A gas turbine engine is provided. The gas turbine engine includes a turbomachine (104); a fan section (102) including a fan (126) rotatable by the turbomachine (104); a nacelle (134) enclosing the fan (126); and an engine controller (150) positioned within the nacelle (134), wherein the nacelle (134) defines an inner surface radius (r) along the radial direction (R) inward of the engine controller (150), wherein the engine controller (150) defines a radial height (Δr) along the radial direction (R), a total volume (V), and a normalized radius (r'), wherein the normalized radius (r') is a ratio of the inner surface radius (r) to the total volume (V) to cube root, and wherein these parameters are related by the following equation: 0.1r′−1<Δrr


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    Title :

    Engine controller for a gas turbine engine


    Contributors:

    Publication date :

    2023-08-29


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64C AEROPLANES , Flugzeuge / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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