Siemens Energy, Inc.

Siemens Aktiengesellschaft

Anthony J Malandra

Ching-Pang Lee

George P Liang

John A Orosa

Gm Salam Azad

Tobias Buchal

Barry J Brown

Christopher K Rawlings

Farzad Taremi

Andrew Lohaus

Eric Munoz

Carmen Andrew Scribner

Horia Flitan

Robert M Dysert

Billie E Sealey

Jose Paulino

A turbine blade airfoil () with a center of mass (ACM) that is laterally offset from the center of mass (PCM) of a platform () to which the airfoil is attached. Respective offsets (d, d) balance these centers of mass (ACM, PCM) about an attachment plane () of the blade root (), providing balanced centrifugal loading on opposite lobes () or other attachment surfaces of the root. The attachment plane () may be a plane of bilateral symmetry of the root, and/or it may include an attachment axis () that passes through the root center of mass (RCM) along a radius of rotation of the airfoil. The airfoil and platform centers of mass (ACM, PCM) may be dynamically balanced about the attachment axis () and/or the attachment plane ().

Turbine blade with laterally biased airfoil and platform centers of mass

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

A turbine exhaust diffuser for a gas turbine engine. The diffuser includes a flow ramp positioned on an ID flowpath boundary within a flowpath of the diffuser. The flow ramp extends circumferentially about the hub and includes a downstream, radially outward point that extends radially outward further from the ID flowpath boundary than an upstream, radially outward point that is positioned upstream from the downstream, radially outward point. A wavy portion is located at the downstream, radially outward point of the flow ramp. The wavy portion includes a circumferentially extending, undulating surface defined by alternating axially extending crests and troughs.

Exhaust diffuser including flow mixing ramp for a gas turbine engine

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

A turbine blade including an airfoil having a pressure sidewall and a suction sidewall joined together along an upstream leading edge and a downstream trailing edge. The leading edge and trailing edge are formed as substantially straight edges, and portions of the pressure sidewall and suction sidewall adjacent the trailing edge form substantially planar surfaces. The airfoil has an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein Z represents a perpendicular distance from a plane normal to a radius of a turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at a radially innermost aerodynamic section of the airfoil, and X and Y represent coordinate values defining the airfoil profile at each distance Z which, when connected by smooth continuing arcs, define profile sections at each distance Z.

External profile for turbine blade airfoil

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Orlando, FL, United States of America

Anthony J Malandra