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A lubrication system for a gas turbine engine includes a tank, a circulation pump, and a heat exchanger. The circulation pump generates a flow of lubricant from the tank to, e.g., a power gear box of the gas turbine engine and the heat exchanger removes an amount of heat from such flow of lubricant

A lubrication system for a gas turbine engine includes a tank, a circulation pump, and a heat exchanger. The circulation pump generates a flow of lubricant from the tank to, e.g., a power gear box of the gas turbine engine and the heat exchanger removes an amount of heat from such flow of lubricant provided to the power gear box. The lubrication system also includes one or more valves in the flow of lubricant for controlling a flowrate and/or temperature of the lubricant provided to, e.g., the power gear box to increase an efficiency and/or durability of the power gear box.

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1. A lubrication system for a gas turbine engine comprising: a tank configured to store a volume of lubricant;a circulation pump for generating a flow of lubricant from the tank to a component of the gas turbine engine;a valve in fluid communication with the flow of lubricant generated by the circul

1. A lubrication system for a gas turbine engine comprising: a tank configured to store a volume of lubricant;a circulation pump for generating a flow of lubricant from the tank to a component of the gas turbine engine;a valve in fluid communication with the flow of lubricant generated by the circulation pump and defining a flow inlet and a flow outlet, the valve also defining a variable throughput between the flow inlet and the flow outlet for controlling a flowrate of lubricant to the component of the gas turbine engine; anda heat exchanger positioned in thermal communication with the flow of lubricant generated by the circulation pump at a location downstream of the valve for controlling a temperature of the lubricant prior to the lubricant reaching the component. 2. The lubrication system of claim 1, wherein the valve is positioned downstream from circulation pump in the flow of lubricant generated by the circulation pump. 3. The lubrication system of claim 1, wherein the circulation pump generates a flow of lubricant from the tank to a power gear box of the gas turbine engine. 4. The lubrication system of claim 1, wherein the circulation pump is driven by a shaft of the gas turbine engine. 5. The lubrication system of claim 1, further comprising: a heat exchange bypass valve in fluid communication with the flow of lubricant generated by the circulation pump and defining an inlet, a first outlet, and a second outlet, wherein the second outlet is in fluid communication with a bypass line, and wherein the bypass line extends between the second outlet and the flow of lubricant generated by the circulation pump at a location downstream from the heat exchanger. 6. The lubrication system of claim 1, wherein the circulation pump is a dedicated circulation pump for the component, and wherein the lubrication system further comprises a main circulation pump for generating a flow of lubricant from the tank to one or more of a compressor section of the gas turbine engine and a turbine section of the gas turbine engine. 7. The lubrication system of claim 6, further comprising: a main heat exchanger positioned in thermal communication with the flow of lubricant generated by the main circulation pump at a location upstream of the main circulation pump. 8. The lubrication system of claim 1, wherein the valve is in operable communication with a controller of the gas turbine engine. 9. The lubrication system of claim 1, wherein the flow of lubricant generated by the circulation pump is split downstream of the circulation pump between a first flow path and a second flow path, wherein the second flow path is configured to provide the flow of lubricant to the component of the gas turbine engine, and wherein the valve is in fluid communication with the second flow path. 10. The lubrication system of claim 9, wherein the circulation pump is further configured to generate a flow of lubricant from the tank through the first flow path to one or more of a compressor section of the gas turbine engine and a turbine section of the gas turbine engine. 11. A lubrication system for a gas turbine engine comprising: a tank configured to store a volume of lubricant;a first circulation pump for generating a first flow of lubricant from the tank to one or more first components of the gas turbine engine;a second circulation pump for generating a second flow of lubricant from the tank to one or more second components of the gas turbine engine, the second flow of lubricant being separate from the first flow of lubricant and the one or more second components being different than the one or more first components; anda valve defining an inlet and an outlet each in flow communication with the second flow of lubricant, the valve defining a variable throughput between the inlet and the outlet for controlling a flowrate of the second flow of lubricant to the one or more second components. 12. The lubrication system of claim 11, wherein the second circulation pump is configured to generate the second flow of lubricant from the tank to a power gear box of the gas turbine engine. 13. The lubrication system of claim 11, wherein the valve is positioned downstream from the second circulation pump in the second flow of lubricant generated by the second circulation pump. 14. The lubrication system of claim 13, wherein the valve further defines a return outlet in fluid communication with a return line, and wherein the return line extends from the return outlet of the valve to the tank for returning a portion of the second flow of lubricant to the tank. 15. The lubrication system of claim 11, further comprising: a heat exchanger in thermal communication with the second flow of lubricant for removing heat from the second flow of lubricant. 16. The lubrication system of claim 15, further comprising: a heat exchanger bypass valve in fluid communication with the second flow of lubricant defining an inlet, a first outlet, and a second outlet, wherein the second outlet is in fluid communication with a bypass line, and wherein the bypass line extends between the bypass outlet and the second flow of lubricant at a location downstream from the heat exchanger. 17. The lubrication system of claim 15, wherein the heat exchanger is in thermal communication with the second flow of lubricant at a location downstream from the second circulation pump. 18. The lubrication system of claim 11, wherein the first circulation pump and the second circulation pump are each driven by a shaft of the gas turbine engine. 19. A gas turbine engine comprising: a turbine section mechanically coupled to a compressor section through a shaft;a fan driven by the shaft through a power gear box; anda lubrication system comprising a tank;a circulation pump for generating a flow of lubricant from the tank to the power gear box;a valve in fluid communication with the flow of lubricant generated by the circulation pump and defining an inlet and an outlet, the valve defining a variable throughput between the inlet and the outlet for controlling a flowrate of lubricant to the power gear box of the gas turbine engine; anda heat exchanger positioned in thermal communication with the flow of lubricant generated by the circulation pump at a location downstream of the valve for controlling a temperature of the flow of lubricant prior to the lubricant reaching the power gear box. 20. The gas turbine engine of claim 19, wherein the circulation pump is a dedicated circulation pump for the power gear box, and wherein the lubrication system further comprises a main circulation pump for generating a flow of lubricant from the tank to one or more of the compressor section of the gas turbine engine and the turbine section of the gas turbine engine.