Numerical Investigation on Actively Cooled Thermal Protection Systems with Ni-Based Alloys
One of the greatest challenges of hypersonic vehicles is their thermal protection and, more specifically, the cooling of their engine. To simulate the behavior of a complete actively cooled thermal protection system, a computational fluid dynamics and finite element analysis coupling method is appli...
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| Veröffentlicht in: | Journal of propulsion and power 2014-05, Vol.30 (3), p.604-616 |
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| container_title | Journal of propulsion and power |
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| creator | He, Yu-Rong Wang, Xin-Zhi Han, Jie-Cai Liu, Xing Wu, Zhao |
| description | One of the greatest challenges of hypersonic vehicles is their thermal protection and, more specifically, the cooling of their engine. To simulate the behavior of a complete actively cooled thermal protection system, a computational fluid dynamics and finite element analysis coupling method is applied to calculate the fluid/thermal/stress distributions for steady-state flight conditions. Work has been done on four different Ni-based alloys and three different panel structures. Temperature and stress profiles at the outlet cross section show that the maximum temperature and stress happen on the side that is close to the combustion chamber, and so this is the section on which the active cooling system should focus. It is better to have small rounded chamfers in the panels to decrease the stress concentration at the corners. Failure maps are presented for four Ni-based alloys showing the comparison of their thermostructural performance, which will be helpful for the selection of the materials in an active cooling system. |
| doi_str_mv | 10.2514/1.B34676 |
| format | Article |
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To simulate the behavior of a complete actively cooled thermal protection system, a computational fluid dynamics and finite element analysis coupling method is applied to calculate the fluid/thermal/stress distributions for steady-state flight conditions. Work has been done on four different Ni-based alloys and three different panel structures. Temperature and stress profiles at the outlet cross section show that the maximum temperature and stress happen on the side that is close to the combustion chamber, and so this is the section on which the active cooling system should focus. It is better to have small rounded chamfers in the panels to decrease the stress concentration at the corners. Failure maps are presented for four Ni-based alloys showing the comparison of their thermostructural performance, which will be helpful for the selection of the materials in an active cooling system.</description><identifier>ISSN: 0748-4658</identifier><identifier>EISSN: 1533-3876</identifier><identifier>DOI: 10.2514/1.B34676</identifier><identifier>CODEN: JPPOEL</identifier><language>eng</language><publisher>Reston: American Institute of Aeronautics and Astronautics</publisher><subject>Alloys ; Chamfering ; Combustion chambers ; Computational fluid dynamics ; Cooling ; Cooling systems ; Dynamical systems ; Finite element method ; Flight conditions ; Hypersonic vehicles ; Materials selection ; Mathematical analysis ; Nickel base alloys ; Panels ; Protection systems ; Stress concentration ; Thermal protection</subject><ispartof>Journal of propulsion and power, 2014-05, Vol.30 (3), p.604-616</ispartof><rights>Copyright © 2013 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Copies of this paper may be made for personal or internal use, on condition that the copier pay the $10.00 per-copy fee to the Copyright Clearance Center, Inc., 222 Rosewood Drive, Danvers, MA 01923; include the code and $10.00 in correspondence with the CCC.</rights><rights>Copyright © 2013 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Copies of this paper may be made for personal or internal use, on condition that the copier pay the $10.00 per-copy fee to the Copyright Clearance Center, Inc., 222 Rosewood Drive, Danvers, MA 01923; include the code 1533-3876/14 and $10.00 in correspondence with the CCC.</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-a346t-c1a901631a0845a078c9c466c4a489ddbdc2b37b81c6c46eb233f95c2cb183db3</citedby><cites>FETCH-LOGICAL-a346t-c1a901631a0845a078c9c466c4a489ddbdc2b37b81c6c46eb233f95c2cb183db3</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,776,780,27903,27904</link.rule.ids></links><search><creatorcontrib>He, Yu-Rong</creatorcontrib><creatorcontrib>Wang, Xin-Zhi</creatorcontrib><creatorcontrib>Han, Jie-Cai</creatorcontrib><creatorcontrib>Liu, Xing</creatorcontrib><creatorcontrib>Wu, Zhao</creatorcontrib><title>Numerical Investigation on Actively Cooled Thermal Protection Systems with Ni-Based Alloys</title><title>Journal of propulsion and power</title><description>One of the greatest challenges of hypersonic vehicles is their thermal protection and, more specifically, the cooling of their engine. 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Failure maps are presented for four Ni-based alloys showing the comparison of their thermostructural performance, which will be helpful for the selection of the materials in an active cooling system.</description><subject>Alloys</subject><subject>Chamfering</subject><subject>Combustion chambers</subject><subject>Computational fluid dynamics</subject><subject>Cooling</subject><subject>Cooling systems</subject><subject>Dynamical systems</subject><subject>Finite element method</subject><subject>Flight conditions</subject><subject>Hypersonic vehicles</subject><subject>Materials selection</subject><subject>Mathematical analysis</subject><subject>Nickel base alloys</subject><subject>Panels</subject><subject>Protection systems</subject><subject>Stress concentration</subject><subject>Thermal protection</subject><issn>0748-4658</issn><issn>1533-3876</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2014</creationdate><recordtype>article</recordtype><recordid>eNp90V1LwzAUBuAgCs4p-BMKInjT2Xw2vdyGH4MxBeeNNyFNM5eRNjNpJ_33RicoXgiBA-HhnPdwADiH2QhRSK7haIIJy9kBGECKcYp5zg7BIMsJTwmj_BichLDJMsg4ywfgZdHV2hslbTJrdjq05lW2xjVJfGPVmp22fTJ1zuoqWa61ryN89K7V6ks99aHVdUjeTbtOFiadyBDh2FrXh1NwtJI26LPvOgTPtzfL6X06f7ibTcfzVMagbaqgLGIaDGXGCZVZzlWhCGOKSMKLqiorhUqclxyq-Md0iTBeFVQhVUKOqxIPwdW-79a7ty6uIGoTlLZWNtp1QUBGEEIZLUikF3_oxnW-iekEIgWmBaS8-E9BSjEnMQH9Gau8C8Hrldh6U0vfC5iJz1MIKPaniPRyT6WR8lezv-4Dh4OFJQ</recordid><startdate>20140501</startdate><enddate>20140501</enddate><creator>He, Yu-Rong</creator><creator>Wang, Xin-Zhi</creator><creator>Han, Jie-Cai</creator><creator>Liu, Xing</creator><creator>Wu, Zhao</creator><general>American Institute of Aeronautics and Astronautics</general><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>8FD</scope><scope>FR3</scope><scope>H8D</scope><scope>L7M</scope><scope>8BQ</scope><scope>JG9</scope></search><sort><creationdate>20140501</creationdate><title>Numerical Investigation on Actively Cooled Thermal Protection Systems with Ni-Based Alloys</title><author>He, Yu-Rong ; Wang, Xin-Zhi ; Han, Jie-Cai ; Liu, Xing ; Wu, Zhao</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a346t-c1a901631a0845a078c9c466c4a489ddbdc2b37b81c6c46eb233f95c2cb183db3</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2014</creationdate><topic>Alloys</topic><topic>Chamfering</topic><topic>Combustion chambers</topic><topic>Computational fluid dynamics</topic><topic>Cooling</topic><topic>Cooling systems</topic><topic>Dynamical systems</topic><topic>Finite element method</topic><topic>Flight conditions</topic><topic>Hypersonic vehicles</topic><topic>Materials selection</topic><topic>Mathematical analysis</topic><topic>Nickel base alloys</topic><topic>Panels</topic><topic>Protection systems</topic><topic>Stress concentration</topic><topic>Thermal protection</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>He, Yu-Rong</creatorcontrib><creatorcontrib>Wang, Xin-Zhi</creatorcontrib><creatorcontrib>Han, Jie-Cai</creatorcontrib><creatorcontrib>Liu, Xing</creatorcontrib><creatorcontrib>Wu, Zhao</creatorcontrib><collection>CrossRef</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>Aerospace Database</collection><collection>Advanced Technologies Database with Aerospace</collection><collection>METADEX</collection><collection>Materials Research Database</collection><jtitle>Journal of propulsion and power</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>He, Yu-Rong</au><au>Wang, Xin-Zhi</au><au>Han, Jie-Cai</au><au>Liu, Xing</au><au>Wu, Zhao</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Numerical Investigation on Actively Cooled Thermal Protection Systems with Ni-Based Alloys</atitle><jtitle>Journal of propulsion and power</jtitle><date>2014-05-01</date><risdate>2014</risdate><volume>30</volume><issue>3</issue><spage>604</spage><epage>616</epage><pages>604-616</pages><issn>0748-4658</issn><eissn>1533-3876</eissn><coden>JPPOEL</coden><abstract>One of the greatest challenges of hypersonic vehicles is their thermal protection and, more specifically, the cooling of their engine. To simulate the behavior of a complete actively cooled thermal protection system, a computational fluid dynamics and finite element analysis coupling method is applied to calculate the fluid/thermal/stress distributions for steady-state flight conditions. Work has been done on four different Ni-based alloys and three different panel structures. Temperature and stress profiles at the outlet cross section show that the maximum temperature and stress happen on the side that is close to the combustion chamber, and so this is the section on which the active cooling system should focus. It is better to have small rounded chamfers in the panels to decrease the stress concentration at the corners. Failure maps are presented for four Ni-based alloys showing the comparison of their thermostructural performance, which will be helpful for the selection of the materials in an active cooling system.</abstract><cop>Reston</cop><pub>American Institute of Aeronautics and Astronautics</pub><doi>10.2514/1.B34676</doi><tpages>13</tpages></addata></record> |
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| ispartof | Journal of propulsion and power, 2014-05, Vol.30 (3), p.604-616 |
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| source | Alma/SFX Local Collection |
| subjects | Alloys Chamfering Combustion chambers Computational fluid dynamics Cooling Cooling systems Dynamical systems Finite element method Flight conditions Hypersonic vehicles Materials selection Mathematical analysis Nickel base alloys Panels Protection systems Stress concentration Thermal protection |
| title | Numerical Investigation on Actively Cooled Thermal Protection Systems with Ni-Based Alloys |
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