Siemens Energy, Inc.

Eric Munoz

Edwin Lee Kite

Charles M Evans

Ching-Pang Lee

Barry J Brown

John Pula

Robert J McClelland

Anthony J Malandra

A gas turbine engine blade (), including an airfoil substrate () having an exterior surface, wherein: a base () of the airfoil substrate is located at a 0% radial on an inner platform surface () and a tip () of the airfoil substrate is located at a 100% radial; wherein at the 0% radial a cross-sectional profile of the exterior surface is substantially characterized by nominal X and Y coordinates present in Table 1; and wherein at a 50% radial location a cross-sectional profile of the exterior surface is characterized by nominal X and Y coordinates present in Table 6.

Gas turbine blade configuration

A turbine blade airfoil (R,M,T,) comprising an outer surface shape defined by Cartesian coordinates of successive transverse profiles at radial increments as set forth in Tables 1a to 1k, wherein each table defines a transverse sectional profile characterized by a smooth curve connecting the coordinates, and the surface shape comprises a smooth surface connecting the sectional profiles. The blade may include a tip shroud with edge profiles defined by Cartesian coordinates set forth in Table 2a and 2b. A gusset/fillet may be provided between the blade airfoil and the tip shroud, with a planar diagonal surface over most of a diagonal bracing area of the gusset/fillet.

Turbine blade airfoil and tip shroud

A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, &#x3b1;, and exit angles, &#x3b2;. Airfoil inlet and exit angles are substantially in accordance with pairs of inlet angle values, &#x3b1;, and exit angle values, &#x3b2;, set forth in one of Tables 1, 3, 5 and 7.

Gas turbine with optimized airfoil element angles

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Miami Gardens, FL, United States of America

Eric Munoz