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특허 상세정보

Stable blade vibration damper for gas turbine engine

특허상세정보
국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F01D-005/26   
미국특허분류(USC) 416/219R ; 416/500
출원번호 US-0308181 (1994-09-19)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 53  인용 특허 : 0
초록

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 pr...

대표
청구항

A stage of a rotor of a gas turbine engine comprising: a rotatable disk having a plurality of contoured slots in a rim portion thereof defined by a common number of contoured disk posts; a common number of blades having complementarily shaped dovetails disposed in said contoured slots, said blades having platform portions extending therefrom in circumferential and axial directions forming a substantially contiguous flowpath surface disposed radially outwardly from said disk rim; and at least one blade-to-blade vibration damper disposed in a cavity bounde...

이 특허를 인용한 특허 피인용횟수: 53

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  20. Theuer, Andre; Palys, Dariusz Oliwiusz; Imfeld, Jost. Method and apparatus for gas turbine combustor inner cap and high frequency acoustic dampers. USP20190310220474.
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  22. Honkomp,Mark Steven; Barrett,Joseph Scott. Methods and apparatus for assembling gas turbine engine rotor assemblies. USP2006087090466.
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  33. Deallenbach, Robert Edward; Nair, Ravichandran Pazhur; Lupe, Douglas Arthur. System and method for securing axially inserted buckets to a rotor assembly. USP2017049624780.
  34. Kray, Nicholas Joseph; Van Nieuwenhove, Stefaan Guido; Baehmann, Peggy Lynn. System for composite marine propellers. USP2017069682756.
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  36. Liang, George. Turbine airfoil cooling system with platform edge cooling channels. USP2010077762773.
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