|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F01D-005/02 B64D-033/02 F01D-025/24 F02C-007/04 B64C-011/14|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 12|
Aircraft gas turbine engine spinner includes conical forward spinner section extending aftwardly from spinner tip to a curved aft spinner section circumscribed about centerline axis, a spinner aspect ratio greater than about 1.8, and wherein spinner aspect ratio is an axial distance between spinner tip and spinner end divided by radial distance from axis to spinner end. Aspect ratio may be in a range of about 2.0-2.2 or about 2.2-2.8. Aft spinner section may be substantially tangential to platform leading edges of platforms of fan blades. Aft spinner sec...
1. A spinner for mounting to a rotor of an aircraft gas turbine engine, the spinner comprising: a conical upstream or forward spinner section extending aftwardly from a spinner tip, the conical upstream or forward spinner section having a decreasing slope which transitions directly into a convex downstream or aft spinner section, the convex downstream or aft spinner section initially having a decreasing slope and subsequently having an increasing slope extending aftwardly to a spinner end which transitions directly into a leading edge of a fan blade plat...