Engine systems and methods
Disclosed examples include an airfoil comprising: a pressure side and a suction side that are coupled together at a substantially radial trailing edge of the airfoil, wherein the substantially radial trailing edge is downstream from a leading edge, the leading edge including a sweep feature of a variable chord length, the variable chord length to include: a first increase in chord length and a decrease in chord length along a radial length from a hub end of the airfoil to an opposite tip end of the airfoil; and a second increase in chord length along the radial length from the hub end to the opposite tip end, the second increase different than the first increase.
1. An airfoil comprising:
a pressure side and a suction side that are coupled together at a substantially radial trailing edge of the airfoil,
wherein the substantially radial trailing edge is downstream from a leading edge, the leading edge including a sweep feature of a variable chord length, the sweep feature extending between an inner edge and an interference edge, the variable chord length to include:
a first increase in chord length and a decrease in chord length along a radial length from a hub end of the airfoil to an opposite tip end of the airfoil; and
a second increase in chord length along the radial length from the hub end to the opposite tip end, the second increase different than the first increase.
2. The airfoil of claim 1 , wherein the decrease in chord length is a first decrease in chord length that is contiguous to the second increase in chord length, and further including a second decrease in chord length along the radial length from the hub end of the airfoil to the opposite tip end of the airfoil.
3. The airfoil of claim 2 , wherein the variable chord length is shorter at the second increase in chord length near the opposite tip end of the airfoil relative to the first increase in chord length near the hub end of the airfoil.
4. The airfoil of claim 3 , further including at least a third increase in chord length and a third decrease in chord length to form a non-uniform.
5. The airfoil of claim 1 , further including a fan frame assembly, wherein the airfoil is integrated into the fan frame assembly at an inner surface and an outer surface, the hub end of the airfoil coupled with the inner surface of the fan frame assembly, the opposite tip end of the airfoil coupled with the outer surface of the fan frame assembly.
6. The airfoil of claim 5 , wherein the leading edge is configured to interfere with airflow through the fan frame assembly to reduce an unsteady surface pressure level compared to a second airfoil without the sweep feature.
7. The airfoil of claim 1 , wherein the leading edge and the substantially radial trailing edge are integrated into the airfoil as a one-piece, unitary construction.
8. A gas turbine engine comprising:
a fan frame assembly; and
an airfoil including a pressure side and a suction side that are coupled together at a substantially radial trailing edge of the airfoil,
wherein the substantially radial trailing edge is downstream from a leading edge, the leading edge including a sweep feature of a variable chord length, the sweep feature extending between an inner edge and an interference edge, the variable chord length to include:
a first increase in chord length and a decrease in chord length along a radial length from a hub end of the airfoil to an opposite tip end of the airfoil; and
a second increase in chord length along the radial length from the hub end to the opposite tip end, the second increase different than the first increase.
9. The gas turbine engine of claim 8 , wherein the decrease in chord length is a first decrease in chord length, the second increase in chord length is contiguous to the first decrease in chord length, and further including a second decrease in chord length along the radial length from the hub end of the airfoil to the opposite tip end of the airfoil.
10. The gas turbine engine of claim 9 , wherein the variable chord length is shorter at the second increase in chord length near the opposite tip end of the airfoil relative to the first increase in chord length near the hub end of the airfoil.
11. The gas turbine engine of claim 10 , further including at least a third increase in chord length and a third decrease in chord length to form a non-uniform.
12. The gas turbine engine of claim 8 , wherein the airfoil is integrated into the fan frame assembly at an inner surface and an outer surface, the hub end of the airfoil coupled with the inner surface of the fan frame assembly, the opposite tip end of the airfoil coupled with the outer surface of the fan frame assembly.
13. The gas turbine engine of claim 12 , wherein the leading edge is configured to interfere with airflow through the fan frame assembly to reduce an unsteady surface pressure level compared to a second airfoil without the sweep feature.
14. The gas turbine engine of claim 8 , wherein the leading edge and the substantially radial trailing edge are integrated into the airfoil as a one-piece, unitary construction.
15. A method comprising:
integrating an airfoil with a fan frame assembly, the airfoil including a pressure side and a suction side that are coupled together at a substantially radial trailing edge of the airfoil,
wherein the substantially radial trailing edge is downstream from a leading edge, the leading edge including a sweep feature of a variable chord length, the sweep feature extending between an inner edge and an interference edge, the variable chord length to include:
a first increase in chord length and a decrease in chord length along a radial length from a hub end of the airfoil to an opposite tip end of the airfoil; and
a second increase in chord length along the radial length from the hub end to the opposite tip end, the second increase different than the first increase; and
altering airflow through the fan frame assembly to change an unsteady surface pressure level.
16. The method of claim 15 , wherein the airfoil is integrated into the fan frame assembly at an inner surface and an outer surface, the hub end of the airfoil coupled with the inner surface of the fan frame assembly, the opposite tip end of the airfoil coupled with the outer surface of the fan frame assembly.
17. The method of claim 16 , wherein the leading edge and the substantially radial trailing edge are integrated into the airfoil as a one-piece, unitary construction.
18. The method of claim 16 , further including retrofitting at least a portion of the leading edge onto the airfoil.
19. The method of claim 15 , wherein the variable chord length is shorter at the second increase in chord length near the opposite tip end of the airfoil relative to the first increase in chord length near the hub end of the airfoil.
20. The method of claim 19 , further including integrating a second decrease in chord length along the radial length from the hub end of the airfoil to the opposite tip end of the airfoil.