Casting core for a cooling arrangement for a gas turbine component
AssigneesSiemens Aktiengesellschaft, Mikro Systems, Inc.
InventorsCHING-PANG LEE, BENJAMIN E. HENEVELD
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Abstract
A ceramic casting core, including: a plurality of rows (162, 166, 168) of gaps (164), each gap (164) comprising an airfoil shape; interstitial core material (172) that defines and separates adjacent gaps (164) in each row (162, 166, 168); and connecting core material (178) that connects adjacent rows (170, 174, 176) of interstitial core material (172). Ends of interstitial core material (172) in one row (170, 174, 176) align with ends of interstitial core material (172) in an adjacent row (170, 174, 176) to form a plurality of continuous and serpentine shaped structures each comprising interstitial core material (172) from at least two adjacent rows (170, 174, 176) and connecting core material (178).
Claims20
A ceramic casting core, comprising:
- a plurality of rows of gaps, each gap comprising an airfoil shape;
- interstitial core material that defines and separates adjacent gaps in each row;
- and
- connecting core material that connects adjacent rows of interstitial core material,
- wherein ends of interstitial core material in one row align with ends of interstitial core material in an adjacent row to form a plurality of continuous and serpentine shaped structures each comprising interstitial core material from at least two adjacent rows and connecting core material.
A casting core for manufacturing a gas turbine engine airfoil, the casting core comprising:
- a first row of core flow defining structure gaps for forming a first row of flow defining structures in a cast component, wherein in the cast component, adjacent first row flow defining structures form respective first segments of respective cooling channels;
- and
- a second row of core flow defining structure gaps for forming a second row of flow defining structures in the cast component, wherein in the cast, component adjacent second row flow defining structures form respective second segments of the respective cooling channels;
- wherein in the cast component, 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 cooling channel comprising a serpentine flow axis.
A casting core for manufacturing a gas turbine engine airfoil, the casting core comprising:
- a plurality of rows of flow defining structure gaps for forming a plurality of rows of segment defining structures in a cast component, wherein in the cast component adjacent segment defining structures within a row define segments of cooling channels,
- wherein in the cast component 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 toward an inlet of a respective single segment of a downstream row, and
- wherein in the cast component each cooling channel defines a serpentine flow axis.
Dependencies are inferred from the claim text.