Gas turbine engine oil tank
A gas turbine engine includes an engine static structure housing that includes a compressor section and a turbine section. A combustor section is arranged axially between the compressor section and the turbine section. A core nacelle encloses the engine static structure to provide a core compartment. An oil tank is arranged in the core compartment and is axially aligned with the compressor section. A heat exchanger is secured to the oil tank and arranged in the core compartment.
1. A gas turbine engine comprising:
an engine static structure housing a compressor section and a turbine section, 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;
an oil tank arranged in the core compartment and axially aligned with the compressor section;
a heat exchanger secured to the oil tank and arranged in the core compartment; and
a lubrication pump configured to provide oil from the oil tank to the heat exchanger.
2. The gas turbine engine according to claim 1 , wherein the compressor section includes a low pressure compressor section arranged axially upstream from a high pressure compressor section, the oil tank axially aligned with at least a portion of the low pressure compressor section.
3. The gas turbine engine according to claim 1 , wherein the compressor and turbine sections are mounted on at least one spool, and comprising a fan case housing a fan connected to the at least one spool, a fan nacelle enclosing the fan case, and a bypass flow path provided between the core and fan nacelles.
4. The gas turbine engine according to claim 3 , comprising radial structure interconnecting the engine static structure and the fan case, a lubrication passage extending through the radial structure, and a tube fluidly interconnecting the lubrication passage to the oil tank.
5. The gas turbine engine according to claim 4 , wherein the radial structure includes flow exit guide vanes.
6. The gas turbine engine according to claim 5 , wherein the flow exit guide vane includes a radially extending cavity providing the lubrication passage.
7. The gas turbine engine according to claim 5 , wherein the flow exit guide vane includes a radially extending cavity, and a conduit arranged in the cavity and fluidly connected to the tube.
8. The gas turbine engine according to claim 4 , comprising a fill tube mounted to the fan case, wherein the fan nacelle includes a cover configured to be removably secured over the fill tube.
9. The gas turbine engine according to claim 3 , comprising at least one bearing compartment configured to support the spool, and a lubrication system having a gearbox arranged in the core compartment, the lubrication pump fluidly connected to the oil tank and the bearing compartment.
10. The gas turbine engine according to claim 3 , wherein the oil tank includes a portion extending through an opening in the core nacelle and exposed to the bypass flow path.
11. The gas turbine engine according to claim 1 , wherein the lubrication pump is arranged fluidly between the oil tank and the heat exchanger.
12. A gas turbine engine comprising:
an engine static structure housing a compressor section and a turbine section, 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;
an oil tank arranged in the core compartment and axially aligned with the compressor section, wherein the oil tank includes an exterior surface arranged in an opening of the core nacelle, the core nacelle having an outer contour facing the bypass flow path, and the exterior surface following the outer contour; and
a heat exchanger secured to the oil tank and arranged in the core compartment.
13. The gas turbine engine according to claim 12 , wherein the oil tank is arcuate in shape and arranged axially forward of a gearbox mounted to the engine static structure.
14. The gas turbine engine according to claim 13 , wherein the oil tank includes a wall having fins extending through slots providing the opening and into the bypass flow path.
15. The gas turbine engine according to claim 12 , wherein the oil tank includes a portion extending through an opening in the core nacelle and exposed to the bypass flow path.
16. A gas turbine engine comprising:
an engine static structure supported relative to a fan case by a radial structure;
an oil tank mounted to the engine static structure;
an oil fill tube mounted to the fan case and fluidly connected to the oil tank; and
a fan nacelle enclosing the fan case, the fan nacelle provides a removable cover directly connected to the fan nacelle and arranged over the oil fill tube.
17. The gas turbine engine according to claim 16 , comprising a core nacelle enclosing the engine static structure to provide a core compartment, the oil tank arranged in the core compartment.
18. The gas turbine engine according to claim 17 , comprising a lubrication passage arranged in the radial structure fluidly interconnecting the oil fill tube to the oil tank.
19. A gas turbine engine comprising:
an engine static structure supported relative to a fan case by a radial structure, a lubrication passage extending through the radial structure, the engine static structure housing a compressor section and a turbine section, 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;
an oil tank arranged in the core compartment and axially aligned with the compressor section;
a heat exchanger secured to the oil tank and arranged in the core compartment;
an oil fill tube mounted to the fan case, and the lubrication passage fluidly interconnecting the oil fill tube to the oil tank; and
a fan nacelle enclosing the fan case, the fan nacelle provides a removable cover arranged over the oil fill tube.