Low noise blades for axial flow compressors

Details Low noise blades for axial flow compressors Low noise blades for axial flow compressors

1975-09-10

1977-03-15

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Tined or irregular periphery

416223A, F04D 2938

Patent

active

040121720

ABSTRACT:
A rotor blade configuration is disclosed which greatly reduces noise generated by the low pressure compressor, or fan, of a turbofan engine. The leading edge of the blade is swept forwardly from its hub up to a point of sweep reversal and then swept rearwardly to the tip of the blade. The slope of the curved leading edge line relative to the direction of airflow is gradually decreased from the hub to the tip to maintain the velocity component, of air relative to the blade leading edge, subsonic, while the relative velocity of the air to the blade is above a critical value and supersonic. This substantially eliminates noise producing, standing shock waves along the blade leading edges. Also described are methods for determining the configuration of such blades to obtain these ends with a minimum increase in blade weight and a minimum blade bending and blade attachment stresses.

REFERENCES:
patent: 2160467 (1939-05-01), Ward
patent: 2359466 (1944-10-01), Currie
patent: 2663493 (1953-12-01), Keast
patent: 2839239 (1958-06-01), Stalker
patent: 2841325 (1958-07-01), Weise
patent: 3347520 (1967-10-01), Owczarek
patent: 3467197 (1969-09-01), Spivey et al.
patent: 3972646 (1976-08-01), Brown et al.

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