发明名称 Thermal screen device for the housing of a turbine to control blade tip clearance
摘要 The stator has a metallic sealing ring support (11) connecting a sealing ring (13) to a high pressure turbine casing (9). The support has a thermal screen element that is arranged at side of a high pressure turbine. The support is fixed to the casing by a radial transversal clamping plate (11c). The element has metallic sheets (21, 22) that arrange space (21a) with surface of the support, where the space i.e. dead cavity, is made of thermally insulating material, and the support is in form of tapered metallic warp e.g. annular ferrule.
申请公布号 EP1903186(B1) 申请公布日期 2017.01.25
申请号 EP20070116773 申请日期 2007.09.19
申请人 Safran Aircraft Engines 发明人 Philippot, Vincent
分类号 F01D11/18 主分类号 F01D11/18
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