|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||415/119; 415/229; 415/231|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 4 인용 특허 : 32|
A dampening system for a miniature high-speed turbojet engine provides single or multiple resilient mounting which includes a seal with an at least partially encapsulated spring for forward and aft bearings which mount a rotor shaft. The self-induced first engine order of the rotating rotor shaft is transmitted through the forward and aft bearing and is then absorbed in the resilient mountings. Dependable seal and vibration reduction is thereby provided irrespective of long term storage.
1. A dampening system for a miniature gas turbine engine comprising:a resilient member mounted between a bearing and a static structure of the gas turbine, said resilient member comprising a seal with an at least partially encapsulated spring.2. The dampening system as recited in claim 1, wherein said seal comprises a resilient C-shaped member in cross-section.3. The dampening system as recited in claim 1, wherein a coil of said spring is canted.4. The dampening system as recited in claim 1, wherein said resilient member is mounted within a groove formed...