Oil thermal management system for cold weather operations of a gas turbine engine

1. An oil thermal management system for a gas turbine engine, comprising:

a geared architecture that drives a fan at a lower speed than a low spool of the gas turbine engine during engine operation;

an oil system in communication with the geared architecture to supply oil;

an oil return passage having a check valve connected to an inlet of an oil tank;

the oil tank connected to at least the geared architecture through a first outlet;

a recirculation conduit connected to a second outlet of the oil tank and the oil return passage between the check valve and the inlet;

a heater system that comprises a heater element thermally coupled with the recirculation conduit;

an oil circulation pump in fluid communication with the recirculation conduit, wherein the oil circulation pump and the heating element are in series along the recirculation conduit in that order from the second outlet to the inlet; and

a control system in communication with the circulation pump, the heating element and a temperature sensor in the oil tank, the control system executes oil pre-start logic operable to delay an engine start procedure and selectively operate the heater system and the circulation pump to heat oil in the oil tank of the oil system to a temperature greater than a predetermined temperature prior to engine start, wherein the predetermined oil temperature is less than −40 degrees F. (−40 degrees C.).

2. The system as recited in claim 1 , wherein the circulation pump is operable to circulate the oil when the oil is less than −40 degrees F. (−40 degrees C.).

3. The system as recited in claim 1 , wherein the oil thermal management system maintains the minimum oil temperature regardless of ambient temperature thereby permitting engine start without external ground equipment.

4. A method for starting a gas turbine engine comprising:

initiating a pre-start flight operation preparation;

sensing an oil temperature of oil in an oil tank with respect to a predetermined oil temperature associated with engine start, the oil in communication with a journal bearing of a geared architecture of the gas turbine engine that drives a fan at a lower speed than a low spool of the gas turbine engine during engine operation;

delaying the engine start in response to the oil temperature being less than the predetermined oil temperature;

circulating the oil while heating through conduction via a circulation pump in fluid communication with a recirculation conduit, wherein an oil return passage returns the oil to an inlet of the oil tank through a check valve, wherein the circulation pump and a heating element are in series along the recirculation conduit in that order from an outlet of the oil tank to the inlet of the oil tank, the recirculation conduit connected to the outlet and an oil return passage downstream of the check valve in the oil return passage, wherein the circulating in the oil tank occurs prior to the engine start in response to the oil temperature being less than the predetermined oil temperature during the pre-start flight operation preparation when the oil is in a high viscosity state, the high viscosity state is due to temperature operations less than −40 degrees F. (−40 degrees C.); and

initiating the engine start procedure once the oil temperature within the oil tank is greater than the predetermined oil engine start temperature.

5. The method as recited in claim 4 , wherein initiating the pre-start flight operation preparation comprises executing oil pre-start logic after cold-soak.

6. The method as recited in claim 4 , wherein initiating the pre-start flight operation preparation comprises executing oil pre-start logic prior to engine start.

7. The system as recited in claim 2 , wherein the circulation pump and the heating element are operated in concert prior to engine start.