Aerofoil members for gas turbine engines

Details Aerofoil members for gas turbine engines Aerofoil members for gas turbine engines

1996-02-09

1997-06-24

Kwon, John T.

Rotary kinetic fluid motors or pumps

Working fluid passage or distributing means associated with...

Plural distributing means immediately upstream of runner

416223A, 416DIG5, F01D 900

Patent

active

056412681

ABSTRACT:
Aerofoil members such as the stator vanes and rotor blades of an axial flow compressor are defined by a number of nominal sections. The leading edge of each nominal section of the blade is set so that an airflow passing therethrough is incident at the optimum angle. The optimum angle is chosen so that the maximum velocities of the airflow at the leading edge are equal. Once the optimum angle has been found for each section of the blade the sections are stacked to define a blade having a leading edge the aerodynamic profile of which ensures that the airflow is incident at the optimum angle along the length of the blade from the root to the tip. The efficiency of the axial flow compressor is improved.

REFERENCES:
patent: 4686796 (1987-08-01), Giebmanns
patent: 4720239 (1988-01-01), Owczarek
patent: 4900230 (1990-02-01), Patel
patent: 5393198 (1995-02-01), Noda et al.

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