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US 2010/0140842 A1Published application
Controlling temperature in exothermic reactions with a phase change material
OwnerKarl M. Nelson, Geoffrey Allen Butlerinventors
Life of this patent
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Abstract
An apparatus may comprise a tool capable of holding a part during curing of the part, and a passive temperature control system. The passive temperature control system may have a phase change material selected as having a phase change temperature that may be capable of controlling heat generated by the part during curing of the part held by the tool.
Claims26
An apparatus comprising:
- a tool capable of holding a part during curing of the part;
- and
- a passive temperature control system, wherein the passive temperature control system has a phase change material capable of controlling excess heat generated from an exothermic reaction by absorbing the excess heat, the exothermic reaction caused during curing of the part, the phase change material being selected as having a phase change temperature between a solid phase and a liquid phase, the phase change material capable of transitioning from the solid phase to the liquid phase as the excess heat is absorbed and the phase change temperature is reached, and the phase change material capable of automatically reverting from the liquid phase to the solid phase.
(canceled)
(canceled)
An apparatus for curing aircraft parts, the apparatus comprising:
- a tool capable of holding an aircraft part during curing of the aircraft part;
- and
- a passive temperature control system, the passive temperature control system having a phase change material selected as having a phase change temperature capable of controlling heat generated by an aircraft part during curing of the aircraft part held by the tool, the passive temperature control system comprising one of:
- a plurality of cavities formed in the tool, and the phase change material located within the plurality of cavities, the plurality of cavities being located a distance from a surface of the tool on which the part is placed to allow the phase change material to absorb heat from the aircraft part, the plurality of cavities being formed in a side of the tool substantially parallel to the surface of the tool and an air gap being present in each cavity in the plurality of cavities;
- a plate having a plurality of grooves, and the phase change material located in the plurality of grooves, the plate being capable of being attached to the tool to allow the phase change material to absorb the heat from the aircraft part;
- a caul plate comprising a hard layer and a support layer and the phase change material embedded within the caul plate, the phase change material being capable of absorbing the heat when the caul plate is located on the aircraft part during curing of the aircraft part, the phase change material being in a form of a plurality of beads, rods, wires, or a plate embedded within the caul plate, the caul plate comprising the hard layer and wherein the plurality of beads is embedded in the support layer, the support layer comprising a material selected from one of a elastomeric material, a composite material, and a plastic;
- and
- the plurality of cavities formed in the tool, the caul plate, and the phase change material located within the plurality of cavities and the caul plate, the plurality of cavities being located the distance from the surface of the tool on which the aircraft part is placed to allow the phase change material to absorb the heat from the aircraft part and the phase change material in the caul plate being located a distance from the aircraft part to allow the phase change material to absorb the heat when the caul plate is located on the aircraft part during curing of the aircraft part, an exothermic reaction occurring in curing one of an adhesive, a potting compound, or a filler between a first component of the aircraft part and a second component of the aircraft part or in curing the composite material for the part, the phase change temperature being for a solid to liquid phase change and is from around 200 degrees Fahrenheit to around 375 degrees Fahrenheit, and the phase change material being selected from one of a metal, a metal alloy, a solder metal, and a eutectic metal.
5 more elements
A method for curing a part, the method comprising:
- placing a part on a tool for curing the part;
- and
- curing the part using a passive temperature control system while the part is on the tool, wherein the passive temperature control system has a phase change material selected as having a phase change temperature capable of controlling heat generated by the part during curing of the part.
A method for curing an aircraft part, the method comprising:
- placing a part on a tool for curing the part;
- and
- curing the part using a passive temperature control system while the part is on the tool, wherein the passive temperature control system has a phase change material selected as having a phase change temperature capable of controlling heat generated by the part during curing of the part, wherein the passive temperature control system comprises one of:
- a plurality of cavities formed in the tool and the phase change material located within the plurality of cavities, wherein the plurality of cavities is located a distance from a surface of the tool on which the part is placed to allow the phase change material to absorb heat from the aircraft part;
- a plate having a plurality of grooves and the phase change material located in the plurality of grooves, wherein the plate is capable of being attached to the tool to allow the phase change material to absorb the heat from the aircraft part;
- a caul plate and the phase change material embedded within the caul plate, wherein the phase change material is capable of absorbing the heat when the caul plate is located on the part during curing of the part;
- and
- the plurality of cavities formed in the tool, the caul plate, and the phase change material located within the plurality of cavities and the caul plate, wherein the plurality of cavities is located the distance from the surface of the tool on which the aircraft part is placed to allow the phase change material to absorb the heat from the aircraft part and wherein the phase change material in the caul plate is located a distance from the aircraft part to allow the phase change material to absorb the heat when the caul plate is located on the aircraft part during curing of the aircraft part.
5 more elements
Dependencies are inferred from the claim text.