EXHAUST NOZZLE ARRANGEMENT FOR GEARED TURBOFAN

摘要

A propulsion system according to an example of the present disclosure includes, among other things, a geared architecture configured to drive a fan section including a fan, and a turbine configured to drive the geared architecture. The turbine has an exit point, and a diameter (Dt) defined as the radially outer diameter of a last blade airfoil stage in the turbine at the exit point. A nacelle at least partially surrounds a core engine housing. The fan configured to deliver air into a bypass duct is defined between the nacelle and the core engine housing. A core engine exhaust nozzle is downstream of the exit point, with a downstream most point of the core engine exhaust nozzle being defined at a distance (Lc or Ln) from the exit point.

主权项

1. A propulsion system, comprising:
a geared architecture configured to drive a fan section including a fan; a turbine configured to drive said geared architecture, said turbine having an exit point, and a diameter (Dt) defined as the radially outer diameter of a last blade airfoil stage in said turbine at said exit point; a nacelle at least partially surrounding a core engine housing, said fan configured to deliver air into a bypass duct defined between said nacelle and said core engine housing; and a core engine exhaust nozzle downstream of said exit point, with a downstream most point of said core engine exhaust nozzle being defined at a distance (Lc or Ln) from said exit point, wherein a ratio of said distance (Lc or Ln) to said diameter (Dt) is greater than or equal to about 0.90.