Propeller fan
In a blade of a propeller fan, a position on a chord line where the camber becomes maximum is set as a maximum camber position A, and a ratio of a distance d between a leading edge and the maximum camber position A to a chord length c is set as a maximum camber position ratio. The end portion on the hub side of the blade is set as a blade root, and the end portion on the outer circumferential side of the blade is set as a blade end. In the blade, the maximum camber position ratio monotonically increases in the direction from the reference blade cross section located between the blade root and the blade end toward the blade end and becomes maximum at the blade end. Thus, fan efficiency of the propeller fan is improved.
1. A propeller fan, comprising a hub formed into a cylindrical shape, and a plurality of blades extending outwardly from a side surface of the hub, wherein
each of the plurality of blades is configured such that
a distance from a chord line to a mean line in a blade cross section is set as a camber, that in the blade cross section,
a position on the chord line where the camber becomes maximum is set as a maximum camber position, that
a ratio of a distance between a leading edge and the maximum camber position in the blade cross section to a chord length is set as a maximum camber position ratio, that
an end portion at a hub side of each of the plurality of blades is set as a blade root, that
an end portion of an outer circumferential side of the each of the plurality of blades is set as a blade end, and that
the maximum camber position ratio at the blade end is larger than the maximum camber position ratio at the blade root,
wherein the maximum camber position ratio is minimum at a first reference blade cross section located between the blade root and the blade end.
2. The propeller fan of claim 1 , wherein
each of the plurality of blades is configured such that
the maximum camber position ratio monotonically increases in the direction from the first reference blade cross section and the blade end toward the blade end and becomes maximum at the blade end.
3. The propeller fan of claim 2 , wherein
each of the plurality of blades is configured such that a distance from the blade root to the first reference blade cross section is shorter than a distance from the blade end to the first reference blade cross section.
4. The propeller fan of claim 2 , wherein
each of the plurality of blades is configured such that the maximum camber position ratio in the blade cross section is equal to or greater than 0.5 to equal to or less than 0.8.
5. The propeller fan of claim 2 , wherein
each of the plurality of blades is configured such that
a maximum value of the camber in the blade cross section is set as a maximum camber, that
a ratio of the maximum camber to the chord length in the blade cross section is set as a camber ratio, that
the camber ratio becomes maximum in a second reference blade cross section located between the blade root and the blade end, monotonically decreases in the direction from the second reference blade cross section toward the blade root, and monotonically decreases in the direction from the second reference blade cross section toward the blade end, and that
the first reference blade cross section serves as the second reference blade cross section.
6. The propeller fan of claim 5 , wherein
each of the plurality of blades is configured such that the camber ratio at the blade end is smaller than the camber ratio at the blade root.
7. The propeller fan of claim 1 , wherein
each of the plurality of blades is configured such that
a maximum value of the camber in the blade cross section is set as a maximum camber, that
a ratio of the maximum camber to the chord length in the blade cross section is set as a camber ratio, and that
the camber ratio becomes maximum in a second reference blade cross section located between the blade root and the blade end, monotonically decreases in the direction from the second reference blade cross section toward the blade root, and monotonically decreases in the direction from the second reference blade cross section toward the blade end.
8. The propeller fan of claim 7 , wherein
each of the plurality of blades is configured such that the camber ratio at the blade end is smaller than the camber ratio at the blade root.
9. A propeller fan, comprising a hub formed into a cylindrical shape, and a plurality of blades extending outwardly from a side surface of the hub, wherein
each of the plurality of blades is configured such that
a distance from a chord line to a mean line in a blade cross section is set as a camber, that in the blade cross section,
a position on the chord line where the camber becomes maximum is set as a maximum camber position, that
a ratio of a distance between a leading edge and the maximum camber position in the blade cross section to a chord length is set as a maximum camber position ratio, that
an end portion at a hub side of each of the plurality of blades is set as a blade root, that
an end portion of an outer circumferential side of the each of the plurality of blades is set as a blade end, and that
the maximum camber position ratio at the blade end is larger than the maximum camber position ratio at the blade root, wherein
each of the plurality of blades is configured such that the maximum camber position ratio becomes maximum in an intermediate blade cross section located between the blade root and the blade end.
10. The propeller fan of claim 9 , wherein
each of the plurality of blades is configured such that the maximum camber position ratio becomes minimum at the blade root and monotonically increases in the direction from the blade root toward the intermediate blade cross section.
11. The propeller fan of claim 9 , wherein
each of the plurality of blades is configured such that a distance from the blade root to the intermediate reference blade cross section is longer than a distance from the blade end to the intermediate reference blade cross section.
12. The propeller fan of claim 9 , wherein
each of the plurality of blades is configured such that
a maximum value of the camber in the blade cross section is set as a maximum camber, that
a ratio of the maximum camber to the chord length in the blade cross section is set as a camber ratio, and that
the camber ratio becomes maximum in a second reference blade cross section located between the blade root and the blade end, monotonically decreases in the direction from the second reference blade cross section toward the blade root, and monotonically decreases in the direction from the second reference blade cross section toward the blade end.
13. The propeller fan of claim 12 , wherein
each of the plurality of blades is configured such that the camber ratio at the blade end is smaller than the camber ratio at the blade root.