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; and
a lubrication pump configured to provide oil from the oil tank to heat exchanger;
wherein the core nacelle has an opening into the core compartment, and the opening exposes an exterior surface of the oil tank.
2. The gas turbine engine of claim 1 , wherein the heat exchanger is secured to the oil tank and arranged in the core compartment.
3. The gas turbine engine of claim 2 , wherein the heat exchanger is integrally formed and shares a common wall with the oil tank.
4. The gas turbine engine of claim 2 , wherein the heat exchanger is mounted to the oil tank using a fastening arrangement.
5. The gas turbine engine of claim 2 , wherein the lubrication pump is arranged fluidly between the oil tank and the heat exchanger.
6. The gas turbine engine of claim 1 , wherein the opening is multiple slots in the core nacelle.
7. The gas turbine engine of claim 6 , wherein the oil tank includes a wall having fins extending through the slots.
8. The gas turbine engine of claim 1 , wherein a portion of the oil tank extends through the opening into the bypass flow path.
9. The gas turbine engine of claim 8 , wherein the portion of the oil tank includes fins.
10. The gas turbine engine of 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.
11. The gas turbine engine of claim 10 , further comprising a 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.
12. The gas turbine engine of claim 11 , wherein the radial structure includes flow exit guide vanes.
13. The gas turbine engine of claim 12 , wherein the flow exit guide vanes include a radially extending cavity providing the lubrication passage.
14. The gas turbine engine of claim 13 , wherein each of the flow exit guide vanes includes a radially extending cavity, and a conduit arranged in the cavity and fluidly connected to the tube.
15. The gas turbine engine of claim 1 , wherein the compressor section includes a low pressure compressor section arranged axially upstream from a high pressure compressor section, and the oil tank is axially aligned with at least a portion of the low pressure compressor section.
16. 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 and having slots providing openings into the core compartment;
an oil tank arranged in the core compartment;
wherein the compressor and turbine sections are mounted on at least one spool, and comprising a fan case housing a fan connected to the spool, a fan nacelle enclosing the fan case, and a bypass flow path provided between the core and fan nacelles; and
wherein the oil tank includes a wall having fins extending through the slots in the core nacelle.
17. The gas turbine engine of claim 16 , wherein the fins extend into the bypass flow path.
18. The gas turbine engine of claim 16 , wherein the oil tank is axially arranged with the compressor section.
19. The gas turbine engine of claim 18 , wherein the compressor section includes a low pressure compressor section arranged axially upstream from a high pressure compressor section, and the oil tank is axially aligned with at least a portion of the low pressure compressor section.
20. The gas turbine engine of claim 16 , further comprising an oil fill tube mounted to the fan case and fluidly connected to the oil tank.