Ducted oil scoop for gas turbine engine
A gas turbine engine includes a rotating shaft. An oil scoop rotates with the rotating shaft. The oil scoop has end walls spaced axially along an axis of rotation of the rotating shaft and an axially central recess. A duct is spaced radially outwardly of the oil scoop. The duct has an oil inlet, with an oil supply nozzle to supply oil into the oil inlet in the duct. The oil inlet is then connected to supply oil into the recess. The oil scoop has an inner hole to allow oil to flow from the recess to an outer periphery of the shaft.
1. A gas turbine engine comprising:
a rotating shaft;
an oil scoop rotating with said rotating shaft, said oil scoop having end walls spaced axially along an axis of rotation of said rotating shaft and an axially central recess;
a duct spaced radially outwardly of said oil scoop, and said duct having an oil inlet, with an oil supply nozzle to supply oil into said oil inlet in said duct, the oil inlet then connected to supply oil into said recess, said oil scoop having an inner hole to allow oil to flow from said recess to an outer periphery of said shaft; and
wherein there is a gap between a radially outer location on said end walls and a radially inner surface on said duct, and said gap being less than 0.050 in (0.127 cm).
2. The gas turbine engine as set forth in claim 1 , wherein said nozzle extends along an angle which is non-perpendicular to an axis of rotation of said rotating shaft.
3. The gas turbine engine as set forth in claim 2 , wherein said nozzle extends along a direction which is generally tangential to an outer periphery of said rotating shaft.
4. The gas turbine engine as set forth in claim 3 , wherein said duct having at least one breather hole for allowing air to flow into a chamber between said recess and an inner peripheral surface of said duct.
5. The gas turbine engine as set forth in claim 4 , wherein there are a plurality of said breather holes.
6. The gas turbine engine as set forth in claim 1 , wherein said oil scoop having a plurality of said inner holes at a radially inner surface to allow oil to flow to said shaft.
7. The gas turbine engine as set forth in claim 1 , wherein said duct is fixed against rotation.
8. The gas turbine engine as set forth in claim 1 , wherein the oil scoop is positioned axially adjacent a bearing supporting said rotating shaft.
9. The gas turbine engine as set forth in claim 1 , wherein said duct having at least one breather hole for allowing air to flow into a chamber between said recess and an inner peripheral surface of said duct.
10. The gas turbine engine as set forth in claim 1 , wherein said oil supply nozzle includes a plurality of oil supply nozzles.
11. A gas turbine engine comprising:
a rotating shaft;
an oil scoop rotating with said rotating shaft, said oil scoop having end walls spaced axially along an axis of rotation of said rotating shaft and an axially central recess;
a duct spaced radially outwardly of said oil scoop, and said duct having an oil inlet, with an oil supply nozzle to supply oil into said oil inlet in said duct, the oil inlet then connected to supply oil into said recess, said oil scoop having an inner hole to allow oil to flow from said recess to an outer periphery of said shaft; and
wherein said duct is fixed against rotation.
12. The gas turbine engine comprising:
a turbine rotor driving a shaft, said shaft being supported on a bearing;
an oil scoop rotating with said shaft, said oil scoop having end walls spaced axially along an axis of rotation of said shaft and an axially central recess;
a duct spaced radially outwardly of said oil scoop, and said duct having an oil inlet, with an oil supply nozzle to supply oil into said oil inlet in said duct, the oil inlet then connected to supply oil into said recess, said oil scoop having an inner hole to allow oil to flow from said recess to an outer periphery of said shaft; and
wherein said duct is fixed against rotation.
13. The gas turbine engine as set forth in claim 12 , wherein there is a gap between a radially outer location on said end walls and a radially inner surface on said duct, and said gap being less than 0.050 in (0.127 cm).
14. The gas turbine engine as set forth in claim 12 , wherein said nozzle extends along an angle which is non-perpendicular to an axis of rotation of said shaft.
15. The gas turbine engine as set forth in claim 14 , wherein said nozzle extends along a direction which is generally tangential to an outer periphery of said shaft.
16. The gas turbine engine as set forth in claim 12 , wherein said duct having at least one breather hole for allowing air to flow into a chamber between said recess and an inner peripheral surface of said duct.
17. The gas turbine engine as set forth in claim 12 , wherein said oil scoop having a plurality of said inner holes at a radially inner surface to allow oil to flow to said shaft.