Exhaust nozzle arrangement for geared turbofan
AssigneeUnited Technologies Corporation
InventorsFrederick M. Schwarz, Robert E. Malecki
Life of this patent
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Abstract
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 section configured to drive the geared architecture. The turbine section has an exit point, and a diameter (Dt) defined as the outer diameter of a last blade airfoil stage in the turbine section at the exit point. A nacelle surrounds a core engine housing. The fan is configured to deliver air into a bypass duct defined between the nacelle and the core engine housing. A core engine exhaust nozzle is downstream of the exit point. A downstream most point of the core engine exhaust nozzle is defined at a distance (Lc or Ln) from the exit point.
Claims19
A propulsion system, comprising:
- a geared architecture that drives a fan section including a fan, said fan including a plurality of fan blades;
- a turbine section that drives said geared architecture, said turbine section having an exit point, and a diameter (Dt) defined as the outer diameter of a last blade airfoil stage in said turbine section at said exit point;
- a nacelle surrounding a core engine housing, said fan that delivers air into a bypass duct defined between said nacelle and said core engine housing;
- 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 1.30;
- wherein said ratio is less than or equal to 1.64;
- and
- wherein said core engine exhaust nozzle includes a plug, said downstream most point of said core engine exhaust nozzle is defined by a downstream end of said plug.
A propulsion system, comprising:
- a geared architecture that drives a fan section including a fan, said fan including a plurality of fan blades;
- a turbine that drives said geared architecture, said turbine having an exit point, and a diameter (Dt) defined as the outer diameter of a last blade airfoil stage in said turbine at said exit point;
- a nacelle surrounding a core engine housing, said fan delivers air into a bypass duct defined between said nacelle and said core engine housing;
- a core engine exhaust nozzle downstream of said exit point, said core engine exhaust nozzle including a plug;
- and
- wherein a downstream most point of said core engine nozzle is defined by a downstream end of said plug at a distance (Lc) from said exit point, and a ratio of said distance (Lc) to said diameter (Dt) is between 1.30 and 1.64.
A propulsion system, comprising:
- a geared architecture that drives a fan section including a fan, said fan including a plurality of fan blades;
- a turbine section including a first turbine that drives a first compressor and a fan drive turbine that drives said geared architecture, said turbine section having an exit point, and a diameter (Dt) defined as the outer diameter of a last blade airfoil stage in said fan drive turbine at said exit point;
- a nacelle surrounding a core engine housing, said core engine housing surrounding at least said turbine section and said first compressor, said fan delivers air into a bypass duct defined between said nacelle and said core engine housing;
- a core engine exhaust nozzle downstream of said exit point, said core engine exhaust nozzle including an inner periphery disposed about a plug;
- and
- wherein a downstream most point of said core engine nozzle is defined by a downstream end of said plug at a distance (Lc) from said exit point, and a ratio of said distance (Lc) to said diameter (Dt) is between 1.30 and 1.64.
Dependencies are inferred from the claim text.