Benefits and Challenges of the Inside-Out Ceramic Turbine: An Experimental Assessment
Distributed aircraft propulsion has renewed the interest in power-dense, high-efficiency power packs. Ceramic turbomachinery could be a major enabler, although no successful design has been achieved in microturbine rotors. Rotor blade loading is tensile and a hurdle for successful conversion to cera...
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| Veröffentlicht in: | Journal of propulsion and power 2022-03, Vol.38 (2), p.221-228 |
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| container_title | Journal of propulsion and power |
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| creator | Dubois, Patrick K Landry, Céderick Thibault, Dominik Plante, Jean-Sébastien Picard, Mathieu Picard, Benoît |
| description | Distributed aircraft propulsion has renewed the interest in power-dense, high-efficiency power packs. Ceramic turbomachinery could be a major enabler, although no successful design has been achieved in microturbine rotors. Rotor blade loading is tensile and a hurdle for successful conversion to ceramics. The inside-out ceramic turbine (ICT) rotor uses the superior compressive properties of monolithic ceramics by supporting ceramic blades against a structural composite rotating shroud. This enables low stress levels throughout the blade, increasing reliability and extending service life. An experimental demonstration of two ICT designs was conducted with 15-kW scale prototypes to identify critical issues: design A, a flexible hub that clamps blades against the structural shroud and design B, a sliding-blade configuration that allows free displacement of the blade. The flexible-hub design was tested up to 1000°C. Rotor integrity was preserved, but local blade cracking occurred. The sliding-blade design was successfully tested up to 1100°C for over 1 hour at a tip speed of 350 m/s with no issue. Tensile loading at the ceramic/metallic interfaces remains the key challenge to address. Reducing friction should overcome blade cracking and allow the proposed ICT to reach the targeted temperature of 1275°C and tip speed of 425 m/s. |
| doi_str_mv | 10.2514/1.B38004 |
| format | Article |
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Ceramic turbomachinery could be a major enabler, although no successful design has been achieved in microturbine rotors. Rotor blade loading is tensile and a hurdle for successful conversion to ceramics. The inside-out ceramic turbine (ICT) rotor uses the superior compressive properties of monolithic ceramics by supporting ceramic blades against a structural composite rotating shroud. This enables low stress levels throughout the blade, increasing reliability and extending service life. An experimental demonstration of two ICT designs was conducted with 15-kW scale prototypes to identify critical issues: design A, a flexible hub that clamps blades against the structural shroud and design B, a sliding-blade configuration that allows free displacement of the blade. The flexible-hub design was tested up to 1000°C. Rotor integrity was preserved, but local blade cracking occurred. The sliding-blade design was successfully tested up to 1100°C for over 1 hour at a tip speed of 350 m/s with no issue. Tensile loading at the ceramic/metallic interfaces remains the key challenge to address. Reducing friction should overcome blade cracking and allow the proposed ICT to reach the targeted temperature of 1275°C and tip speed of 425 m/s.</description><identifier>ISSN: 1533-3876</identifier><identifier>ISSN: 0748-4658</identifier><identifier>EISSN: 1533-3876</identifier><identifier>DOI: 10.2514/1.B38004</identifier><language>eng</language><publisher>Reston: American Institute of Aeronautics and Astronautics</publisher><subject>Aircraft ; Aircraft propulsion ; Bending stresses ; Ceramics ; Clamps ; Compressive properties ; Compressor blades ; Configuration management ; Crack initiation ; Crack propagation ; Design ; Efficiency ; Friction reduction ; Gas turbine engines ; Power supplies ; Prototypes ; Rotor blades ; Rotor blades (turbomachinery) ; Service life ; Sliding ; Tip speed ; Turbines ; Turbomachinery</subject><ispartof>Journal of propulsion and power, 2022-03, Vol.38 (2), p.221-228</ispartof><rights>Copyright © 2021 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. All requests for copying and permission to reprint should be submitted to CCC at ; employ the eISSN to initiate your request. See also AIAA Rights and Permissions .</rights><rights>Copyright © 2021 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-3876 to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-a285t-9cc3636498ea16b1a7341f08360d7ec52ea3dd3b4ac38d6493a30446fa417cb33</citedby><cites>FETCH-LOGICAL-a285t-9cc3636498ea16b1a7341f08360d7ec52ea3dd3b4ac38d6493a30446fa417cb33</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,776,780,27901,27902</link.rule.ids></links><search><creatorcontrib>Dubois, Patrick K</creatorcontrib><creatorcontrib>Landry, Céderick</creatorcontrib><creatorcontrib>Thibault, Dominik</creatorcontrib><creatorcontrib>Plante, Jean-Sébastien</creatorcontrib><creatorcontrib>Picard, Mathieu</creatorcontrib><creatorcontrib>Picard, Benoît</creatorcontrib><title>Benefits and Challenges of the Inside-Out Ceramic Turbine: An Experimental Assessment</title><title>Journal of propulsion and power</title><description>Distributed aircraft propulsion has renewed the interest in power-dense, high-efficiency power packs. Ceramic turbomachinery could be a major enabler, although no successful design has been achieved in microturbine rotors. Rotor blade loading is tensile and a hurdle for successful conversion to ceramics. The inside-out ceramic turbine (ICT) rotor uses the superior compressive properties of monolithic ceramics by supporting ceramic blades against a structural composite rotating shroud. This enables low stress levels throughout the blade, increasing reliability and extending service life. An experimental demonstration of two ICT designs was conducted with 15-kW scale prototypes to identify critical issues: design A, a flexible hub that clamps blades against the structural shroud and design B, a sliding-blade configuration that allows free displacement of the blade. The flexible-hub design was tested up to 1000°C. Rotor integrity was preserved, but local blade cracking occurred. The sliding-blade design was successfully tested up to 1100°C for over 1 hour at a tip speed of 350 m/s with no issue. Tensile loading at the ceramic/metallic interfaces remains the key challenge to address. Reducing friction should overcome blade cracking and allow the proposed ICT to reach the targeted temperature of 1275°C and tip speed of 425 m/s.</description><subject>Aircraft</subject><subject>Aircraft propulsion</subject><subject>Bending stresses</subject><subject>Ceramics</subject><subject>Clamps</subject><subject>Compressive properties</subject><subject>Compressor blades</subject><subject>Configuration management</subject><subject>Crack initiation</subject><subject>Crack propagation</subject><subject>Design</subject><subject>Efficiency</subject><subject>Friction reduction</subject><subject>Gas turbine engines</subject><subject>Power supplies</subject><subject>Prototypes</subject><subject>Rotor blades</subject><subject>Rotor blades (turbomachinery)</subject><subject>Service life</subject><subject>Sliding</subject><subject>Tip speed</subject><subject>Turbines</subject><subject>Turbomachinery</subject><issn>1533-3876</issn><issn>0748-4658</issn><issn>1533-3876</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2022</creationdate><recordtype>article</recordtype><recordid>eNplkMFKw0AQhhdRsFbBR1gQwUvqbmaz2XprQ9VCoZf2HCbJxKakm7qbgH17UyIoeJp_4OOb4WfsXopJGEn1LCdzMEKoCzaSEUAAJtaXf_I1u_F-L4TURscjtp2TpbJqPUdb8GSHdU32gzxvSt7uiC-trwoK1l3LE3J4qHK-6VxWWXrhM8sXX0dy1YFsizWfeU_en5dbdlVi7enuZ47Z9nWxSd6D1fptmcxWAYYmaoNpnoMGraaGUOpMYgxKlsKAFkVMeRQSQlFApjAHU_QcIAildIlKxnkGMGYPg_foms-OfJvum87Z_mQa6t4lpsLInnoaqNw13jsq02P_M7pTKkV6Li2V6VBajz4OKFaIv7J_3DcBL2iH</recordid><startdate>20220301</startdate><enddate>20220301</enddate><creator>Dubois, Patrick K</creator><creator>Landry, Céderick</creator><creator>Thibault, Dominik</creator><creator>Plante, Jean-Sébastien</creator><creator>Picard, Mathieu</creator><creator>Picard, Benoît</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></search><sort><creationdate>20220301</creationdate><title>Benefits and Challenges of the Inside-Out Ceramic Turbine: An Experimental Assessment</title><author>Dubois, Patrick K ; Landry, Céderick ; Thibault, Dominik ; Plante, Jean-Sébastien ; Picard, Mathieu ; Picard, Benoît</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a285t-9cc3636498ea16b1a7341f08360d7ec52ea3dd3b4ac38d6493a30446fa417cb33</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2022</creationdate><topic>Aircraft</topic><topic>Aircraft propulsion</topic><topic>Bending stresses</topic><topic>Ceramics</topic><topic>Clamps</topic><topic>Compressive properties</topic><topic>Compressor blades</topic><topic>Configuration management</topic><topic>Crack initiation</topic><topic>Crack propagation</topic><topic>Design</topic><topic>Efficiency</topic><topic>Friction reduction</topic><topic>Gas turbine engines</topic><topic>Power supplies</topic><topic>Prototypes</topic><topic>Rotor blades</topic><topic>Rotor blades (turbomachinery)</topic><topic>Service life</topic><topic>Sliding</topic><topic>Tip speed</topic><topic>Turbines</topic><topic>Turbomachinery</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Dubois, Patrick K</creatorcontrib><creatorcontrib>Landry, Céderick</creatorcontrib><creatorcontrib>Thibault, Dominik</creatorcontrib><creatorcontrib>Plante, Jean-Sébastien</creatorcontrib><creatorcontrib>Picard, Mathieu</creatorcontrib><creatorcontrib>Picard, Benoît</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><jtitle>Journal of propulsion and power</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Dubois, Patrick K</au><au>Landry, Céderick</au><au>Thibault, Dominik</au><au>Plante, Jean-Sébastien</au><au>Picard, Mathieu</au><au>Picard, Benoît</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Benefits and Challenges of the Inside-Out Ceramic Turbine: An Experimental Assessment</atitle><jtitle>Journal of propulsion and power</jtitle><date>2022-03-01</date><risdate>2022</risdate><volume>38</volume><issue>2</issue><spage>221</spage><epage>228</epage><pages>221-228</pages><issn>1533-3876</issn><issn>0748-4658</issn><eissn>1533-3876</eissn><abstract>Distributed aircraft propulsion has renewed the interest in power-dense, high-efficiency power packs. 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The sliding-blade design was successfully tested up to 1100°C for over 1 hour at a tip speed of 350 m/s with no issue. Tensile loading at the ceramic/metallic interfaces remains the key challenge to address. Reducing friction should overcome blade cracking and allow the proposed ICT to reach the targeted temperature of 1275°C and tip speed of 425 m/s.</abstract><cop>Reston</cop><pub>American Institute of Aeronautics and Astronautics</pub><doi>10.2514/1.B38004</doi><tpages>8</tpages></addata></record> |
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| identifier | ISSN: 1533-3876 |
| ispartof | Journal of propulsion and power, 2022-03, Vol.38 (2), p.221-228 |
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| source | Alma/SFX Local Collection |
| subjects | Aircraft Aircraft propulsion Bending stresses Ceramics Clamps Compressive properties Compressor blades Configuration management Crack initiation Crack propagation Design Efficiency Friction reduction Gas turbine engines Power supplies Prototypes Rotor blades Rotor blades (turbomachinery) Service life Sliding Tip speed Turbines Turbomachinery |
| title | Benefits and Challenges of the Inside-Out Ceramic Turbine: An Experimental Assessment |
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