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
Engine controller for a gas turbine engine
2023-08-29
Patent
Electronic Resource
English
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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