초록 ▼

An airfoiled blade is disclosed which comprises a plurality of airfoil sections, a root portion, and a tip portion. Each section has along substantially the entire length thereof a cross-sectional airfoil shape characterized by a parabolic leading edge, a front loading and a blunt trailing edge. Eac

An airfoiled blade is disclosed which comprises a plurality of airfoil sections, a root portion, and a tip portion. Each section has along substantially the entire length thereof a cross-sectional airfoil shape characterized by a parabolic leading edge, a front loading and a blunt trailing edge. Each of the airfoil sections has a chord passing therethrough with a 50% point and a maximum thickness forward of the 50% point, toward the leading edge. A thickness ratio range from a first of the airfoil sections nearest the tip portion to a last of the airfoil sections nearest the root portion of substantially 3% to 28% is preferred. In one embodiment, the blade further includes a second airfoil section, a third airfoil section and a fourth airfoil section located between the first and last airfoil sections. The first airfoil section has a thickness ratio of substantially 3.3%, the second airfoil section has a thickness ratio of substantially 4.1%, the airfoil section has a thickness ratio of substantially 7.3%, the fourth airfoil section has a thickness ratio of substantially 14.3%, and the last airfoil section has a thickness ratio of substantially 27.4%.

대표청구항 ▼

[ We claim:] [1.] A blade having a plurality of airfoil sections, a base portion, and a tip portion, comprising:each airfoil section having along substantially the entire length thereof a cross-sectional airfoil shape characterized by a parabolic leading edge, a front loading and a blunt trailing ed

[ We claim:] [1.] A blade having a plurality of airfoil sections, a base portion, and a tip portion, comprising:each airfoil section having along substantially the entire length thereof a cross-sectional airfoil shape characterized by a parabolic leading edge, a front loading and a blunt trailing edge, wherein each of said airfoil sections has a chord passing therethrough with a 50% point and a maximum thickness forward of said 50% point and toward said leading edge; anda thickness ratio range from a first of said airfoil sections nearest said tip portion to a last of said airfoil sections nearest said root portion of substantially 3% to 28%.