ROTATING TURBINE COMPONENT WITH PREFERENTIAL HOLE ALIGNMENT

A turbine airfoil includes: a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge, and extending between a root and a tip; an internal rib extending between the pressure sidewall and the suction sidewall; and a crossover hole formed in the ri...

Full description

Saved in:
Bibliographic Details
Main Authors MOLTER, STEPHEN, MARK, PEARSON, SHAWN, MICHAEL, BRASSFIELD, STEVEN, ROBERT, ERTEL, NICHOLAS, STEGEMILLER, MARK, EDWARD, CAMARILLO, VANESSA
Format Patent
LanguageEnglish
French
German
Published 22.07.2015
Subjects
BLASTING
COMBINED OPERATIONS
ENGINE PLANTS IN GENERAL
HEATING
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
STEAM ENGINES
TRANSPORTING
UNIVERSAL MACHINE TOOLS
WEAPONS
Online AccessGet full text

Cover

More Information
Summary:A turbine airfoil includes: a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge, and extending between a root and a tip; an internal rib extending between the pressure sidewall and the suction sidewall; and a crossover hole formed in the rib, the crossover hole having a noncircular cross-sectional shape with a major axis defining a maximum dimension of the cross-sectional shape; wherein the major axis of the crossover hole lies in plane with the rib and is non-parallel to an imaginary curvilinear lateral centerline which defines a locus of points lying halfway between the pressure and suction sidewalls. The orientation of the crossover holes minimizes stress concentration caused by the presence of the crossover holes.
Bibliography:Application Number: EP20130747744