EP2241723A1 - Paroi d'extrémité de grille d'aube de turbine - Google Patents

Paroi d'extrémité de grille d'aube de turbine Download PDF

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Publication number
EP2241723A1
EP2241723A1 EP08872470A EP08872470A EP2241723A1 EP 2241723 A1 EP2241723 A1 EP 2241723A1 EP 08872470 A EP08872470 A EP 08872470A EP 08872470 A EP08872470 A EP 08872470A EP 2241723 A1 EP2241723 A1 EP 2241723A1
Authority
EP
European Patent Office
Prior art keywords
turbine
blade
blades
stationary blade
stationary
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
EP08872470A
Other languages
German (de)
English (en)
Other versions
EP2241723B1 (fr
EP2241723A4 (fr
Inventor
Yasuro Sakamoto
Eisaku Ito
Susumu Wakazono
Takashi Hiyama
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.)
Mitsubishi Power Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Publication of EP2241723A1 publication Critical patent/EP2241723A1/fr
Publication of EP2241723A4 publication Critical patent/EP2241723A4/fr
Application granted granted Critical
Publication of EP2241723B1 publication Critical patent/EP2241723B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • 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
    • 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
    • F05D2250/711—Shape curved convex

Definitions

  • the present invention employs the following solutions. defining 0% Cax as a leading edge position of the turbine stationary blades or the turbine moving blades in an axial direction and 100% Cax as a trailing edge position of the turbine stationary blades or the turbine moving blades in the axial direction, and defining 0% pitch as a position on a pressure side surface of the turbine stationary blades or the turbine moving blades, and 100% pitch as a position on a suction side surface of a turbine stationary blade or a turbine moving blade facing the pressure side surface of the turbine stationary blade or the turbine moving blade, a convex portion, which is gently swollen as a whole, which has an apex at a position of 0 to 20 % pitch at a position of 5 to 25 % Cax, which gently slopes from this apex toward a downstream side and the suction side surface of the adjacently disposed turbine stationary blade or turbine moving blade, and which slopes slightly steeply from the apex toward an upstream side, is
  • the depth (degree of concavity) of the bottom point P5 of this second concave portion 41 is set at 5 % to 15 % (about 9.4 % in this embodiment) of the axial chord length of the fourth-stage stationary blade B2 (length of the fourth-stage stationary blade B2 in the axial direction).
  • a turbine blade cascade endwall has been described as exemplified in the third-stage stationary-blade tip endwall, the third-stage stationary-blade hub endwall, the fourth-stage stationary-blade tip endwall, and the fourth-stage stationary-blade hub endwall; however, the present invention is not limited thereto, and it can be applied to a hub endwall of turbine moving blades, a tip endwall of turbine moving blades, a stationary-blade tip endwall of other stages, or a stationary-blade tip endwall of other stages.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Hydraulic Turbines (AREA)
EP08872470.3A 2008-02-12 2008-09-25 Paroi d'extrémité de grille d'aube de turbine Active EP2241723B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2008030937A JP5291355B2 (ja) 2008-02-12 2008-02-12 タービン翼列エンドウォール
PCT/JP2008/067231 WO2009101722A1 (fr) 2008-02-12 2008-09-25 Paroi d'extrémité de grille d'aube de turbine

Publications (3)

Publication Number Publication Date
EP2241723A1 true EP2241723A1 (fr) 2010-10-20
EP2241723A4 EP2241723A4 (fr) 2013-03-06
EP2241723B1 EP2241723B1 (fr) 2014-08-13

Family

ID=40956766

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08872470.3A Active EP2241723B1 (fr) 2008-02-12 2008-09-25 Paroi d'extrémité de grille d'aube de turbine

Country Status (6)

Country Link
US (1) US20100284818A1 (fr)
EP (1) EP2241723B1 (fr)
JP (1) JP5291355B2 (fr)
KR (1) KR20100097757A (fr)
CN (1) CN101925723B (fr)
WO (1) WO2009101722A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3404211A1 (fr) * 2017-05-15 2018-11-21 MTU Aero Engines GmbH Segment de grille d'aubes d'une turbine avec paroi de plateforme contourée, grille d'aubes, canal d'aube, plateforme, turbine et moteur d'aéronef associés
EP3404210A1 (fr) * 2017-05-15 2018-11-21 MTU Aero Engines GmbH Segment de grille d'aubes d'une turbomachine avec paroi de plateforme non-axisymétrique , grille d'aubes, canal d'aube, plateforme, turbomachine associés

Families Citing this family (23)

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Publication number Priority date Publication date Assignee Title
US8403645B2 (en) 2009-09-16 2013-03-26 United Technologies Corporation Turbofan flow path trenches
FR2950942B1 (fr) * 2009-10-02 2013-08-02 Snecma Rotor d'un compresseur de turbomachine a paroi d'extremite interne optimisee
JP2012233406A (ja) 2011-04-28 2012-11-29 Hitachi Ltd ガスタービン静翼
JP5842382B2 (ja) 2011-05-13 2016-01-13 株式会社Ihi ガスタービンエンジン
US8915706B2 (en) 2011-10-18 2014-12-23 General Electric Company Transition nozzle
US8992179B2 (en) * 2011-10-28 2015-03-31 General Electric Company Turbine of a turbomachine
US9051843B2 (en) 2011-10-28 2015-06-09 General Electric Company Turbomachine blade including a squeeler pocket
US9255480B2 (en) 2011-10-28 2016-02-09 General Electric Company Turbine of a turbomachine
US8967959B2 (en) 2011-10-28 2015-03-03 General Electric Company Turbine of a turbomachine
CN102536329B (zh) * 2011-12-31 2014-04-02 西北工业大学 一种压气机/涡轮环形叶栅的非轴对称端壁造型方法
US9103213B2 (en) 2012-02-29 2015-08-11 General Electric Company Scalloped surface turbine stage with purge trough
US9085985B2 (en) 2012-03-23 2015-07-21 General Electric Company Scalloped surface turbine stage
US9267386B2 (en) 2012-06-29 2016-02-23 United Technologies Corporation Fairing assembly
EP2696029B1 (fr) * 2012-08-09 2015-10-07 MTU Aero Engines AG Grille d'aube avec définition de contour de la paroi latérale et turbomachine
EP2885506B8 (fr) 2012-08-17 2021-03-31 Raytheon Technologies Corporation Surface profilée de chemin d'écoulement
CN106089806A (zh) * 2016-05-30 2016-11-09 西北工业大学 一种减小扩压器分离损失的端壁处理方法
DE102016211315A1 (de) 2016-06-23 2017-12-28 MTU Aero Engines AG Lauf- oder Leitschaufel mit erhabenen Bereichen
ES2819128T3 (es) * 2017-03-03 2021-04-15 MTU Aero Engines AG Contorneo de una plataforma de una rejilla de paletas
WO2019190539A1 (fr) * 2018-03-30 2019-10-03 Siemens Aktiengesellschaft Plate-forme d'étage de turbine avec contour de paroi d'extrémité incorporant une face d'accouplement ondulée
US11639666B2 (en) 2021-09-03 2023-05-02 Pratt & Whitney Canada Corp. Stator with depressions in gaspath wall adjacent leading edges
US11415012B1 (en) * 2021-09-03 2022-08-16 Pratt & Whitney Canada Corp. Tandem stator with depressions in gaspath wall
CN114542502B (zh) * 2022-01-26 2023-05-26 西北工业大学 叶栅前端壁旋涡发生器可调的压气机/涡轮叶栅实验装置
DE102022113750A1 (de) * 2022-05-31 2023-11-30 MTU Aero Engines AG Ringraumkonturierung

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GB944166A (en) * 1960-03-02 1963-12-11 Werner Hausammann Rotor for turbines or compressors
WO2006067359A1 (fr) * 2004-12-21 2006-06-29 Honeywell International, Inc. Roue de turbine a inducteur a balayage arriere
EP1681438A2 (fr) * 2004-12-24 2006-07-19 The General Electric Company Etage de turbine avec plate-forme de surface échancrée
JP2007247542A (ja) * 2006-03-16 2007-09-27 Mitsubishi Heavy Ind Ltd タービン翼列エンドウォール
US20070258819A1 (en) * 2006-05-02 2007-11-08 United Technologies Corporation Airfoil array with an endwall protrusion and components of the array

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JP4346412B2 (ja) * 2003-10-31 2009-10-21 株式会社東芝 タービン翼列装置
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GB944166A (en) * 1960-03-02 1963-12-11 Werner Hausammann Rotor for turbines or compressors
WO2006067359A1 (fr) * 2004-12-21 2006-06-29 Honeywell International, Inc. Roue de turbine a inducteur a balayage arriere
EP1681438A2 (fr) * 2004-12-24 2006-07-19 The General Electric Company Etage de turbine avec plate-forme de surface échancrée
JP2007247542A (ja) * 2006-03-16 2007-09-27 Mitsubishi Heavy Ind Ltd タービン翼列エンドウォール
US20070258819A1 (en) * 2006-05-02 2007-11-08 United Technologies Corporation Airfoil array with an endwall protrusion and components of the array

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Title
ROSE M ET AL: "THE EFFECT OF END-WALL PROFILING ON SECONDARY FLOW AND LOSS DEVELOPMENT IN A TURBINE CASCADE", PROCEEDINGS OF ASME TURBO EXPO 2002, GT-2002-30339, ASME,, 3 June 2002 (2002-06-03), pages 135-145, XP008138428, *
See also references of WO2009101722A1 *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3404211A1 (fr) * 2017-05-15 2018-11-21 MTU Aero Engines GmbH Segment de grille d'aubes d'une turbine avec paroi de plateforme contourée, grille d'aubes, canal d'aube, plateforme, turbine et moteur d'aéronef associés
EP3404210A1 (fr) * 2017-05-15 2018-11-21 MTU Aero Engines GmbH Segment de grille d'aubes d'une turbomachine avec paroi de plateforme non-axisymétrique , grille d'aubes, canal d'aube, plateforme, turbomachine associés
US10934849B2 (en) 2017-05-15 2021-03-02 MTU Aero Engines AG Endwall contouring for a turbomachine

Also Published As

Publication number Publication date
CN101925723B (zh) 2016-06-01
WO2009101722A1 (fr) 2009-08-20
US20100284818A1 (en) 2010-11-11
JP2009191656A (ja) 2009-08-27
CN101925723A (zh) 2010-12-22
EP2241723B1 (fr) 2014-08-13
EP2241723A4 (fr) 2013-03-06
CN104165070A (zh) 2014-11-26
JP5291355B2 (ja) 2013-09-18
KR20100097757A (ko) 2010-09-03

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