Coupled Lateral and Torsional Vibration of Rub-Impact Rotor during Hovering Flight
When aircraft make a maneuvering during flight, additional loads acting on the engine rotor system are generated, which may induce rub-impact faults between the rotor and stator. To study the rub-impact response characteristics of the rotor system during hovering flight, the dynamic model of a rub-i...
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| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Wiley
2021-01-01
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| Series: | Shock and Vibration |
| Online Access: | http://dx.doi.org/10.1155/2021/4077556 |
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| _version_ | 1832566282543693824 |
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| author | Nan Zheng Moli Chen Guihuo Luo Zhifeng Ye |
| author_facet | Nan Zheng Moli Chen Guihuo Luo Zhifeng Ye |
| author_sort | Nan Zheng |
| collection | DOAJ |
| description | When aircraft make a maneuvering during flight, additional loads acting on the engine rotor system are generated, which may induce rub-impact faults between the rotor and stator. To study the rub-impact response characteristics of the rotor system during hovering flight, the dynamic model of a rub-impact rotor system is established with lateral-torsional vibration coupling effect under arbitrary maneuvering flight conditions using the finite element method and Lagrange equation. An implicit numerical integral method combining the Newmark-β and Newton–Raphson methods is used to solve the vibration response. The results indicate that the dynamic characteristics of the rotor system will change during maneuvering flight, and the subharmonic vibrations are amplified in both lateral and torsional vibrations due to maneuvering overload. The form of the rub-impact is different during level and hovering flight conditions: the rub-impact may occur at an arbitrary phase of the whole cycle under the condition of level flight, while only local rub-impact occurs during hovering flight. Under the both flight conditions, the rub-impact has a large effect on the spectral characteristics, periodicity, and stability of the rotor system. |
| format | Article |
| id | doaj-art-70af4002cca941beb9a65ee4b7f3c5ae |
| institution | Kabale University |
| issn | 1070-9622 1875-9203 |
| language | English |
| publishDate | 2021-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | Shock and Vibration |
| spelling | doaj-art-70af4002cca941beb9a65ee4b7f3c5ae2025-02-03T01:04:31ZengWileyShock and Vibration1070-96221875-92032021-01-01202110.1155/2021/40775564077556Coupled Lateral and Torsional Vibration of Rub-Impact Rotor during Hovering FlightNan Zheng0Moli Chen1Guihuo Luo2Zhifeng Ye3Key Laboratory of Aero-Engine Thermal Environment and Structure, Ministry of Industry and Information Technology, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaKey Laboratory of Aero-Engine Thermal Environment and Structure, Ministry of Industry and Information Technology, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaKey Laboratory of Aero-Engine Thermal Environment and Structure, Ministry of Industry and Information Technology, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaKey Laboratory of Aero-Engine Thermal Environment and Structure, Ministry of Industry and Information Technology, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaWhen aircraft make a maneuvering during flight, additional loads acting on the engine rotor system are generated, which may induce rub-impact faults between the rotor and stator. To study the rub-impact response characteristics of the rotor system during hovering flight, the dynamic model of a rub-impact rotor system is established with lateral-torsional vibration coupling effect under arbitrary maneuvering flight conditions using the finite element method and Lagrange equation. An implicit numerical integral method combining the Newmark-β and Newton–Raphson methods is used to solve the vibration response. The results indicate that the dynamic characteristics of the rotor system will change during maneuvering flight, and the subharmonic vibrations are amplified in both lateral and torsional vibrations due to maneuvering overload. The form of the rub-impact is different during level and hovering flight conditions: the rub-impact may occur at an arbitrary phase of the whole cycle under the condition of level flight, while only local rub-impact occurs during hovering flight. Under the both flight conditions, the rub-impact has a large effect on the spectral characteristics, periodicity, and stability of the rotor system.http://dx.doi.org/10.1155/2021/4077556 |
| spellingShingle | Nan Zheng Moli Chen Guihuo Luo Zhifeng Ye Coupled Lateral and Torsional Vibration of Rub-Impact Rotor during Hovering Flight Shock and Vibration |
| title | Coupled Lateral and Torsional Vibration of Rub-Impact Rotor during Hovering Flight |
| title_full | Coupled Lateral and Torsional Vibration of Rub-Impact Rotor during Hovering Flight |
| title_fullStr | Coupled Lateral and Torsional Vibration of Rub-Impact Rotor during Hovering Flight |
| title_full_unstemmed | Coupled Lateral and Torsional Vibration of Rub-Impact Rotor during Hovering Flight |
| title_short | Coupled Lateral and Torsional Vibration of Rub-Impact Rotor during Hovering Flight |
| title_sort | coupled lateral and torsional vibration of rub impact rotor during hovering flight |
| url | http://dx.doi.org/10.1155/2021/4077556 |
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