EP2410130A2 - Aubes directrices de sortie de soufflante d'un turboréacteur - Google Patents

Aubes directrices de sortie de soufflante d'un turboréacteur Download PDF

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Publication number
EP2410130A2
EP2410130A2 EP11004584A EP11004584A EP2410130A2 EP 2410130 A2 EP2410130 A2 EP 2410130A2 EP 11004584 A EP11004584 A EP 11004584A EP 11004584 A EP11004584 A EP 11004584A EP 2410130 A2 EP2410130 A2 EP 2410130A2
Authority
EP
European Patent Office
Prior art keywords
profiles
line angle
skeleton line
distribution
thickness
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Withdrawn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
EP11004584A
Other languages
German (de)
English (en)
Other versions
EP2410130A3 (fr
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/fr
Publication of EP2410130A3 publication Critical patent/EP2410130A3/fr
Withdrawn legal-status Critical Current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
    • F01D5/141—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

Definitions

  • the invention relates to fan Nachleitradschaufeln for a turbofan engine, which extend in a blade height between an inner and an outer side wall in the bypass channel and their profiling by a plurality of radially stacked - determined by a skeleton line angle distribution with associated, superimposed thickness distribution over a chord length - aerodynamic Profiles is formed.
  • the Vorleitradschaufeln In a turbofan engine, downstream of the fan in the bypass duct at the circumference evenly distributed Nachleitradschaufeln are arranged to remove the swirl from the air flow in the bypass duct.
  • the shape of the Nachleitradschaufeln is formed by a plurality of aerodynamically favorable, a horizontal section of the Nachleitradschaufel representing radially stacked profiles. All the scraper vanes circumferentially disposed in the bypass duct have the same maximum profile thickness and the same axial length, that is, a matching chord length extending between the blade leading edge and the blade trailing edge.
  • the profile of the Nachleitradschaufeln is determined by its skeleton line and a skeleton line superimposed thickness distribution.
  • the thickness distribution is defined as the course of the dimensionless thickness over the dimensionless chord length (0 to 100%), the thickness being made dimensionless with the maximum profile thickness.
  • the skeleton line is described as the course of the dimensionless skeleton line angle distribution along the chord length.
  • ⁇ i is the local angle of the skeleton line
  • BIA the entrance angle
  • BOA the exit angle
  • the invention is therefore based on the object to make the profile of fan Nachleitradschaufeln so that the pressure losses are minimized and ultimately the fuel consumption is reduced.
  • the object is achieved with a blade profile designed in accordance with the features of patent claim 1 and variable within an upper and a lower boundary.
  • the basic idea of the invention consists in a new, optimal execution of the skeleton line angle distribution in an area lying between an upper and a lower boundary and a specific skeletal angle distribution superimposed specific thickness distribution to form fan Nachleitradschaufelprofilen, compared to the known Nachleitradschaufeln by reduced pressure losses and a characterized increased working area and reduce the fuel consumption of the engine and increase its operational stability.
  • the new blade profiling comprises an upper and lower profile forming upper and lower boundaries, passing through predetermined support points along the chord at 0; 9; 14; 22; 35; 46; 60; 89 and 100% correspondingly assigned dimensionless values of an upper-skeleton line angle of 0; 0.2; 0.4; 0.6; 0.8; 0.9; 0.9; 0.95 and 1 and an upper thickness of 0; 0.85; 0.95; 1; 0.95; 0.875; 0.7; 0.2 and 0 as the upper limit of skeleton line angle and thickness distribution; and a - lower - skeleton line angle of 0; 0.05; 0.1; 0.25; 0.45; 0.6; 0.725; 0.85 and 1 and a - lower - thickness of 0; 0.4; 0.55; 0.75; 0.95; 1; 0.9; 0.35 and 0 are determined as the lower limit of the skeleton line angle and thickness distribution.
  • the new blade profiling further comprises a plurality of intermediate profiles located between the upper and the lower boundary, determined by interpol
  • the thickness distribution is set in relation to the respective skeleton line angle distribution such that the respective support point with the associated maximum value of the thickness distribution corresponds in each case to the support point (St), where the skeleton line angle distribution of the upper and lower boundaries is 0.6 each.
  • the intermediate profiles lying between the profiles of the upper and lower boundary are the result of an interpolated skeleton line angle distribution and an interpolated thickness distribution and their superimposition.
  • the interpolation takes place at the defined interpolation points between the respective value of the upper and lower limits.
  • the support point along the chord is determined with the associated value 0.6 of the skeletal line angle distribution by linear interpolation between the 0.6 values of the skeletal line angle distribution of the upper and lower limits.
  • the profiles of the upper boundary in the middle of the blade height and the bypass channel and the profiles of the lower boundary on the upper and lower side wall of the bypass channel are provided, while in the intermediate areas between the profiles of the upper and lower boundary interpolated intermediate profiles are provided.
  • the profiles of the upper and / or lower boundary and / or the interpolated intermediate profiles may be provided at any blade height.
  • Fig. 1 In the curve labeled 1 Smax , the upper limit of the skeleton line angle distribution and, in the curve labeled 2 Smin , the lower limit of the skeleton line angle distribution for the optimal design of Nachleitradschaufelprofilen that are arranged in the bypass duct of a turbofan engine.
  • the upper and lower limits of thickness distribution are indicated by 1 Dmax and 2 Dmin, respectively .
  • the skeleton line angle and the thickness of the profile which are each made dimensionless, as explained above, are each applied over the likewise dimensionless chord.
  • the support points St along the profile chord for the size of the skeleton line angle or the thickness are for all skeleton line angle and thickness distributions at 0, 9, 14, 22, 35, 46, 60, 89 and 100%.
  • the skeleton line angles ⁇ l o , ⁇ l u and profile thicknesses d o , d u assigned to the respective support points St for the upper and lower boundary of the skeleton line distribution or the thickness distribution 1 Smax , 1 Dmax ; 2 Smin , 2 Dmin and the corresponding profiles are listed in the following table: St 1 Smax upper ⁇ l o 1 Dmax limitation d o 2 Smin lower ⁇ l u 2 Dmin limit d u 0 0 0 0 0 9 0.2 0.85 0.05 0, 4 14 0.4 0.95 0.1 0.55 22 0.6 1 0.25 0.75 35 0.8 0.95 0.45 0.95 46 0.9 0.875 0, 6 1 60 0.9 0.7 0.725 0.9 89 0.95 0.2 0.85 0.35 100 1 0 1 0
  • Fig. 2 and the tabulated list of the support points St associated skeleton line angle and profile thickness reaches the thickness distribution in the upper and lower boundary curve their maximum value at the support points 22% and 46% of the chord, ie at the same support points at which the skeleton line angle of the upper and lower limit curve has the value 0.6.
  • a unique relationship between the thickness distribution and the skeleton line angle distribution is established. Between the support points St the course of the skeleton line and thickness distribution is continuous.
  • the thus defined upper and lower profiles and intermediate profiles may be formed on any blade section along the blade height.
  • the upper profile 1 max in the blade center and the lower profile 2 min lie on the inner and outer side wall of the bypass channel, while between the inner and the outer side wall and the blade center is an interpolated intermediate profile 3 int .

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  • 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)
EP11004584.6A 2010-07-19 2011-06-06 Aubes directrices de sortie de soufflante d'un turboréacteur Withdrawn EP2410130A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102010027588A DE102010027588A1 (de) 2010-07-19 2010-07-19 Fan-Nachleitradschaufel eines Turbofantriebwerks

Publications (2)

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

Family

ID=44993267

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11004584.6A Withdrawn EP2410130A3 (fr) 2010-07-19 2011-06-06 Aubes directrices de sortie de soufflante d'un turboréacteur

Country Status (3)

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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3029270A1 (fr) * 2014-11-18 2016-06-08 Honeywell International Inc. Ailettes et procédés pour réduire le flottement aérodynamique
FR3108141A1 (fr) * 2020-03-10 2021-09-17 Safran Aircraft Engines Aube de compresseur de turbomachine, compresseur et turbomachine munis de celle-ci

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014200644B4 (de) * 2014-01-16 2017-03-02 MTU Aero Engines AG Strangprofil und Verfahren zur Herstellung einer Schaufel eines Nachleitrads, Schaufel eines Nachleitrads, Nachleitrad und Turbomaschine mit solch einem Nachleitrad
JP6468414B2 (ja) * 2014-08-12 2019-02-13 株式会社Ihi 圧縮機静翼、軸流圧縮機、及びガスタービン
DE102015213451B4 (de) * 2015-07-17 2024-02-29 KSB SE & Co. KGaA Kreiselpumpen-Schaufelprofil
CN108702250B (zh) * 2015-12-22 2021-01-01 索尼移动通讯有限公司 蜂窝网络的节点、终端以及传送有效载荷消息的方法
WO2017108095A1 (fr) * 2015-12-22 2017-06-29 Sony Mobile Communications Inc. Amélioration de couverture dynamique
FR3049013B1 (fr) * 2016-03-16 2019-11-22 Safran Aircraft Engines Aube de redresseur
DE102016115868A1 (de) 2016-08-26 2018-03-01 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit hohem Ausnutzungsgrad
CN111339609B (zh) * 2018-12-19 2023-07-21 中国航发商用航空发动机有限责任公司 叶片及其厚度分布的构造方法、构造装置以及计算机可读存储介质
JP7294528B2 (ja) * 2020-04-01 2023-06-20 株式会社Ihi 静翼及び航空機用ガスタービンエンジン
CN114198324B (zh) * 2021-12-10 2022-10-25 西安交通大学 一种多元耦合离心风机集流器、离心风机及其制备方法
US12509988B2 (en) 2024-06-14 2025-12-30 Pratt & Whitney Canada Corp. Turbine engine airfoil

Family Cites Families (11)

* 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 (fr) * 1998-03-19 1999-09-22 Asea Brown Boveri AG Veine profilée pour une turbomachine axiale
DE102005042115A1 (de) * 2005-09-05 2007-03-08 Rolls-Royce Deutschland Ltd & Co Kg Schaufel einer Strömungsarbeitsmaschine mit blockweise definierter Profilskelettlinie
US7891943B2 (en) * 2005-11-29 2011-02-22 Ishikawajima-Harima Heavy Industries, Co. Ltd. Stator cascade of turbo type fluid machine
DE102005060699A1 (de) * 2005-12-19 2007-06-21 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Verstellstator
DE102006019946B4 (de) * 2006-04-28 2016-12-22 Honda Motor Co., Ltd. Flügelprofil für einen Axialströmungskompressor, das die Verluste im Bereich niedriger Reynolds-Zahlen verringern kann
DE102006055869A1 (de) 2006-11-23 2008-05-29 Rolls-Royce Deutschland Ltd & Co Kg Schaufelblattdesign für die Lauf- und Leitschaufeln einer Turbomaschine
EP2133573B1 (fr) * 2008-06-13 2011-08-17 Siemens Aktiengesellschaft Aube ou pale pour un compresseur à flux axial
US8333552B2 (en) * 2008-06-20 2012-12-18 General Electric Company Combined acoustic absorber and heat exchanging outlet guide vanes
WO2010002294A1 (fr) * 2008-07-04 2010-01-07 Volvo Aero Corporation Aube pour composant de turbine à gaz, composant de turbine à gaz et turbine à gaz
DE102009034530A1 (de) * 2009-07-23 2011-01-27 Rolls-Royce Deutschland Ltd & Co Kg Querschnittsprofil für die Stützen oder die Verkleidung von Stützen und Versorgungsleitungen eines Turbofantriebwerks

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3029270A1 (fr) * 2014-11-18 2016-06-08 Honeywell International Inc. Ailettes et procédés pour réduire le flottement aérodynamique
US9879539B2 (en) 2014-11-18 2018-01-30 Honeywell International Inc. Engine airfoils and methods for reducing airfoil flutter
FR3108141A1 (fr) * 2020-03-10 2021-09-17 Safran Aircraft Engines Aube de compresseur de turbomachine, compresseur et turbomachine munis de celle-ci
BE1028097B1 (fr) * 2020-03-10 2022-01-26 Safran Aero Boosters Aube de compresseur de turbomachine, compresseur et turbomachine munis de celle-ci

Also Published As

Publication number Publication date
EP2410130A3 (fr) 2018-04-18
DE102010027588A1 (de) 2012-01-19
US8784042B2 (en) 2014-07-22
US20120014780A1 (en) 2012-01-19

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