TURBINE AIRFOIL WITH TURBULATING FEATURE ON A COLD WALL

A turbine airfoil (10) includes a flow blocking body (26) positioned an internal cavity (40). A first near-wall cooling channel (72) is defined between the flow blocking body (26) and an airfoil pressure sidewall (16). A second near-wall cooling channel (74) is defined between the flow blocking body...

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Bibliographische Detailangaben
Hauptverfasser:	Sanders, Paul A, Marsh, Jan H
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A turbine airfoil (10) includes a flow blocking body (26) positioned an internal cavity (40). A first near-wall cooling channel (72) is defined between the flow blocking body (26) and an airfoil pressure sidewall (16). A second near-wall cooling channel (74) is defined between the flow blocking body (26) and an airfoil suction sidewall (18). A connecting channel (76) is defined between the flow blocking body (26) an internal partition wall (24) that connects the airfoil pressure (16) and suction (18) sidewalls. The connecting channel (76) is connected to the first (72) and second (74) near-wall cooling channels along a radial extent. Turbulating features (90, 90a-b) are located in the connecting channel (76) and are formed on the flow blocking body (26) and/or on the partition wall (24). The turbulating features (90, 90a-b) are effective to produce a higher coolant flow rate through the first (72) and second (74) near-wall cooling channels in comparison to the connecting channel (76).