JP2008540921A5 - - Google Patents

Download PDF

Info

Publication number
JP2008540921A5
JP2008540921A5 JP2008511417A JP2008511417A JP2008540921A5 JP 2008540921 A5 JP2008540921 A5 JP 2008540921A5 JP 2008511417 A JP2008511417 A JP 2008511417A JP 2008511417 A JP2008511417 A JP 2008511417A JP 2008540921 A5 JP2008540921 A5 JP 2008540921A5
Authority
JP
Japan
Prior art keywords
dovetail
blade
backcut
turbine
disk
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
JP2008511417A
Other languages
English (en)
Japanese (ja)
Other versions
JP2008540921A (ja
JP4870754B2 (ja
Filing date
Publication date
Application filed filed Critical
Priority claimed from PCT/US2006/018472 external-priority patent/WO2006124619A2/en
Publication of JP2008540921A publication Critical patent/JP2008540921A/ja
Publication of JP2008540921A5 publication Critical patent/JP2008540921A5/ja
Application granted granted Critical
Publication of JP4870754B2 publication Critical patent/JP4870754B2/ja
Anticipated expiration legal-status Critical
Active legal-status Critical Current

Links

JP2008511417A 2005-05-12 2006-05-12 動翼／ディスク（７ＦＡ＋ｅ、第２段）の応力を低減するための動翼／ディスクダブテールバックカット Active JP4870754B2 (ja)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
US68003305P 2005-05-12 2005-05-12
US68003205P 2005-05-12 2005-05-12
US60/680,032 2005-05-12
US60/680,033 2005-05-12
PCT/US2006/018472 WO2006124619A2 (en) 2005-05-12 2006-05-12 BLADE/DISK DOVETAIL BACKCUT FOR BLADE/DISK STRESS REDUCTION (7FA+e, STAGE 2)

Publications (3)

Publication Number Publication Date
JP2008540921A JP2008540921A (ja) 2008-11-20
JP2008540921A5 true JP2008540921A5 (https=) 2009-08-06
JP4870754B2 JP4870754B2 (ja) 2012-02-08

Family

ID=37431920

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2008511417A Active JP4870754B2 (ja) 2005-05-12 2006-05-12 動翼／ディスク（７ＦＡ＋ｅ、第２段）の応力を低減するための動翼／ディスクダブテールバックカット

Country Status (4)

Country Link
US (1) US7419361B1 (https=)
EP (1) EP1882085A4 (https=)
JP (1) JP4870754B2 (https=)
WO (1) WO2006124619A2 (https=)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080101938A1 (en) * 2006-10-26 2008-05-01 General Electric Blade/disk dovetail backcut for blade/disk stress reduction (7FA, stage 1)
US20080101937A1 (en) * 2006-10-26 2008-05-01 General Electric Blade/disk dovetail backcut for blade/disk stress reduction (9FA, stage 1)
US20080101939A1 (en) * 2006-10-26 2008-05-01 General Electric Blade/disk dovetail backcut for blade/disk stress reduction (7FA, stage 2)
US8051709B2 (en) * 2009-02-25 2011-11-08 General Electric Company Method and apparatus for pre-spinning rotor forgings
US9151167B2 (en) 2012-02-10 2015-10-06 General Electric Company Turbine assembly
US9151169B2 (en) * 2012-03-29 2015-10-06 General Electric Company Near-flow-path seal isolation dovetail
US9200539B2 (en) 2012-07-12 2015-12-01 General Electric Company Turbine shell support arm
US9903210B2 (en) 2013-05-21 2018-02-27 Siemens Energy, Inc. Turbine blade tip shroud
US9828858B2 (en) 2013-05-21 2017-11-28 Siemens Energy, Inc. Turbine blade airfoil and tip shroud
EP3034798B1 (en) * 2014-12-18 2018-03-07 Ansaldo Energia Switzerland AG Gas turbine vane
US20170356297A1 (en) * 2016-06-13 2017-12-14 General Electric Company Lockwire Tab Backcut For Blade Stress Reduction (9E.04)
CN106825356B (zh) * 2016-12-09 2018-09-21 无锡航亚科技股份有限公司 一种精锻叶片型线修整的方法
JP7385992B2 (ja) * 2018-12-28 2023-11-24 川崎重工業株式会社 回転体の動翼およびディスク
CN115791142B (zh) * 2023-02-09 2023-06-13 中国航发四川燃气涡轮研究院 轴向限位叶片结构及配置方法
CN116857018B (zh) * 2023-08-11 2026-03-24 中国航发沈阳发动机研究所 一种涡轮盘与盘前封严盘的连接定位结构

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6232202A (ja) * 1985-08-05 1987-02-12 Hitachi Ltd ブレ−ドダブテ−ル
JPS63134804A (ja) * 1986-11-25 1988-06-07 Hitachi Ltd タ−ビン動翼の取付構造
JPS63138403A (ja) * 1986-12-01 1988-06-10 Fujitsu Ltd デ−タ転送方式
JPS63138403U (https=) * 1987-03-04 1988-09-12
GB2228540B (en) * 1988-12-07 1993-03-31 Rolls Royce Plc Cooling of turbine blades
JPH04134605U (ja) * 1991-06-07 1992-12-15 三菱重工業株式会社 蒸気タービンの動翼
US5435694A (en) * 1993-11-19 1995-07-25 General Electric Company Stress relieving mount for an axial blade
FR2725239B1 (fr) * 1994-09-30 1996-11-22 Gec Alsthom Electromec Disposition pour l'ecretement des pointes de contrainte dans l'ancrage d'une ailette de turbine, comportant une racine dite en "pied-sapin"
US5573377A (en) 1995-04-21 1996-11-12 General Electric Company Assembly of a composite blade root and a rotor
DE19728085A1 (de) * 1997-07-02 1999-01-07 Asea Brown Boveri Fügeverbindung zwischen zwei Fügepartnern sowie deren Verwendung
US6059525A (en) 1998-05-19 2000-05-09 General Electric Co. Low strain shroud for a turbine technical field
US6033185A (en) 1998-09-28 2000-03-07 General Electric Company Stress relieved dovetail
US6183202B1 (en) * 1999-04-30 2001-02-06 General Electric Company Stress relieved blade support
US6439851B1 (en) * 2000-12-21 2002-08-27 United Technologies Corporation Reduced stress rotor blade and disk assembly
US6375423B1 (en) 2000-12-26 2002-04-23 General Electric Company Method for removal of dovetailed turbine bucket from a turbine wheel
US6390775B1 (en) 2000-12-27 2002-05-21 General Electric Company Gas turbine blade with platform undercut
US6520836B2 (en) 2001-02-28 2003-02-18 General Electric Company Method of forming a trailing edge cutback for a turbine bucket
US6739837B2 (en) * 2002-04-16 2004-05-25 United Technologies Corporation Bladed rotor with a tiered blade to hub interface

Similar Documents

Publication Publication Date Title
JP2008540921A5 (https=)
WO2009112775A3 (fr) Aube avec plateforme non axisymetrique
CN103287573B (zh) 用于旋转机械的翼型
JP2013130193A5 (https=)
DK1963671T3 (da) Vinge til en vindmøllerotor
CN104169589B (zh) 用于涡轮机整体叶盘的改进壳体和装配有所述壳体的涡轮机
WO2009112776A3 (fr) Aube avec plateforme non axisymetrique : creux et bosse sur extrados
WO2008097287A3 (en) Aero-mixing of rotating blade structures
WO2009146810A3 (de) Rotorblatt für eine windkraftanlage sowie windkraftanlage
JP2013517148A5 (https=)
EP2301841A3 (en) Variable shape rotor blade
US10415402B2 (en) Blade wear pads and manufacture methods
US9039490B2 (en) Method of shaping an edge of an aerofoil
WO2008035135A3 (en) First stage turbine airfoil
JP2009262320A (ja) ブリスクをフライス加工する方法
JP2013517149A5 (https=)
WO2009156105A3 (de) Verfahren und fertigungsform zur fertigung eines rotorblattes für eine windenergieanlage
RU2014152841A (ru) Способ изготовления металлического элемента усиления лопатки турбомашины
GB2445896A (en) Turbine nozzle blade airfoil geometry
RU2012139421A (ru) Способ изготовления металлической вставки для защиты передней кромки из керамического материала
JP2013525689A5 (https=)
JP2013148086A5 (https=)
JP2016098695A5 (https=)
JP2005351277A5 (https=)
JP4870754B2 (ja) 動翼／ディスク（７ＦＡ＋ｅ、第２段）の応力を低減するための動翼／ディスクダブテールバックカット