US 7,055,306 B2 · Combined stage single shaft turbofan engine

Abstract

A turbofan engine includes a combined stage rotor mounted for common rotation with a shaft, a compressor stage, and a turbine stage. Each of the plurality of fan blades of the combined stage rotor are contiguous with a respective compressor blade. The combined stage rotor is located at a junction between a fan bypass duct and a core duct. The fan bypass stage portion includes a plurality of the fan blades which communicate incoming airflow into fan bypass airflow through the fan bypass duct. The compressor stage portion includes a plurality of the compressor blades which communicated airflow into core airflow through the core duct. The plurality of fan blades extend substantially perpendicular to the plurality of compressor blades such that the plurality of compressor blade portions extend at least partially into the core duct and preferably will include splitters for enhanced efficiency.

Claims26

Dependent claims

A combined stage rotor blade for a turbofan engine comprising:

a first rotor blade portion which communicates airflow toward a fan bypass section of the turbofan;
and
a second rotor blade portion contiguous and at least partially transverse with said first rotor blade portion, said second rotor blade portion communicates airflow toward a core section of the turbofan.

Dependencies are inferred from the claim text.

Combined stage single shaft turbofan engine

Life of this patent

Combined stage single shaft turbofan engine

Life of this patent

Abstract

Claims26