Cooling arrangement for a gas turbine component
AssigneesSiemens Aktiengesellschaft, Mikro Systems, Inc.
InventorsCHING-PANG LEE, BENJAMIN E. HENEVELD
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Abstract
A cooling arrangement (82) for a gas turbine engine component, the cooling arrangement (82) having a plurality of rows (92, 94, 96) of airfoils (98), wherein adjacent airfoils (98) within a row (92, 94, 96) define segments (110, 130, 140) of cooling channels (90), and wherein outlets (114, 134) of the segments (110, 130) in one row (92, 94) align aerodynamically with inlets (132, 142) of segments (130, 140) in an adjacent row (94, 96) to define continuous cooling channels (90) with non continuous walls (116, 120), each cooling channel (90) comprising a serpentine shape.
Claims18
A cooling arrangement for a gas turbine engine component, the cooling arrangement comprising a plurality of rows of airfoils, wherein adjacent airfoils within a row define segments of cooling channels, and wherein outlets of the segments in one row align aerodynamically with inlets of segments in an adjacent row to define continuous cooling channels with non continuous walls, each cooling channel comprising a serpentine shape.
A cooling arrangement for a gas turbine engine component, the cooling arrangement comprising:
- a first row of airfoils, wherein adjacent first row airfoils form respective first segments of respective cooling channels;
- and
- a second row of airfoils, wherein adjacent second row airfoils form respective second segments of the respective cooling channels;
- wherein an axial extension of an outlet of each respective first segment aligns with an inlet of the respective second segment to define the respective cooling channel, each comprising a serpentine flow axis.
A gas turbine engine airfoil comprising:
- a trailing edge region comprising a plurality of rows of segment defining structures, wherein adjacent segment defining structures within a row define segments of cooling channels, wherein adjacent segment defining structures of an upstream one of the rows are configured to aerodynamically aim a flow of cooling air exiting the respective segment of the upstream row at an inlet of a respective single adjacent segment of a downstream row, and wherein each cooling channel defines a serpentine flow axis.
The cooling arrangement of claim 15, wherein at least one non-continuous wall of each cooling channel alternates between being defined by a pressure side of an airfoil and a suction side of an airfoil in a direction of flow.
Dependencies are inferred from the claim text.