Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Paul A Sanders

Jan H Marsh

Evan C Landrum

Matthias Hase

Vaidyanathan Krishnan

Brian J Wessell

A turbine airfoil () includes an elongated hollow body () defining a radial cavity (T, T) positioned in an airfoil interior (). A pair of radial flow passes (B,E/C,D) incorporating near-wall cooling () channels are formed on opposite sides of the elongated hollow body (), which are in serial flow relationship conducting a coolant in opposite radial directions, forming a serpentine cooling path (). A downstream radial flow pass (C, D) of the serpentine cooling path () is fluidically connected to the radial cavity (T, T). Relatively heated coolant from the serpentine cooling path is directed into the radial cavity (T, T) to warm the elongated hollow body (). The coolant is subsequently discharged via impingement openings () on the elongated hollow body () into first and second impingement volumes () that respectively adjoin the pressure and suction side walls (). A temperature gradient between the elongated hollow body () and the outer wall () is thereby reduced.

Turbine airfoil with independent cooling circuit for mid-body temperature control

An airfoil () includes at least one internal cooling channel (A-F) extending in the radial direction and adjoined on opposite sides by an airfoil pressure sidewall () and an airfoil suction sidewall (). An internal surface () of the airfoil pressure sidewall () and an internal surface () of the airfoil suction sidewall () define heat transfer surfaces in relation to a coolant flowing through the internal cooling channel (A-F). A flow splitter feature () is located in a flow path of the coolant in the internal cooling channel (A-F) between the pressure and suction sidewalls (). The flow splitter feature () is effective to create a flow separation region downstream of the flow splitter feature (), whereby coolant flow velocity is locally increased along the internal surfaces () of the pressure and suction sidewalls ().

Turbine airfoil with internal cooling channels having flow splitter feature

A turbine airfoil () includes a flow blocking body () positioned an internal cavity (). A first near-wall cooling channel () is defined between the flow blocking body () and an airfoil pressure sidewall (). A second near-wall cooling channel () is defined between the flow blocking body () and an airfoil suction sidewall (). A connecting channel () is defined between the flow blocking body () an internal partition wall () that connects the airfoil pressure () and suction () sidewalls. The connecting channel () is connected to the first () and second () near-wall cooling channels along a radial extent. Turbulating features (-) are located in the connecting channel () and are formed on the flow blocking body () and/or on the partition wall (). The turbulating features (-) are effective to produce a higher coolant flow rate through the first () and second () near-wall cooling channels in comparison to the connecting channel ().

Turbine airfoil with turbulating feature on a cold wall

A turbine airfoil () includes an impingement structure (A,B) comprising a hollow elongated main body () positioned in an interior portion () of an airfoil body (). The main body () extends lengthwise along a radial direction and defines coolant cavity () therewithin that receives a cooling fluid (). The main body () is spaced from a pressure side wall () and a suction side wall () of the airfoil body () and may be spaced from an airfoil tip (), to define respective passages () therebetween. A plurality of impingement openings () are formed through the main body () that connect the coolant cavity () with one or more of the respective passages (). The impingement openings () direct the cooling fluid () flowing in the coolant cavity () to impinge on the pressure and/or suction side walls () and/or the airfoil tip ().

Turbine airfoil with internal impingement cooling feature

A turbine airfoil () includes a flow displacement element (A-B,A'-B&#x2032;) positioned in an interior portion () of an airfoil body () between a pair of adjacent partition walls () and comprising a radially extending elongated main body (). The main body () is spaced from the pressure and suction side walls () and further spaced from one or both of the adjacent partition walls (), whereby a first near wall passage () is defined between the main body () and the pressure side wall (), a second near wall passage () is defined between the main body () and the pressure side wall () and a central channel () is defined between the main body () and a respective one of the adjacent partition walls (). The central channel () is connected to the near wall passages () along a radial extent. One or more radial ribs () are positioned in the central channel () that extend partially across the central channel () between the main body () and the respective adjacent partition wall ().

Turbine airfoil having flow displacement feature with partially sealed radial passages

A turbine airfoil () includes a flow displacement element () occupying a space between a pair of adjacent partition walls () in an interior portion () of a generally hollow airfoil body (). The flow displacement element () includes an elongated main body () extending lengthwise in a radial direction and a pair of connector ribs () respectively connecting the main body () to pressure and suction sides () of the airfoil (). A pair of adjacent radial flow passes (--) of symmetrically opposed flow cross-sections are defined on chordally opposite sides of the flow displacement element (). The radial flow passes (--) conduct cooling fluid in opposite radial directions and are connected in series via a chordal passage () defined in the interior portion () between the flow displacement element () and a radial end face () of the airfoil body (), to form a serpentine cooling path ().

Internally cooled turbine airfoil with flow displacement feature

A gas turbine system () including a burner arrangement having a tubular combustion chamber (), a turbine () and a transition duct () connecting the combustion chamber () and the turbine (), wherein the transition duct () is provided with an axially extending cooling air channel (). The transition duct () includes a plurality of axially extending cooling air channels, and wherein each cooling air channel () is provided with one single inlet () opened to the outside of the transition duct () and with one single outlet () opened to the inside of the transition duct ().

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Charlotte, NC, United States of America

Paul A Sanders