BLADE FOR A TURBINE ENGINE AND METHOD FOR PRODUCTION OF SAID BLADE

The blade has a two-part main body of titanium alloy, the two parts bonded together by a high temperature and high pressure connection. In the connection area (31), a groove (23) in the first part (11) has a wall (27) immediately next to the second part (13), to define a connection angle of more tha...

Full description

Saved in:
Bibliographic Details
Main Authors PICKERT, URSULA, TIEMANN, PETER
Format Patent
LanguageEnglish
French
German
Published 26.05.2004
Edition7
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
CLADDING OR PLATING BY SOLDERING OR WELDING
COMBINED OPERATIONS
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING
ENGINE PLANTS IN GENERAL
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MACHINE TOOLS
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
METAL-WORKING NOT OTHERWISE PROVIDED FOR
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
OTHER WORKING OF METAL
PERFORMING OPERATIONS
SOLDERING OR UNSOLDERING
STEAM ENGINES
TRANSPORTING
UNIVERSAL MACHINE TOOLS
WEAPONS
WELDING
WORKING BY LASER BEAM
Online AccessGet full text

Cover

More Information
Summary:The blade has a two-part main body of titanium alloy, the two parts bonded together by a high temperature and high pressure connection. In the connection area (31), a groove (23) in the first part (11) has a wall (27) immediately next to the second part (13), to define a connection angle of more than 70 degrees . The alloy is titanium aluminide. The two parts form a common wall thickness within the connection area, which varies along the area. The first blade part forms the suction side, and the second part forms the pressure side. The blade is formed as a gas turbine rotor blade, especially for the last turbine stage.
Bibliography:Application Number: EP20020748865