发明名称 ROTOR DAMPER
摘要 A rotor stage (100) of a gas turbine engine (10) comprises a platform (120) from which rotor blades extend. The platform is provided with a circumferentially extending damper ring (200), the damper ring having an engagement surface (210) that engages with a platform engagement surface (110) of the platform (120). The platform engagement surface (110) and the damper engagement surface (210) can move relative to each other in the radial direction. In use, the damper engagement surface (210) moves less in the radial direction than the platform engagement surface (110) in response to diametral mode excitation. This causes friction between the two surfaces, thereby dissipating energy and damping the excitation.
申请公布号 EP3112588(A2) 申请公布日期 2017.01.04
申请号 EP20160161162 申请日期 2016.03.18
申请人 Rolls-Royce plc 发明人 Edwards, Garry
分类号 F01D5/10;F01D5/16;F01D5/30;F01D5/34 主分类号 F01D5/10
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