Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Andrew Lohaus

Ching-Pang Lee

Farzad Taremi

Kok-Mun Tham

Gm Salam Azad

Tobias Buchal

Daniel M Eshak

Samuel R Miller, Jr

Daniel Vöhringer

Li Shing Wong

Anthony J Malandra

Susanne Kamenzky

Carmen Andrew Scribner

Horia Flitan

Jr Samuel R Miller

A gas turbine blade having a casted metal airfoil, the airfoil has a main wall defining at least one interior cavity, having a first side wall and a second side wall, which are coupled to each other at a leading edge and a trailing edge, extending in a radial direction from a blade root to a blade tip and defining a radial span from 0% at the blade root to 100% at the blade tip. The main airfoil has a radial span dependent chord length defined by a straight line connecting the leading edge and the trailing edge as well as a radial span dependent solidity ratio of metal area to total cross-sectional area. Solidity ratios in a machined zone of the airfoil from 80% to 85% of span are below 35%, in particular all solidity ratios in the zone.

Gas turbine blade and method for producing such blade

A contoured turbine airfoil assembly including an end wall () formed by platforms () located circumferentially adjacent to each other, and a row of airfoils () integrally joined to the end wall () and spaced laterally apart to define flow passages () therebetween for channeling gases in an axial direction. A trough () is defined between a pressure side ridge () and a suction side ridge () located forward of each pair of airfoils (). Each trough () has a direction of elongation aligned to direct flow into the flow passage () centrally between each pair of airfoils ().

End wall configuration for gas turbine engine

A shrouded turbine airfoil () with a leakage flow conditioner () configured to direct leakage flow to be aligned with main hot gas flow is disclosed. The leakage flow conditioner () may be positioned on a radially outer surface () of an outer shroud base () of the outer shroud () on a tip () of an airfoil (). The leakage flow conditioner () may include a radially outer surface () that is positioned further radially inward than the radially outer surface () of the outer shroud base () creating a radially outward extending wall surface () that serves to redirect leakage flow. In at least one embodiment, the radially outward extending wall surface () may be aligned with a pressure side () of the shrouded turbine airfoil () to increase the efficiency of a turbine engine by redirecting leakage flow to be aligned with main hot gas flow to reduce aerodynamic loss upon re-introduction to the main gas flow.

Shrouded turbine airfoil with leakage flow conditioner

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 inlet angle values, &#x3b1;, and exit angle values, &#x3b2;, set forth in one of Tables 1, 2, 3, and 4.

Turbine airfoil with optimized airfoil element angles

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Berlin, Germany

Andrew Lohaus