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Reduced-Order Modeling of Aeroelastic Phenomena
Reduced-Order Modeling of Aeroelastic Phenomena
상세정보
- 자료유형
- 학위논문 서양
- 최종처리일시
- 20260209102847
- ISBN
- 9798291563595
- DDC
- 629.1
- 서명/저자
- Reduced-Order Modeling of Aeroelastic Phenomena
- 발행사항
- [Sl] : University of Illinois at Urbana-Champaign, 2023
- 발행사항
- Ann Arbor : ProQuest Dissertations & Theses, 2023
- 형태사항
- 166 p
- 주기사항
- Source: Dissertations Abstracts International, Volume: 87-02, Section: B.
- 주기사항
- Advisor: Bodony, Daniel J.
- 학위논문주기
- Thesis (Ph.D.)--University of Illinois at Urbana-Champaign, 2023.
- 초록/해제
- 요약Traditional methods to identify the aeroelastic stability of turbomachinery have been focused on the use of either experimental investigations of the device or fully coupled fluid-structural simulation techniques. While both methods provide accurate depictions of the underlying stability of the device in question, the time or computational cost associated with obtaining the stability analyses becomes excessive when the aeroelastic stability of the device must be evaluated over multiple operating regimes.In this dissertation, a reduced-order modeling method is developed and presented in order to greatly diminish the numerical expense associated with evaluating aeroelastic stability at a defined operating condition. The method differs from existing low-order approaches in that it leverages the use of piston theory in conjunction with steady-state simulation data from computational fluid dynamics simulations in order to predict the fluid loading that arises in response to the structural deformation. The model is applied to previously-studied, canonical panel flutter configurations to demonstrate the accuracy of the method. The application of the method on the high-pressure turbine of a dual-stage turbocharger is then demonstrated and the stability predictions compared against experimental observations conducted independently by scientists at the Army Research Laboratory. The reduced-order modeling method is confirmed to accurately diagnose the qualitative stability properties of the device with respect to aeroelastic flutter and a discussion regarding methods to properly diagnose the susceptibility of the device to forced response is presented.To address the shortcomings of aerodynamic piston theory in subsonic flow regimes and in modest supersonic flow regimes, a stability method incorporating spatial pressure fluctuation modes learned using dynamic mode decomposition is developed. This method is first applied to two- and three-dimensional flows over beams and panels exhibiting a harmonic response consistent with aeroelastic flutter. The manner in which to learn the leading spatial modes that dominate the pressure response for each configuration is presented and these spatial modes are compared against the spatial modes computed by a boundary element method in each scenario to confirm that the dynamic mode decomposition algorithm indeed learns the correct pressure response. These leading spatial modes are then used to compute the stability of the structures in modest supersonic regimes. The results are compared against separate investigations, both numerical and experimental, that have been previously presented in the literature to confirm that the stability method incorporating approximate pressure fluctuation modes learned from data can accurately predict the onset of aeroelastic flutter.
- 일반주제명
- Aerospace engineering
- 일반주제명
- Applied mathematics
- 일반주제명
- Fluid mechanics
- 키워드
- Aeroelasticity
- 기타저자
- University of Illinois at Urbana-Champaign Aerospace Engineering
- 기본자료저록
- Dissertations Abstracts International. 87-02B.
- 전자적 위치 및 접속
- 로그인 후 원문을 볼 수 있습니다.
MARC
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■040 ▼aMiAaPQ▼cMiAaPQ
■0820 ▼a629.1
■1001 ▼aFellows, David William.
■24510▼aReduced-Order Modeling of Aeroelastic Phenomena
■260 ▼a[Sl]▼bUniversity of Illinois at Urbana-Champaign▼c2023
■260 1▼aAnn Arbor▼bProQuest Dissertations & Theses▼c2023
■300 ▼a166 p
■500 ▼aSource: Dissertations Abstracts International, Volume: 87-02, Section: B.
■500 ▼aAdvisor: Bodony, Daniel J.
■5021 ▼aThesis (Ph.D.)--University of Illinois at Urbana-Champaign, 2023.
■520 ▼aTraditional methods to identify the aeroelastic stability of turbomachinery have been focused on the use of either experimental investigations of the device or fully coupled fluid-structural simulation techniques. While both methods provide accurate depictions of the underlying stability of the device in question, the time or computational cost associated with obtaining the stability analyses becomes excessive when the aeroelastic stability of the device must be evaluated over multiple operating regimes.In this dissertation, a reduced-order modeling method is developed and presented in order to greatly diminish the numerical expense associated with evaluating aeroelastic stability at a defined operating condition. The method differs from existing low-order approaches in that it leverages the use of piston theory in conjunction with steady-state simulation data from computational fluid dynamics simulations in order to predict the fluid loading that arises in response to the structural deformation. The model is applied to previously-studied, canonical panel flutter configurations to demonstrate the accuracy of the method. The application of the method on the high-pressure turbine of a dual-stage turbocharger is then demonstrated and the stability predictions compared against experimental observations conducted independently by scientists at the Army Research Laboratory. The reduced-order modeling method is confirmed to accurately diagnose the qualitative stability properties of the device with respect to aeroelastic flutter and a discussion regarding methods to properly diagnose the susceptibility of the device to forced response is presented.To address the shortcomings of aerodynamic piston theory in subsonic flow regimes and in modest supersonic flow regimes, a stability method incorporating spatial pressure fluctuation modes learned using dynamic mode decomposition is developed. This method is first applied to two- and three-dimensional flows over beams and panels exhibiting a harmonic response consistent with aeroelastic flutter. The manner in which to learn the leading spatial modes that dominate the pressure response for each configuration is presented and these spatial modes are compared against the spatial modes computed by a boundary element method in each scenario to confirm that the dynamic mode decomposition algorithm indeed learns the correct pressure response. These leading spatial modes are then used to compute the stability of the structures in modest supersonic regimes. The results are compared against separate investigations, both numerical and experimental, that have been previously presented in the literature to confirm that the stability method incorporating approximate pressure fluctuation modes learned from data can accurately predict the onset of aeroelastic flutter.
■590 ▼aSchool code: 0090.
■650 4▼aAerospace engineering
■650 4▼aApplied mathematics
■650 4▼aFluid mechanics
■653 ▼aFluid-structural interaction
■653 ▼aAeroelasticity
■653 ▼aComputational fluid dynamics
■653 ▼aData-driven modeling
■653 ▼aUnsteady aerodynamic modeling
■690 ▼a0538
■690 ▼a0204
■690 ▼a0364
■71020▼aUniversity of Illinois at Urbana-Champaign▼bAerospace Engineering.
■7730 ▼tDissertations Abstracts International▼g87-02B.
■790 ▼a0090
■791 ▼aPh.D.
■792 ▼a2023
■793 ▼aEnglish
■85640▼uhttp://www.riss.kr/pdu/ddodLink.do?id=T17365884▼nKERIS▼z이 자료의 원문은 한국교육학술정보원에서 제공합니다.
