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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    Title :

    CROSSWIND PERFORMANCE AIRCRAFT ENGINE SPINNER


    Contributors:

    Publication date :

    2017-04-20


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



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    IMPROVED CROSSWIND PERFORMANCE AIRCRAFT ENGINE SPINNER

    CLARK ADAM WAYNE / CEDAR RICHARD DAVID / RIDDLE DAVID BAKER | European Patent Office | 2019

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    IMPROVED CROSSWIND PERFORMANCE AIRCRAFT ENGINE SPINNER

    CLARK ADAM WAYNE / CEDAR RICHARD DAVID / RIDDLE DAVID BAKER | European Patent Office | 2018

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    Aircraft Crosswind Performance

    J. F. O'Gara | NTIS | 1964


    Aircraft crosswind performance

    O'Gara, J.F. | Engineering Index Backfile | 1964