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Статті в журналах з теми "Aerodynamic excitation"
Liu, Jian, Wei-Yang Qiao, and Wen-Hua Duan. "Investigation of Unsteady Aerodynamic Excitation on Rotor Blade of Variable Geometry Turbine." International Journal of Rotating Machinery 2019 (May 21, 2019): 1–13. http://dx.doi.org/10.1155/2019/4396546.
Повний текст джерелаKirk, R. G. "Evaluation of Aerodynamic Instability Mechanisms for Centrifugal Compressors—Part I: Current Theory." Journal of Vibration and Acoustics 110, no. 2 (April 1, 1988): 201–6. http://dx.doi.org/10.1115/1.3269499.
Повний текст джерелаStamatellou, Antiopi-Malvina, and Anestis I. Kalfas. "On the Efficiency of a Piezoelectric Energy Harvester under Combined Aeroelastic and Base Excitation." Micromachines 12, no. 8 (August 14, 2021): 962. http://dx.doi.org/10.3390/mi12080962.
Повний текст джерелаPeng, Meng, and Hans A. DeSmidt. "Stability Analysis of a Flutter Panel with Axial Excitations." Advances in Acoustics and Vibration 2016 (July 31, 2016): 1–7. http://dx.doi.org/10.1155/2016/7194764.
Повний текст джерелаZhang, Xiaojie, Yanrong Wang, and Xianghua Jiang. "An Efficient Approach for Predicting Resonant Response with the Utilization of the Time Transformation Method and the Harmonic Forced Response Method." Aerospace 8, no. 11 (October 20, 2021): 312. http://dx.doi.org/10.3390/aerospace8110312.
Повний текст джерелаYoung, T. H., T. C. Tseng, and L. S. Song. "Dynamic Stability of Fluttered Systems Subjected to Parametric Random Excitations." Journal of Vibration and Control 8, no. 3 (March 2002): 291–310. http://dx.doi.org/10.1177/107754602023684.
Повний текст джерелаPust, Ladislav, and Ludek Pesek. "Blades Forced Vibration Under Aero-Elastic Excitation Modeled by Van der Pol." International Journal of Bifurcation and Chaos 27, no. 11 (October 2017): 1750166. http://dx.doi.org/10.1142/s0218127417501668.
Повний текст джерелаLi, Jianxiong, Xiaodong Yang, Anping Hou, Yingxiu Chen, and Manlu Li. "Aerodynamic Damping Prediction for Turbomachinery Based on Fluid-Structure Interaction with Modal Excitation." Applied Sciences 9, no. 20 (October 18, 2019): 4411. http://dx.doi.org/10.3390/app9204411.
Повний текст джерелаZahn, R., and C. Breitsamter. "Airfoil buffet aerodynamics at plunge and pitch excitation based on long short-term memory neural network prediction." CEAS Aeronautical Journal 13, no. 1 (October 18, 2021): 45–55. http://dx.doi.org/10.1007/s13272-021-00550-6.
Повний текст джерелаChiang, Hsiao-Wei D., and R. E. Kielb. "An Analysis System for Blade Forced Response." Journal of Turbomachinery 115, no. 4 (October 1, 1993): 762–70. http://dx.doi.org/10.1115/1.2929314.
Повний текст джерелаДисертації з теми "Aerodynamic excitation"
Laumert, Björn. "Numerical Investigation of Aerodynamic Blade Excitation Mechanisms in Transonic Turbine Stages." Doctoral thesis, KTH, Energy Technology, 2002. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3417.
Повний текст джерелаWith the present drive in turbomachine engine developmenttowards thinner and lighter bladings, closer spaced blade rowsand higher aerodynamic loads per blade row and blade, advanceddesign criteria and accurate prediction methods for vibrationalproblems such as forced response become increasingly importantin order to be able to address and avoid fatigue failures ofthe machine early in the design process. The present worksupports both the search for applicable design criteria and thedevelopment of advanced prediction methods for forced responsein transonic turbine stages. It is aimed at a betterunderstanding of the unsteady aerodynamic mechanisms thatgovern forced response in transonic turbine stages and furtherdevelopment of numerical methods for rotor stator interactionpredictions.
The investigation of the unsteady aerodynamic excitationmechanisms is based on numerical predictions of thethree-dimensional unsteady flow field in representative testturbine stages. It is conducted in three successive steps. Thefirst step is a documentation of the pressure perturbations onthe blade surface and the distortion sources in the bladepassage. This is performed in a phenomenological manner so thatthe observed pressure perturbations are related to thedistortion phenomena that are present in the blade passage. Thesecond step is the definition of applicable measures toquantify the pressure perturbation strength on the bladesurface. In the third step, the pressure perturbations areintegrated along the blade arc to obtain the dynamic bladeforce. The study comprises an investigation of operationvariations and addresses radial forcing variations. With thehelp of this bottom-up approach the basic forcing mechanisms oftransonic turbine stages are established and potential routesto control the aerodynamic forcing are presented.
For the computation of rotor stator interaction aerodynamicsfor stages with arbitrary pitch ratios a new numerical methodhas been developed, validated and demonstrated on a transonicturbine test stage. The method, which solves the unsteadythree-dimensional Euler equations, is formulated in thefour-dimensional time-space domain and the derivation of themethod is general such that both phase lagged boundaryconditions and moving grids are considered. Time-inclination isutilised to account for unequal pitchwise periodicity bydistributing time co-ordinates at grid nodes such that thephase lagged boundary conditions can be employed. The method isdemonstrated in a comparative study on a transonic turbinestage with a nominal non integer blade count ratio and anadjusted blade count ratio with a scaled rotor geometry. Thepredictions show significant differences in the blade pressureperturbation signal of the second vane passing frequency, whichwould motivate the application of the new method for rotorstator predictions with non-integer blade count ratios.
Ilgin, Huseyin Emre. "A Study On Tall Buildings And Aerodynamic Modifications Against Wind Excitation." Master's thesis, METU, 2006. http://etd.lib.metu.edu.tr/upload/12607000/index.pdf.
Повний текст джерела#8217
s understanding of tall building design, that requires a high level of interdisciplinary approach, by providing a broad overview of the tall building with its general concepts
to demonstrate the importance of human element as a critical component in the design of tall building by clarifying the wind forces and resulting movements which cause discomfort to building occupants and create serious serviceability issues
and to show the significance of aerodynamic modifications as an effective design approach in terms of mitigating wind excitation. In order to achieve these purposes, firstly, a comprehensive literature survey, which includes the definition, emergence and historical background, basic planning and design parameters, and lateral load considerations of tall buildings is presented. Following a structural classification of the tall buildings, wind excitation, its negative effects on occupant comfort and serviceabilty issues, and the methods to control wind excitation are studied. Finally, the significance of aerodynamic modifications against wind excitation, which include modifications of building&
#8217
s cross-sectional shape and its corner geometry, sculptured building tops, horizontal and vertical openings through-building, are presented from the scholarship on this topic.
Jöcker, Markus. "Numerical Investigation of the Aerodynamic Vibration Excitation of High-Pressure Turbine Rotors." Doctoral thesis, KTH, Energy Technology, 2002. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3416.
Повний текст джерелаThe design parameters axial gap and stator count of highpressure turbine stages are evaluated numerically towards theirinfluence on the unsteady aerodynamic excitation of rotorblades. Of particular interest is if and how unsteadyaerodynamic considerations in the design could reduce the riskofhigh cycle fatigue (HCF) failures of the turbine rotor.
A well-documented 2D/Q3D non-linear unsteady code (UNSFLO)is chosen to perform the stage flow analyses. The evaluatedresults are interpreted as aerodynamic excitation mechanisms onstream sheets neglecting 3D effects. Mesh studies andvalidations against measurements and 3D computations provideconfidence in the unsteady results. Three test cases areanalysed. First, a typical aero-engine high pressure turbinestage is studied at subsonic and transonic flow conditions,with four axial gaps (37% - 52% of cax,rotor) and two statorconfigurations (43 and 70 NGV). Operating conditions areaccording to the resonant conditions of the blades used inaccompanied experiments. Second, a subsonic high pressureturbine intended to drive the turbopump of a rocket engine isinvestigated. Four axial gap variations (10% - 29% ofcax,rotor) and three stator geometry variations are analysed toextend and generalise the findings made on the first study.Third, a transonic low pressure turbine rotor, known as theInternational Standard Configuration 11, has been modelled tocompute the unsteady flow due to blade vibration and comparedto available experimental data.
Excitation mechanisms due to shock, potential waves andwakes are described and related to the work found in the openliterature. The strength of shock excitation leads to increasedpressure excitation levels by a factor 2 to 3 compared tosubsonic cases. Potential excitations are of a typical wavetype in all cases, differences in the propagation direction ofthe waves and the wave reflection pattern in the rotor passagelead to modifications in the time and space resolved unsteadypressures on the blade surface. The significant influence ofoperating conditions, axial gap and stator size on the wavepropagation is discussed on chosen cases. The wake influence onthe rotorblade unsteady pressure is small in the presentevaluations, which is explicitly demonstrated on the turbopumpturbine by a parametric study of wake and potentialexcitations. A reduction in stator size (towards R≈1)reduces the potential excitation part so that wake andpotential excitation approach in their magnitude.
Potentials to reduce the risk of HCF excitation in transonicflow are the decrease of stator exit Mach number and themodification of temporal relations between shock and potentialexcitation events. A similar temporal tuning of wake excitationto shock excitation appears not efficient because of the smallwake excitation contribution. The increase of axial gap doesnot necessarily decrease the shock excitation strength neitherdoes the decrease of vane size because the shock excitation mayremain strong even behind a smaller stator. The evaluation ofthe aerodynamic excitation towards a HCF risk reduction shouldonly be done with regard to the excited mode shape, asdemonstrated with parametric studies of the mode shapeinfluence on excitability.
Keywords:Aeroelasticity, Aerodynamics, Stator-RotorInteraction, Excitation Mechanism, Unsteady Flow Computation,Forced Response, High Cycle Fatigue, Turbomachinery,Gas-Turbine, High-Pressure Turbine, Turbopump, CFD, Design
Elkoby, Ronen. "Acoustic excitation of wing wake flows." Thesis, Georgia Institute of Technology, 2000. http://hdl.handle.net/1853/12265.
Повний текст джерелаRaubenheimer, Gert. "Vibration excitation of axial compressor rotor blades." Thesis, Stellenbosch : Stellenbosch University, 2011. http://hdl.handle.net/10019.1/17987.
Повний текст джерелаENGLISH ABSTRACT: Turbomachines are exposed to several environmental factors which may cause failure of components. One of these factors, high cycle fatigue, is often caused by blade utter. This thesis forms part of a project of the European Seventh Framework Programme (FP7), called project Future. Project Future is doing theoretical and experimental investigation into the occurrence of utter in turbomachinery. The objective of this thesis was to evaluate the effectiveness of a gas injection system as a means of exciting vibrations on the rst stage rotor blades of a compressor. Unsteady simulations of the excitation velocity perturbations were performed in the Computational Fluid Dynamics (CFD) software, Numeca FINE/Turbo. Experimental testing on the in-house Rofanco compressor test bench, using one prototype of the 15 injector system, provided data that was used to implement boundary conditions and to verify certain aspects of the unsteady simulation results. The simulation results revealed the following: the injector bypass frequency was so dominant that the excitation frequency was hardly detectable in the majority of cases. Furthermore, several secondary frequencies were consistently present. The injector bypass frequency, as well as the secondary frequencies, occurred as a result of the convolution of Fast Fourier Transforms. While the injector bypass frequencies can theoretically be eliminated, it will not be possible to eliminate the secondary frequencies from the blade response. In conclusion, according to the CFD results, it will not be possible to excite a single excitation frequency by making use of a nite number of gas injector vibration exciters.
AFRIKAANSE OPSOMMING: Turbomasjiene word onderwerp aan verskeie omgewingsfaktore wat falings van komponente kan veroorsaak. Een van hierdie faktore, naamlik hoëfrekwensie vermoeidheid, word onder andere veroorsaak deur lem adder. Hierdie tesis is deel van 'n projek in die Sewende Europese Raamwerk Program (European Seventh Framework Programme - FP7), projek Future. Projek Future doen teoretiese en eksperimentele ondersoek na die voorkoms van lemfl adder in turbomasjienerie. Die doelwit van hierdie tesis was om die effektiwiteit van 'n gasinspuiter vibrasie-opwekkingstelsel te evalueer, deur gebruik te maak van onbestendige simulasie in die berekenings vloei-meganika sagtewarepakket, Numeca FINE/Turbo. Eksperimentele toetswerk op die plaaslike Rofanco kompressortoetsbank, met 'n prototipe van die 15 inspuiter stelsel, het inligting verskaf wat gebruik is om die inlaattoestande te spesi seer en simulasieresultate te korreleer. Die simulasieresultate het getoon dat die frekwensie waarteen 'n lem by die inspuiters verbybeweeg, so prominent is, dat dit in die meerderheid van gevalle baie meer prominent is as die opwekkingsfrekwensie. Verder was daar ook deurgaans 'n aantal sekondêre frekwensies teenwoordig. Die teenwoordigheid van die inspuiter verbybeweeg frekwensie en die sekondêre frekwensies is die resultaat van die konvolusie van Vinnige Fourier Transforme. Alhoewel dit in teorie moontlik sal wees om die inspuiter verbybeweeg frekwensie te elimineer, is dit onmoontlik om die sekondêre frekwensies uit die lem vibrasie te elimineer. Ter opsomming, volgens die berekenings vloei-meganika resultate, is dit nie moontlik om met 'n stelsel van 'n eindige aantal inspuiters, 'n enkele vibrasie frekwensie op te wek nie.
Clifford, Christopher J. "An Investigation of Physics and Control of Flow Passing a NACA 0015 in Fully-Reversed Condition." The Ohio State University, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=osu1440156651.
Повний текст джерелаSood, Sanjeev. "Active vibration control of flexible structures under aerodynamic excitation." Thesis, 2018. http://eprint.iitd.ac.in:80//handle/2074/7930.
Повний текст джерела"A STUDY ON TALL BUILDINGS AND AERODYNAMIC MODIFICATIONS AGAINST WIND EXCITATION." Master's thesis, METU, 2006. http://etd.lib.metu.edu.tr/upload/12607000/index.pdf.
Повний текст джерелаLIU, CI-YAO, and 劉賜耀. "The influence of acoustic excitation on aerodynamic performance of three dimensional wings." Thesis, 1991. http://ndltd.ncl.edu.tw/handle/44118131932286691071.
Повний текст джерелаКниги з теми "Aerodynamic excitation"
Raman, Ganesh. Enhanced mixing of an axisymmetric jet by aerodynamic excitation. Cleveland, Ohio: Lewis Research Center, 1986.
Знайти повний текст джерелаRaman, Ganesh. Enhanced mixing of an axisymmetric jet by aerodynamic excitation. Cleveland, Ohio: Lewis Research Center, 1986.
Знайти повний текст джерелаM, Abbott John, and United States. National Aeronautics and Space Administration., eds. Control of flow separation and mixing by aerodynamic excitation. [Washington, D.C.]: NASA, 1990.
Знайти повний текст джерелаM, Abbott John, and United States. National Aeronautics and Space Administration., eds. Control of flow separation and mixing by aerodynamic excitation. [Washington, D.C.]: NASA, 1990.
Знайти повний текст джерелаUnited States. National Aeronautics and Space Administration., ed. Effect of acoustic excitation on stalled flows over an airfoil. [Washington, DC]: National Aeronautics and Space Administration, 1990.
Знайти повний текст джерелаUnited States. National Aeronautics and Space Administration., ed. A steadying effect of acoustic excitation on transitory stall. [Washington, DC]: National Aeronautics and Space Administration, 1991.
Знайти повний текст джерелаCenter, Lewis Research, ed. Modal forced vibration analysis of aerodynamically excited turbosystems: Final report. Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1995.
Знайти повний текст джерелаMartinez-Sanchez, Manuel. Turbine blade-tip clearance excitation forces: Final report on Contract number NAS8-35018. Cambridge, Mass: Massachusetts Institute of Technology, 1985.
Знайти повний текст джерелаMartinez-Sanchez, Manuel. Turbine blade-tip clearance excitation forces: Final report on Contract number NAS8-35018. Cambridge, Mass: Massachusetts Institute of Technology, 1985.
Знайти повний текст джерелаM, Greitzer Edward, George C. Marshall Space Flight Center., and Massachusetts Institute of Technology, eds. Turbine blade-tip clearance excitation forces: Final report on Contract number NAS8-35018. Cambridge, Mass: Massachusetts Institute of Technology, 1985.
Знайти повний текст джерелаЧастини книг з теми "Aerodynamic excitation"
Daborn, P. M., P. R. Ind, and D. J. Ewins. "Replicating Aerodynamic Excitation in the Laboratory." In Topics in Modal Analysis, Volume 7, 259–72. New York, NY: Springer New York, 2013. http://dx.doi.org/10.1007/978-1-4614-6585-0_24.
Повний текст джерелаAubrun, Sandrine, Alain Seraudie, Daniel Biron, and Daniel Arnal. "Influence of Acoustic Excitation on 3D Boundary Layer Instabilities." In Aerodynamic Drag Reduction Technologies, 180–87. Berlin, Heidelberg: Springer Berlin Heidelberg, 2001. http://dx.doi.org/10.1007/978-3-540-45359-8_20.
Повний текст джерелаAbegg, C., H. Bippes, A. Boiko, V. Krishnan, T. Lerche, A. Pöthke, Y. Wu, and U. Dallmann. "Transitional Flow Physics and Flow Control for Swept Wings: Experiments on Boundary-Layer Receptivity, Instability Excitation and HLF-Technology." In Aerodynamic Drag Reduction Technologies, 199–206. Berlin, Heidelberg: Springer Berlin Heidelberg, 2001. http://dx.doi.org/10.1007/978-3-540-45359-8_22.
Повний текст джерелаUrban, Brigitte, Heinz Stetter, and Nicolas Vortmeyer. "Aerodynamic Excitation of Transonic Turbine Cascade; Description of the Experimental Method." In Notes on Numerical Fluid Mechanics (NNFM), 488–95. Wiesbaden: Vieweg+Teubner Verlag, 1999. http://dx.doi.org/10.1007/978-3-663-10901-3_63.
Повний текст джерелаIchchou, Mohamed N., Olivier Bareille, Bernard Troclet, Bastien Hiverniau, Marie De Rochambeau, and Dimitrios Chronopoulos. "Vibroacoustics Under Aerodynamic Excitations." In Flinovia - Flow Induced Noise and Vibration Issues and Aspects, 227–47. Cham: Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-09713-8_11.
Повний текст джерелаSato, W., A. Yamagata, and H. Hattori. "A study on unsteady aerodynamic excitation forces on radial turbine blade due to rotor-stator interaction." In 11th International Conference on Turbochargers and Turbocharging, 389–98. Elsevier, 2014. http://dx.doi.org/10.1533/978081000342.389.
Повний текст джерелаТези доповідей конференцій з теми "Aerodynamic excitation"
Hauptmann, Thomas, and Joerg R. Seume. "Aerodynamic Excitation Analysis for Variable Tip Gap." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-57217.
Повний текст джерелаPourzeynali, S., and T. K. Datta. "RESPONSE OF SUSPENSION BRIDGES TO AERODYNAMIC EXCITATION." In Proceedings of the Second International Conference. WORLD SCIENTIFIC, 2002. http://dx.doi.org/10.1142/9789812776228_0040.
Повний текст джерелаEwing, Mark. "Response of a tactical missile to aerodynamic excitation." In 36th Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-1495.
Повний текст джерелаKumar, Arun, Erik Sallstrom, Simone Sebben, and Bengt Jacobson. "Predictive Model of Driver’s Perception of Vehicle Stability under Aerodynamic Excitation." In WCX SAE World Congress Experience. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2023. http://dx.doi.org/10.4271/2023-01-0903.
Повний текст джерелаKielb, Robert E., John W. Barter, Jeffrey P. Thomas, and Kenneth C. Hall. "Blade Excitation by Aerodynamic Instabilities: A Compressor Blade Study." In ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/gt2003-38634.
Повний текст джерелаLi, Jianlan, Huafeng Liu, Chen Yu, and Shuhong Huang. "Catastrophe Performance Analysis of Aerodynamic Excitation for Steam Turbine." In 2012 IEEE PES Asia-Pacific Power and Energy Engineering Conference (APPEEC). IEEE, 2012. http://dx.doi.org/10.1109/appeec.2012.6307677.
Повний текст джерелаMelbourne, W. H. "Shaping Tall Buildings to Reduce Aerodynamic Excitation and Response." In Structures Congress 2000. Reston, VA: American Society of Civil Engineers, 2000. http://dx.doi.org/10.1061/40492(2000)89.
Повний текст джерелаBibo, Amin, and Mohammed F. Daqaq. "Energy Harvesting Under Combined Aerodynamic and Base Excitations." In ASME 2012 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/smasis2012-7908.
Повний текст джерелаKulatilaka, Waruna, Sukesh Roy, and James Gord. "Multi-Photon Fluorescence Imaging of Flame Species Using Femtosecond Excitation." In 28th Aerodynamic Measurement Technology, Ground Testing, and Flight Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-2882.
Повний текст джерелаBibo, Amin, and Mohammed F. Daqaq. "Concurrent Energy Harvesting From Vibratory Base Excitations and Aerodynamic Flows." In ASME 2013 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/smasis2013-3115.
Повний текст джерелаЗвіти організацій з теми "Aerodynamic excitation"
Candler, Graham V. Effect of Internal Energy Excitation on Supersonic Blunt-Body Aerodynamics. Fort Belvoir, VA: Defense Technical Information Center, March 2001. http://dx.doi.org/10.21236/ada387503.
Повний текст джерела