GAS TURBINE ENGINE

Abstract: a gas turbine engine comprises a turbomachine having an unducted primary fan, a core engine a combustor casing enclosing a combustor, a core cowl surrounding at least a portion of the core engine and a fluid distribution assembly. the outer surface of the core cowl defines a peak cowl diameter (d) in a radial direction, and the outer surface of the combustor casing defines a maximum combustor casing diameter (d) along the radial direction. the core engine defines an overall core axial length (l) along an axial direction and an under-core cowl axial length (l) along the axial direction. the gas turbine engine defines a core cowl diameter ratio (cdr) equal to the peak cowl diameter (d) divided by the maximum combustor casing diameter (d) and a core cowl length ratio (clr) equal to the under-core cowl axial length (l) divided by the overall core axial length (l).

Inventor(s): Daniel John Oehrle, Randy M. Vondrell, Apolinario Barra Ruiz

CPC Classification: F02C7/32 (Arrangement, mounting, or driving, of auxiliaries)

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