EP2539544A2 - Corps d'aube présentant des segments de profil successifs - Google Patents

Corps d'aube présentant des segments de profil successifs

Info

Publication number
EP2539544A2
EP2539544A2 EP11711017A EP11711017A EP2539544A2 EP 2539544 A2 EP2539544 A2 EP 2539544A2 EP 11711017 A EP11711017 A EP 11711017A EP 11711017 A EP11711017 A EP 11711017A EP 2539544 A2 EP2539544 A2 EP 2539544A2
Authority
EP
European Patent Office
Prior art keywords
profile section
center point
profile
point component
section
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Withdrawn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
EP11711017A
Other languages
German (de)
English (en)
Inventor
Sergio Elorza Gomez
Peter EIBELSHÄUSER
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP2539544A2 publication Critical patent/EP2539544A2/fr
Withdrawn legal-status Critical Current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
    • 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
    • F05D2200/00—Mathematical features
    • F05D2200/20—Special functions
    • F05D2200/26—Special functions trigonometric
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49337—Composite blade

Definitions

  • the invention relates to an airfoil for a blade of a turbomachine with threaded profile sections, in particular an airfoil of a compressor blade, and a method for threading profile sections of such a blade.
  • Object of the present invention is therefore to provide an improved airfoil for a
  • Advantageous developments are the subject of the dependent claims.
  • profile sections of an airfoil are threaded in such a way that a first center point component of a second profile section is selected as a function of at least one midpoint component of a first profile section.
  • the midpoint position of a profile section can in particular be the position i * c of its
  • Center point components XCG in the axial, TCG in radial direction and ®CG in the circumferential direction wherein in particular reference is made to a usual coordinate system whose axial coordinate with a longitudinal axis of the flow grid or the turbomachine is aligned.
  • At least one of these components which for the sake of greater compactness is referred to as the first center point component, is then formed for a second profile section as a function of one or more center point components of one, preferably radially outwardly preceding one, i.e. selected radially inward, first profile section. This allows for optimal threading of subsequent ones
  • the individual profile sections are designed in advance in terms of fluid, in particular aerodynamically, preferably optimized, and then according to the invention, i.e. in dependence of
  • Center point component of the second profile section additionally selected as a function of its graduation angle and / or in dependence on a stagger angle of the first profile section.
  • first center point component of the second profile section can also be dependent on at least one other, second
  • Center point component of the second profile section are selected.
  • an axial center location i.e. a
  • Mid-point component in the axial direction determined for the second profile cut, and then its mid-point circumferential position, i.e. its midpoint component in
  • Circumferential direction to be selected depending on this axial center position.
  • the mass mean or center of gravity or position of a radially inner first profile section (i) is known by its position or position xcofi) in axial, rcG) in radial and ®CG (in the circumferential direction and its stagger angle ⁇ ( t ), and the axial and radial positions xcGft + i), fcGfi + i) of the center of mass of a radially adjacent second
  • Midpoint circumferential position ®cG (t + i) of the second profile section (i + 1) at least approximately the relationship
  • substantially all profile sections of the airfoil at least approximately obey this relationship.
  • radially inner profile section deviate from this. Therefore, preferably at least radially outer profile sections meet the above relationship, in particular all profile sections from 35% of a channel height of the blade grid, preferably from 25% of the channel height upwards.
  • the radial position rcG (i) or rcGfi + i) of the first or second profile section may also be used, so that the Center point circumferential position ®cG (i + i) of the second profile section (i + J) at least approximately, for example, the relationship
  • the stagger angle ß ⁇ or ß ( i + i) of the first or second profile section can be used approximately, so that the
  • Center point circumferential position ®CG (I + I) of the second profile section at least approximately, for example, the relationship
  • the blade can be inclined in the circumferential direction by the angle ® ⁇ ean . Then, the center-point circumferential position .RTM.CG (t + i) of the second profile section (i + 1) according to one of the above-explained relationships, the term
  • 'CG (/ + 1) may be added such that the midpoint circumferential position ®CG (I + I) of the second profile section (i + 1) is at least approximately equal to the relationship
  • Fig. 1A is a meridional view of an airfoil with threaded profile sections according to the prior art
  • Fig. 1B is an axial view of the airfoil of Fig. 1A.
  • FIG. 2 A, 2B an airfoil according to an embodiment of the present invention in FIG.
  • FIGS. 2A, 2B show, in meridional or axial view, an airfoil 1 of FIG
  • a compressor blade according to an embodiment of the present invention.
  • some threaded profile sections are drawn in, of which a second one is labeled "i + 1".
  • the individual profile sections are first generated under aerodynamic aspects, for example by setting or optimizing their skeleton line and their design circles. Subsequently, starting with a radially innermost profile section at the bottom of the flow channel, the axial center of gravity positions of the profile sections are recursively specified. For each profile section at least from 25% of the height of the channel upwards (from bottom to top in Fig. 2) its center of gravity position in the circumferential direction according to the relationship (2) or (2 "') is chosen, then finally the complete, both in aerodynamic and in terms of strength optimal 3D geometry of this blade results without the need for time and cost-intensive aero-strength iterations must be performed.

Landscapes

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

Abstract

Selon un procédé selon l'invention permettant la liaison de segments de profil successifs ((i), (i+1)) d'un corps d'aube (1) pour une grille d'aube d'une turbomachine, un premier composant de position centrale (formule (II)) d'un second segment de profil ((i+1)) est choisi en fonction d'au moins un composant de position centrale ((formule (IV)), xCG(i), rCG(i)) d'un premier segment de profil ((i)), en particulier selon la formule (I) comprenant : (i) une grandeur du premier segment de profil; (i+1) une grandeur du second segment de profil; (formule (III)) un composant de position centrale d'un segment de profil dans la direction périphérique, de préférence dans l'équerre ou la mesure d'arc; xCG un composant de position centrale d'un segment de profil dans la direction axiale; rCG un composant de position centrale d'un segment de profil dans la direction radiale; ß un angle de décalage d'un segment de profil; et (formule (V)) une inclinaison périphérique, de préférence dans l'équerre ou la mesure d'arc.
EP11711017A 2010-02-27 2011-01-29 Corps d'aube présentant des segments de profil successifs Withdrawn EP2539544A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102010009615.6A DE102010009615B4 (de) 2010-02-27 2010-02-27 Schaufelblatt mit gefädelten Profilschnitten
PCT/DE2011/000084 WO2011103849A2 (fr) 2010-02-27 2011-01-29 Corps d'aube présentant des segments de profil successifs

Publications (1)

Publication Number Publication Date
EP2539544A2 true EP2539544A2 (fr) 2013-01-02

Family

ID=44454085

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11711017A Withdrawn EP2539544A2 (fr) 2010-02-27 2011-01-29 Corps d'aube présentant des segments de profil successifs

Country Status (4)

Country Link
US (1) US9435207B2 (fr)
EP (1) EP2539544A2 (fr)
DE (1) DE102010009615B4 (fr)
WO (1) WO2011103849A2 (fr)

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2556409B1 (fr) * 1983-12-12 1991-07-12 Gen Electric Aube perfectionnee pour moteur a turbine a gaz et procede de fabrication
DE3441115C1 (de) 1984-11-10 1986-01-30 Daimler-Benz Ag, 7000 Stuttgart Laufrad fuer eine Gasturbine
DE4228879A1 (de) 1992-08-29 1994-03-03 Asea Brown Boveri Axialdurchströmte Turbine
DE59704501D1 (de) * 1996-03-28 2001-10-11 Mtu Aero Engines Gmbh Schaufelblatt für Strömungsmaschinen
US6241474B1 (en) * 1998-12-30 2001-06-05 Valeo Thermique Moteur Axial flow fan
US6331100B1 (en) * 1999-12-06 2001-12-18 General Electric Company Doubled bowed compressor airfoil
JP2005282492A (ja) * 2004-03-30 2005-10-13 Mitsubishi Fuso Truck & Bus Corp 翼形状作成プログラム及び方法
DE102005025213B4 (de) * 2005-06-01 2014-05-15 Honda Motor Co., Ltd. Schaufel einer Axialströmungsmaschine
DE102005042115A1 (de) * 2005-09-05 2007-03-08 Rolls-Royce Deutschland Ltd & Co Kg Schaufel einer Strömungsarbeitsmaschine mit blockweise definierter Profilskelettlinie
DE102006055869A1 (de) * 2006-11-23 2008-05-29 Rolls-Royce Deutschland Ltd & Co Kg Schaufelblattdesign für die Lauf- und Leitschaufeln einer Turbomaschine
FR2935427B1 (fr) * 2008-08-27 2010-09-24 Snecma Methode de reduction des niveaux vibratoires d'un doublet et roues aubagees contrarotatives de turbomachine.

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
None *
See also references of WO2011103849A2 *

Also Published As

Publication number Publication date
WO2011103849A3 (fr) 2011-11-03
DE102010009615B4 (de) 2016-11-17
WO2011103849A2 (fr) 2011-09-01
DE102010009615A1 (de) 2011-09-01
US9435207B2 (en) 2016-09-06
US20120315148A1 (en) 2012-12-13

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