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 disposed radially outside of the axial centerline, the gutter including
an inner surface at least partially defining an axial bore in which the gear train is arranged; and
a channel that receives fluid directed out of the gear train, the channel extending radially into the gutter from the inner surface, and circumferentially to a channel outlet;
wherein the axial 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.
2. The turbine engine system of claim 1 , wherein the cross-sectional channel area is defined by at least a portion of the channel located adjacent and upstream of the channel outlet.
3. The turbine engine system of claim 1 , wherein the inner surface has a surface radius; and the channel has a radially extending channel height that is equal to or less than eight percent of the surface radius.
4. The turbine engine system of claim 1 , wherein the inner surface has a surface radius; and the channel has an axially extending channel width that is equal to or less than fifteen percent of the surface radius.
5. The turbine engine system of claim 1 , wherein the channel outlet has a cross-sectional outlet area that is between fifty-five and seventy-five percent of the cross-sectional channel area.
6. The turbine engine 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.
7. The turbine engine system of claim 1 , wherein at least a portion of the channel has rectangular cross-sectional channel geometry.
8. The turbine engine system of claim 1 , wherein the channel extends radially into the gutter to a channel end; and at least a portion of the channel has a cross-sectional channel geometry that tapers axially as the channel extends radially towards the channel end.
9. The turbine engine system of claim 1 , wherein at least a portion of the channel has a cross-sectional channel geometry formed by an inner region and an outer region located radially outboard of the inner region; and the inner region has a rectangular geometry, and the outer region has a triangular geometry.
10. The turbine engine system of claim 1 , wherein the channel outlet has a triangular cross-sectional geometry.
11. The turbine engine system of claim 1 , wherein the gutter further includes a conduit that extends through the gutter and spirals at least partially around the axial centerline between the channel outlet and a conduit outlet.
12. The turbine engine system of claim 1 , wherein the gear train includes one or more fluid passages arranged circumferentially around the axial centerline and aligned axially with the channel; and the one or more fluid passages are fluidly coupled to the channel outlet through the channel.
13. The turbine engine system of claim 1 , wherein the gear train is configured as a planetary gear train or a star gear train.
14. The turbine engine system of claim 1 , further comprising: a plurality of turbine engine rotors arranged along the axial centerline and including a first rotor and a second rotor, each of the turbine engine rotors including a plurality of rotor blades arranged around and connected to a rotor disk; wherein the first rotor is connected to and driven by the second rotor through the gear train.
15. The turbine engine system of claim 14 , wherein the first rotor is configured as a fan rotor and the second rotor is configured as a turbine rotor.