Lubrication arrangement for a gas turbine engine gear assembly
An exemplary apparatus for supplying lubricant to a gear assembly in a gas turbine engine includes a valve having a valve inlet configured to be coupled to a source of lubricant. A valve outlet is configured to direct lubricant to the gear assembly. The valve is selectively controllable into a plurality of settings for varying an amount of lubricant flowing from the valve inlet to the valve outlet. A bypass is associated with the valve. The bypass has an inlet configured to receive lubricant from the source and an outlet configured to direct lubricant to the gear assembly. The bypass permits at least a selected amount of lubricant to flow to the gear assembly independent of a setting of the valve.
1. A method of supplying lubricant to a geared architecture in a gas turbine engine, the method comprising:
providing a fan including a plurality of fan blades rotatable about an axis;
situating a geared architecture for rotating the fan about the axis;
providing a lubrication arrangement for supplying lubricant to the geared architecture, the lubrication arrangement including a source of lubricant, having a selectively controllable valve and a bypass associated with the valve;
selectively directing lubricant from the source to the geared architecture through the selectively controllable valve; and
always directing lubricant to the geared architecture through the bypass associated with the valve independent of an amount of the lubricant directed through the selectively controllable valve;
wherein the bypass includes a restrictor, and the method comprises controlling the restrictor to alter an amount of lubricant directed through the bypass to the geared architecture.
2. The method of claim 1 , comprising always ensuring at least a minimum amount of lubricant can be delivered to the geared architecture through the bypass.
3. The method of claim 1 , wherein the bypass is configured to permit a fixed maximum amount of lubricant flow through the bypass.
4. The method of claim 1 , wherein the valve comprises a return outlet that is configured to direct lubricant toward the lubricant supply responsive to the valve setting restricting an amount of lubricant that can flow through the valve outlet to an amount that is less than an amount that is received at the valve inlet.
5. The method of claim 1 , wherein there is a pressure ratio across the fan blades, the pressure ratio being less than about 1.50.
6. The method of claim 5 , wherein the pressure ratio is less than about 1.45.
7. The method of claim 1 , wherein the gas turbine engine comprises an engine core and there is a bypass ratio of air flow through the fan to air flow into the core, the bypass ratio being greater than about 6:1.
8. The method of claim 7 , wherein the bypass ratio is greater than about 10:1.
9. The method of claim 1 , wherein the geared architecture comprises an epicyclical gear train.
10. The method of claim 9 , wherein the geared architecture has a gear reduction ratio of greater than 2.3.
11. The method of claim 1 , wherein the geared architecture has a gear reduction ratio of greater than 2.3.
12. A method of supplying lubricant to a geared architecture in a gas turbine engine, the method comprising the steps of:
providing a fan including a plurality of fan blades rotatable about an axis, wherein there is a pressure ratio across the fan blades, the pressure ratio being less than about 1.50;
providing a geared architecture situated for rotating the fan about the axis, wherein the geared architecture has a gear reduction ratio of greater than 2.3;
providing a lubrication arrangement for supplying lubricant to the geared architecture, the lubrication arrangement including a source of lubricant, having a selectively controllable valve and a bypass associated with the valve;
selectively directing lubricant from the source to the geared architecture through the selectively controllable valve; and
constantly directing lubricant to the geared architecture through the bypass associated with the valve independent of an amount of the lubricant directed through the selectively controllable valve;
wherein the bypass includes a restrictor, and the method comprises controlling the restrictor to alter an amount of lubricant directed through the bypass to the geared architecture.
13. The method of claim 12 , wherein the bypass is configured to permit a fixed maximum amount of lubricant flow through the bypass.
14. The method of claim 12 , wherein the valve comprises a return outlet that is configured to direct lubricant toward the lubricant supply responsive to a valve setting restricting an amount of lubricant that can flow through the valve outlet to an amount that is less than an amount that is received at the valve inlet.
15. The method of claim 12 , wherein the pressure ratio is less than about 1.45.
16. The method of claim 12 , wherein the gas turbine engine comprises an engine core and there is a bypass ratio of air flow through the fan to air flow into the core, the bypass ratio being greater than about 6:1.
17. The method of claim 16 , wherein the bypass ratio is greater than about 10:1.
18. The method of claim 12 , wherein the geared architecture comprises an epicyclical gear train.