General Electric Company

Daniel John Oehrle

Randy M Vondrell

John Carl Glessner

Mark Edward Linz

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 (D) in the 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 the 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). The CDR is between 2.7 and 3.5 and the CLR is between 0.25 and 0.50.

Gas turbine engine

A gas turbine engine includes a turbomachine defining a core flowpath extending through a first compressor and a second compressor, wherein a first compressor frame defines a compressor bypass passage extending from the core flowpath at the first compressor frame; and a forward compressor frame positioned between the first compressor and the second compressor, wherein the forward compressor frame defines at least in part a second portion of the core flowpath at a location downstream of the first portion of the core flowpath, wherein the forward compressor frame defines a compressor bleed passage extending from the core flowpath at a location downstream of the first compressor and upstream of the second compressor to egress a flow of air away from the core flowpath.

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West Chester, OH, United States of America

Daniel John Oehrle