TURBINE BLADE TRAILING EDGE WITH LOW FLOW FRAMING CHANNEL

The present disclosure provides a core structure comprising a trailing edge section including a plurality of rib-forming apertures (126) defined by a plurality of radially-extending channel elements (130) and axially-extending passage elements (128) and a radially outer low flow framing channel elem...

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Bibliographische Detailangaben
Hauptverfasser:	GOLSEN MATTHEW J, MCDONALD WAYNE J, MARSH JAN H
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	BLASTING CASTING ENGINE PLANTS IN GENERAL FOUNDRY MOULDING HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PERFORMING OPERATIONS POWDER METALLURGY STEAM ENGINES TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	The present disclosure provides a core structure comprising a trailing edge section including a plurality of rib-forming apertures (126) defined by a plurality of radially-extending channel elements (130) and axially-extending passage elements (128) and a radially outer low flow framing channel element (134) located adjacent to a radially outer edge (124). The core structure may be used for casting a gas turbine engine airfoil (11). The radially outer framing channel element (134) comprises a plurality of notches (14) extending radially inwardly from the radially outer edge (124). A distal portion (144a) of the notches (140) overlaps in an axial direction with the rib-forming apertures (126) of a first axially-aligned outer row (138a). A radial height of at least one of a first and a second axially-extending passage element (148a, 148b, 150) is greater than a prevalent radial height of other axially-extending passage elements (128) in the core structure. 本公开提供了种包括后缘部段的型芯结构，其中，后缘部段包括由多个径向延伸通道单元(130)和轴向延伸通道单元(1