EP2410130A3 - Fan outlet guide vanes of a turbofan engine - Google Patents

Fan outlet guide vanes of a turbofan engine Download PDF

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Publication number
EP2410130A3
EP2410130A3 EP11004584.6A EP11004584A EP2410130A3 EP 2410130 A3 EP2410130 A3 EP 2410130A3 EP 11004584 A EP11004584 A EP 11004584A EP 2410130 A3 EP2410130 A3 EP 2410130A3
Authority
EP
European Patent Office
Prior art keywords
guide vanes
turbofan engine
outlet guide
fan outlet
line angle
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Withdrawn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
EP11004584.6A
Other languages
German (de)
French (fr)
Other versions
EP2410130A2 (en
Inventor
Carsten Dr. Clemen
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2410130A2 publication Critical patent/EP2410130A2/en
Publication of EP2410130A3 publication Critical patent/EP2410130A3/en
Withdrawn legal-status Critical Current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
    • 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
    • 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
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • 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
    • F05D2240/301—Cross-sectional characteristics
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Fan-Nachleitradschaufelprofile sind in einer neuen, optimalen Ausführung der Skelettlinienwinkelverteilung in einem zwischen einer oberen und einer unteren Begrenzung liegenden Bereich sowie einer der jeweiligen Skelettlinienwinkelverteilung überlagerten spezifischen Dickenverteilung ausgebildet und zeichnen sich gegenüber den bekannten Nachleitradschaufeln durch verringerte Druckverluste und einen erhöhten Arbeitsbereich aus, so dass der Treibstoffverbrauch des Triebwerks gesenkt sowie dessen Betriebsstabilität erhöht werden kann.

Figure imgaf001
Fan Nachleitradschaufelprofile are formed in a new, optimal execution of the skeleton line angle distribution in a lying between an upper and a lower boundary area and a respective skeleton line angle distribution superimposed specific thickness distribution and are distinguished from the known Nachleitradschaufeln by reduced pressure losses and an increased working range, so that the fuel consumption of the engine can be lowered and its operational stability can be increased.
Figure imgaf001
EP11004584.6A 2010-07-19 2011-06-06 Fan outlet guide vanes of a turbofan engine Withdrawn EP2410130A3 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102010027588A DE102010027588A1 (en) 2010-07-19 2010-07-19 Fan-Nachleitradschaufel a turbofan engine

Publications (2)

Publication Number Publication Date
EP2410130A2 EP2410130A2 (en) 2012-01-25
EP2410130A3 true EP2410130A3 (en) 2018-04-18

Family

ID=44993267

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11004584.6A Withdrawn EP2410130A3 (en) 2010-07-19 2011-06-06 Fan outlet guide vanes of a turbofan engine

Country Status (3)

Country Link
US (1) US8784042B2 (en)
EP (1) EP2410130A3 (en)
DE (1) DE102010027588A1 (en)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014200644B4 (en) * 2014-01-16 2017-03-02 MTU Aero Engines AG Extruded profile and method for producing a blade of a Nachleitrads, blade of a Nachleitrads, Nachleitrad and turbomachinery with such a Nachleitrad
JP6468414B2 (en) * 2014-08-12 2019-02-13 株式会社Ihi Compressor vane, axial compressor, and gas turbine
US9879539B2 (en) * 2014-11-18 2018-01-30 Honeywell International Inc. Engine airfoils and methods for reducing airfoil flutter
DE102015213451B4 (en) * 2015-07-17 2024-02-29 KSB SE & Co. KGaA Centrifugal pump blade profile
CN108702249B (en) * 2015-12-22 2021-02-26 索尼移动通讯有限公司 Node, terminal and method for dynamic coverage enhancement
US11005616B2 (en) * 2015-12-22 2021-05-11 Sony Corporation Dynamic coverage enhancement
FR3049013B1 (en) * 2016-03-16 2019-11-22 Safran Aircraft Engines DAWN OF RECTIFIER
DE102016115868A1 (en) 2016-08-26 2018-03-01 Rolls-Royce Deutschland Ltd & Co Kg High-efficiency fluid flow machine
CN111339609B (en) * 2018-12-19 2023-07-21 中国航发商用航空发动机有限责任公司 Blade, method and device for constructing thickness distribution of blade, and computer-readable storage medium
FR3108141B1 (en) * 2020-03-10 2022-08-12 Safran Aircraft Engines Turbomachine compressor blade, compressor and turbomachine fitted therewith
EP4130436A4 (en) * 2020-04-01 2024-04-24 IHI Corporation Static blade and aircraft gas turbine engine
CN114198324B (en) * 2021-12-10 2022-10-25 西安交通大学 Multi-element coupling centrifugal fan collector, centrifugal fan and preparation method of centrifugal fan collector

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006055869A1 (en) * 2006-11-23 2008-05-29 Rolls-Royce Deutschland Ltd & Co Kg Rotor and guide blades designing method for turbo-machine i.e. gas turbine engine, involves running skeleton curve in profile section in sectional line angle distribution area lying between upper and lower limit curves
US20080181780A1 (en) * 2006-04-28 2008-07-31 Toyotaka Sonoda Airfoil for axial-flow compressor capable of lowering loss in low Reynolds number region
EP2133573A1 (en) * 2008-06-13 2009-12-16 Siemens Aktiengesellschaft Vane or blade for an axial flow compressor

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5259187A (en) 1993-02-05 1993-11-09 General Electric Company Method of operating an aircraft bypass turbofan engine having variable fan outlet guide vanes
EP0943784A1 (en) * 1998-03-19 1999-09-22 Asea Brown Boveri AG Contoured channel for an axial turbomachine
DE102005042115A1 (en) * 2005-09-05 2007-03-08 Rolls-Royce Deutschland Ltd & Co Kg Blade of a fluid flow machine with block-defined profile skeleton line
EP1956247A4 (en) * 2005-11-29 2014-05-14 Ihi Corp Cascade of stator vane of turbo fluid machine
DE102005060699A1 (en) * 2005-12-19 2007-06-21 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with adjustable stator
US8333552B2 (en) * 2008-06-20 2012-12-18 General Electric Company Combined acoustic absorber and heat exchanging outlet guide vanes
WO2010002294A1 (en) * 2008-07-04 2010-01-07 Volvo Aero Corporation A vane for a gas turbine component, a gas turbine component and a gas turbine engine
DE102009034530A1 (en) 2009-07-23 2011-01-27 Rolls-Royce Deutschland Ltd & Co Kg Cross-sectional profile for the columns or the lining of columns and supply lines of a turbofan engine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080181780A1 (en) * 2006-04-28 2008-07-31 Toyotaka Sonoda Airfoil for axial-flow compressor capable of lowering loss in low Reynolds number region
DE102006055869A1 (en) * 2006-11-23 2008-05-29 Rolls-Royce Deutschland Ltd & Co Kg Rotor and guide blades designing method for turbo-machine i.e. gas turbine engine, involves running skeleton curve in profile section in sectional line angle distribution area lying between upper and lower limit curves
EP2133573A1 (en) * 2008-06-13 2009-12-16 Siemens Aktiengesellschaft Vane or blade for an axial flow compressor

Also Published As

Publication number Publication date
US20120014780A1 (en) 2012-01-19
DE102010027588A1 (en) 2012-01-19
EP2410130A2 (en) 2012-01-25
US8784042B2 (en) 2014-07-22

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