# US 2012/0003597 A1 · Industrial oven for curing composite material structures > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2012/0003597 A1 - Document ID: US20120003597A1 - Status: Published application - Kind: A1 - Application number: 12/859,148 - Filed: 2010-08-18 - Published: 2012-01-05 - Earliest claimed: 2010-07-02 - Assignees: Asc Process Systems - Inventors: Dave Mason - Web page: https://patentgrep.com/patent/US20120003597A1 ## CPC - F27B 17/0083: {with means for circulating the atmosphere} - B29C 35/02: Heating or curing, e.g. crosslinking or vulcanizing {during moulding, e.g. in a mould}(cold vulcanisation B29C35/18 {; vulcanising tyres, presses therefor B29D30/0601}) - B29C 35/0227: {using pressure vessels, e.g. autoclaves, vulcanising pans (B29C35/065 takes precedence)} - B29C 2035/046: {dried air} - F27B: FURNACES, KILNS, OVENS OR RETORTS IN GENERAL; OPEN SINTERING OR LIKE APPARATUS - B29C: SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING (making preforms B29B11/00; making laminated products by combining previously unconnected layers which become one product whose layers will remain together B32B37/00 - B32B41/00) ## Abstract An industrial oven system for curing composite material parts can include an oven compartment configured to receive a composite material structure therein that extends along a majority of the length and/or width of the compartment, the compartment having an inner wall that defines a cavity between proximal and distal ends of the compartment. A shroud can be disposed circumferentially between the inner wall of the compartment and an outer wall of the composite material structure. The shroud defines a first longitudinal annular channel between the inner wall and an outer surface of the shroud, and defines a second longitudinal annular channel between the outer wall of the composite material structure and an inner surface of the shroud. The shroud is contoured to direct a heated airflow longitudinally along the annular channels and over the composite material structure to cure the composite material structure, the heated airflow generally being at a higher temperature than a surface of the composite material part. One or more contour elements of the shroud can direct more heat to a corresponding thicker portion of the composite material structure generally aligned with the contour element relative to an amount of heat directed to adjacent relatively thinner portions of the composite material structure so as to effect a desired heating rate of the composite material structure to achieve a substantially uniform temperature along substantially the entire length of the composite material structure, thereby inhibiting warping of the composite material structure during a curing process. ## Claims ### Claim 1 An industrial oven system for curing composite material parts, comprising: an oven compartment having an inner wall that defines a cavity between a proximal end of the compartment and a distal closed end of the compartment, the compartment configured to receive a composite material structure therein that extends along a majority of the length and/or width of the compartment; and a shroud disposed circumferentially between the inner wall of the compartment and an outer wall of the composite material structure along the length of the composite material structure, the shroud defining a first annular channel between the inner wall and an outer surface of the shroud and defining a second annular channel between the outer wall of the composite material structure and an inner surface of the shroud, said channels extending longitudinally between the proximal and distal ends of the compartment, wherein the shroud is contoured to direct a heated airflow longitudinally along the annular channels and over the composite material structure to cure the composite material structure, the heated airflow generally being at a higher temperature than a surface of the composite material part, one or more contour elements of the shroud configured to direct more heat to a corresponding thicker portion of the composite material structure generally aligned with the contour element relative to an amount of heat directed to adjacent relatively thinner portions of the composite material structure so as to effect a desired heating rate of the composite material structure to achieve a substantially uniform temperature along substantially the entire length of the composite material structure, thereby inhibiting warping of the composite material structure during a curing process. ### Claim 2 (depends on 1) The system of claim 1, wherein at least a portion of the shroud is removably disposed in the compartment. ### Claim 3 (depends on 2) The system of claim 2, wherein at least a portion of the shroud is attached to the composite material structure, said at least a portion of the shroud positionable along with the composite material structure in the compartment at the same time. ### Claim 4 (depends on 1) The system of claim 1, wherein the one or more contour elements of the shroud are configured to adjust the velocity and/or temperature of the heated airflow between the shroud and the composite material structure to adjust the convection heat transfer rate from said heated airflow to the composite material structure to achieve said substantially uniform temperature increase of the composite material structure along the length of the composite material structure. ### Claim 5 (depends on 1) The system of claim 1, wherein the one or more contour elements of the shroud comprises a recessed portion disposed radially closer to the composite material part than adjacent portions of the shroud. ### Claim 6 (depends on 1) The system of claim 1, wherein the one or more contour elements of the shroud comprises a louver or scoop configured to redirect at least a portion of the heated airflow flowing along the first annular channel into the heated airflow flowing along the second annular channel, thereby increasing the heat transfer to the composite material structure proximate the louver or scoop. ### Claim 7 (depends on 1) The system of claim 1, further comprising a door movably attached to the proximal end of the compartment, the door configured to direct at least a portion of the heated airflow from the first annular channel to the second annular channel when the door is in a closed position to thereby inhibit a loss in the velocity of said heated airflow. ### Claim 8 (depends on 7) The system of claim 7, wherein the door directs a second portion of the heated airflow into a central opening defined by a tool structure that supports the composite material structure, the second annular longitudinal channel defined between the inner surface of the shroud and an outer surface of the tool structure, and wherein said second portion of the heated airflow is configured to flow adjacent the composite material structure at a suitable velocity so that a rate of convection heat transfer to the composite material structure from said second portion of the heated airflow is substantially equal to a rate of conduction heat transfer to the composite material structure from said tool structure. ### Claim 9 (depends on 1) The system of claim 1, further comprising a tool to which the composite material structure is removably attached, the tool disposed between the composite material structure and the inner surface of the shroud. ### Claim 10 (depends on 1) The system of claim 1, wherein the composite material structure weighs at least bout 2000 lbs. ### Claim 11 (depends on 10) The system of claim 10, wherein the composite material structure is a fuselage for an aircraft. ### Claim 12 (depends on 10) The system of claim 10, wherein the composite material structure is a wing for an aircraft. ### Claim 13 (depends on 3) The system of claim 3, wherein said at least a portion of the shroud defines a lower portion of the shroud carried by a movable support structure. ### Claim 14 (depends on 13) The system of claim 13, wherein said movable support portion defines at least a portion of an insulated floor section of the compartment. ### Claim 15 (depends on 1) The system of claim 1, further comprising a fan coupled to the distal closed end of the compartment, a peripheral portion of the fan configured to force air past one or more heaters and along the first annular channel to generate the heater airflow, and a central portion of the fan configured to draw airflow about the composite material structure and through the second annular channel. ### Claim 16 A system for curing composite material parts, comprising: an elongate shroud positionable circumferentially between an inner wall of an industrial oven compartment and an outer wall of a composite material structure along the length of the composite material structure, the shroud defining a first annular channel between the inner wall and an outer surface of the shroud and defining a second annular channel between the outer wall of the composite material structure and an inner surface of the shroud, said channels extending longitudinally between the proximal and distal ends of the compartment, wherein the shroud is contoured to direct a heated airflow longitudinally along the annular channels and over the composite material structure to cure the composite material structure, the heated airflow generally being at a higher temperature than a surface of the composite material part, one or more contour elements of the shroud configured to direct more heat to a corresponding thicker portion of the composite material structure generally aligned with the contour element relative to an amount of heat directed to adjacent relatively thinner portions of the composite material structure to effect a desired heating rate of the composite material structure to achieve a substantially uniform temperature along substantially the entire length of the composite material structure, thereby inhibiting warping of the composite material structure during a curing process. ### Claim 17 (depends on 16) The system of claim 16, wherein at least a portion of the shroud is removably disposed in the compartment. ### Claim 18 (depends on 17) The system of claim 17, wherein at least a portion of the shroud is attached to the composite material structure, said at least a portion of the shroud positionable along with the composite material structure in the compartment at the same time. ### Claim 19 (depends on 16) The system of claim 16, wherein the one or more contour elements of the shroud are configured to adjust the velocity and/or temperature of the heated airflow between the shroud and the composite material structure to adjust the convection heat transfer rate from said heated airflow to the composite material structure to achieve said substantially uniform temperature increase of the composite material structure along the length of the composite material structure. ### Claim 20 (depends on 16) The system of claim 16, wherein the one or more contour elements of the shroud comprises a recessed portion disposed radially closer to the composite material part than adjacent portions of the shroud. ### Claim 21 (depends on 16) The system of claim 16, wherein the one or more contour elements of the shroud comprises a louver or scoop configured to redirect at least a portion of the heated airflow flowing along the first annular channel into the heated airflow flowing along the second annular channel, thereby increasing the heat transfer to the composite material structure proximate the louver or scoop. ### Claim 22 A method for curing composite material structures in an industrial oven, comprising: inserting a tool support structure carrying a composite material structure into an oven compartment having an inner wall that defines a cavity between a proximal end of the compartment and a distal closed end of the compartment, a shroud disposed circumferentially between the inner wall of the compartment and an outer wall of the tool support structure along the length of the tool support structure; and flowing a heated airflow longitudinally along a first annular channel between the inner wall of the compartment and an outer surface of the shroud, said heated airflow further generally being at a higher temperature than a surface of the composite material structure and flowing along a second annular channel between the outer wall of the tool support structure and an inner surface of the shroud, said channels extending longitudinally between the proximal and distal ends of the compartment, wherein flowing the heated airflow comprises directing, with one or more contour elements of the shroud relatively more heat via the heated airflow to a corresponding thicker portion of the composite material structure generally aligned with the contour element, and relatively less heat to adjacent relatively thinner portions of the composite material structure to effect a desired heating rate of the composite material structure to achieve a substantially uniform temperature along substantially the entire length of the composite material structure to thereby inhibit warping of the composite material structure during the curing process. ### Claim 23 (depends on 22) The method of claim 22, wherein inserting the tool support structure into the oven compartment comprises simultaneously inserting at least a portion of the shroud into the oven compartment, said portion of the shroud attached to the tool support structure. ### Claim 24 (depends on 22) The method of claim 22, wherein the desired substantially uniform temperature increase rate is between about 2° F./min and about 5° F./min. ### Claim 25 (depends on 22) The method of claim 22, wherein the one or more contour elements adjust the velocity and/or temperature of the heated airflow between the shroud and the tool support structure to adjust the convection heat transfer rate from said heated airflow to the tool support structure to achieve said substantially uniform temperature increase rate of the composite material structure along the length of the composite material structure. ### Claim 26 (depends on 22) The method of claim 22, wherein flowing the heated airflow comprises flowing a portion of the heated airflow over the composite material structure at a velocity sufficient to achieve a rate of convection heat transfer to the composite material structure from said portion of the heated airflow that is substantially equal to a rate of conduction heat transfer to the composite material structure from said tool support structure. ### Claim 27 (depends on 22) The method of claim 22, wherein directing with one or more contour elements of the shroud relatively more heat via the heated airflow to a corresponding thicker portion of the composite material structure comprises redirecting at least a portion of the heated airflow flowing along the first annular channel to a heated airflow flowing along the second annular channel at a location between a proximal end and a distal end of the shroud. ### Claim 28 A method of manufacturing a shroud for use in an industrial oven for curing a composite material structure, comprising: modeling an oven, a tool support structure configured to carry a composite material structure and removably positionable in a compartment of the oven, and a shroud disposed between the tool support structure and an inner wall of the compartment with a computational fluid dynamics algorithm, the composite material structure extending along a majority of the length and/or width of the compartment; calculating the heat transfer characteristics of the shroud and composite material structure to be cured by simulating a heated airflow between the inner wall and the shroud, and between the shroud and the tool support structure; and using said calculated heat transfer characteristics to determine the heated airflow velocity and/or temperature at a plurality of intervals along the length of the shroud, and the location of one or more contour elements along the length of the shroud, to maintain a substantially uniform temperature that varies no more than about 30° F. to 40° F. along substantially the entire length of the composite material structure. ### Claim 29 (depends on 28) The method of claim 28, wherein one or more contour elements of the shroud adjust the velocity and/or temperature of the heated airflow between the shroud and the tool support structure to adjust the convection heat transfer rate from said heated airflow to the tool support structure to achieve said substantially uniform temperature increase rate of the composite material structure along the length of the composite material structure. ### Claim 30 (depends on 29) The method of claim 29, wherein the one or more contour elements comprises a recessed portion disposed radially closer to the composite material part than adjacent portions of the shroud. ### Claim 31 (depends on 29) The method of claim 29, wherein the one or more contour elements of the shroud comprises a louver or scoop configured to redirect at least a portion of the heated airflow flowing along a first annular channel between the compartment and the shroud into a heated airflow flowing along a second annular channel between the shroud and the tool support structure, thereby increasing the heat transfer to the composite material structure proximate the louver or scoop.