Throat distribution for a rotor and rotor blade having camber and location of local maximum thickness distribution
A rotor for a compressor includes a hub and a plurality of airfoils having a root, a tip opposite the root and a span that extends from 0% at the root to 100% at the tip. Each of the airfoils is coupled to the hub at the root and is spaced apart from adjacent ones of the airfoils over the span by a throat dimension. The throat dimension has a maximum value at a spanwise location between 60% of the span and 90% of the span of the adjacent ones of the airfoils, and at 10% of the span of the adjacent ones of the airfoils above or below the spanwise location of the maximum value, the throat dimension is less than 97% of the maximum value. The throat dimension at 5% of the span of the adjacent ones of the airfoils is less than 70% of the maximum value.
1. A rotor for a compressor, comprising:
a hub; and
a plurality of airfoils having a root, a tip opposite the root and a span that extends from 0% at the root to 100% at the tip, each of the plurality of airfoils coupled to the hub at the root and spaced apart from adjacent ones of the plurality of airfoils over the span by a throat dimension defined between the adjacent ones of the plurality of airfoils, the throat dimension has a maximum value at a spanwise location between 60% of the span and 90% of the span of the adjacent ones of the plurality of airfoils, at 10% of the span of the adjacent ones of the plurality of airfoils above or below the spanwise location of the maximum value, the throat dimension is less than 97% of the maximum value, and the throat dimension between 90% of the span and the tip of the adjacent ones of the plurality of airfoils has a first value that is less than 70% of the maximum value.
2. The rotor of claim 1 , wherein the throat dimension between the root and 20% of the span of the adjacent ones of the plurality of airfoils has a second value that is less than 60% of the maximum value.
3. The rotor of claim 2 , wherein the throat dimension between the root and 20% of the span of the adjacent ones of the plurality of airfoils has a second value, and the second value is less than the first value.
4. The rotor of claim 3 , wherein the second value is between the root and 5% of the span of the adjacent ones of the plurality of airfoils.
5. The rotor of claim 1 , wherein the maximum value is between about 70% and 80% of the span of the adjacent ones of the plurality of airfoils.
6. The rotor of claim 1 , wherein the throat dimension decreases from the maximum value to the tip.
7. The rotor of claim 1 , wherein the rotor is a fan axial rotor associated with a gas turbine engine.
8. The rotor of claim 1 , wherein the throat dimension at 5% of the span of the adjacent ones of the plurality of airfoils is less than 70% of the maximum value.
9. A rotor for a compressor, comprising:
a hub; and
a plurality of airfoils having a root, a tip opposite the root and a span that extends from 0% at the root to 100% at the tip, each of the plurality of airfoils coupled to the hub at the root and spaced apart from adjacent ones of the plurality of airfoils over the span by a throat dimension defined between the adjacent ones of the plurality of airfoils, the throat dimension has a maximum value at a spanwise location between 60% of the span and 90% of the span of the adjacent ones of the plurality of airfoils, at 10% of the span of the adjacent ones of the plurality of airfoils above or below the spanwise location of the maximum value, the throat dimension is less than 97% of the maximum value, the throat dimension between 90% of the span and the tip of the adjacent ones of the plurality of airfoils has a first value, and the throat dimension between the root and 10% of the span of the adjacent ones of the plurality of airfoils has a second value that is less than 60% of the maximum value.
10. The rotor of claim 9 , wherein the second value is less than the first value.
11. The rotor of claim 9 , wherein the first value is less than 70% of the maximum value.
12. The rotor of claim 9 , wherein the second value is between the root and 5% of the span of the adjacent ones of the plurality of airfoils.
13. The rotor of claim 9 , wherein the maximum value is between about 70% and 80% of the span of the adjacent ones of the plurality of airfoils.
14. The rotor of claim 9 , wherein the first value is greater than 60% of the maximum value.
15. A rotor for a compressor, comprising:
a hub; and
a plurality of airfoils having a root, a tip opposite the root and a span that extends from 0% at the root to 100% at the tip, each of the plurality of airfoils coupled to the hub at the root and spaced apart from adjacent ones of the plurality of airfoils over the span by a throat dimension defined between the adjacent ones of the plurality of airfoils, the throat dimension has a maximum value at a spanwise location between 60% of the span and 90% of the span of the adjacent ones of the plurality of airfoils, at 10% of the span of the adjacent ones of the plurality of airfoils above or below the spanwise location of the maximum value, the throat dimension is less than 97% of the maximum value, the throat dimension between 90% of the span and the tip of the adjacent ones of the plurality of airfoils has a first value, the throat dimension between the root and 10% of the span of the adjacent ones of the plurality of airfoils has a second value that is less than 70% of the maximum value, the second value is less than the first value and the first value is less than 70% of the maximum value.
16. The rotor of claim 15 , wherein the second value is between the root and 5% of the span of the adjacent ones of the plurality of airfoils.
17. The rotor of claim 15 , wherein the maximum value is between about 70% and 80% of the span of the adjacent ones of the plurality of airfoils.
18. The rotor of claim 15 , wherein the first value is greater than 60% of the maximum value.
19. The rotor of claim 15 , wherein the throat dimension has a third value at the root, which is less than the second value.