发明名称 Stable blade vibration damper for gas turbine engine
摘要 An improved, highly stable blade-to-blade vibration damper configuration which provides substantially continuous blade vibration damping and sealing of an interplatform gap due to positional stability thereof. Disposed in a subplatform cavity, the damper is comprised of a generally triangular shaped body having a vertex thereof aligned with the interplatform gap. A primary damper load face abuts a first inclined platform load face and a secondary damper load face abuts a second inclined platform load face. Maintenance of sliding planar contact between primary and first load faces and sliding linear contact between secondary and second load faces is afforded by orienting inclined platform faces to have an included angle greater than that of the damper vertex and offsetting a damper center of gravity toward the primary load face. The damper may include one or more legs to orient the damper in the cavity and one or more extending tabs to discourage hot gas flow thereby. In a preferred embodiment, the damper is utilized as an as-cast member, without the need for additional processing or machining, and the vertex included angle is greater than about 90 degrees.
申请公布号 US5478207(A) 申请公布日期 1995.12.26
申请号 US19940308181 申请日期 1994.09.19
申请人 GENERAL ELECTRIC COMPANY 发明人 STEC, PHILIP F.
分类号 F01D5/22;F01D11/00;(IPC1-7):F01D5/26 主分类号 F01D5/22
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