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1. WO2006124618 - BLADE/DISK DOVETAIL BACKCUT FOR BLADE/DISK STRESS REDUCTION (6FA AND 6FA+e, STAGE 1)

Publication Number WO/2006/124618
Publication Date 23.11.2006
International Application No. PCT/US2006/018471
International Filing Date 12.05.2006
IPC
B21D 53/78 2006.01
BPERFORMING OPERATIONS; TRANSPORTING
21MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
DWORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
53Making other particular articles
78propeller blades; turbine blades
B63H 1/26 2006.01
BPERFORMING OPERATIONS; TRANSPORTING
63SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
HMARINE PROPULSION OR STEERING
1Propulsive elements directly acting on water
02of rotary type
12with rotation axis substantially in propulsive direction
14Propellers
26Blades
CPC
F01D 5/147
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
5Blades; Blade-carrying members
12Blades
14Form or construction
147Construction, i.e. structural features, e.g. of weight-saving hollow blades
F01D 5/3007
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
5Blades; Blade-carrying members
30Fixing blades to rotors; Blade roots ; ; Blade spacers
3007of axial insertion type
F05D 2230/10
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2230Manufacture
10by removing material
F05D 2240/80
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2240Components
80Platforms for stationary or moving blades
F05D 2260/94
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2260Function
94Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
F05D 2260/941
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2260Function
94Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
941particularly aimed at mechanical or thermal stress reduction
Applicants
  • GENERAL ELECTRIC COMPANY [US]/[US] (AllExceptUS)
  • CHAN, Sze Bun, Brian [CA]/[US] (UsOnly)
  • GOPALAKRISHNAN, Babu, Santhana [IN]/[IN] (UsOnly)
  • ZEMITIS, William, Scott [US]/[US] (UsOnly)
Inventors
  • CHAN, Sze Bun, Brian
  • GOPALAKRISHNAN, Babu, Santhana
  • ZEMITIS, William, Scott
Agents
  • MCQUAY, Mardson
Priority Data
60/680,03612.05.2005US
Publication Language English (EN)
Filing Language English (EN)
Designated States
Title
(EN) BLADE/DISK DOVETAIL BACKCUT FOR BLADE/DISK STRESS REDUCTION (6FA AND 6FA+e, STAGE 1)
(FR) COUPE DE PALE ET DE DISQUE EN QUEUE D'ARONDE POUR UNE REDUCTION DE LA CONTRAINTE DE LA PALE ET DU DISQUE (6FA ET 6FA+E, ETAGE 1)
Abstract
(EN)
Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance.
(FR)
Selon l'invention, la voie de charge à la pale sur un disque de turbine à gaz peut être déviée afin de renforcer considérablement la résistance à la fatigue du disque. Une pluralité de pales de turbine à gaz peuvent être fixées à un disque de turbine à gaz. Chacune de ces pales de turbine à gaz comprend un tenon en queue d'aronde ajustable dans une mortaise correspondant dans le disque de turbine à gaz. Afin de réduire la contrainte du disque de turbine à gaz, une zone optimale de suppression de matériau est définie conformément à la forme géométrique de la pale et/ou du disque de façon à maximiser l'équilibre entre la réduction de contrainte sur le disque de turbine à gaz, la vie utile de la pale de turbine à gaz et la conservation voire l'amélioration du comportement aéromécanique de la pale de turbine à gaz. La suppression de matériau de la zone de suppression de matériau permet de maximiser l'équilibre.
Also published as
EP6759703
US11476096
ESP200750070
GB0721953.8
GB721953
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