Heatshield for a gas turbine engine
AssigneeSiemens Energy Global GmbH & Co. KG
InventorsMats Kinell, Petr Laletin, Sara Rabal Carrera
Life of this patent
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Abstract
A heatshield for a gas turbine engine includes a main body having a leading edge, a trailing edge, lateral edges, a first surface and a second surface, the first surface being exposed to a hot working gas in use passing through the gas turbine engine. The main body having an array of cooling channels for conveying a coolant flow, where each cooling channel of the array of cooling channels having a surface. At least one cooling channel of the array of cooling channels includes at least one flow disturbing feature extending from the surface and into the cooling channel.
Claims20
A heatshield for a gas turbine engine, comprising:
- a main body having a leading edge, a trailing edge, lateral edges, a first surface and a second surface, the first surface being exposed to a hot working gas in use passing through the gas turbine engine,
- the main body having an array of cooling channels for conveying a coolant flow, each cooling channel of the array of cooling channels having a surface,
- wherein at least one cooling channel of the array of cooling channels comprises at least one flow disturbing feature extending from the surface and into the cooling channel,
- wherein the at least one flow disturbing feature comprises a cross-sectional shape of a convex polygon, and
- wherein the cross-sectional shape comprises a diagonal line between opposite corners of the cross-sectional shape, and the diagonal line is in-line with a longitudinal extent of the cooling channel.
Dependencies are inferred from the claim text.