Gearbox lubrication system for aircraft
A gearbox for a rotary wing aircraft including a sump, a primary lubricant reservoir fluidically connected to the sump, one or more primary lubricant jets fluidically connected to the primary lubricant reservoir, an auxiliary lubricant reservoir fluidically connected to the sump, one or more auxiliary lubricant jets fluidically connected to the auxiliary lubricant reservoir, and at least one valve selectively fluidically connecting the sump and the primary lubricant reservoir based on a first lubricant pressure and the sump and the auxiliary lubricant reservoir based on a second lubricant pressure at the at least one valve.
1. A gearbox lubrication system for an aircraft comprising:
a sump;
a primary lubricant reservoir fluidically connected to the sump;
one or more primary lubricant jets fluidically connected to the primary lubricant reservoir;
an auxiliary lubricant reservoir fluidically connected to the sump;
one or more auxiliary lubricant jets fluidically connected to the auxiliary lubricant reservoir; and
at least one valve selectively fluidically connecting the sump and the primary lubricant reservoir based on a first lubricant pressure and the sump and the auxiliary lubricant reservoir based on a second lubricant pressure at the at least one valve, wherein the at least one valve directs lubricant from the sump into the auxiliary lubricant reservoir during a first operating phase of the aircraft and wherein the at least one valve directs lubricant from the sump to the primary lubricant reservoir during a second operating phase of the aircraft.
2. The gearbox lubrication system according to claim 1 , wherein the auxiliary lubricant reservoir is selectively fluidically isolated from the primary lubricant reservoir.
3. The gearbox lubrication system according to claim 1 , wherein the at least one valve comprises a shuttle valve.
4. The gearbox lubrication system according to claim 1 , further comprising: a bypass conduit fluidically connected to the primary lubricant reservoir and the sump downstream of the at least one valve.
5. The gearbox lubrication system according to claim 1 , further comprising: a pressure sensor fluidically connected between the primary lubricant reservoir and the one or more primary lubricant jets and operatively connected to the at least one valve.
6. The gearbox lubrication system according to claim 5 , further comprising: another pressure sensor fluidically connected between the auxiliary lubricant reservoir and the one or more auxiliary lubricant jets.
7. The gearbox lubrication system according to claim 1 , wherein the gearbox lubrication system is mounted in a rotary wing aircraft.
8. The gearbox lubrication system according to claim 1 , wherein the at least one valve shifts from a first configuration, wherein the lubricant is passed from the sump into the auxiliary lubricant reservoir to a second configuration wherein the lubricant is passed from the sump to the primary lubricant reservoir once pressure in the auxiliary lubricant reservoir reaches a selected level.
9. The gearbox lubrication system according to claim 8 , wherein the at least one valve shifts from the second configuration wherein the lubricant is passed from the sump to the primary lubricant reservoir to the first configuration wherein the lubricant is passed from the sump into the auxiliary lubricant reservoir once pressure in the primary lubricant reservoir drops below the selected level.
10. The gearbox lubrication system according to claim 1 , further comprising:
at least one pump fluidically connected between the sump and the at least one valve.
11. The gearbox lubrication system according to claim 10 , wherein in an emergency operation mode, the at least one pump is operated to reduce an amount of lubricant in the sump.
12. The gearbox lubrication system according to claim 11 , wherein in the emergency operation mode, the at least one valve fluidically isolates the primary lubricant reservoir and the auxiliary lubricant reservoir from the sump.