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Blade arrangement, particularly guide vane arrangement, for rotating turbo-engine, particularly turbine, has blade root, which has upstream blade root front edge and downstream blade root rear edge
Blade arrangement, particularly guide vane arrangement, for rotating turbo-engine, particularly turbine, has blade root, which has upstream blade root front edge and downstream blade root rear edge
The blade arrangement has a blade root, which has an upstream blade root front edge and a downstream blade root rear edge, where at the edges an attachment hook is provided, which is inserted into an receptacle groove of a component of a turbo-engine and which has two blade root sides laterally connecting the front edge and rear edge of the blade root with each other. A structure (9) that is wrapped around the blade root side laterally in peripheral direction is provided along one of the blade root sides and on the other blade root side a support surface is provided.
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