Axial compressor blading

An axial compressor has at least one circumferential row of aerofoil members ( 30 a , 30 b , 30 c) in which at least one of the two end walls ( 37 ) between adjacent blades is given a non-axisymmetric profile, defined by circumferentially-extending sinusoids at a number of axial positions (AA, BB, C...

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Bibliographic Details
Main Author HARVEY NEIL W
Format Patent
LanguageEnglish
Published 15.03.2007
Subjects
BLASTING
ENGINE PLANTS IN GENERAL
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MARINE PROPULSION OR STEERING
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
PERFORMING OPERATIONS
RELATED EQUIPMENT
SHIPS OR OTHER WATERBORNE VESSELS
STEAM ENGINES
TRANSPORTING
WEAPONS
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Summary:An axial compressor has at least one circumferential row of aerofoil members ( 30 a , 30 b , 30 c) in which at least one of the two end walls ( 37 ) between adjacent blades is given a non-axisymmetric profile, defined by circumferentially-extending sinusoids at a number of axial positions (AA, BB, CC). Corresponding points on the successive sinusoids are joined by spline curves, so that the curvature of the end wall is smooth. This end-wall profiling modifies the boundary layer flow at the wall, reducing or eliminating the corner separation and reversed flow associated with known arrangements.
Bibliography:Application Number: US20060504697