A gas turbine engine defines an axial direction and a radial direction and comprises a turbomachine having an unducted primary fan, a core engine a combustor casing enclosing a combustor and defining an outer surface, a core cowl surrounding at least a portion of the core engine. The outer surface of the core cowl defines a peak cowl diameter in the radial direction, and the outer surface of the combustor casing defines a maximum combustor casing diameter along the radial direction. The core engine defines an overall core axial length along the axial direction and an under-core cowl axial length along the axial direction. The gas turbine engine defines a core cowl diameter ratio equal to the peak cowl diameter divided by the maximum combustor casing diameter and a core cowl length ratio equal to the under-core cowl axial length divided by the overall core axial length.
GAS TURBINE ENGINE
2025-06-19
Patent
Electronic Resource
English