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公开(公告)号：US20190107046A1
公开(公告)日：2019-04-11
申请号：US15725327
申请日：2017-10-05
Applicant: General Electric Company
Abstract: An apparatus and method relating to a turbine engine with an annular frame about a centerline defining an axial direction, the annular frame formed from an inner frame wall and an outer frame wall disposed around and radially spaced from the inner frame wall to define an annular airflow passage between the inner and outer frame walls. The annular frame further includes at least two struts each extending between a root at the inner frame wall and a tip at the outer frame wall to define a span-wise direction.
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公开(公告)号：US20170106991A1
公开(公告)日：2017-04-20
申请号：US14886262
申请日：2015-10-19
Applicant: General Electric Company
Inventor： Adam Wayne Clark , Richard David Cedar , David Baker Riddle
CPC classification number: B64D33/02 , B64C11/14 , B64D2033/0286 , F01D5/02 , F01D25/24 , F02C7/04 , F05D2220/323 , F05D2240/20 , F05D2250/232 , F05D2250/51 , Y02T50/671
Abstract: 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 section may have cambered or an elliptical axially curved cross-section. Spinner axial cross-section may have longer spinner axial distance compared to baseline axial distance of baseline cross-section and spinner aspect ratio greater than baseline aspect ratio of baseline cross-section.
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