|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||415/119; 415/229; 384/536|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 11 인용 특허 : 31|
A dampening system for a miniature high-speed turbojet engine provides single or multiple resilient mountings 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.
1. A rotor system for a miniature gas turbine engine comprising:an engine housing portion having a groove;a resilient member mounted within said groove;a bearing mounted adjacent said resilient member;a shaft rotationally mounted within said bearing;a compressor supported upon said shaft, said compressor facing forward toward an inlet; anda turbine supported upon said shaft, said turbine facing rearward toward an exhaust.2. The rotor system as recited in claim 1, wherein said resilient member comprises an elastomeric member.3. The rotor system as recited...