 Alstom Technology Ltd Airfoil for gas turbine, blade and vane
DE102013213416B4 (en) * 2013-07-09 2017-11-09 MTU Aero Engines AG Shovel for a gas turbine machine
JP5916826B2 (en) * 2014-09-24 2016-05-11 三菱日立パワーシステムズ株式会社 Rotating machine blade and gas turbine
US9995166B2 (en) * 2014-11-21 2018-06-12 General Electric Company Turbomachine including a vane and method of assembling such turbomachine
US9890641B2 (en) 2015-01-15 2018-02-13 United Technologies Corporation Gas turbine engine truncated airfoil fillet
DE102015224283A1 (en) 2015-12-04 2017-06-08 MTU Aero Engines AG Guide vane cluster for a turbomachine
US11098591B1 (en) 2019-02-04 2021-08-24 Raytheon Technologies Corporation Turbine blade with contoured fillet

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH342326A (en) * 1955-03-31 1959-11-15 Kress Herwig Ing Dr Blade fastened in the blade carrier for axially perfused turbomachines and processes for their production
DE3514122A1 (en) * 1985-04-19 1986-10-23 MAN Gutehoffnungshütte GmbH, 4200 Oberhausen METHOD FOR PRODUCING A GUIDE BLADE FOR A TURBINE OR COMPRESSOR LEAD, AND GUIDE BLADE PRODUCED BY THE METHOD
US6511294B1 (en) * 1999-09-23 2003-01-28 General Electric Company Reduced-stress compressor blisk flowpath
US6524070B1 (en) * 2000-08-21 2003-02-25 General Electric Company Method and apparatus for reducing rotor assembly circumferential rim stress
US6851924B2 (en) * 2002-09-27 2005-02-08 Siemens Westinghouse Power Corporation Crack-resistance vane segment member

Also Published As

Publication number Publication date
US20070177979A1 (en) 2007-08-02
EP1759090A1 (en) 2007-03-07
DE102004026386A1 (en) 2005-12-22
RU2383748C2 (en) 2010-03-10
WO2005116404A1 (en) 2005-12-08
RU2006145067A (en) 2008-07-10

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