Patent ID: 9574518
Date: 2017-02-21
CPC Classifications: B64D,F02K,F05D

Claim:
1. A turbofan engine comprising: a core engine with a core engine shroud and a core exhaust duct; a nacelle radially surrounding at least a fore portion of the core engine; a bypass duct defined between the nacelle and the core engine shroud; a bypass splitter shell substantially coaxial with the nacelle and the core engine, wherein the bypass splitter shell includes a trailing edge outside of the nacelle and a leading edge that extends into the bypass duct to define a peripheral bypass duct between the bypass splitter shell and the nacelle, and to define an interstitial bypass duct between the bypass splitter shell and the core engine shroud; and an actuator coupled to the bypass splitter shell and configured to axially translate the bypass splitter shell between an idle configuration with a first inlet area of the interstitial bypass duct and an active configuration with a second inlet area of the interstitial bypass duct, wherein the first inlet area is greater than the second inlet area; wherein the turbofan engine includes an idle state wherein the core engine is operating at ground idle speed and the turbofan engine is in the idle configuration.