发明名称 Dispenser for a high-pressure turbine of a jet engine
摘要 <p>A high temperature turbine nozzle with automatic regulation of flow of cooling air passing therethrough. Each of vanes includes a first sleeve drilled with holes and a second sleeve that is engaged in the first sleeve, drilled with corresponding holes, and made of a material possessing a coefficient of expansion different from that of the first sleeve.</p>
申请公布号 GB201211902(D0) 申请公布日期 2012.08.15
申请号 GB20120011902 申请日期 2011.01.06
申请人 SNECMA 发明人
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