公开(公告)号：US20180216576A1

公开(公告)日：2018-08-02

申请号：US15293358

申请日：2016-10-14

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Mark John Laricchiuta ,  Daniel Robert Dwyer ,  Jeffrey Donald Clements ,  Kenneth Scheffel ,  Thomas Ory Moniz

IPC: F02K3/075 ,  B64D29/00

CPC classification number: F02K3/075 ,  B64D29/00 ,  F02K3/06 ,  F05D2220/80 ,  F05D2260/96

Abstract: A supersonic turbofan engine includes a fan section having a single-stage fan defining a fan pressure ratio greater than 1.9. The supersonic turbofan engine also includes a core turbine engine defining a core air flowpath. A nacelle at least partially surrounds the fan of the fan section and the core turbine engine. The supersonic turbofan engine defines a bypass ratio, the bypass ratio being greater than or equal to three.