An exhaust vane (26) disposed in a divergent section (13) of an aircraft gas turbine engine exhaust nozzle (10) is sideways pivotable about a vane pivot axis (28). The nozzle vane pivot axis (28) may be centrally located at an unvectored nozzle throat (18). Transversely spaced apart upper and lower tips (24, 25) of the exhaust vane (26) may be incorporated to sealingly engage a nozzle outer wall (23) along upper and lower surfaces (35, 37) of the outer wall (23) of the nozzle. The exhaust vane (26) has flat or contoured vane sidewalls (20) and contoured vane sidewalls (20) may be concave. The exhaust vane (26) may have transversely biased apart upper and lower vane sections (29, 30) extending transversely inwardly from the upper and lower tips (24, 25) of the exhaust vane (26) respectively. The exhaust vane may be articulated having upstream and downstream sections (32, 34) separately sideways pivotable about the vane pivot axis (28) and a second pivot axis (38) downstream of and parallel to the vane pivot axis (28) respectively.


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    Title :

    NOZZLE WITH YAW VECTORING VANE


    Additional title:

    TUYERE AVEC AUBE FIXE A GUIDAGE DE LACET


    Contributors:

    Publication date :

    2015-07-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    Vectoring exhaust nozzle technology

    BARNES, G. / CURRY, S. / WOOD, A. | AIAA | 1984




    Computation of vectoring nozzle performance

    CHEATHAM, P. / WALKER, S. / GRIDLEY, M. | AIAA | 1990


    Computation of vectoring nozzle performance

    CHEATHAM, PATRICK L. / WALKER, STEVEN H. / GRIDLEY, MARVIN C. | AIAA | 1991