Mixed flow turbine or radial turbine
A mixed flow turbine or radial turbine suppresses a rapid increase in load applied on a leading edge of a blade, and can reduce incidence loss. The mixed flow turbine or radial turbine includes a hub, and a plurality of blades provided on an outer circumference surface of the hub at substantially equal intervals. The camber line of the blade section is convex-curved to the rotational direction side as seen entirely from a leading edge side toward trailing edge side. On a leading edge section of the blade, there is provided an inflected section that is inflected so that a camber line in a sectional surface along the outer circumference surface is concave-curved to the rotational direction side.
1. A mixed flow turbine or a radial turbine comprising:
a hub; and
a plurality of blades provided on an outer circumference surface of the hub at substantially equal intervals, each of the blades having a main section and an inflected section, the inflected section located at a leading edge side of the blade,
wherein the main section of each of the blades is inflected such that a camber line at the main section is convex-curved towards a rotational direction side as seen in a direction of a rotational axis,
wherein the inflected section of each of the blades is inflected such that a camber line at the inflected section in a sectional surface along the outer circumference surface of the hub is concave-curved against the rotational direction side as seen in the direction of the rotational axis,
wherein a rate of change of the camber line at the inflected section towards a circumferential direction including turnover at the inflected section becomes greater as a radial direction position becomes smaller, and
wherein the main section and the inflected section are located on opposite sides of an inflection point, the inflection point being located on a camber line of the blade closer to the leading edge side than a trailing edge side.
2. A mixed flow turbine or a radial turbine according to claim 1 , wherein in a projection of the sectional surface of a leading edge section projected onto a virtual cylindrical surface which is coaxial with the rotational axis, an inflected section is inflected such that a camber line at the inflected section is concave-curved to the rotational direction side.
3. A mixed flow turbine or a radial turbine according to claim 1 , wherein at least an upstream side outer surface and/or a downstream side outer surface in a rotational direction of the inflected section of each of the blades has a thickened section that smoothly increases a thickness of the blade from a leading edge of the blade.
4. A mixed flow turbine or a radial turbine according to claim 1 , wherein the inflected section of each of the blades is configured so that a curvature of the camber line of a cross-section of the blade at the inflected section becomes smaller as the camber line at the inflected section gets closer to an outer diameter side of the blade along a leading edge of the blade from a hub side of the blade.
5. A mixed flow turbine or a radial turbine according to claim 2 , wherein at least an upstream side outer surface and/or a downstream side outer surface in a rotational direction of the inflected section of each of the blades has a thickened section that smoothly increases a thickness of the blade from a leading edge of the blade.
6. A mixed flow turbine or a radial turbine according to claim 2 , wherein the inflected section of each of the blades is configured so that a curvature of the camber line of a cross-section of the blade at the inflected section becomes smaller as the camber line at the inflected section gets closer to an outer diameter side of the blade along the leading edge of the blade from a hub side of the blade.
7. A mixed flow turbine or a radial turbine according to claim 3 , wherein the inflected section of each of the blades is configured so that a curvature of the camber line of a cross-section of the blade at the inflected section becomes smaller as the camber line at the inflected section gets closer to an outer diameter side of the blade along the leading edge of the blade from a hub side of the blade.
8. A mixed flow turbine or a radial turbine according to claim 5 , wherein the inflected section of each of the blades is configured so that a curvature of the camber line of a cross-section of the blade at the inflected section becomes smaller as the camber line at the inflected section gets closer to an outer diameter side of the blade along the leading edge of the blade from a hub side of the blade.
9. A mixed flow turbine or a radial turbine comprising:
a hub; and
a plurality of blades provided on an outer circumference surface of the hub at substantially equal intervals, each of the blades having a main section and an inflected section, the inflected section located at a leading edge side of the blade,
wherein the main section of each of the blades is inflected such that a camber line at the main section is convex-curved towards a rotational direction side as seen in a direction of a rotational axis,
wherein the inflected section of each of the blades is inflected such that a camber line at the inflected section in a sectional surface along the outer circumference surface of the hub is concave-curved against the rotational direction side as seen in the direction of the rotational axis,
wherein the main section and the inflected section are located on opposite sides of an inflection point, the inflection point being located on a camber line of the blade closer to the leading edge side than a trailing edge side, and
wherein the inflected section of each of the blades is configured so that a curvature of the camber line of a cross-section of the blade at the inflected section becomes smaller as the camber line at the inflected section gets closer to an outer diameter side of the blade along a leading edge of the blade from a hub side of the blade.
10. A mixed flow turbine or a radial turbine comprising:
a hub; and
a plurality of blades provided on an outer circumference surface of the hub at substantially equal intervals, each of the blades having a main section and an inflected section, the inflected section located at a leading edge side of the blade,
wherein the main section of each of the blades is inflected such that a camber line at the main section is convex-curved towards a rotational direction side as seen in a direction of a rotational axis,
wherein the inflected section of each of the blades is inflected such that a camber line at the inflected section in a sectional surface along the outer circumference surface of the hub is concave-curved against the rotational direction side as seen in the direction of the rotational axis,
wherein the main section and the inflected section are located on opposite sides of an inflection point, the inflection point being located on a camber line of the blade closer to the leading edge side than a trailing edge side,
wherein in a projection of the sectional surface of a leading edge section projected onto a virtual cylindrical surface which is coaxial with the rotational axis, an inflected section is inflected such that a camber line at the inflected section is concave-curved to the rotational direction side, and
wherein the inflected section of each of the blades is configured so that a curvature of the camber line of a cross-section of the blade at the inflected section becomes smaller as the camber line at the inflected section gets closer to an outer diameter side of the blade along a leading edge of the blade from a hub side of the blade.
11. A mixed flow turbine or a radial turbine comprising:
a hub; and
a plurality of blades provided on an outer circumference surface of the hub at substantially equal intervals, each of the blades having a main section and an inflected section, the inflected section located at a leading edge side of the blade,
wherein the main section of each of the blades is inflected such that a camber line at the main section is convex-curved towards a rotational direction side as seen in a direction of a rotation axis,
wherein the inflected section of each of the blades is inflected such that a camber line at the inflected section in a sectional surface along the outer circumference surface of the hub is concave-curved against the rotational direction side as seen in the direction of the rotational axis,
wherein the main section and the inflected section are located on opposite sides of an inflection point, the inflection point being located on a camber line of the blade closer to the leading edge side than the trailing edge side,
wherein at least an upstream side outer surface and/or a downstream side outer surface in the rotational direction of the inflected section of each of the blades has a thickened section that smoothly increases a thickness of the blade from a leading edge of the blade, and
wherein the inflected section of each of the blades is configured so that a curvature of the camber line of a cross-section of the blade at the inflected section becomes smaller as the camber line at the inflected section gets closer to an outer diameter side of the blade along the leading edge of the blade from a hub side of the blade.
12. A mixed flow turbine or a radial turbine comprising:
a hub; and
a plurality of blades provided on an outer circumference surface of the hub at substantially equal intervals, each of the blades having a main section and an inflected section, the inflected section located at a leading edge side of the blade,
wherein the main section of each of the blades is inflected such that a camber line at the main section is convex-curved towards a rotational direction side as seen in a direction of a rotational axis,
wherein the inflected section of each of the blades is inflected such that a camber line at the inflected section in a sectional surface along the outer circumference surface of the hub is concave-curved against the rotational direction side as seen in the direction of the rotational axis,
wherein the main section and the inflected section are located on opposite sides of an inflection point, the inflection point being located on a camber line of the blade closer to the leading edge side than a trailing edge side,
wherein in a projection of the sectional surface of a leading edge section projected onto a virtual cylindrical surface which is coaxial with the rotational axis, an inflected section is inflected such that the camber line at the inflected section is concave-curved to the rotational direction side,
wherein at least an upstream side outer surface and/or a downstream side outer surface in a rotational direction of the inflected section of each of the blades has a thickened section that smoothly increases a thickness of the blade from a leading edge of the blade, and
wherein the inflected section of each of the blades is configured so that a curvature of the camber line of a cross-section of the blade at the inflected section becomes smaller as the camber line at the inflected section gets closer to an outer diameter side of the blade along the leading edge of the blade from a hub side of the blade.