Lubricant system
An aircraft engine having a fan or propeller stage mounted to a planetary gearing system through a planetary gearing output drive shaft is provided with a lubricant system having a seal with lubricant delivery chamber for receiving a lubricant and a sealing surface sealing against a rotatable shaft, the rotatable shaft has a hollow interior and an opening in registration with the delivery chamber. The lubricant system has a lubricant pump in fluidical communication with and downstream of the opening.
1. An aircraft engine having a fan or propeller stage mounted to a planetary gearing system through a planetary gearing output drive shaft and having a lubricant system having a seal with a lubricant delivery chamber for receiving a lubricant and a sealing surface sealing against a rotatable shaft, the rotatable shaft being configured to drive a sun gear of the planetary gearbox and having a hollow interior and an opening in registration with the delivery chamber,
wherein the lubricant system has a lubricant pump in fluidical communication with and downstream of the opening;
wherein the rotatable shaft has an internal hollow lubricant transfer coupling rotatable with the rotatable shaft having one or more apertures in registration with the opening or openings in the rotatable shaft and which transfers the lubricant between the opening in the rotatable shaft and the lubricant pump; and
wherein the transfer coupling is connected to the pump via a torque coupling which transfers torque from the coupling to the pump.
2. The aircraft engine according to claim 1 , wherein the lubricant pump is located radially inside the planetary gearing output drive shaft.
3. The aircraft engine according to claim 1 , wherein the lubricant pump is located axially forward of the planetary gearing system.
4. The aircraft engine according to claim 1 , wherein the seal is a collar arranged coaxially with the rotatable shaft, the sealing surface sealing against an external surface of the rotatable shaft.
5. The aircraft engine according to claim 1 , wherein the delivery chamber is annular.
6. The aircraft engine according to claim 5 , wherein the delivery chamber has a plurality of inlets, that are connected to a source of lubricant.
7. The aircraft engine according to claim 1 , wherein the torque coupling is connected to a pump inlet to permit passage of lubricant from the transfer coupling to the pump.
8. The aircraft engine according to claim 1 , wherein the apertures extend from an external surface sealing with the interior surface of the rotatable shaft to the interior of the transfer coupling.
9. The aircraft engine according to claim 1 , wherein the pump is selected from the group comprising: vane pumps, gear pumps, gerotor pumps, or piston pumps.
10. The aircraft engine according to claim 1 , wherein the pump has a first stage and a second stage and a first outlet and a second outlet, the first stages supplying lubricant to the first outlet, the second stage supplying lubricant to the second outlet; the pressure of the lubricant at the first outlet being different to the pressure of the lubricant at the second outlet.
11. The aircraft engine according to claim 1 , wherein the pump has an outlet that supplies lubricant to a gearing system.
12. The aircraft engine according to claim 11 , wherein the gearing system drives an output shaft for a fan or propeller stage of a gas turbine.
13. The aircraft engine according to claim 12 , wherein the outlet is a spray outlet.
14. The aircraft engine according to claim 3 , wherein the transfer coupling extends from an axially rearward end of the planetary gearbox to an axially forward end of the planetary gearbox.