Advanced test protocols for rapid detection and quantification of nonlinear dynamic responses in aeroengine casing assemblies
Abstract In this research, computationally efficient testing protocols were developed for the accurate detection and quantification of nonlinearities in the bolted flange interfaces of aeroengine casing assemblies. Aeroengine casings are joined by bolted flanges that are exposed to high loading ampl...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Mir-Haidari, Seyed-Ehsan [verfasserIn] Behdinan, Kamran [verfasserIn] |
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| Format: |
E-Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
2021 |
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| Schlagwörter: |
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| Anmerkung: |
© The Author(s), under exclusive licence to Springer Nature B.V. 2021 |
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| Übergeordnetes Werk: |
Enthalten in: Nonlinear dynamics - Dordrecht [u.a.] : Springer Science + Business Media B.V, 1990, 104(2021), 3 vom: 02. Apr., Seite 2219-2239 |
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| Übergeordnetes Werk: |
volume:104 ; year:2021 ; number:3 ; day:02 ; month:04 ; pages:2219-2239 |
| Links: |
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| DOI / URN: |
10.1007/s11071-021-06375-6 |
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SPR044270178 |
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| 520 | |a Abstract In this research, computationally efficient testing protocols were developed for the accurate detection and quantification of nonlinearities in the bolted flange interfaces of aeroengine casing assemblies. Aeroengine casings are joined by bolted flanges that are exposed to high loading amplitudes, leading to bending and large deflections that cause structural nonlinearities. Initially, to assess these structural nonlinearities, a computationally efficient finite element (FE) modelling methodology was developed to accurately capture the vibrational characteristics of the casings while also significantly improving computational efficiency. The technical accuracy of the vibrational characteristics obtained from the FE modelling technique developed here was validated using simulation methods and experimental vibration testing such as modal analysis, the modal assurance criterion, and mode shape assessment. The modes most susceptible to nonlinear dynamic response were then theoretically identified using the mode shape results acquired through the FE model. Thus, a two-step experimental approach is proposed for achieving the accurate and time-efficient quantification of nonlinearities. In the first stage, a rapid experimental nonlinear assessment is performed using a stinger–shaker set-up to validate the FE simulation results of the susceptible nonlinear modes identified. In the second stage, a precise high-resolution measurement is taken with respect to the modes identified in order to precisely capture the nonlinear characteristics. The integration of the proposed theoretical FE modelling technique with advanced experiment formulations results in a significantly more time-efficient and accurate nonlinear testing protocol for aeroengine structures. Furthermore, the nonlinear damping and stiffness parameters of aeroengine casings were also explored in this research and analysed to improve the existing design and development strategies. | ||
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10.1007/s11071-021-06375-6 doi (DE-627)SPR044270178 (SPR)s11071-021-06375-6-e DE-627 ger DE-627 rakwb eng 510 ASE 30.20 bkl Mir-Haidari, Seyed-Ehsan verfasserin aut Advanced test protocols for rapid detection and quantification of nonlinear dynamic responses in aeroengine casing assemblies 2021 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © The Author(s), under exclusive licence to Springer Nature B.V. 2021 Abstract In this research, computationally efficient testing protocols were developed for the accurate detection and quantification of nonlinearities in the bolted flange interfaces of aeroengine casing assemblies. Aeroengine casings are joined by bolted flanges that are exposed to high loading amplitudes, leading to bending and large deflections that cause structural nonlinearities. Initially, to assess these structural nonlinearities, a computationally efficient finite element (FE) modelling methodology was developed to accurately capture the vibrational characteristics of the casings while also significantly improving computational efficiency. The technical accuracy of the vibrational characteristics obtained from the FE modelling technique developed here was validated using simulation methods and experimental vibration testing such as modal analysis, the modal assurance criterion, and mode shape assessment. The modes most susceptible to nonlinear dynamic response were then theoretically identified using the mode shape results acquired through the FE model. Thus, a two-step experimental approach is proposed for achieving the accurate and time-efficient quantification of nonlinearities. In the first stage, a rapid experimental nonlinear assessment is performed using a stinger–shaker set-up to validate the FE simulation results of the susceptible nonlinear modes identified. In the second stage, a precise high-resolution measurement is taken with respect to the modes identified in order to precisely capture the nonlinear characteristics. The integration of the proposed theoretical FE modelling technique with advanced experiment formulations results in a significantly more time-efficient and accurate nonlinear testing protocol for aeroengine structures. Furthermore, the nonlinear damping and stiffness parameters of aeroengine casings were also explored in this research and analysed to improve the existing design and development strategies. Aeroengine (dpeaa)DE-He213 Nonlinear theory (dpeaa)DE-He213 Bolted flange connection (dpeaa)DE-He213 Nonlinear testing (dpeaa)DE-He213 Modal characteristic analysis (dpeaa)DE-He213 Finite element analysis (dpeaa)DE-He213 Behdinan, Kamran verfasserin aut Enthalten in Nonlinear dynamics Dordrecht [u.a.] : Springer Science + Business Media B.V, 1990 104(2021), 3 vom: 02. Apr., Seite 2219-2239 (DE-627)315297034 (DE-600)2012600-1 1573-269X nnns volume:104 year:2021 number:3 day:02 month:04 pages:2219-2239 https://dx.doi.org/10.1007/s11071-021-06375-6 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER SSG-OPC-MAT SSG-OPC-ASE GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4328 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 30.20 ASE AR 104 2021 3 02 04 2219-2239 |
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10.1007/s11071-021-06375-6 doi (DE-627)SPR044270178 (SPR)s11071-021-06375-6-e DE-627 ger DE-627 rakwb eng 510 ASE 30.20 bkl Mir-Haidari, Seyed-Ehsan verfasserin aut Advanced test protocols for rapid detection and quantification of nonlinear dynamic responses in aeroengine casing assemblies 2021 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © The Author(s), under exclusive licence to Springer Nature B.V. 2021 Abstract In this research, computationally efficient testing protocols were developed for the accurate detection and quantification of nonlinearities in the bolted flange interfaces of aeroengine casing assemblies. Aeroengine casings are joined by bolted flanges that are exposed to high loading amplitudes, leading to bending and large deflections that cause structural nonlinearities. Initially, to assess these structural nonlinearities, a computationally efficient finite element (FE) modelling methodology was developed to accurately capture the vibrational characteristics of the casings while also significantly improving computational efficiency. The technical accuracy of the vibrational characteristics obtained from the FE modelling technique developed here was validated using simulation methods and experimental vibration testing such as modal analysis, the modal assurance criterion, and mode shape assessment. The modes most susceptible to nonlinear dynamic response were then theoretically identified using the mode shape results acquired through the FE model. Thus, a two-step experimental approach is proposed for achieving the accurate and time-efficient quantification of nonlinearities. In the first stage, a rapid experimental nonlinear assessment is performed using a stinger–shaker set-up to validate the FE simulation results of the susceptible nonlinear modes identified. In the second stage, a precise high-resolution measurement is taken with respect to the modes identified in order to precisely capture the nonlinear characteristics. The integration of the proposed theoretical FE modelling technique with advanced experiment formulations results in a significantly more time-efficient and accurate nonlinear testing protocol for aeroengine structures. Furthermore, the nonlinear damping and stiffness parameters of aeroengine casings were also explored in this research and analysed to improve the existing design and development strategies. Aeroengine (dpeaa)DE-He213 Nonlinear theory (dpeaa)DE-He213 Bolted flange connection (dpeaa)DE-He213 Nonlinear testing (dpeaa)DE-He213 Modal characteristic analysis (dpeaa)DE-He213 Finite element analysis (dpeaa)DE-He213 Behdinan, Kamran verfasserin aut Enthalten in Nonlinear dynamics Dordrecht [u.a.] : Springer Science + Business Media B.V, 1990 104(2021), 3 vom: 02. Apr., Seite 2219-2239 (DE-627)315297034 (DE-600)2012600-1 1573-269X nnns volume:104 year:2021 number:3 day:02 month:04 pages:2219-2239 https://dx.doi.org/10.1007/s11071-021-06375-6 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER SSG-OPC-MAT SSG-OPC-ASE GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4328 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 30.20 ASE AR 104 2021 3 02 04 2219-2239 |
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10.1007/s11071-021-06375-6 doi (DE-627)SPR044270178 (SPR)s11071-021-06375-6-e DE-627 ger DE-627 rakwb eng 510 ASE 30.20 bkl Mir-Haidari, Seyed-Ehsan verfasserin aut Advanced test protocols for rapid detection and quantification of nonlinear dynamic responses in aeroengine casing assemblies 2021 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © The Author(s), under exclusive licence to Springer Nature B.V. 2021 Abstract In this research, computationally efficient testing protocols were developed for the accurate detection and quantification of nonlinearities in the bolted flange interfaces of aeroengine casing assemblies. Aeroengine casings are joined by bolted flanges that are exposed to high loading amplitudes, leading to bending and large deflections that cause structural nonlinearities. Initially, to assess these structural nonlinearities, a computationally efficient finite element (FE) modelling methodology was developed to accurately capture the vibrational characteristics of the casings while also significantly improving computational efficiency. The technical accuracy of the vibrational characteristics obtained from the FE modelling technique developed here was validated using simulation methods and experimental vibration testing such as modal analysis, the modal assurance criterion, and mode shape assessment. The modes most susceptible to nonlinear dynamic response were then theoretically identified using the mode shape results acquired through the FE model. Thus, a two-step experimental approach is proposed for achieving the accurate and time-efficient quantification of nonlinearities. In the first stage, a rapid experimental nonlinear assessment is performed using a stinger–shaker set-up to validate the FE simulation results of the susceptible nonlinear modes identified. In the second stage, a precise high-resolution measurement is taken with respect to the modes identified in order to precisely capture the nonlinear characteristics. The integration of the proposed theoretical FE modelling technique with advanced experiment formulations results in a significantly more time-efficient and accurate nonlinear testing protocol for aeroengine structures. Furthermore, the nonlinear damping and stiffness parameters of aeroengine casings were also explored in this research and analysed to improve the existing design and development strategies. Aeroengine (dpeaa)DE-He213 Nonlinear theory (dpeaa)DE-He213 Bolted flange connection (dpeaa)DE-He213 Nonlinear testing (dpeaa)DE-He213 Modal characteristic analysis (dpeaa)DE-He213 Finite element analysis (dpeaa)DE-He213 Behdinan, Kamran verfasserin aut Enthalten in Nonlinear dynamics Dordrecht [u.a.] : Springer Science + Business Media B.V, 1990 104(2021), 3 vom: 02. Apr., Seite 2219-2239 (DE-627)315297034 (DE-600)2012600-1 1573-269X nnns volume:104 year:2021 number:3 day:02 month:04 pages:2219-2239 https://dx.doi.org/10.1007/s11071-021-06375-6 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER SSG-OPC-MAT SSG-OPC-ASE GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4328 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 30.20 ASE AR 104 2021 3 02 04 2219-2239 |
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10.1007/s11071-021-06375-6 doi (DE-627)SPR044270178 (SPR)s11071-021-06375-6-e DE-627 ger DE-627 rakwb eng 510 ASE 30.20 bkl Mir-Haidari, Seyed-Ehsan verfasserin aut Advanced test protocols for rapid detection and quantification of nonlinear dynamic responses in aeroengine casing assemblies 2021 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © The Author(s), under exclusive licence to Springer Nature B.V. 2021 Abstract In this research, computationally efficient testing protocols were developed for the accurate detection and quantification of nonlinearities in the bolted flange interfaces of aeroengine casing assemblies. Aeroengine casings are joined by bolted flanges that are exposed to high loading amplitudes, leading to bending and large deflections that cause structural nonlinearities. Initially, to assess these structural nonlinearities, a computationally efficient finite element (FE) modelling methodology was developed to accurately capture the vibrational characteristics of the casings while also significantly improving computational efficiency. The technical accuracy of the vibrational characteristics obtained from the FE modelling technique developed here was validated using simulation methods and experimental vibration testing such as modal analysis, the modal assurance criterion, and mode shape assessment. The modes most susceptible to nonlinear dynamic response were then theoretically identified using the mode shape results acquired through the FE model. Thus, a two-step experimental approach is proposed for achieving the accurate and time-efficient quantification of nonlinearities. In the first stage, a rapid experimental nonlinear assessment is performed using a stinger–shaker set-up to validate the FE simulation results of the susceptible nonlinear modes identified. In the second stage, a precise high-resolution measurement is taken with respect to the modes identified in order to precisely capture the nonlinear characteristics. The integration of the proposed theoretical FE modelling technique with advanced experiment formulations results in a significantly more time-efficient and accurate nonlinear testing protocol for aeroengine structures. Furthermore, the nonlinear damping and stiffness parameters of aeroengine casings were also explored in this research and analysed to improve the existing design and development strategies. Aeroengine (dpeaa)DE-He213 Nonlinear theory (dpeaa)DE-He213 Bolted flange connection (dpeaa)DE-He213 Nonlinear testing (dpeaa)DE-He213 Modal characteristic analysis (dpeaa)DE-He213 Finite element analysis (dpeaa)DE-He213 Behdinan, Kamran verfasserin aut Enthalten in Nonlinear dynamics Dordrecht [u.a.] : Springer Science + Business Media B.V, 1990 104(2021), 3 vom: 02. Apr., Seite 2219-2239 (DE-627)315297034 (DE-600)2012600-1 1573-269X nnns volume:104 year:2021 number:3 day:02 month:04 pages:2219-2239 https://dx.doi.org/10.1007/s11071-021-06375-6 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER SSG-OPC-MAT SSG-OPC-ASE GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4328 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 30.20 ASE AR 104 2021 3 02 04 2219-2239 |
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10.1007/s11071-021-06375-6 doi (DE-627)SPR044270178 (SPR)s11071-021-06375-6-e DE-627 ger DE-627 rakwb eng 510 ASE 30.20 bkl Mir-Haidari, Seyed-Ehsan verfasserin aut Advanced test protocols for rapid detection and quantification of nonlinear dynamic responses in aeroengine casing assemblies 2021 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © The Author(s), under exclusive licence to Springer Nature B.V. 2021 Abstract In this research, computationally efficient testing protocols were developed for the accurate detection and quantification of nonlinearities in the bolted flange interfaces of aeroengine casing assemblies. Aeroengine casings are joined by bolted flanges that are exposed to high loading amplitudes, leading to bending and large deflections that cause structural nonlinearities. Initially, to assess these structural nonlinearities, a computationally efficient finite element (FE) modelling methodology was developed to accurately capture the vibrational characteristics of the casings while also significantly improving computational efficiency. The technical accuracy of the vibrational characteristics obtained from the FE modelling technique developed here was validated using simulation methods and experimental vibration testing such as modal analysis, the modal assurance criterion, and mode shape assessment. The modes most susceptible to nonlinear dynamic response were then theoretically identified using the mode shape results acquired through the FE model. Thus, a two-step experimental approach is proposed for achieving the accurate and time-efficient quantification of nonlinearities. In the first stage, a rapid experimental nonlinear assessment is performed using a stinger–shaker set-up to validate the FE simulation results of the susceptible nonlinear modes identified. In the second stage, a precise high-resolution measurement is taken with respect to the modes identified in order to precisely capture the nonlinear characteristics. The integration of the proposed theoretical FE modelling technique with advanced experiment formulations results in a significantly more time-efficient and accurate nonlinear testing protocol for aeroengine structures. Furthermore, the nonlinear damping and stiffness parameters of aeroengine casings were also explored in this research and analysed to improve the existing design and development strategies. Aeroengine (dpeaa)DE-He213 Nonlinear theory (dpeaa)DE-He213 Bolted flange connection (dpeaa)DE-He213 Nonlinear testing (dpeaa)DE-He213 Modal characteristic analysis (dpeaa)DE-He213 Finite element analysis (dpeaa)DE-He213 Behdinan, Kamran verfasserin aut Enthalten in Nonlinear dynamics Dordrecht [u.a.] : Springer Science + Business Media B.V, 1990 104(2021), 3 vom: 02. Apr., Seite 2219-2239 (DE-627)315297034 (DE-600)2012600-1 1573-269X nnns volume:104 year:2021 number:3 day:02 month:04 pages:2219-2239 https://dx.doi.org/10.1007/s11071-021-06375-6 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER SSG-OPC-MAT SSG-OPC-ASE GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4328 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 30.20 ASE AR 104 2021 3 02 04 2219-2239 |
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Aeroengine casings are joined by bolted flanges that are exposed to high loading amplitudes, leading to bending and large deflections that cause structural nonlinearities. Initially, to assess these structural nonlinearities, a computationally efficient finite element (FE) modelling methodology was developed to accurately capture the vibrational characteristics of the casings while also significantly improving computational efficiency. The technical accuracy of the vibrational characteristics obtained from the FE modelling technique developed here was validated using simulation methods and experimental vibration testing such as modal analysis, the modal assurance criterion, and mode shape assessment. The modes most susceptible to nonlinear dynamic response were then theoretically identified using the mode shape results acquired through the FE model. Thus, a two-step experimental approach is proposed for achieving the accurate and time-efficient quantification of nonlinearities. In the first stage, a rapid experimental nonlinear assessment is performed using a stinger–shaker set-up to validate the FE simulation results of the susceptible nonlinear modes identified. In the second stage, a precise high-resolution measurement is taken with respect to the modes identified in order to precisely capture the nonlinear characteristics. The integration of the proposed theoretical FE modelling technique with advanced experiment formulations results in a significantly more time-efficient and accurate nonlinear testing protocol for aeroengine structures. 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Mir-Haidari, Seyed-Ehsan |
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Mir-Haidari, Seyed-Ehsan ddc 510 bkl 30.20 misc Aeroengine misc Nonlinear theory misc Bolted flange connection misc Nonlinear testing misc Modal characteristic analysis misc Finite element analysis Advanced test protocols for rapid detection and quantification of nonlinear dynamic responses in aeroengine casing assemblies |
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510 ASE 30.20 bkl Advanced test protocols for rapid detection and quantification of nonlinear dynamic responses in aeroengine casing assemblies Aeroengine (dpeaa)DE-He213 Nonlinear theory (dpeaa)DE-He213 Bolted flange connection (dpeaa)DE-He213 Nonlinear testing (dpeaa)DE-He213 Modal characteristic analysis (dpeaa)DE-He213 Finite element analysis (dpeaa)DE-He213 |
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advanced test protocols for rapid detection and quantification of nonlinear dynamic responses in aeroengine casing assemblies |
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Advanced test protocols for rapid detection and quantification of nonlinear dynamic responses in aeroengine casing assemblies |
| abstract |
Abstract In this research, computationally efficient testing protocols were developed for the accurate detection and quantification of nonlinearities in the bolted flange interfaces of aeroengine casing assemblies. Aeroengine casings are joined by bolted flanges that are exposed to high loading amplitudes, leading to bending and large deflections that cause structural nonlinearities. Initially, to assess these structural nonlinearities, a computationally efficient finite element (FE) modelling methodology was developed to accurately capture the vibrational characteristics of the casings while also significantly improving computational efficiency. The technical accuracy of the vibrational characteristics obtained from the FE modelling technique developed here was validated using simulation methods and experimental vibration testing such as modal analysis, the modal assurance criterion, and mode shape assessment. The modes most susceptible to nonlinear dynamic response were then theoretically identified using the mode shape results acquired through the FE model. Thus, a two-step experimental approach is proposed for achieving the accurate and time-efficient quantification of nonlinearities. In the first stage, a rapid experimental nonlinear assessment is performed using a stinger–shaker set-up to validate the FE simulation results of the susceptible nonlinear modes identified. In the second stage, a precise high-resolution measurement is taken with respect to the modes identified in order to precisely capture the nonlinear characteristics. The integration of the proposed theoretical FE modelling technique with advanced experiment formulations results in a significantly more time-efficient and accurate nonlinear testing protocol for aeroengine structures. Furthermore, the nonlinear damping and stiffness parameters of aeroengine casings were also explored in this research and analysed to improve the existing design and development strategies. © The Author(s), under exclusive licence to Springer Nature B.V. 2021 |
| abstractGer |
Abstract In this research, computationally efficient testing protocols were developed for the accurate detection and quantification of nonlinearities in the bolted flange interfaces of aeroengine casing assemblies. Aeroengine casings are joined by bolted flanges that are exposed to high loading amplitudes, leading to bending and large deflections that cause structural nonlinearities. Initially, to assess these structural nonlinearities, a computationally efficient finite element (FE) modelling methodology was developed to accurately capture the vibrational characteristics of the casings while also significantly improving computational efficiency. The technical accuracy of the vibrational characteristics obtained from the FE modelling technique developed here was validated using simulation methods and experimental vibration testing such as modal analysis, the modal assurance criterion, and mode shape assessment. The modes most susceptible to nonlinear dynamic response were then theoretically identified using the mode shape results acquired through the FE model. Thus, a two-step experimental approach is proposed for achieving the accurate and time-efficient quantification of nonlinearities. In the first stage, a rapid experimental nonlinear assessment is performed using a stinger–shaker set-up to validate the FE simulation results of the susceptible nonlinear modes identified. In the second stage, a precise high-resolution measurement is taken with respect to the modes identified in order to precisely capture the nonlinear characteristics. The integration of the proposed theoretical FE modelling technique with advanced experiment formulations results in a significantly more time-efficient and accurate nonlinear testing protocol for aeroengine structures. Furthermore, the nonlinear damping and stiffness parameters of aeroengine casings were also explored in this research and analysed to improve the existing design and development strategies. © The Author(s), under exclusive licence to Springer Nature B.V. 2021 |
| abstract_unstemmed |
Abstract In this research, computationally efficient testing protocols were developed for the accurate detection and quantification of nonlinearities in the bolted flange interfaces of aeroengine casing assemblies. Aeroengine casings are joined by bolted flanges that are exposed to high loading amplitudes, leading to bending and large deflections that cause structural nonlinearities. Initially, to assess these structural nonlinearities, a computationally efficient finite element (FE) modelling methodology was developed to accurately capture the vibrational characteristics of the casings while also significantly improving computational efficiency. The technical accuracy of the vibrational characteristics obtained from the FE modelling technique developed here was validated using simulation methods and experimental vibration testing such as modal analysis, the modal assurance criterion, and mode shape assessment. The modes most susceptible to nonlinear dynamic response were then theoretically identified using the mode shape results acquired through the FE model. Thus, a two-step experimental approach is proposed for achieving the accurate and time-efficient quantification of nonlinearities. In the first stage, a rapid experimental nonlinear assessment is performed using a stinger–shaker set-up to validate the FE simulation results of the susceptible nonlinear modes identified. In the second stage, a precise high-resolution measurement is taken with respect to the modes identified in order to precisely capture the nonlinear characteristics. The integration of the proposed theoretical FE modelling technique with advanced experiment formulations results in a significantly more time-efficient and accurate nonlinear testing protocol for aeroengine structures. Furthermore, the nonlinear damping and stiffness parameters of aeroengine casings were also explored in this research and analysed to improve the existing design and development strategies. © The Author(s), under exclusive licence to Springer Nature B.V. 2021 |
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3 |
| title_short |
Advanced test protocols for rapid detection and quantification of nonlinear dynamic responses in aeroengine casing assemblies |
| url |
https://dx.doi.org/10.1007/s11071-021-06375-6 |
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| author2 |
Behdinan, Kamran |
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| doi_str |
10.1007/s11071-021-06375-6 |
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2024-07-03T23:50:43.450Z |
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| score |
7.4007034 |