Fan for a turbine engine
A fan for a turbine engine having a core air flowpath and a bypass air flowpath. The fan includes a disk, a plurality of fan blades, and a plurality of splitter blades. The disk rotates about a centerline axis. The plurality of fan blades are coupled to the disk. The plurality of splitter blades are coupled to the disk and positioned between the plurality of fan blades. The plurality of splitter blades are axially aligned on the disk at a splitter blade axial distance from an annular inlet of the core air flowpath such that the plurality of splitter blades direct debris that passes through the fan into the bypass air flowpath.
1. A fan for a turbine engine having a core air flowpath and a bypass air flowpath, the fan comprising:
a disk that rotates about a centerline axis;
a plurality of fan blades coupled to the disk; and
a plurality of splitter blades coupled to the disk and positioned between the plurality of fan blades, the plurality of splitter blades being axially aligned on the disk at a splitter blade axial distance from an annular inlet of the core air flowpath such that the plurality of splitter blades direct debris that passes through the fan into the bypass air flowpath,
wherein the annular inlet includes a flowpath splitter radius defined from the centerline axis to a flowpath splitter of the turbine engine at the annular inlet, and the plurality of splitter blades each includes a splitter blade radius defined from the centerline axis to a tip of the plurality of splitter blades, the splitter blade radius being equal to or less than the flowpath splitter radius,
wherein each of the plurality of fan blades includes a fan blade chord and each of the plurality of splitter blades includes a splitter blade chord, and the splitter blade chord is less than or equal to the fan blade chord,
wherein each of the plurality of splitter blades includes a splitter blade leading edge located within the fan blade chord of the plurality of fan blades, and
wherein the plurality of splitter blades includes a plurality of first splitter blades and a plurality of second splitter blades, the plurality of second splitter blades having different characteristics than the plurality of first splitter blades.
2. The fan of claim 1 , wherein the plurality of fan blades each includes a fan blade span and the plurality of splitter blades each includes a splitter blade span, the splitter blade span being less than the fan blade span.
3. The fan of claim 1 , wherein the plurality of fan blades each includes a fan blade camber and the plurality of splitter blades each includes a splitter blade camber, the splitter blade camber being different than the fan blade camber.
4. The fan of claim 1 , wherein the plurality of fan blades each includes a fan blade twist angle and the plurality of splitter blades each includes a splitter blade twist angle, the splitter blade twist angle being different than the fan blade twist angle.
5. The fan of claim 1 , wherein the plurality of fan blades each includes a fan blade lean angle and the plurality of splitter blades each includes a splitter blade lean angle, the splitter blade lean angle being different than the fan blade lean angle.
6. The fan of claim 1 , wherein the plurality of fan blades each includes a fan blade trailing edge and the plurality of splitter blades each includes a splitter blade trailing edge, the splitter blade trailing edge being aligned on the disk axially forward of the fan blade trailing edge.
7. The fan of claim 6 , wherein the plurality of fan blades each includes a fan blade leading edge, the splitter blade leading edge being aligned on the disk axially aft of the fan blade leading edge.
8. The fan of claim 6 , wherein the plurality of splitter blades being aligned on the disk such that the splitter blade chord is entirely axially within the fan blade chord.
9. A turbine engine comprising:
a core air flowpath having an annular inlet;
a bypass air flowpath; and
a fan positioned axially forward of the core air flowpath and the bypass air flowpath, the fan comprising:
a disk that rotates about a centerline axis;
a plurality of fan blades coupled to the disk; and
a plurality of splitter blades coupled to the disk and positioned between the plurality of fan blades, the plurality of splitter blades being axially aligned on the disk at a splitter blade axial distance from the annular inlet of the core air flowpath such that the plurality of splitter blades direct debris that passes through the fan into the bypass air flowpath; and
a flowpath splitter that separates the core air flowpath at the annular inlet and the bypass air flowpath, the annular inlet including a flowpath splitter radius defined from the centerline axis to the flowpath splitter, and the plurality of splitter blades each includes a splitter blade radius defined from the centerline axis to a tip of the plurality of splitter blades, the splitter blade radius being equal to or less than the flowpath splitter radius,
wherein each of the plurality of fan blades includes a fan blade chord and each of the plurality of splitter blades includes a splitter blade chord, and the splitter blade chord is less than or equal to the fan blade chord,
wherein each of the plurality of splitter blades includes a splitter blade leading edge located within the fan blade chord of the plurality of fan blades, and
wherein the plurality of splitter blades includes a plurality of first splitter blades and a plurality of second splitter blades, the plurality of second splitter blades having different characteristics than the plurality of first splitter blades.
10. The turbine engine of claim 9 , wherein the plurality of fan blades each includes a fan blade span and the plurality of splitter blades each includes a splitter blade span, the splitter blade span being less than the fan blade span.
11. The turbine engine of claim 9 , wherein the plurality of fan blades each includes a fan blade camber and the plurality of splitter blades each includes a splitter blade camber, the splitter blade camber being different than the fan blade camber.
12. The turbine engine of claim 9 , wherein the plurality of fan blades each includes a fan blade twist angle and the plurality of splitter blades each includes a splitter blade twist angle, the splitter blade twist angle being different than the fan blade twist angle.
13. The turbine engine of claim 9 , wherein the plurality of fan blades each includes a fan blade lean angle and the plurality of splitter blades each includes a splitter blade lean angle, the splitter blade lean angle being different than the fan blade lean angle.
14. The turbine engine of claim 9 , wherein the plurality of fan blades each includes a fan blade trailing edge and the plurality of splitter blades each includes a splitter blade trailing edge, the splitter blade trailing edge being aligned on the disk axially forward of the fan blade trailing edge.
15. The turbine engine of claim 14 , wherein the plurality of fan blades each includes a fan blade leading edge, the splitter blade leading edge being aligned on the disk axially aft of the fan blade leading edge.
16. The turbine engine of claim 14 , wherein the plurality of splitter blades being aligned on the disk such that the splitter blade chord is entirely axially within the fan blade chord.