Fluid collection gutter for a geared turbine engine
A turbine engine system includes a gutter and a gear train with an axial centerline. The gutter is disposed radially outside of the axial centerline. The gutter includes an inner surface and a channel that receives fluid directed out of the gear train. The inner surface at least partially defines a bore in which the gear train is arranged. The channel extends radially into the gutter from the inner surface, and circumferentially to a channel outlet. The bore has a cross-sectional bore area, and the channel has a cross-sectional channel area that is substantially equal to or less than about two percent of the bore area.
1. A turbine engine system, comprising:
a gear train with an axial centerline; and
a gutter at least partially circumscribing the gear train; the gutter including an inner surface and a channel;
the channel axially aligned with one or more fluid passages in the gear train along the axial centerline, and the channel configured to receive fluid directed radially out of the gear train through the one or more fluid passages;
the channel extending radially into the gutter from the inner surface; and the channel extending circumferentially to a channel outlet;
wherein the inner surface has a surface radius measured from the axial centerline, and the channel has a radially extending channel height that is equal to or less than eight percent of the surface radius; and
wherein the channel has an axially extending channel width that is equal to or less than fifteen percent of the surface radius.
2. The system of claim 1 , wherein
the inner surface at least partially defines a bore in which the gear train is arranged; and
the bore has a cross-sectional bore area; and
the channel has a cross-sectional channel area that is equal to or less than two percent of the cross-sectional bore area.
3. The system of claim 2 , wherein the cross-sectional channel area is defined by a portion of the channel located adjacent and upstream of the channel outlet.
4. The system of claim 1 , further comprising:
a plurality of turbine engine rotors arranged along the axial centerline;
the plurality of turbine engine rotors including a first rotor and a second rotor;
each of the plurality of turbine engine rotors including a plurality of rotor blades arranged around and connected to a rotor disk; and
the first rotor connected to and driven by the second rotor through the gear train.
5. The system of claim 4 , wherein the first rotor is configured as a fan rotor and the second rotor is configured as a turbine rotor.
6. The system of claim 5 , wherein the gear train comprises a planetary gear train.
7. The system of claim 5 , wherein the gear train comprises a star gear train.
8. The system of claim 1 , wherein at least a portion of the channel has a cross-sectional channel geometry that transitions between a first geometry and a second geometry as the channel extends circumferentially within the gutter.
9. The system of claim 1 , wherein
at least a portion of the channel has a cross-sectional channel geometry comprising a first region and a second region located radially outboard of the first region; and
the first region and the second region are configured with at least different shapes and/or different sizes.
10. The system of claim 9 , wherein
the first region has a first axial width; and
the second region has a second axial width that is less than the first axial width.
11. The system of claim 9 , wherein the first region has a rectangular shape.
12. The system of claim 11 , wherein the second region has a triangular shape.
13. The system of claim 11 , wherein
the first region has a first axial width;
the second region has a second axial width that is less than the first axial width; and
the second region has a rectangular shape.
14. The system of claim 11 , wherein the second region has an isosceles trapezoidal shape.
15. The system of claim 14 , wherein
the cross-sectional channel geometry further comprises a third region located radially outboard of the second region; and
the first region, the second region and the third region are configured with at least different shapes and/or different axial widths.
16. The system of claim 15 , wherein the third region has a rectangular shape.
17. A turbine engine system, comprising:
a gear train with an axial centerline; and
a gutter at least partially circumscribing the gear train;
the gutter including an inner surface and a channel;
the channel configured to receive fluid directed out of the gear train;
the channel extending radially into the gutter from the inner surface; and
the channel extending circumferentially to a channel outlet;
wherein the inner surface has a surface radius measured from the axial centerline;
wherein at least a portion of the channel has an axially extending channel width that is equal to or less than fifteen percent of the surface radius; and
wherein the portion of the channel is located adjacent and upstream of the channel outlet.
18. The system of claim 17 , wherein
the inner surface at least partially defines a bore in which the gear train is arranged;
the bore has a cross-sectional bore area; and
the channel has a cross-sectional channel area that is equal to or less than two percent of the cross-sectional bore area.
19. The system of claim 17 , further comprising:
a plurality of turbine engine rotors arranged along the axial centerline;
the plurality of turbine engine rotors including a first rotor and a second rotor;
each of the plurality of turbine engine rotors including a plurality of rotor blades arranged around and connected to a rotor disk;
the first rotor connected to and driven by the second rotor through the gear train; and
the gear train comprising an epicyclic gear train.
20. The system of claim 17 , wherein the channel is axially aligned with a plurality of fluid passages in a ring gear of the gear train along the axial centerline.