EP0661413A1 - Grill d'aubes avec bord d'attaque sous la forme de flèche - Google Patents

Grill d'aubes avec bord d'attaque sous la forme de flèche Download PDF

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Publication number
EP0661413A1
EP0661413A1 EP94119705A EP94119705A EP0661413A1 EP 0661413 A1 EP0661413 A1 EP 0661413A1 EP 94119705 A EP94119705 A EP 94119705A EP 94119705 A EP94119705 A EP 94119705A EP 0661413 A1 EP0661413 A1 EP 0661413A1
Authority
EP
European Patent Office
Prior art keywords
blade
blades
grille
gravity
grid according
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.)
Granted
Application number
EP94119705A
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German (de)
English (en)
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EP0661413B1 (fr
Inventor
Reinhard Dr. Niehus
Norbert Hübner
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 Motoren und Turbinen Union Muenchen 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 Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0661413A1 publication Critical patent/EP0661413A1/fr
Application granted granted Critical
Publication of EP0661413B1 publication Critical patent/EP0661413B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • 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

Definitions

  • the invention relates to an axial vane grille according to the preamble of patent claim 1.
  • the design according to the invention has the advantage that, in addition to the effect known from the prior art, the influence of the secondary flow in rotor blade grilles, the radial pressure gradient over the blades in the region close to the boundary can be influenced by the straight, arrow-shaped course, so that the undesirable formation of Horseshoe whirling on the side wall is at least reduced. Since the improvement in step efficiency that can be achieved in this way is not based solely on influencing the secondary flow in rotor blades, which is influenced by the centrifugal force, as is known from the prior art, the invention can be used in the case of rotor and guide vane grids of compressor and turbine blades.
  • the side wall is understood to mean both the hub-side, that is to say the radially inner, and the housing-side, that is to say the radially outer, boundary of the ring channel, which can be designed as a blade platform formed in the circumferential and axial direction or as a shroud or machine housing.
  • the inventive design of the blade grids on the blades is preferably carried out both on the hub side on the blade feet and on the housing side on the blade tip.
  • the straight line within the areas of the blade tips or blade feet depending on the boundary layer thickness a distance from the respective side wall to the blade center of approximately 10% of the associated blade height.
  • the blade height associated with a blade point results from the distance between the radially inner boundary and the radially outer side wall perpendicular to the longitudinal axis of the machine and through the blade point.
  • Flow-favorable positive arrow angles ⁇ G and ⁇ N between the front edge of the blade and a solder on the radially inner or radially outer boundary of the ring channel are between 5 ° and 45 °.
  • Negative sweep angles ⁇ G and ⁇ N between -10 ° and 0 ° allow the advantages associated with sweeping even under structurally difficult conditions.
  • the radial pressure gradient can in turn be manipulated in a streamlined manner.
  • the transition region can be designed with a constant curvature and with low stress.
  • the curved section extends after the straight section up to a relative distance of 25% of the associated blade height, starting from the respective boundary into the interior of the blade.
  • the rotor blades In the case of a design of the rotor blade as a hollow blade, in order to avoid a high bending moment load on the rotor blading of rotor blade grids under centrifugal force, the rotor blades have cavities which extend at least over part of the blade length, the expansion of the cavities being distributed over the blade profile depth such that the focal points of the profile cuts are on a common level. In turbine blades, the cavities can be used as cooling channels be trained.
  • axial displacement of the individual profile cuts can have a favorable influence on the bending moment stress on the airfoil, the offset being able to be chosen such that the center of gravity of the blade comes to rest in the center of gravity of the disc.
  • the center of gravity of the disc is also on the common plane. Strength-reducing tensions in the blade root area are thus avoided.
  • rotor blade grilles with a shroud which concentrically surrounds the blade grille and is connected to the tip of the blade, or is attached there.
  • the centers of gravity of the blades of such a vane grille and the center of gravity of the shroud are spaced axially from the center of gravity of the vane grille in such a way that the center of gravity of the disk receiving the rotor blades lies on the center of gravity of the vane grille. This in turn results in a design with low bending stress in the area of the blade feet.
  • a profile of the blade trailing edges which is similar to the shape of the blade leading edges results with a constant or with a constant increase or decrease in the blade depth over the blade length.
  • FIG. 1a An axial-circumferential-radial coordinate system z-. ⁇ .-r is used for directional and reference information.
  • Figures 1a to 4b show representations in the z-r plane.
  • the blades 6 of the guide and rotor blades 4, 5 extend radially in an annular channel 7 arranged concentrically to the machine longitudinal axis A of the axial turbine 1.
  • the axially concentric hub and housing side walls form the radially inner and radially outer channel boundary 8 and 9 of the annular channel 7 and give it a divergent course with respect to the flow direction S.
  • the rotor blade grids 3 are designed in a disk construction, i.e. the rotor blades 5 are each attached to a disk 10 in a grid manner.
  • FIG. 1b shows an axial turbine 1 'designed according to the prior art, the guide and rotor blade grids 2' and 3 'of which are uncurved Guide and rotor blades 4 'or 5' is equipped.
  • Fig. 2 shows the threading of individual profile cuts P1, P2, P3 and P4 of an airfoil 6 of the axial turbine 1.
  • threading axis F a reference line perpendicular to the machine longitudinal axis A
  • the profile cuts P n coincide with lines of the same relative blade height h in the zr plane.
  • the associated blade height h in turn results from the distance to be measured perpendicular to the longitudinal axis A of the machine between the inner and outer channel boundaries 8 and 9.
  • the blade leading edge 11 has a rectilinear section B G or B N in the rz plane.
  • the arrow angle . ⁇ .G and . ⁇ .N to be measured relative to a perpendicular L to the respective channel boundary 8.9 is 25 ° within the sections B G and B N on the housing side and 45 ° on the hub side.
  • the blade leading edge 11 each has a curved extending section Ü G or Ü N , which corresponds to a second or higher order polynomial.
  • the blade edge 11 is again straight in the rz plane.
  • the transitions from curved to rectilinear course in the blade leading edge 11 are formed continuously.
  • the shape of the trailing edge 12 of the blade results from the specification of the blade depth t (h), which decreases linearly here with increasing duct height h.
  • the rotor blade grille 3 shown in FIG. 3 in the r-z plane is of disk construction, the rotor blades 5 positively in a uniform manner in the circumferential direction via their molded-on blade feet 13. spaced apart disk grooves 14 of the disk 10 are attached.
  • the centers of gravity SP G and SP S of the rotor blade grille 3 and the disk 10 lying on the machine longitudinal axis A coincide.
  • the focal points SP L of the moving blades 5 lie on a common plane E by appropriate threading of the profile cuts P, which is perpendicular to the machine axis A and runs through the common focal point SPS and SPG of the disk 10 or of the moving blade grille 3.
  • the rotor blade grille 3 is provided with a cover band 15 which is segmented in the circumferential direction and comprises the rotor blades at the radially outer end.
  • Fig. 4 shows an alternative embodiment of a blade 5 to avoid bending stresses in the blade 5 due to unbalanced centers of gravity SP P of the profile cuts P n .
  • the interior of the airfoil 6 has a cavity 16 which extends over the channel height h and whose extension over the airfoil depth t (h) is designed such that the centers of gravity SP P of the profile cuts P n are in a common r-. ⁇ .. Level.
  • FIG. 5 shows a blade blade 6 which is additionally concave with respect to the blade suction side 18 and which is curved in the circumferential direction.
  • This additional curvature advantageously has an influence on the radial pressure gradient in the outflow plane of a guide blade or rotor blade 4, 5 to take. Due to the circumferential bend, the profile cuts close to the limit are aerodynamically relieved. With a simultaneous higher load on the center area of the blade 4.5, as a result of which a more favorable efficiency can be achieved overall for the blade 4.5.

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  • 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)
  • Chain Conveyers (AREA)
EP19940119705 1993-12-23 1994-12-14 Grill d'aubes avec bord d'attaque sous la forme de flèche Expired - Lifetime EP0661413B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4344189 1993-12-23
DE19934344189 DE4344189C1 (de) 1993-12-23 1993-12-23 Axial-Schaufelgitter mit gepfeilten Schaufelvorderkanten

Publications (2)

Publication Number Publication Date
EP0661413A1 true EP0661413A1 (fr) 1995-07-05
EP0661413B1 EP0661413B1 (fr) 1998-08-26

Family

ID=6506022

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19940119705 Expired - Lifetime EP0661413B1 (fr) 1993-12-23 1994-12-14 Grill d'aubes avec bord d'attaque sous la forme de flèche

Country Status (3)

Country Link
EP (1) EP0661413B1 (fr)
DE (1) DE4344189C1 (fr)
ES (1) ES2123700T3 (fr)

Cited By (50)

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EP0833060A2 (fr) * 1996-09-30 1998-04-01 Kabushiki Kaisha Toshiba Aube pour machine axiale à fluide
WO1999013199A1 (fr) * 1997-09-08 1999-03-18 Siemens Aktiengesellschaft Aube pour une turbomachine, et turbine a vapeur
EP0916812A1 (fr) * 1997-11-17 1999-05-19 Asea Brown Boveri AG Etage final pour turbine axial
EP0957236A1 (fr) * 1998-05-15 1999-11-17 Asea Brown Boveri AG Aubes mobiles pour turbine
WO1999064725A1 (fr) * 1998-06-12 1999-12-16 Ebara Corporation Deflecteur d'injecteur de turbine
WO2000061918A2 (fr) * 1999-03-22 2000-10-19 Siemens Westinghouse Power Corporation Dispositif d'elimination de tourbillon du bord d'attaque de la surface portante
EP1111188A3 (fr) * 1999-12-21 2003-01-08 General Electric Company Aube inclinée avec arête amont bombée
FR2828709A1 (fr) * 2001-08-17 2003-02-21 Snecma Moteurs Aube de redresseur
WO2006059996A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Ailettes de rotor de soufflante pour moteur a turbine en bout
EP1710397A2 (fr) 2005-03-31 2006-10-11 Kabushiki Kaisha Toshiba Aube de guidage courbée
EP1760321A2 (fr) 2005-09-05 2007-03-07 Rolls-Royce Deutschland Ltd & Co KG Pale d'une turbomachine
EP1798375A2 (fr) 2005-12-19 2007-06-20 Rolls-Royce Deutschland Ltd & Co KG Profil d'aube pour aubes statoriques variables
EP1905952A2 (fr) 2006-09-12 2008-04-02 United Technologies Corporation Aube statorique de compresseur et entretoise d'un moteur à turbine
EP1927724A2 (fr) * 2006-11-23 2008-06-04 Rolls-Royce Deutschland Ltd & Co KG Aube de turbomachine
EP1985802A2 (fr) * 2007-04-27 2008-10-29 Rolls-Royce Deutschland Ltd & Co KG Déroulement de bord avant pour composants de turbomachines
EP1995469A1 (fr) * 2006-03-14 2008-11-26 Mitsubishi Heavy Industries, Ltd. Lame destinee a une machine a fluide a ecoulement axial
EP1731716A3 (fr) * 2005-06-06 2009-10-21 General Electric Company Aubes de guidage statoriques inclinées vers l'avant
EP1731733A3 (fr) * 2005-06-06 2009-10-28 General Electric Company Turboréacteur contrarotatif intégré
US8382438B2 (en) 2004-11-12 2013-02-26 Rolls-Royce Deutschland Ltd & Co Kg Blade of a turbomachine with enlarged peripheral profile depth
RU2498082C2 (ru) * 2007-12-14 2013-11-10 Снекма Монокристаллическая турбинная лопатка, модуль турбомашины и турбомашина
WO2014090907A1 (fr) * 2012-12-13 2014-06-19 Nuovo Pignone Srl Aube de turbomachine, turbomachine correspondante et procédé de fabrication d'une aube de turbine
EP2824277A1 (fr) * 2013-07-12 2015-01-14 MTU Aero Engines GmbH Etage de turbine à gaz
RU2558171C2 (ru) * 2010-10-18 2015-07-27 Сименс Акциенгезелльшафт Кольцевой диффузор газовой турбины
WO2015126941A1 (fr) 2014-02-19 2015-08-27 United Technologies Corporation Profil aérodynamique de moteur à turbine à gaz
WO2015175051A2 (fr) 2014-02-19 2015-11-19 United Technologies Corporation Profil aérodynamique de moteur à turbine à gaz
CN105089709A (zh) * 2014-05-12 2015-11-25 阿尔斯通技术有限公司 具有改进的冷却的翼型件
EP3163019A1 (fr) * 2015-10-26 2017-05-03 MTU Aero Engines GmbH Aube
US9752439B2 (en) 2014-02-19 2017-09-05 United Technologies Corporation Gas turbine engine airfoil
US9777580B2 (en) 2014-02-19 2017-10-03 United Technologies Corporation Gas turbine engine airfoil
US10036257B2 (en) 2014-02-19 2018-07-31 United Technologies Corporation Gas turbine engine airfoil
EP2218874B1 (fr) * 2009-02-13 2018-09-19 United Technologies Corporation Section transversale d'aube fixe de turbine pour la déviation d'écoulement avec une configuration de bord de fuite axiale/circonférentielle
US10184483B2 (en) 2014-02-19 2019-01-22 United Technologies Corporation Gas turbine engine airfoil
US10309414B2 (en) 2014-02-19 2019-06-04 United Technologies Corporation Gas turbine engine airfoil
US10352331B2 (en) 2014-02-19 2019-07-16 United Technologies Corporation Gas turbine engine airfoil
US10370974B2 (en) 2014-02-19 2019-08-06 United Technologies Corporation Gas turbine engine airfoil
US10385866B2 (en) 2014-02-19 2019-08-20 United Technologies Corporation Gas turbine engine airfoil
US10393139B2 (en) 2014-02-19 2019-08-27 United Technologies Corporation Gas turbine engine airfoil
US10422226B2 (en) 2014-02-19 2019-09-24 United Technologies Corporation Gas turbine engine airfoil
US10465702B2 (en) 2014-02-19 2019-11-05 United Technologies Corporation Gas turbine engine airfoil
US10495106B2 (en) 2014-02-19 2019-12-03 United Technologies Corporation Gas turbine engine airfoil
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US10550852B2 (en) 2014-02-19 2020-02-04 United Technologies Corporation Gas turbine engine airfoil
US10557477B2 (en) 2014-02-19 2020-02-11 United Technologies Corporation Gas turbine engine airfoil
US10570915B2 (en) 2014-02-19 2020-02-25 United Technologies Corporation Gas turbine engine airfoil
US10584715B2 (en) 2014-02-19 2020-03-10 United Technologies Corporation Gas turbine engine airfoil
US10590775B2 (en) 2014-02-19 2020-03-17 United Technologies Corporation Gas turbine engine airfoil
US10605259B2 (en) 2014-02-19 2020-03-31 United Technologies Corporation Gas turbine engine airfoil
EP3816397A1 (fr) * 2019-10-31 2021-05-05 General Electric Company Aubes de turbines avec ecoulement contrôlé
US11220910B2 (en) * 2019-07-26 2022-01-11 Pratt & Whitney Canada Corp. Compressor stator

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DE59907976D1 (de) 1998-02-20 2004-01-22 Rolls Royce Deutschland Anordnung von Axialturbinenschaufeln
WO2006059968A1 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Boite de vitesses contre-rotative pour moteur a turbine de bout
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
EP1834067B1 (fr) 2004-12-01 2008-11-26 United Technologies Corporation Ensemble de pales de soufflante pour moteur a turbine de bout et procede de montage
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WO2006060000A1 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Ensemble aubes de guidage d'admission de soufflante variable, turbomachine dotee d'un tel ensemble et procede de commande correspondant
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US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
EP1825116A2 (fr) 2004-12-01 2007-08-29 United Technologies Corporation Refroidissement par ejecteur de l'enveloppe exterieure d'un moteur a turbine de bout
US8468795B2 (en) 2004-12-01 2013-06-25 United Technologies Corporation Diffuser aspiration for a tip turbine engine
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US4012172A (en) * 1975-09-10 1977-03-15 Avco Corporation Low noise blades for axial flow compressors
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Cited By (90)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0833060A3 (fr) * 1996-09-30 1998-12-02 Kabushiki Kaisha Toshiba Aube pour machine axiale à fluide
AU701429B2 (en) * 1996-09-30 1999-01-28 Kabushiki Kaisha Toshiba Blade for axial fluid machine
US6079948A (en) * 1996-09-30 2000-06-27 Kabushiki Kaisha Toshiba Blade for axial fluid machine having projecting portion at the tip and root of the blade
EP0833060A2 (fr) * 1996-09-30 1998-04-01 Kabushiki Kaisha Toshiba Aube pour machine axiale à fluide
CN1100194C (zh) * 1996-09-30 2003-01-29 株式会社东芝 用于轴流式流体机械的叶片
WO1999013199A1 (fr) * 1997-09-08 1999-03-18 Siemens Aktiengesellschaft Aube pour une turbomachine, et turbine a vapeur
US6354798B1 (en) 1997-09-08 2002-03-12 Siemens Aktiengesellschaft Blade for a fluid-flow machine, and steam turbine
EP0916812A1 (fr) * 1997-11-17 1999-05-19 Asea Brown Boveri AG Etage final pour turbine axial
US6099248A (en) * 1997-11-17 2000-08-08 Abb Alstom Power (Switzerland) Ltd Output stage for an axial-flow turbine
EP0957236A1 (fr) * 1998-05-15 1999-11-17 Asea Brown Boveri AG Aubes mobiles pour turbine
US6491493B1 (en) 1998-06-12 2002-12-10 Ebara Corporation Turbine nozzle vane
WO1999064725A1 (fr) * 1998-06-12 1999-12-16 Ebara Corporation Deflecteur d'injecteur de turbine
WO2000061918A3 (fr) * 1999-03-22 2001-01-11 Siemens Westinghouse Power Dispositif d'elimination de tourbillon du bord d'attaque de la surface portante
WO2000061918A2 (fr) * 1999-03-22 2000-10-19 Siemens Westinghouse Power Corporation Dispositif d'elimination de tourbillon du bord d'attaque de la surface portante
EP1111188A3 (fr) * 1999-12-21 2003-01-08 General Electric Company Aube inclinée avec arête amont bombée
FR2828709A1 (fr) * 2001-08-17 2003-02-21 Snecma Moteurs Aube de redresseur
US8382438B2 (en) 2004-11-12 2013-02-26 Rolls-Royce Deutschland Ltd & Co Kg Blade of a turbomachine with enlarged peripheral profile depth
WO2006059996A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Ailettes de rotor de soufflante pour moteur a turbine en bout
EP1710397A3 (fr) * 2005-03-31 2008-03-12 Kabushiki Kaisha Toshiba Aube de guidage courbée
EP1710397A2 (fr) 2005-03-31 2006-10-11 Kabushiki Kaisha Toshiba Aube de guidage courbée
EP1731733A3 (fr) * 2005-06-06 2009-10-28 General Electric Company Turboréacteur contrarotatif intégré
EP1731716A3 (fr) * 2005-06-06 2009-10-21 General Electric Company Aubes de guidage statoriques inclinées vers l'avant
EP1760321A2 (fr) 2005-09-05 2007-03-07 Rolls-Royce Deutschland Ltd & Co KG Pale d'une turbomachine
EP1798375A2 (fr) 2005-12-19 2007-06-20 Rolls-Royce Deutschland Ltd & Co KG Profil d'aube pour aubes statoriques variables
EP1995469A4 (fr) * 2006-03-14 2013-08-14 Mitsubishi Heavy Ind Ltd Lame destinee a une machine a fluide a ecoulement axial
EP1995469A1 (fr) * 2006-03-14 2008-11-26 Mitsubishi Heavy Industries, Ltd. Lame destinee a une machine a fluide a ecoulement axial
EP1905952A3 (fr) * 2006-09-12 2011-07-06 United Technologies Corporation Aube statorique de compresseur et entretoise d'un moteur à turbine
EP1905952A2 (fr) 2006-09-12 2008-04-02 United Technologies Corporation Aube statorique de compresseur et entretoise d'un moteur à turbine
US7726937B2 (en) * 2006-09-12 2010-06-01 United Technologies Corporation Turbine engine compressor vanes
EP1927724A3 (fr) * 2006-11-23 2009-05-20 Rolls-Royce Deutschland Ltd & Co KG Aube de turbomachine
US8152473B2 (en) 2006-11-23 2012-04-10 Rolls-Royce Deutschland Ltd & Co Kg Airfoil design for rotor and stator blades of a turbomachine
EP1927724A2 (fr) * 2006-11-23 2008-06-04 Rolls-Royce Deutschland Ltd & Co KG Aube de turbomachine
EP1985802A3 (fr) * 2007-04-27 2010-11-17 Rolls-Royce Deutschland Ltd & Co KG Déroulement de bord avant pour composants de turbomachines
US8047802B2 (en) 2007-04-27 2011-11-01 Rolls-Royce Deutschland Ltd & Co Kg Course of leading edges for turbomachine components
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ES2123700T3 (es) 1999-01-16
DE4344189C1 (de) 1995-08-03

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