Turbomaschinenschaufel mit einer permanenten Referenzmarke zur Bearbeitung

A turbine blade (18) for a gas turbine engine includes a machining datum (60) that extends radially from a pocket (54) in the outer shroud (36) of the blade. The datum is spaced from a sidewall (64) of the pocket so that the datum is peripherally continuous irrespective of whether the blade is in a...

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Bibliographic Details
Main Authors STAUFFER, BRUCE A, WILCOX, GILBERT B
Format Patent
LanguageGerman
Published 22.07.2004
Edition7
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOTDIRECTED TO A PARTICULAR RESULT
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g.ARRANGEMENTS FOR COPYING OR CONTROLLING
ENGINE PLANTS IN GENERAL
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MACHINE TOOLS
MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OFPARTICULAR DETAILS OR COMPONENTS
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
METAL-WORKING NOT OTHERWISE PROVIDED FOR
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
PERFORMING OPERATIONS
STEAM ENGINES
TRANSPORTING
WEAPONS
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Summary:A turbine blade (18) for a gas turbine engine includes a machining datum (60) that extends radially from a pocket (54) in the outer shroud (36) of the blade. The datum is spaced from a sidewall (64) of the pocket so that the datum is peripherally continuous irrespective of whether the blade is in a prefinished state or in a completely finished state. Because the datum's peripheral continuity survives the original manufacturing process, the datum is available for use in post-manufacturing inspection and repair operations.
Bibliography:Application Number: DE19986021703T