Gas turbine engine oil tank with integrated packaging configuration
A gas turbine engine includes a fan case radially outwardly of a core compartment. A compressor section is located within an engine core compartment and includes a front mount flange and an aft mount flange. An oil tank is mounted to at least one of the fan case or the front and aft mount flanges. The oil tank has a cooling structure integrated into an outer surface such that the oil tank is subjected to cooling air flow from a plurality of air sources.
1. A gas turbine engine comprising:
an engine static structure;
a fan case supported relative to the engine static structure by a radial structure;
a compressor section and a turbine section housed within the engine static structure, and a combustor section arranged axially between the compressor section and the turbine section;
a core nacelle enclosing the engine static structure to provide a core compartment; and
an oil tank mounted within the core compartment between a compressor mount flange and a firewall, the oil tank having a cooling structure integrated into an outer surface of the oil tank such that the oil tank is subjected to cooling air flow from a plurality of air sources, and wherein a main oil fill portion of the oil tank extends aft of the firewall, and including a service oil fill connection located in front of the firewall and extending through a fan exit guide vane to a fan case structure.
2. The gas turbine engine according to claim 1 wherein the cooling structure comprises an oil cooler integrally formed in the outer surface of the oil tank, the oil cooler including a plurality of ribs extending outwardly from the outer surface.
3. The gas turbine engine according to claim 1 wherein the oil tank comprises a main oil fill compartment that provides a main supply of lubrication for engine components, and wherein the cooling structure comprises an oil cooler that is integrally formed in the outer surface of the oil tank.
4. The gas turbine engine according to claim 1 wherein the plurality of air sources comprises at least one of fan air, core ventilation air, free stream air, and core bleed air.
5. The gas turbine engine according to claim 1 including a nacelle door interface incorporated into the outer surface of the oil tank.
6. The gas turbine engine according to claim 5 wherein the nacelle door interface comprises one of a seal land or an inner v-groove incorporated into the outer surface of the oil tank.
7. The gas turbine engine according to claim 1 including an accessory gearbox mounted on the engine static structure and configured to provide rotational drive to accessory drive components, and wherein the accessory gearbox is arranged within the core compartment with the oil tank and cooling structure being enclosed within the core compartment in a position axially forward of the accessory gearbox.
8. The gas turbine engine according to claim 1 wherein the compressor mount flange comprises a front compressor mount flange and wherein the compressor includes an aft compressor mount flange, wherein the oil tank is mounted to the aft compressor mount flange at the firewall.
9. The gas turbine engine according to claim 1 including an oil pump defining a centerline, and wherein the firewall includes an opening through which the main oil fill portion of the oil tank extends in an aft direction to provide a main supply interface at a firewall plane that is above the centerline of the oil pump.
10. A gas turbine engine comprising:
an engine static structure;
a fan case supported relative to the engine static structure by a radial structure; a compressor section and a turbine section housed within the engine static
structure, and a combustor section arranged axially between the compressor section and the turbine section;
a core nacelle enclosing the engine static structure to provide a core compartment; and
an oil tank mounted within the core compartment between a compressor mount flange and a firewall, the oil tank having a cooling structure integrated into an outer surface of the oil tank such that the oil tank is subjected to cooling aft flow from a plurality of air sources, and wherein the compressor mount flange comprises a front compressor mount flange and wherein the compressor includes an aft compressor mount flange wherein the oil tank is mounted to the aft compressor mount flange at the firewall and wherein the cooling structure comprises an oil cooler integrally formed in the outer surface of the oil tank, the oil cooler including a plurality of ribs extending outwardly from the outer surface.
11. The gas turbine engine according to claim 10 , wherein the plurality of air sources comprises at least one of fan air, core ventilation air, free stream air, and core bleed air.
12. The gas turbine engine according to claim 10 , including an accessory gearbox mounted on the engine static structure and configured to provide rotational drive to accessory drive components, and wherein the accessory gearbox is arranged within the core compartment with the oil tank and cooling structure being enclosed within the core compartment in a position axially forward of the accessory gearbox.
13. The gas turbine engine according to claim 10 , including an oil pump defining a centerline, and wherein the firewall includes an opening through which the main oil fill portion of the oil tank extends in an aft direction to provide a main supply interface at a firewall plane that is above the centerline of the oil pump.
14. The gas turbine engine according to claim 10 , wherein a main oil fill portion of the oil tank extends aft of the firewall, and including a service oil fill connection located in front of the firewall and extending through a fan exit guide vane to a fan case structure.
15. A gas turbine engine comprising:
an engine static structure;
a fan case supported relative to the engine static structure by a radial structure; a compressor section and a turbine section housed within the engine static
structure, and a combustor section arranged axially between the compressor section and the turbine section;
a core nacelle enclosing the engine static structure to provide a core compartment; and
an oil tank mounted within the core compartment between a compressor mount flange and a firewall, the oil tank having a cooling structure integrated into an outer surface of the oil tank such that the oil tank is subjected to cooling air flow from a plurality of aft sources, and wherein the compressor mount flange comprises a front compressor mount flange and wherein the compressor includes an aft compressor mount flange wherein the oil tank is mounted to the aft compressor mount flange at the firewall and wherein the oil tank comprises a main oil fill compartment that provides a main supply of lubrication for engine components, and wherein the cooling structure comprises an oil cooler that is integrally formed in the outer surface of the oil tank.
16. The gas turbine engine according claim 15 wherein the plurality of air sources comprises at least one of fan air, core ventilation air, free stream air, and core bleed air.
17. The gas turbine engine according to claim 15 including an accessory gearbox mounted on the engine static structure and configured to provide rotational drive to accessory drive components, and wherein the accessory gearbox is arranged within the core compartment with the oil tank and cooling structure being enclosed within the core compartment in a position axially forward of the accessory gearbox.
18. The gas turbine engine according claim 15 including an oil pump defining a centerline, and wherein the firewall includes an opening through which the main oil fill portion of the oil tank extends in an aft direction to provide a main supply interface at a firewall plane that is above the centerline of the oil pump.
19. The gas turbine engine according to claim 15 wherein a main oil fill portion of the oil tank extends aft of the firewall, and including a service oil fill connection located in front of the firewall and extending through a fan exit guide vane to a fan case structure.