Siemens Energy Global Gmbh & Co. Kg

Siemens Energy, Inc.

Farzad Taremi

Ross James Gustafson

Li Shing Wong

Ching-Pang Lee

Andrew Lohaus

Horia Flitan

Kok-Mun Tham

Gm Salam Azad

Tobias Buchal

Anthony J Malandra

Carmen Andrew Scribner

Andrew Miller

Andrew S Lohaus

Masayoshi Senga

Bharat Prabhu

Anne Maria Starke

Ross Gustafson

A turbine blade includes a root arranged to attach the turbine blade to a rotor and a vane extending in a radial direction from the root to a tip surface. The vane includes a leading edge, a trailing edge, a pressure-side surface, and a suction-side surface that cooperate to define a vane perimeter. A perimeter wall extends radially from the tip surface and surrounds a portion of the vane perimeter. A first trench wall extends across the tip surface and cooperates with the perimeter wall to substantially enclose a pressure-side pocket and a second trench wall extends across the tip surface and cooperates with the perimeter wall to substantially enclose a suction-side pocket.

Turbine blade

A turbine operable to convey a flow of exhaust gas along a central axis includes a strut having a flow portion positioned within the flow of exhaust gas and a strut cover having a length and positioned to surround the flow portion of the strut, the strut cover including a leading-edge portion, a mid-chord portion, and a trailing-edge portion. The mid-chord portion has a uniform cross-section, and the trailing-edge portion has a trailing-edge center positioned such that the mid-chord portion and the trailing-edge portion define a master chord plane. The leading-edge portion defines a leading-edge nose, and the leading-edge portion is twisted with respect to the master chord plane and the leading-edge nose along the length defines a curve that is not coincident with the master chord plane.

Strut cover for a turbine

A turbine stage includes a first airfoil and a second airfoil extending respectively from a first platform and a second platform that form an endwall for a flow passage. The endwall has a nominal surface that is axisymmetric about an axis of the turbine stage. The endwall further includes at least one contoured region that is non-axisymmetric with respect to the axis. The at least one contoured region extends from the first platform to the second platform across a platform splitline. The global maximum variation in elevation &#x394;EW of the endwall is at least 3% of an axial chord length L of the airfoils on the endwall. The maximum variation in elevation &#x394;MF at the mate facea of the platforms lies in the range 15-60% &#x394;EW.

Turbine stage platform with endwall contouring incorporating wavy mate face

A turbine stage includes an array of airfoils spaced apart circumferentially to define a flow passage therebetween for channeling a working medium. The airfoils extend radially outward from an inner endwall located at a hub side thereof. The inner endwall is inclined at an angle to an engine axis such that the flow passage is divergent from an upstream side to a downstream side. The inner endwall is non-axisymmetric about the engine axis, having a mid-passage bulge located between circumferentially adjacent first and second airfoils. The bulge has a peak at a position between 20-60% Caxand at a position between 30-70% pitch.

Endwall contouring for a conical endwall

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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Palm Beach Gardens, FL, United States of America

Farzad Taremi