Turbine wheel with backswept inducer
View Patent ↗An exemplary blade ( 220 ) for a turbine wheel includes an exducer portion with a trailing edge and an inducer portion with a leading edge wherein the inducer portion has a positive local blade angle at the leading edge with respect to the intended direction of rotation of the turbine wheel. An exemplary turbine wheel ( 200 ) includes a plurality of such exemplary blades. Various other exemplary turbine-related technologies are also disclosed.
1. A blade comprising:
an exducer portion with a trailing edge; and
an inducer portion with a leading edge extending between a backplate end at a backplate of a turbine wheel and a shroud end, wherein the inducer portion has positive local blade angles near the leading edge defined with respect to a meridional direction and an intended direction of rotation of the turbine wheel and wherein, to account for mechanical stress associated with the positive local blade angles, the positive local blade angles decrease in value in a direction from the backplate end to the shroud end.
2. The blade of claim 1 wherein the local blade angles near the leading edge comprise positive local blade angles between approximately 10° and approximately 25°.
3. The blade of claim 1 wherein the turbine wheel operates at a blade-jet-speed ratio, U/C value, less than about 0.7.
4. The blade of claim 1 wherein the backplate end of the leading edge and the shroud end of the leading edge are displaced by a wrap angle.
5. The blade of claim 1 wherein the local blade angle is defined by an equation tan(β)=rdΘ/dx m wherein β is the local blade angle, Θ is an angular coordinate defined with respect to a rotational axis of a turbine wheel, and x m is a meridional coordinate.
6. A turbine wheel having a rotational axis, a backplate and a plurality of blades wherein one or more blades includes an inducer portion with a leading edge extending between a backplate end at the backplate and a shroud end, wherein the inducer portion includes positive local blade angles near the leading edge defined with respect to a meridional direction and an intended direction of rotation of the turbine wheel and wherein, to account for mechanical stress associated with the positive local blade angles, the positive local blade angles decrease in value in a direction from the backplate end to the shroud end.
7. The turbine wheel of claim 6 wherein the backplate end of the leading edge and the shroud end of the leading edge are displaced by a wrap angle
8. The turbine wheel of claim 6 wherein the local blade angle is defined by an equation tan(β)=rdΘ/dx m wherein β is the local blade angle, Θ is an angular coordinate defined with respect to the rotational axis, and x m is a meridional coordinate.
9. A method of reducing positive incidence of a turbine wheel blade at blade-jet-speed ratios, U/C values, less than about 0.7 comprising providing a blade with a backswept inducer, wherein the blade comprises a leading edge extending between a backplate end at a backplate of a turbine wheel and a shroud end that comprises positive local blade angles near the leading edge defined with respect to a meridional direction and an intended direction of rotation of the turbine wheel and wherein, to account for mechanical stress associated with the positive local blade angles, the positive local blade angles decrease in value in a direction from the backplate end to the shroud end.
10. The method of claim 9 wherein the backplate end of the leading edge and the shroud end of the leading edge are displaced by a wrap angle.
11. The method of claim 9 wherein the local blade angle is defined by an equation tan(β) =rdΘ/dx m wherein β is the local blade angle, Θ is an angular coordinate defined with respect to a rotational axis of the turbine wheel, and x m is a meridional coordinate.