Active Control of Noise from Hot Supersonic Jets
This paper presents diagnostic experiments aimed at understanding and mitigating supersonic jet noise from the coherent wave-packet structures that are the source of peak aft-angle mixing noise. Both isothermal and heated, nearly perfectly expanded, Mach 1.5 jets were forced in the near-nozzle regio...
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Veröffentlicht in: | AIAA journal 2018-03, Vol.56 (3), p.933-948 |
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description | This paper presents diagnostic experiments aimed at understanding and mitigating supersonic jet noise from the coherent wave-packet structures that are the source of peak aft-angle mixing noise. Both isothermal and heated, nearly perfectly expanded, Mach 1.5 jets were forced in the near-nozzle region with air injection generated by a spinning-valve device designed to excite the jet at frequencies approaching those of the dominant turbulent structures. Substantial reductions in the peak aft-angle radiation were achieved with steady blowing at amplitudes corresponding to 2–6% of the mass flow rate of the primary jet. The noise benefit saturated at mass flow rates above 4%, with as much as a 6 dB reduction in overall sound pressure level at aft angles. Increasing the mass flow rates yielded a monotonically increasing high-frequency noise penalty at the sideline, where noise levels in the natural jet were already 15 dB lower than the aft-angle peak, so that the penalty due to actuation was minor. Although both steady and periodic unsteady mass injections were produced by the spinning valve when it rotated, it was calibrated to hold the steady mass flow rate constant as the frequency of unsteady blowing was changed. In this way, the effect of steady and unsteady blowings on the acoustic field could be decoupled. It is shown that the noise benefit was uniquely associated with the steady component of blowing, whereas the unsteady component resulted in additive tones in the spectra. This implied linearity is consistent with theory and experiments showing that the wave-packet structures, which give rise to the dominant aft-angle radiation, evolve in the turbulent mean flowfield in a nearly linear fashion from their origin in the near-nozzle region. The interpretation of noise reduction is that the steady component of blowing spreads the mean flow more rapidly, resulting in weaker wave packets. Periodic unsteady blowing forces coherent wave packets that are largely uncorrelated from the random natural ones, which then leads to the observed additive tones. |
doi_str_mv | 10.2514/1.J056159 |
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Both isothermal and heated, nearly perfectly expanded, Mach 1.5 jets were forced in the near-nozzle region with air injection generated by a spinning-valve device designed to excite the jet at frequencies approaching those of the dominant turbulent structures. Substantial reductions in the peak aft-angle radiation were achieved with steady blowing at amplitudes corresponding to 2–6% of the mass flow rate of the primary jet. The noise benefit saturated at mass flow rates above 4%, with as much as a 6 dB reduction in overall sound pressure level at aft angles. Increasing the mass flow rates yielded a monotonically increasing high-frequency noise penalty at the sideline, where noise levels in the natural jet were already 15 dB lower than the aft-angle peak, so that the penalty due to actuation was minor. Although both steady and periodic unsteady mass injections were produced by the spinning valve when it rotated, it was calibrated to hold the steady mass flow rate constant as the frequency of unsteady blowing was changed. In this way, the effect of steady and unsteady blowings on the acoustic field could be decoupled. It is shown that the noise benefit was uniquely associated with the steady component of blowing, whereas the unsteady component resulted in additive tones in the spectra. This implied linearity is consistent with theory and experiments showing that the wave-packet structures, which give rise to the dominant aft-angle radiation, evolve in the turbulent mean flowfield in a nearly linear fashion from their origin in the near-nozzle region. The interpretation of noise reduction is that the steady component of blowing spreads the mean flow more rapidly, resulting in weaker wave packets. Periodic unsteady blowing forces coherent wave packets that are largely uncorrelated from the random natural ones, which then leads to the observed additive tones.</description><identifier>ISSN: 0001-1452</identifier><identifier>EISSN: 1533-385X</identifier><identifier>DOI: 10.2514/1.J056159</identifier><language>eng</language><publisher>Virginia: American Institute of Aeronautics and Astronautics</publisher><subject>Acoustic noise ; Actuation ; Aerodynamics ; Air injection ; Blowing rate ; Diagnostic systems ; Flow control ; Flow rates ; Fluid dynamics ; Jet aircraft noise ; Linearity ; Mass flow rate ; Noise ; Noise levels ; Noise reduction ; Nozzles ; Radiation ; Sound pressure ; Wave packets</subject><ispartof>AIAA journal, 2018-03, Vol.56 (3), p.933-948</ispartof><rights>Copyright © 2017 by Aniruddha Sinha, Aaron Towne, Tim Colonius, Robert H. Schlinker, Ramons Reba, John C. Simonich, and Daniel W. Shannon. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. All requests for copying and permission to reprint should be submitted to CCC at ; employ the ISSN (print) or (online) to initiate your request. See also AIAA Rights and Permissions .</rights><rights>Copyright © 2017 by Aniruddha Sinha, Aaron Towne, Tim Colonius, Robert H. Schlinker, Ramons Reba, John C. Simonich, and Daniel W. Shannon. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the ISSN 0001-1452 (print) or 1533-385X (online) to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.</rights><lds50>peer_reviewed</lds50><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-a363t-f32373d929733b6155b99d260e9206b6269b4968f19cc29a45667ce39fb5deb33</citedby><cites>FETCH-LOGICAL-a363t-f32373d929733b6155b99d260e9206b6269b4968f19cc29a45667ce39fb5deb33</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>Sinha, Aniruddha</creatorcontrib><creatorcontrib>Towne, Aaron</creatorcontrib><creatorcontrib>Colonius, Tim</creatorcontrib><creatorcontrib>Schlinker, Robert H</creatorcontrib><creatorcontrib>Reba, Ramons</creatorcontrib><creatorcontrib>Simonich, John C</creatorcontrib><creatorcontrib>Shannon, Daniel W</creatorcontrib><title>Active Control of Noise from Hot Supersonic Jets</title><title>AIAA journal</title><description>This paper presents diagnostic experiments aimed at understanding and mitigating supersonic jet noise from the coherent wave-packet structures that are the source of peak aft-angle mixing noise. Both isothermal and heated, nearly perfectly expanded, Mach 1.5 jets were forced in the near-nozzle region with air injection generated by a spinning-valve device designed to excite the jet at frequencies approaching those of the dominant turbulent structures. Substantial reductions in the peak aft-angle radiation were achieved with steady blowing at amplitudes corresponding to 2–6% of the mass flow rate of the primary jet. The noise benefit saturated at mass flow rates above 4%, with as much as a 6 dB reduction in overall sound pressure level at aft angles. Increasing the mass flow rates yielded a monotonically increasing high-frequency noise penalty at the sideline, where noise levels in the natural jet were already 15 dB lower than the aft-angle peak, so that the penalty due to actuation was minor. Although both steady and periodic unsteady mass injections were produced by the spinning valve when it rotated, it was calibrated to hold the steady mass flow rate constant as the frequency of unsteady blowing was changed. In this way, the effect of steady and unsteady blowings on the acoustic field could be decoupled. It is shown that the noise benefit was uniquely associated with the steady component of blowing, whereas the unsteady component resulted in additive tones in the spectra. This implied linearity is consistent with theory and experiments showing that the wave-packet structures, which give rise to the dominant aft-angle radiation, evolve in the turbulent mean flowfield in a nearly linear fashion from their origin in the near-nozzle region. The interpretation of noise reduction is that the steady component of blowing spreads the mean flow more rapidly, resulting in weaker wave packets. Periodic unsteady blowing forces coherent wave packets that are largely uncorrelated from the random natural ones, which then leads to the observed additive tones.</description><subject>Acoustic noise</subject><subject>Actuation</subject><subject>Aerodynamics</subject><subject>Air injection</subject><subject>Blowing rate</subject><subject>Diagnostic systems</subject><subject>Flow control</subject><subject>Flow rates</subject><subject>Fluid dynamics</subject><subject>Jet aircraft noise</subject><subject>Linearity</subject><subject>Mass flow rate</subject><subject>Noise</subject><subject>Noise levels</subject><subject>Noise reduction</subject><subject>Nozzles</subject><subject>Radiation</subject><subject>Sound pressure</subject><subject>Wave packets</subject><issn>0001-1452</issn><issn>1533-385X</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2018</creationdate><recordtype>article</recordtype><recordid>eNpl0MFKAzEQBuAgCtbqwTcICIKHrZnMJrtzLIu1lqIHFbyF7DaBLW2zJlvBt3elBQ-ehoGPf4afsWsQE6kgv4fJQigNik7YCBRihqX6OGUjIQRkkCt5zi5SWg-bLEoYMTFt-vbL8Srs-hg2PHj-HNrkuI9hy-eh56_7zsUUdm3DF65Pl-zM201yV8c5Zu-zh7dqni1fHp-q6TKzqLHPPEoscEWSCsR6eEjVRCuphSMpdK2lpjonXXqgppFkc6V10TgkX6uVqxHH7OaQ28XwuXepN-uwj7vhpJGgCyQgWQ7q7qCaGFKKzpsutlsbvw0I81uIAXMsZLC3B2tba__S_sMfybxbQQ</recordid><startdate>20180301</startdate><enddate>20180301</enddate><creator>Sinha, Aniruddha</creator><creator>Towne, Aaron</creator><creator>Colonius, Tim</creator><creator>Schlinker, Robert H</creator><creator>Reba, Ramons</creator><creator>Simonich, John C</creator><creator>Shannon, Daniel W</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>20180301</creationdate><title>Active Control of Noise from Hot Supersonic Jets</title><author>Sinha, Aniruddha ; Towne, Aaron ; Colonius, Tim ; Schlinker, Robert H ; Reba, Ramons ; Simonich, John C ; Shannon, Daniel W</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a363t-f32373d929733b6155b99d260e9206b6269b4968f19cc29a45667ce39fb5deb33</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2018</creationdate><topic>Acoustic noise</topic><topic>Actuation</topic><topic>Aerodynamics</topic><topic>Air injection</topic><topic>Blowing rate</topic><topic>Diagnostic systems</topic><topic>Flow control</topic><topic>Flow rates</topic><topic>Fluid dynamics</topic><topic>Jet aircraft noise</topic><topic>Linearity</topic><topic>Mass flow rate</topic><topic>Noise</topic><topic>Noise levels</topic><topic>Noise reduction</topic><topic>Nozzles</topic><topic>Radiation</topic><topic>Sound pressure</topic><topic>Wave packets</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Sinha, Aniruddha</creatorcontrib><creatorcontrib>Towne, Aaron</creatorcontrib><creatorcontrib>Colonius, Tim</creatorcontrib><creatorcontrib>Schlinker, Robert H</creatorcontrib><creatorcontrib>Reba, Ramons</creatorcontrib><creatorcontrib>Simonich, John C</creatorcontrib><creatorcontrib>Shannon, Daniel W</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>AIAA journal</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Sinha, Aniruddha</au><au>Towne, Aaron</au><au>Colonius, Tim</au><au>Schlinker, Robert H</au><au>Reba, Ramons</au><au>Simonich, John C</au><au>Shannon, Daniel W</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Active Control of Noise from Hot Supersonic Jets</atitle><jtitle>AIAA journal</jtitle><date>2018-03-01</date><risdate>2018</risdate><volume>56</volume><issue>3</issue><spage>933</spage><epage>948</epage><pages>933-948</pages><issn>0001-1452</issn><eissn>1533-385X</eissn><abstract>This paper presents diagnostic experiments aimed at understanding and mitigating supersonic jet noise from the coherent wave-packet structures that are the source of peak aft-angle mixing noise. Both isothermal and heated, nearly perfectly expanded, Mach 1.5 jets were forced in the near-nozzle region with air injection generated by a spinning-valve device designed to excite the jet at frequencies approaching those of the dominant turbulent structures. Substantial reductions in the peak aft-angle radiation were achieved with steady blowing at amplitudes corresponding to 2–6% of the mass flow rate of the primary jet. The noise benefit saturated at mass flow rates above 4%, with as much as a 6 dB reduction in overall sound pressure level at aft angles. Increasing the mass flow rates yielded a monotonically increasing high-frequency noise penalty at the sideline, where noise levels in the natural jet were already 15 dB lower than the aft-angle peak, so that the penalty due to actuation was minor. Although both steady and periodic unsteady mass injections were produced by the spinning valve when it rotated, it was calibrated to hold the steady mass flow rate constant as the frequency of unsteady blowing was changed. In this way, the effect of steady and unsteady blowings on the acoustic field could be decoupled. It is shown that the noise benefit was uniquely associated with the steady component of blowing, whereas the unsteady component resulted in additive tones in the spectra. This implied linearity is consistent with theory and experiments showing that the wave-packet structures, which give rise to the dominant aft-angle radiation, evolve in the turbulent mean flowfield in a nearly linear fashion from their origin in the near-nozzle region. The interpretation of noise reduction is that the steady component of blowing spreads the mean flow more rapidly, resulting in weaker wave packets. Periodic unsteady blowing forces coherent wave packets that are largely uncorrelated from the random natural ones, which then leads to the observed additive tones.</abstract><cop>Virginia</cop><pub>American Institute of Aeronautics and Astronautics</pub><doi>10.2514/1.J056159</doi><tpages>16</tpages><oa>free_for_read</oa></addata></record> |
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subjects | Acoustic noise Actuation Aerodynamics Air injection Blowing rate Diagnostic systems Flow control Flow rates Fluid dynamics Jet aircraft noise Linearity Mass flow rate Noise Noise levels Noise reduction Nozzles Radiation Sound pressure Wave packets |
title | Active Control of Noise from Hot Supersonic Jets |
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