Siemens Energy, Inc.

Siemens Westinghouse Power Corporation

Joseph Fadok

David Allen Little

Jody W Wilson

Eduardo E Bancalari

Eduardo Bancalari

A transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine has an internal passage from an inlet to an outlet that is offset from the inlet in the longitudinal, radial and tangential directions. The offset outlet and the curved internal passage discharge the gas flow toward the first stage blade array at an angle in the tangential direction relative to the longitudinal direction. This angled discharge can be presented directly to the blades, thus avoiding the need for first stage vanes and the associated costs and complexity.

Combustion transition duct providing stage 1 tangential turning for turbine engines

Aspects of the invention relate to a method for clocking a row of stationary airfoils relative to an adjacent row of airfoils, and a turbine blade ring configured for use in such a method. The method according to aspects of the invention is advantageous because it can avoid extensive disassembly of the turbine in order to clock the blade ring. The method includes engaging the outer peripheral surface of a blade ring with a plurality of roller pins such that the weight of the blade ring is entirely supported by the roller pins. A tangential force is applied to the blade ring such that the blade ring rotates on the roller pins, thereby adjusting the position of the stationary airfoils affixed to the blade ring. Additional rotational adjustments can be made to the blade ring until the blade ring is clocked to the desired position.

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Winter Springs, FL, United States of America

Joseph Fadok