초록 ▼

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

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.

대표청구항 ▼

1. A turbine engine system, comprising: a gear train with an axial centerline; anda 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; anda channel that receives fluid directed

1. A turbine engine system, comprising: a gear train with an axial centerline; anda 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; anda 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.