Gas turbine engine with graphene heat pipe
A graphene heat pipe for a gas turbine engine includes a body of graphene. The body has a hot side to accept heat from the gas turbine engine, a cold side to reject heat from the body, and an adiabatic portion to flow heat within the body between the hot side and the cold side.
1. A graphene heat pipe for a gas turbine engine, the graphene heat pipe comprising:
a body comprising a copper substrate coated with graphene, the body having a hot side to accept heat from the gas turbine engine, a cold side to reject heat from the body, and an adiabatic portion to flow heat within the body between the hot side and the cold side, wherein the graphene heat pipe is a strip wrapped into a wound coil, and the graphene heat pipe is formed as a solid structure such that the graphene heat pipe is formed absent an interior phase change volume and no phase change occurs within the graphene heat pipe.
2. A gas turbine engine of an aircraft, the gas turbine engine comprising:
a fan section comprising a fan duct that establishes a fan flow path;
a compressor section comprising a plurality of blades and vanes that establish a compressor flow path; and
a graphene heat pipe installed to flow heat from the compressor flow path to the fan flow path, wherein the graphene heat pipe comprises a body comprising graphene, the body directly contacting an interior surface of a vane of the compressor section, the body having a hot side to accept heat from the compressor flow path, a cold side to reject heat from the body to the fan flow path, and an adiabatic portion to flow heat within the body between the hot side and the cold side, the graphene heat pipe is a strip wrapped into a wound coil, and the graphene heat pipe is formed as a solid structure such that graphene heat pipe is formed absent an interior phase change volume and no phase change occurs within the graphene heat pipe.
3. The gas turbine engine of claim 2 , wherein the body is at least partially coated with graphene.
4. The gas turbine engine of claim 2 , wherein the body is integrally formed of graphene.
5. A method for cooling a compressor flow path of a gas turbine engine, the method comprising:
providing a graphene heat pipe within the gas turbine engine, wherein the graphene heat pipe comprises a body comprising graphene, the body directly contacting an interior surface of a vane of a compressor section of the gas turbine engine, the body having a hot side, a cold side, and an adiabatic portion to flow heat within the body between the hot side and the cold side, the graphene heat pipe is a strip wrapped into a wound coil and formed as a solid structure such that the graphene heat pipe is formed absent an interior phase change volume and no phase change occurs within the graphene heat pipe;
accepting heat at the hot side of the graphene heat pipe proximate to the compressor flow path of the gas turbine engine;
flowing heat from the hot side of the graphene heat pipe through the adiabatic portion of the graphene heat pipe to the cold side of the graphene heat pipe; and
rejecting heat from the cold side of the graphene heat pipe to a fan flow path of the gas turbine engine.
6. The method as in claim 5 , wherein the body is a copper substrate at least partially coated with graphene.
7. The method as in claim 5 , further comprising installing a plurality of the graphene heat pipes at a plurality of axially distributed locations within the gas turbine engine.
8. The method as in claim 5 , wherein the body is integrally formed of graphene.
9. The method as in claim 5 , wherein the body is a copper substrate infused with graphene.
10. The method as in claim 5 , further comprising installing a plurality of the graphene heat pipes at a plurality of radially distributed locations within the gas turbine engine.