Thermal management systems having an oil tank comprising solid-solid phase change material for gas turbine engines
A thermal management system for a gas turbine engine includes an oil tank, a pump in fluid communication with the oil tank configured to generate a flow of oil from the oil tank, at least one heat exchanger downstream of the oil tank, and one or more thermal loads downstream of the at least one heat exchanger. The oil tank is formed from a solid-solid phase change material.
1. A thermal management system for a gas turbine engine including a compressor section, a combustion section, and a turbine section in serial flow order and at least partially defining a working gas flow path, the thermal management system comprising:
an oil tank comprising a solid-solid phase change material, a solid-liquid phase change material, or both the solid-solid phase change material and the solid-liquid phase change material, wherein the oil tank comprises at least one wall formed of the solid-solid phase change material;
a pump in fluid communication with the oil tank, the pump configured to generate a flow of oil from the oil tank;
at least one heat exchanger positioned downstream of the oil tank; and
one or more thermal loads positioned downstream of the at least one heat exchanger.
2. The thermal management system of claim 1 , wherein:
the at least one wall defines a chamber configured to store the oil.
3. The thermal management system of claim 1 , wherein the at least one wall defines a plurality of recesses.
4. The thermal management system of claim 1 , further comprising:
a plurality of rods extending from an interior surface of the at least one wall;
wherein the plurality of rods are formed from the solid-solid phase change material.
5. The thermal management system of claim 1 , wherein the at least one wall of the oil tank comprises:
an outer wall; and
an inner wall;
wherein the outer wall and the inner wall define a first chamber; and
wherein the inner wall defines a second chamber fluidly isolated from the first chamber.
6. The thermal management system of claim 5 , wherein the outer wall is formed from the solid-solid phase change material.
7. The thermal management system of claim 5 , wherein the inner wall is formed from the solid-solid phase change material.
8. The thermal management system of claim 5 , wherein:
the outer wall is formed from the solid-solid phase change material; and
the inner wall is formed from the solid-solid phase change material.
9. The thermal management system of claim 5 , wherein:
the first chamber includes the solid-liquid phase change material; and
the second chamber includes the oil.
10. The thermal management system of claim 9 , wherein the solid-liquid phase change material comprises a material having a transition temperature between 165° F. and 305° F. and a latent heat between 30 Btu/lb and 200 Btu/lb.
11. The thermal management system of claim 9 , wherein the first chamber includes a solid foam defining a plurality of cells, and wherein the solid-liquid phase change material is disposed in the plurality of cells of the solid foam.
12. The thermal management system of claim 1 , wherein:
the oil tank defines a fluid inlet and a fluid outlet; and
the fluid inlet and the fluid outlet each include a plurality of protrusions extending from an interior surface of the fluid inlet and the fluid outlet.
13. The thermal management system of claim 12 , wherein the plurality of protrusions are formed from the solid-solid phase change material.
14. The thermal management system of claim 1 , wherein the at least one heat exchanger comprises:
a first oil cooler including an air-cooled oil cooler; and
a second oil cooler including a fuel-cooled oil cooler.
15. The thermal management system of claim 1 , wherein the one or more thermal loads comprise a reduction gearbox, an accessory gearbox, one or more sumps, or a combination thereof.
16. The thermal management system of claim 1 , wherein the solid-solid phase change material comprises a material having a transition temperature between 200° F. and 305° F. and a latent heat between 3 Btu/lb and 200 Btu/lb.
17. The thermal management system of claim 1 , wherein the solid-solid phase change material is configured to absorb heat from the oil.
18. The thermal management system of claim 1 , wherein the oil tank is configured to maintain a temperature of the oil below a threshold temperature during a transient condition of the gas turbine engine.
19. The thermal management system of claim 18 , wherein the transient condition comprises an acceleration from ground idle to takeoff condition of an aircraft, a climb operating condition of the aircraft, a step climb condition of the aircraft, an acceleration from flight idle to cruise condition of the aircraft, a landing condition of the aircraft, another engine transient condition, or a combination thereof.
20. A gas turbine engine, comprising:
a fan;
a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a working gas flow path; and
a thermal management system comprising:
an oil tank comprising a solid-solid phase change material, a solid-liquid phase change material, or both the solid-solid phase change material and the solid-liquid phase change material, wherein the oil tank comprises at least one wall formed of the solid-solid phase change material,
a pump in fluid communication with the oil tank, the pump configured to generate a flow of oil from the oil tank,
at least one heat exchanger positioned downstream of the oil tank, and
one or more thermal loads positioned downstream of the at least one heat exchanger.