EP1760321A2 - Pale d'une turbomachine - Google Patents

Pale d'une turbomachine Download PDF

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Publication number
EP1760321A2
EP1760321A2 EP06016439A EP06016439A EP1760321A2 EP 1760321 A2 EP1760321 A2 EP 1760321A2 EP 06016439 A EP06016439 A EP 06016439A EP 06016439 A EP06016439 A EP 06016439A EP 1760321 A2 EP1760321 A2 EP 1760321A2
Authority
EP
European Patent Office
Prior art keywords
blade
zone
skeleton line
hsv
line
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.)
Ceased
Application number
EP06016439A
Other languages
German (de)
English (en)
Other versions
EP1760321A3 (fr
Inventor
Volker Gümmer
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 EP1760321A2 publication Critical patent/EP1760321A2/fr
Publication of EP1760321A3 publication Critical patent/EP1760321A3/fr
Ceased legal-status Critical Current

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Classifications

    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—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
    • 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
    • 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
    • F05D2250/71—Shape curved
    • 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 blades of fluid flow machines such as fans, compressors, pumps and fans in the axial, semi-axial or even radial design.
  • the working medium can be gaseous or liquid.
  • the invention relates to at least one blade of a fluid flow machine.
  • the blading in question is within a housing which limits the flow of a rotor and, if present, a stator with a fluid to the outside.
  • a rotor comprises a plurality of rotor blades attached to a rotating shaft and emits energy to the working fluid
  • a stator consists of a plurality of fixed, mostly in the housing mounted stator blades.
  • FIG. 1 shows a schematic representation of two blade configurations according to the prior art in the meridian plane given by the radial direction r and the axial direction x.
  • a standard blade is shown without variation of the skeleton line type.
  • the blade consists of only one block (Z0) in which the type of skeleton line is given uniformly according to fixed rules.
  • This category includes the so-called CDA (controlled diffusion aerofoils) US4431376 , From an aerodynamic point of view, the CDA aims for a moderate profile frontload.
  • the invention relates to a rotor with a fixed connection to the hub and a free blade end with a radial gap on the housing.
  • the invention relates to a stator which has a fixed connection to the edge on the housing side and has a free blade end with a radial gap on the hub side.
  • the invention relates to a rotor or stator, the hub side as well as the housing side has a firm connection to the edge (shroud configuration).
  • the present invention has for its object to provide a rotor or stator blade of the aforementioned type which, while avoiding the disadvantages of the prior art, effectively influencing the edge flow by targeted and problematic, block-wise definition of the profile skeleton lines along the blade height.
  • Fig. 2 gives a precise definition of the meridional flow lines and the streamline profile sections.
  • the middle meridional flow line is formed by the geometric center of the ring channel. If one establishes a normal at each location of the middle streamline, one obtains the course of the ring channel width W along the flow path and, on the other hand, a number of normals with whose help further meridional flow lines result with the same relative subdivision in the direction of the channel height.
  • the intersection of a meridional streamline with a blade results in a streamline profile intersection.
  • FIG. 3a shows the rotor blade according to the invention with a radial gap on the housing "RmR" in the meridian plane determined by the axial coordinate x and the radial coordinate r.
  • the blade edge zones Z1 and Z2, the transition zones T1 and T2 and the blade central zone Z0 are particularly marked and limited in each case by meridional flow lines as defined in FIG.
  • Each of the five bucket zones is assigned a subset (WZ1, WT1, WZ0, WT2, WZ2) which is measured in the direction of the channel width W.
  • FIGS. 3 b and 3 c show the stator blade according to the invention with a radial gap at the hub "SmR” and the blade according to the invention (rotor or stator) without a radial gap "RSoR”.
  • the respective skeletal line type is determined in relative representation with the help of the related inclination angle ⁇ * and the related run length S *, see Fig.6a.
  • the image shows a streamline profile cut of the blade on a meridian flow surface (um-plane).
  • FIG. 6b shows the definition of the skeleton line type "PF" in the above-derived relative representation.
  • Skeleton lines according to the invention are located below a borderline. Skeleton lines in the exclusion area above and on the boundary line are not according to the invention.
  • a skeleton line distribution which can be provided according to the invention for the blade block at a fixed end is shown.
  • FIG. 6c shows in the relative representation the definition of the skeleton line type "PM".
  • Skeleton lines according to the invention are located above a boundary line. Skeleton lines in the exclusion area below and on the boundary line are not according to the invention.
  • a skeleton line distribution which can be provided according to the invention for the block in the center of the blade is shown.
  • Fig. 6d shows in the relative representation the definition of the skeleton line type "PR".
  • Skeleton lines according to the invention are located below a borderline. Skeleton lines in the exclusion area above and on the boundary line are not according to the invention.
  • a skeleton line distribution which can be provided according to the invention for the blade block at the radial gap is shown.
  • an edge flow control is achieved, which can increase the efficiency of each stage by about 1% with the same stability.
  • a reduction in the number of blades of up to 20% is possible.
  • the inventive concept is applicable to different types of turbomachines and, depending on the degree of utilization of the concept, leads to reductions in costs and weight for the turbomachine of 2% to 10%.
EP06016439A 2005-09-05 2006-08-07 Pale d'une turbomachine Ceased EP1760321A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102005042115A DE102005042115A1 (de) 2005-09-05 2005-09-05 Schaufel einer Strömungsarbeitsmaschine mit blockweise definierter Profilskelettlinie

Publications (2)

Publication Number Publication Date
EP1760321A2 true EP1760321A2 (fr) 2007-03-07
EP1760321A3 EP1760321A3 (fr) 2011-07-27

Family

ID=37467618

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06016439A Ceased EP1760321A3 (fr) 2005-09-05 2006-08-07 Pale d'une turbomachine

Country Status (3)

Country Link
US (1) US7419353B2 (fr)
EP (1) EP1760321A3 (fr)
DE (1) DE102005042115A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10208765B2 (en) 2015-01-28 2019-02-19 MTU Aero Engines AG Gas turbine axial compressor
EP3730801A4 (fr) * 2017-12-20 2021-05-05 Ihi Corporation Ventilateur et aube de stator de compresseur

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006055869A1 (de) * 2006-11-23 2008-05-29 Rolls-Royce Deutschland Ltd & Co Kg Schaufelblattdesign für die Lauf- und Leitschaufeln einer Turbomaschine
DE102009033593A1 (de) * 2009-07-17 2011-01-20 Rolls-Royce Deutschland Ltd & Co Kg Triebwerkschaufel mit überhöhter Vorderkantenbelastung
DE102010009615B4 (de) 2010-02-27 2016-11-17 MTU Aero Engines AG Schaufelblatt mit gefädelten Profilschnitten
DE102010027588A1 (de) * 2010-07-19 2012-01-19 Rolls-Royce Deutschland Ltd & Co Kg Fan-Nachleitradschaufel eines Turbofantriebwerks
JP5608062B2 (ja) * 2010-12-10 2014-10-15 株式会社日立製作所 遠心型ターボ機械
US9309769B2 (en) 2010-12-28 2016-04-12 Rolls-Royce Corporation Gas turbine engine airfoil shaped component
FR2991373B1 (fr) * 2012-05-31 2014-06-20 Snecma Aube de soufflante pour turboreacteur d'avion a profil cambre en sections de pied
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
US10577973B2 (en) 2016-02-18 2020-03-03 General Electric Company Service tube for a turbine engine
DE102016115868A1 (de) * 2016-08-26 2018-03-01 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit hohem Ausnutzungsgrad
GB201719538D0 (en) 2017-11-24 2018-01-10 Rolls Royce Plc Gas turbine engine
GB201719539D0 (en) 2017-11-24 2018-01-10 Rolls Royce Plc Gas Turbine Engine
IT202000005146A1 (it) * 2020-03-11 2021-09-11 Ge Avio Srl Motore a turbina con profilo aerodinamico avente alta accelerazione e bassa curva di paletta
US11286779B2 (en) * 2020-06-03 2022-03-29 Honeywell International Inc. Characteristic distribution for rotor blade of booster rotor

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4431376A (en) 1980-10-27 1984-02-14 United Technologies Corporation Airfoil shape for arrays of airfoils
EP0661413A1 (fr) 1993-12-23 1995-07-05 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Grill d'aubes avec bord d'attaque sous la forme de flèche
EP1106835A2 (fr) 1999-12-06 2001-06-13 General Electric Company Aube de compresseur
EP1106836A2 (fr) 1999-12-06 2001-06-13 General Electric Company Aube de compresseur à double courbure

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2663493A (en) * 1949-04-26 1953-12-22 A V Roe Canada Ltd Blading for compressors, turbines, and the like
GB719061A (en) * 1950-06-21 1954-11-24 United Aircraft Corp Blade arrangement for improving the performance of a gas turbine plant
US2660401A (en) * 1951-08-07 1953-11-24 Gen Electric Turbine bucket
JP3082378B2 (ja) * 1991-12-20 2000-08-28 株式会社デンソー 送風ファン
JP3816150B2 (ja) * 1995-07-18 2006-08-30 株式会社荏原製作所 遠心流体機械
JPH10103002A (ja) * 1996-09-30 1998-04-21 Toshiba Corp 軸流流体機械用翼
US6244817B1 (en) * 1996-12-05 2001-06-12 Mcdonnell Douglas Corporation Method and apparatus for a fan noise controller
EP0945625B1 (fr) 1998-03-23 2004-03-03 SPAL S.r.l. Ventilateur à courant axial
ES2212251T3 (es) * 1998-03-23 2004-07-16 Spal S.R.L. Ventilador de flujo axial.
FR2828709B1 (fr) * 2001-08-17 2003-11-07 Snecma Moteurs Aube de redresseur
FR2851798B1 (fr) * 2003-02-27 2005-04-29 Snecma Moteurs Aube en fleche de turboreacteur

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4431376A (en) 1980-10-27 1984-02-14 United Technologies Corporation Airfoil shape for arrays of airfoils
EP0661413A1 (fr) 1993-12-23 1995-07-05 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Grill d'aubes avec bord d'attaque sous la forme de flèche
EP1106835A2 (fr) 1999-12-06 2001-06-13 General Electric Company Aube de compresseur
EP1106836A2 (fr) 1999-12-06 2001-06-13 General Electric Company Aube de compresseur à double courbure

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
R. F. BEHLKE, JOURNAL OF TURBOMACHINERY, vol. 8, July 1986 (1986-07-01)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10208765B2 (en) 2015-01-28 2019-02-19 MTU Aero Engines AG Gas turbine axial compressor
EP3730801A4 (fr) * 2017-12-20 2021-05-05 Ihi Corporation Ventilateur et aube de stator de compresseur
US11203945B2 (en) 2017-12-20 2021-12-21 Ihi Corporation Stator vane of fan or compressor

Also Published As

Publication number Publication date
DE102005042115A1 (de) 2007-03-08
US7419353B2 (en) 2008-09-02
EP1760321A3 (fr) 2011-07-27
US20070053779A1 (en) 2007-03-08

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