Air oil cooler airflow augmentation system

1. A lubricant supply system for a gas turbine engine comprising:

a lubricant pump delivering lubricant to an outlet line that splits into at least a hot line and a cool line, said hot line being directed primarily to locations associated with the gas turbine engine that are not intended to receive cooler lubricant, and said cool line being directed to at least one component with an operating temperature lower than the locations associated with the gas turbine engine that are not intended to receive cooler lubricant;

at least one heat exchanger within the cool line at which lubricant is cooled, the least one heat exchanger including at least an air/oil cooler wherein air is pulled across said air/oil cooler to cool lubricant, wherein at least a portion of the lubricant in said cool line is passed through a first fuel/oil cooler, the at least a portion of lubricant bypassing the air/oil cooler configured to cool the lubricant using fuel, leading to a combustion section of the gas turbine engine, and the lubricant in said hot line not passing through said first fuel/oil cooler; and

an ejector within the air/oil cooler for augmenting air flow across the air/oil cooler selectively responsive to an operating condition not providing air flow sufficient for cooling lubricant to desired temperature.

2. The system as recited in claim 1 , including selectively actuating a fan to provide airflow through to the ejector to augment airflow across the air/oil cooler.

3. The system as recited in claim 1 , including selectively providing airflow from a compressor section to provide airflow to the ejector to augment airflow across the air/oil cooler.

4. The system as set forth in claim 1 , wherein a valve is positioned on said cool line and splits said cool line into two lines, with a first line being directed through said first fuel/oil cooler at which the lubricant is cooled by fuel leading to the combustion section for the gas turbine engine, and the lubricant in the cool line that is not being directed to the first fuel/oil cooler but being directed to at least one other cooler through a second line, and, said cool line being split into said two lines at a location downstream of a point where said outlet line is split into said hot line and said cool line.

5. The system as set forth in claim 4 , wherein a bypass valve selectively bypasses fuel downstream of said fuel/oil cooler back upstream.

6. The system as set forth in claim 5 , wherein said bypass valve alternatively directs the fuel upstream of the first fuel/oil cooler, or downstream of the first fuel/oil cooler.

7. The system as set forth in claim 4 , wherein said at least one other cooler also includes an oil-to-oil cooler at which lubricant from a generator exchanges heat with the lubricant in said second line.

8. The system as set forth in claim 7 , wherein lubricant from said generator is also passed through a second fuel/oil cooler at a location upstream of said first fuel/oil cooler.

9. A gas turbine engine comprising:

a fan, a compressor section, including a low pressure compressor section and a high pressure compressor section;

a combustor;

a turbine section including both a low pressure turbine and a high pressure turbine section, and said low pressure turbine section driving said low pressure compressor section; and

a fan drive gear system provided such that said low pressure turbine further driving said fan, with said fan and said low pressure compressor being driven at different speeds;

a lubricant system including a lubricant pump delivering lubricant to an outlet line that splits into at least a hot line and a cool line, said hot line being directed primarily to locations associated with the gas turbine engine that are not intended to receive cooler lubricant, and said cool line being directed to at least one component with an operating temperature lower than the locations associated with the gas turbine engine that are not intended to receive cooler lubricant;

at least one heat exchanger within the cool line at which lubricant is cooled, the least one heat exchanger including at least an air/oil cooler wherein air is pulled across said air/oil cooler to cool lubricant, wherein at least a portion of the lubricant in said cool line is passed through a first fuel/oil cooler, the at least a portion of the lubricant bypassing the air/oil cooler, configured to cool the lubricant using fuel, leading to a combustion section of the associated gas turbine engine, and the lubricant in said hot line not passing through said first fuel/oil cooler; and

an ejector within the air/oil cooler for augmenting air flow across the air/oil cooler selectively responsive to an operating condition not providing air flow sufficient for cooling lubricant to desired temperature.

10. The gas turbine engine as recited in claim 9 , including selectively actuating a fan to provide airflow through to the ejector to augment airflow across the air/oil cooler.

11. The gas turbine engine as recited in claim 9 , including selectively providing airflow from a compressor section to provide airflow to the ejector to augment airflow across the air/oil cooler.

12. The gas turbine engine as set forth in claim 9 , wherein said locations in the engine that are not intended to receive cooler lubricant include bearings associated with at least the turbine section.

13. The gas turbine engine as recited in claim 9 , wherein a valve is positioned on said cool line and splits said cool line into two lines, with said first line being directed through the first fuel/oil cooler at which the lubricant is cooled by fuel leading to the combustion section for the gas turbine engine, and the lubricant in the cool line that is not being directed to the first fuel/oil cooler but being directed to at least one other cooler through a second line and, said cool line is split into said two lines at a location downstream of a point where said outlet line is split into said hot line and said cool line.

14. The gas turbine engine as recited in claim 13 , wherein a bypass valve selectively bypasses fuel downstream of said first fuel/oil cooler back upstream.

15. The gas turbine engine as recited in claim 14 , wherein said bypass valve alternatively directs the fuel upstream of the first fuel/oil cooler, or downstream of the first fuel/oil cooler.

16. The gas turbine engine as recited in claim 13 , wherein said at least one other cooler also includes an oil-to-oil cooler at which lubricant from a generator exchanges heat with the lubricant in said second line.

17. The gas turbine engine as set forth in claim 14 , wherein oil from said generator is also passed through a second fuel/oil cooler at a location upstream of said first fuel/oil cooler.

18. A method of managing lubricant supply for a gas turbine engine comprising the steps of:

moving a lubricant from a main lubricant pump into an outlet line, and splitting the outlet line into a cool line and a hot line, the cool line which is delivered into at least one heat exchanger to cool the lubricant, and the cooled lubricant then being delivered to at least a one component requiring cooler lubricant;

supplying lubricant from the hot line which is not passed through said at least one heat exchanger to bearings associated with at least a turbine section in the gas turbine engine; said at least one heat exchanger including at least an air/oil cooler wherein air is pulled across said air/oil cooler to cool lubricant, and said air/oil cooler being provided with an ejector selectively tapping compressed air to increase airflow across the air/oil cooler; and

passing at least a portion of the lubricant in the cool line through a first fuel/oil cooler, the at least a portion of the lubricant bypassing the air/oil cooler, configured to cool the lubricant using fuel, leading to a combustion section of the gas turbine engine, and the lubricant in said hot line not passing through said first fuel/oil cooler.