Siemens Westinghouse Power Corporation

Siemens Energy, Inc.

Eduardo E Bancalari

David Allen Little

Jody W Wilson

Joseph Fadok

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

A gas turbine engine (,) having a closed-loop cooling circuit (,) for transferring heat from the hot turbine section (,) to the compressed air (,) produced by the compressor section (,). The closed-loop cooling system (,) includes a heat exchanger (,) disposed in the flow path of the compressed air (,) between the outlet of the compressor section (,) and the inlet of the combustor (,). A cooling fluid (,) may be driven by a pump (,) located outside of the engine casing (,) or a pump (,) mounted on the rotor shaft (,). The cooling circuit (,) may include an orifice (,) for causing the cooling fluid (,) to change from a liquid state to a gaseous state, thereby increasing the heat transfer capacity of the cooling circuit (,).

Gas turbine cooling system

An airfoil for a combustion turbine comprising a leading edge, a trailing edge, and an airfoil portion defined therebetween is provided. The airfoil has an axial chord length. The airfoil portion has an accelerating flow section and a decelerating flow section. The accelerating flow section is formed such that a gas flow continues to accelerate for over more than one half of the axial chord length such that a flow boundary layer remains substantially attached along the decelerating section of the airfoil.

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Orlando, FL, United States of America

Eduardo E Bancalari