Patent
US 10,830,094GAS TURBINE ENGINE WITH GRAPHENE HEAT PIPE
Matthew P. Forcier
US
Copyright © 2026 Matter42. All rights reserved.
Patent
Atlas literature
Patent
US 10,830,094Patent drawings and their descriptions. Click a drawing to enlarge it.
FIG. 1 in accordance with an embodiment of the disclosure; [0023]
FIG. 2 is a partial view of graphene heat pipe installation location examples in the gas turbine engine of
FIG. 3 depicts an example of a graphene heat pipe in accordance with an embodiment of the disclosure; [0024]
FIG. 4 depicts another example of a graphene heat pipe in accordance with another embodiment of the disclosure; [0025]
FIG. 5 depicts a further example of a graphene heat pipe in accordance with another embodiment of the disclosure; and [0026]
FIG. 6 is a flow chart illustrating a method in accordance with an embodiment of the disclosure.
Claims define the patent's legal scope. Independent claims stand alone; dependent claims (nested) narrow them. Click a claim to expand its dependents.
A graphene heat pipe for a gas turbine engine, the graphene heat pipe comprising: a body comprising a copper substrate coated with g raphene, 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. Currently amended
2-8. Canceled
Canceled
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 the graphene heat pipe is formed absent an interior phase change volume and no phase change occurs within the graphene heat pipe. Currently amended
The gas turbine engine of claim 9, wherein the body is at least partially coated with graphene. Previously presented
The gas turbine engine of claim 9, wherein the body is integrally formed of graphene. Previously presented
Canceled
13-16. Canceled
Canceled
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-a 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. Currently amended
The method as in claim 17, wherein the body is a copper substrate at least partially coated with graphene. Currently amended
The method as in claim 17, further comprising installing a plurality of the graphene heat pipes at a plurality of axially distributed locations within the gas turbine engine. Currently amended
The method as in claim 17, wherein the body is integrally formed of graphene. New
The method as in claim 17, wherein the body is a copper substrate infused with graphene. New
The method as in claim 17, further comprising installing a plurality of the graphene heat pipes at a plurality of radially distributed locations within the gas turbine engine. New
Canceled
Layer stacks claimed or described, ordered top of device to substrate.
graphene heat pipe
gas turbine engine with graphene heat pipe
No layer stack recorded.
Materials described outside the worked examples.
graphene
copper substrate
Cu
Performance values and ranges asserted in the specification or claims.
| Property | Value | Material |
|---|---|---|
thermal conductivity relative to copper heat pipe | — | graphene |
Related documents with shared materials, methods, properties, or citations.
Patent
Atlas literature
Patent
US 10,830,094Patent drawings and their descriptions. Click a drawing to enlarge it.
FIG. 1 in accordance with an embodiment of the disclosure; [0023]
FIG. 2 is a partial view of graphene heat pipe installation location examples in the gas turbine engine of
FIG. 3 depicts an example of a graphene heat pipe in accordance with an embodiment of the disclosure; [0024]
FIG. 4 depicts another example of a graphene heat pipe in accordance with another embodiment of the disclosure; [0025]
FIG. 5 depicts a further example of a graphene heat pipe in accordance with another embodiment of the disclosure; and [0026]
FIG. 6 is a flow chart illustrating a method in accordance with an embodiment of the disclosure.
Claims define the patent's legal scope. Independent claims stand alone; dependent claims (nested) narrow them. Click a claim to expand its dependents.
A graphene heat pipe for a gas turbine engine, the graphene heat pipe comprising: a body comprising a copper substrate coated with g raphene, 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. Currently amended
2-8. Canceled
Canceled
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 the graphene heat pipe is formed absent an interior phase change volume and no phase change occurs within the graphene heat pipe. Currently amended
The gas turbine engine of claim 9, wherein the body is at least partially coated with graphene. Previously presented
The gas turbine engine of claim 9, wherein the body is integrally formed of graphene. Previously presented
Canceled
13-16. Canceled
Canceled
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-a 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. Currently amended
The method as in claim 17, wherein the body is a copper substrate at least partially coated with graphene. Currently amended
The method as in claim 17, further comprising installing a plurality of the graphene heat pipes at a plurality of axially distributed locations within the gas turbine engine. Currently amended
The method as in claim 17, wherein the body is integrally formed of graphene. New
The method as in claim 17, wherein the body is a copper substrate infused with graphene. New
The method as in claim 17, further comprising installing a plurality of the graphene heat pipes at a plurality of radially distributed locations within the gas turbine engine. New
Canceled
Layer stacks claimed or described, ordered top of device to substrate.
graphene heat pipe
gas turbine engine with graphene heat pipe
No layer stack recorded.
Materials described outside the worked examples.
graphene
copper substrate
Cu
Performance values and ranges asserted in the specification or claims.
| Property | Value | Material |
|---|---|---|
thermal conductivity relative to copper heat pipe | — | graphene |
Related documents with shared materials, methods, properties, or citations.
Patent
Atlas literature
Patent
US 10,830,094Patent drawings and their descriptions. Click a drawing to enlarge it.
FIG. 1 in accordance with an embodiment of the disclosure; [0023]
FIG. 2 is a partial view of graphene heat pipe installation location examples in the gas turbine engine of
FIG. 3 depicts an example of a graphene heat pipe in accordance with an embodiment of the disclosure; [0024]
FIG. 4 depicts another example of a graphene heat pipe in accordance with another embodiment of the disclosure; [0025]
FIG. 5 depicts a further example of a graphene heat pipe in accordance with another embodiment of the disclosure; and [0026]
FIG. 6 is a flow chart illustrating a method in accordance with an embodiment of the disclosure.
Claims define the patent's legal scope. Independent claims stand alone; dependent claims (nested) narrow them. Click a claim to expand its dependents.
A graphene heat pipe for a gas turbine engine, the graphene heat pipe comprising: a body comprising a copper substrate coated with g raphene, 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. Currently amended
2-8. Canceled
Canceled
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 the graphene heat pipe is formed absent an interior phase change volume and no phase change occurs within the graphene heat pipe. Currently amended
The gas turbine engine of claim 9, wherein the body is at least partially coated with graphene. Previously presented
The gas turbine engine of claim 9, wherein the body is integrally formed of graphene. Previously presented
Canceled
13-16. Canceled
Canceled
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-a 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. Currently amended
The method as in claim 17, wherein the body is a copper substrate at least partially coated with graphene. Currently amended
The method as in claim 17, further comprising installing a plurality of the graphene heat pipes at a plurality of axially distributed locations within the gas turbine engine. Currently amended
The method as in claim 17, wherein the body is integrally formed of graphene. New
The method as in claim 17, wherein the body is a copper substrate infused with graphene. New
The method as in claim 17, further comprising installing a plurality of the graphene heat pipes at a plurality of radially distributed locations within the gas turbine engine. New
Canceled
Layer stacks claimed or described, ordered top of device to substrate.
graphene heat pipe
gas turbine engine with graphene heat pipe
No layer stack recorded.
Materials described outside the worked examples.
graphene
copper substrate
Cu
Performance values and ranges asserted in the specification or claims.
| Property | Value | Material |
|---|---|---|
thermal conductivity relative to copper heat pipe | — | graphene |
Related documents with shared materials, methods, properties, or citations.
Patent
Atlas literature
Patent
US 10,830,094Patent drawings and their descriptions. Click a drawing to enlarge it.
FIG. 1 in accordance with an embodiment of the disclosure; [0023]
FIG. 2 is a partial view of graphene heat pipe installation location examples in the gas turbine engine of
FIG. 3 depicts an example of a graphene heat pipe in accordance with an embodiment of the disclosure; [0024]
FIG. 4 depicts another example of a graphene heat pipe in accordance with another embodiment of the disclosure; [0025]
FIG. 5 depicts a further example of a graphene heat pipe in accordance with another embodiment of the disclosure; and [0026]
FIG. 6 is a flow chart illustrating a method in accordance with an embodiment of the disclosure.
Claims define the patent's legal scope. Independent claims stand alone; dependent claims (nested) narrow them. Click a claim to expand its dependents.
A graphene heat pipe for a gas turbine engine, the graphene heat pipe comprising: a body comprising a copper substrate coated with g raphene, 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. Currently amended
2-8. Canceled
Canceled
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 the graphene heat pipe is formed absent an interior phase change volume and no phase change occurs within the graphene heat pipe. Currently amended
The gas turbine engine of claim 9, wherein the body is at least partially coated with graphene. Previously presented
The gas turbine engine of claim 9, wherein the body is integrally formed of graphene. Previously presented
Canceled
13-16. Canceled
Canceled
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-a 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. Currently amended
The method as in claim 17, wherein the body is a copper substrate at least partially coated with graphene. Currently amended
The method as in claim 17, further comprising installing a plurality of the graphene heat pipes at a plurality of axially distributed locations within the gas turbine engine. Currently amended
The method as in claim 17, wherein the body is integrally formed of graphene. New
The method as in claim 17, wherein the body is a copper substrate infused with graphene. New
The method as in claim 17, further comprising installing a plurality of the graphene heat pipes at a plurality of radially distributed locations within the gas turbine engine. New
Canceled
Layer stacks claimed or described, ordered top of device to substrate.
graphene heat pipe
gas turbine engine with graphene heat pipe
No layer stack recorded.
Materials described outside the worked examples.
graphene
copper substrate
Cu
Performance values and ranges asserted in the specification or claims.
| Property | Value | Material |
|---|---|---|
thermal conductivity relative to copper heat pipe | — | graphene |
Related documents with shared materials, methods, properties, or citations.