Aircraft gas turbine engine (10) spinner (50) includes conical forward section (60) extending aftwardly from spinner tip (54) to a curved aft spinner section (62) circumscribed about centerline axis (30), a spinner aspect ratio (A/R) greater than 1.8. Aspect ratio (A/R) may be in a range of about 2.0 - 2.2 or about 2.2 - 2.8. Aft spinner section (62) may be substantially tangential to platform leading edges (37) of platforms (35) of fan blades (18). Aft spinner section (62) may have cambered or an elliptical axially curved cross-section. Spinner axial cross-section (B1-B3) may have longer spinner axial distance (A1-A3) compared to baseline axial distance (A0) of baseline cross-section (B0) and spinner aspect ratio (A/R) greater than baseline aspect ratio (A/R0) of baseline cross-section (B0).
IMPROVED CROSSWIND PERFORMANCE AIRCRAFT ENGINE SPINNER
FLUGZEUGTRIEBWERKSPINNER MIT VERBESSERTER QUERABFLUGSLEISTUNG
CÔNE DE MOTEUR D'AÉRONEF À PERFORMANCE AMÉLIORÉE PAR VENT LATÉRAL
2018-04-11
Patent
Electronic Resource
English