Volume 7C: Structures and Dynamics最新文献_第4页

The Influence of Circumferential Grooves on the Flutter Stability of a Transonic Fan 周向沟槽对跨声速风扇颤振稳定性的影响

Volume 7C: Structures and Dynamics Pub Date : 2018-06-11 DOI: 10.1115/GT2018-76422

Matthias Kniefs, M. Lange, R. Mailach, S. Iseni, D. Micallef, F. Mare

{"title":"The Influence of Circumferential Grooves on the Flutter Stability of a Transonic Fan","authors":"Matthias Kniefs, M. Lange, R. Mailach, S. Iseni, D. Micallef, F. Mare","doi":"10.1115/GT2018-76422","DOIUrl":"https://doi.org/10.1115/GT2018-76422","url":null,"abstract":"Circumferential grooves in the casing of an axial compressor rotor or fan are known to be beneficial by extending the operating range of the machine. The goal of this paper is to analyze, if such grooves have a significant effect on the flutter stability, too. Generally, flutter should always be avoided as these self-excited blade vibrations can lead to high-cycle fatigue and therefore may damage the blades. In the present paper, the flutter behavior of a nominal fan is analyzed by performing a unidirectional Fluid-Structure-Interaction (FSI) simulation. To model the traveling wave arising during flutter, three different possibilities are available for computational fluid dynamics (CFD): the traveling wave mode method (TWM), the Fourier transformation method (FT) and the influence coefficient method (INFC). The TWM and INFC will be used within this investigation. At first, the computed flutter stability of the commercial CFD solver ANSYS CFX is compared to the results of the academic CFD solver TBLOCK. Therefore, a MATLAB code is introduced to be able to use the very efficient INFC method in combination with ANSYS CFX. The main part of this paper deals with the examination of three different circumferential grooves. Two of them had been optimized regarding aerodynamics and aeroacoustics in a joint research project and produce a minor change in flutter behavior. The third groove is of an arbitrary chosen design and it is discussed how its axial position has an impact on the vibration characteristic of the fan. All CFD simulations are conducted for two different operating points at 100% speed and the first two eigenmodes of the fan blade.","PeriodicalId":347795,"journal":{"name":"Volume 7C: Structures and Dynamics","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125318623","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 2

Influence of Intrarow Interaction on the Aerodynamic Damping of an Axial Turbine Stage 槽内相互作用对轴流涡轮级气动阻尼的影响

Volume 7C: Structures and Dynamics Pub Date : 2018-06-11 DOI: 10.1115/GT2018-76777

Tobias R. Müller, D. Vogt, K. Vogel, B. Phillipsen

{"title":"Influence of Intrarow Interaction on the Aerodynamic Damping of an Axial Turbine Stage","authors":"Tobias R. Müller, D. Vogt, K. Vogel, B. Phillipsen","doi":"10.1115/GT2018-76777","DOIUrl":"https://doi.org/10.1115/GT2018-76777","url":null,"abstract":"The present numerical study aims at examining the influence of intrarow interaction effects in aerodynamic damping predictions of an axial turbine rotor. The investigated operating point corresponds to a resonance crossing associated with the fundamental engine order of the stator blade row. Accordingly, the pressure perturbations induced by the vibration of the rotor at its modal frequency are found to be coincident in frequency and thus superimpose with the pressure perturbations resulting from intrarow interaction phenomena. A methodology for extracting vibration induced pressure perturbations for the subsequent calculation of the vibration induced modal aerodynamic damping is established and applied within the scope of the present study.\u0000 Applying this methodology, both the influence of the underlying mean and transient flow field as well as the influence of acoustic wave reflections at the adjacent stator blade row is investigated on the predicted aerodynamic damping. In this context, the underlying mean flow field, which is found to be slightly altered in the presence of intrarow interaction phenomena, was proven to have a significant influence on vibration induced pressure perturbations. Moreover, acoustic wave reflections at the adjacent stator blade row are found to have the capability of influencing the aerodynamic damping depending on their actual phasing when impinging onto the turbine rotor.","PeriodicalId":347795,"journal":{"name":"Volume 7C: Structures and Dynamics","volume":"369 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122816125","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 3

Analysis of Nonlinear Modal Damping due to Friction at Blade Roots Using High-Fidelity Modelling 基于高保真模型的叶根摩擦非线性模态阻尼分析

Volume 7C: Structures and Dynamics Pub Date : 2018-06-11 DOI: 10.1115/GT2018-76546

Junjie Chen, C. Zang, Biao Zhou, E. Petrov

{"title":"Analysis of Nonlinear Modal Damping due to Friction at Blade Roots Using High-Fidelity Modelling","authors":"Junjie Chen, C. Zang, Biao Zhou, E. Petrov","doi":"10.1115/GT2018-76546","DOIUrl":"https://doi.org/10.1115/GT2018-76546","url":null,"abstract":"In this paper, a methodology is developed for analysis of modal damping in root joints of bladed discs using large finite element models and detailed description of friction contacts at contact interfaces of the joints. The methods allows the analysis of: (i) a single blade vibration and (ii) a bladed-disc assembly for any family of modes (lower and higher modes) calculating the modal damping factors for different levels of vibrations.\u0000 Three-dimension solid finite element models are used in the calculations. The analysis is performed in time domain through the transient dynamics analysis. The methodology allows the use of widely available finite element packages and based on the direct calculation of the energy dissipated at root joints due to micro-slip over the multitude of contact elements modelling the surface-to-surface friction contact interactions.\u0000 The numerical studies of the dependency of modal damping factors on the vibration amplitudes are performed for simplified and realistic bladed disc models for different blade mode shapes, engine-order excitation numbers and nodal diameter numbers using high-fidelity models.","PeriodicalId":347795,"journal":{"name":"Volume 7C: Structures and Dynamics","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132064029","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 3

Study of the Impact of Multi-Row Interaction on Flutter Analysis for a Representative LPT Geometry 多排相互作用对典型LPT几何结构颤振分析的影响研究

Volume 7C: Structures and Dynamics Pub Date : 2018-06-11 DOI: 10.1115/GT2018-75762

A. Sotillo, J. Gallardo

{"title":"Study of the Impact of Multi-Row Interaction on Flutter Analysis for a Representative LPT Geometry","authors":"A. Sotillo, J. Gallardo","doi":"10.1115/GT2018-75762","DOIUrl":"https://doi.org/10.1115/GT2018-75762","url":null,"abstract":"Acoustic reflections and multiple blade-row effects have an impact on aeroelastic behavior, which can change the aerodynamic damping by a significant amount. However, conventional flutter analyses neglect these effects as they ignore any information about the multistage unsteady interaction. In order to capture them, the authors of this paper have developed a multistage coupling methodology for ITP’s in-house unsteady 3D frequency-domain linearized RANS solver. The current approach allows carrying out CFD simulations on a multistage environment built upon an arbitrary number of blade-rows; each one of them could also have an arbitrary number of frequencies and/or interblade phase angles. The coupling mechanism between consecutive blade-rows arises in a somewhat straightforward way after the solutions are decomposed as the sum of several spinning modes in the inter-row boundaries and the continuity of acoustic, vortical and entropic waves is enforced. This method is suitable for flutter and forced response computations, and also for tonal noise propagation.\u0000 The focus of this paper is on the study of multiple blade-row effects on flutter stability margin. A brief analysis of results for a couple of simple test cases is presented to demonstrate the correctness of the method. Then, a detailed flutter analysis for a representative LPT geometry is performed and the results are compared with a single row conventional analysis. The impact of neighboring and further blade-rows, as well as spinning modes scattered from the fundamental circumferential mode, are accounted for in the unsteady aerodynamic loading of the excited blade.","PeriodicalId":347795,"journal":{"name":"Volume 7C: Structures and Dynamics","volume":"13 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122332275","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 2

An Approach to Approximate the Full Strain Field of Turbofan Blades During Operation 涡扇叶片工作时全应变场的近似方法

Volume 7C: Structures and Dynamics Pub Date : 2018-06-11 DOI: 10.1115/GT2018-77056

Gen Fu, A. Untăroiu, W. O'Brien

{"title":"An Approach to Approximate the Full Strain Field of Turbofan Blades During Operation","authors":"Gen Fu, A. Untăroiu, W. O'Brien","doi":"10.1115/GT2018-77056","DOIUrl":"https://doi.org/10.1115/GT2018-77056","url":null,"abstract":"The measurement of the aeromechanical response of the fan blades is important to quantifying their integrity. The accurate knowledge of the response at critical locations of the structure is crucial when assessing the structural condition. A reliable and low cost measuring technique is necessary. Currently, sensors can only provide the measured data at several discrete points. A significant number of sensors may be required to fully characterize the aeromechanical response of the blades. However, the amount of instrumentation that can be placed on the structure is limited due to data acquisition system limitations, instrumentation accessibility, and the effect of the instrumentation on the measured response. From a practical stand point, it is not possible to place sensors at all the critical locations for different excitations. Therefore, development of an approach that derives the full strain field response based on a limited set of measured data is required.\u0000 In this study, the traditional model reduction method is used to expand the full strain field response of the structure by using a set of discrete measured data. Two computational models are developed and used to verify the expansion approach. The solution of the numerical model is chosen as the reference solution. In addition, the numerical model also provides the mode shapes of the structure. In the expansion approach, this information is used to develop the algorithm. First, a cantilever beam model is created. The influences of the sensor location, number of sensors and the number of modes included are analyzed using this cantilever beam model. The expanded full field response data is compared with the reference solution to evaluate the expansion procedure. The rotor 67 blade model is then used to test the expansion method. The results show that the expanded full field data is in good agreement with the calculated data. The expansion algorithm can be used for the full field strain by using the limited sets of strain data.","PeriodicalId":347795,"journal":{"name":"Volume 7C: Structures and Dynamics","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124435099","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1

A Mistuned Forced Response Analysis of an Embedded Compressor Blisk Using a Reduced Order Model 基于降阶模型的嵌入式压缩机叶片失谐强迫响应分析

Volume 7C: Structures and Dynamics Pub Date : 2018-06-11 DOI: 10.1115/gt2018-76455

M. Gutierrez, P. Petrie-Repar, R. Kielb, N. Key

{"title":"A Mistuned Forced Response Analysis of an Embedded Compressor Blisk Using a Reduced Order Model","authors":"M. Gutierrez, P. Petrie-Repar, R. Kielb, N. Key","doi":"10.1115/gt2018-76455","DOIUrl":"https://doi.org/10.1115/gt2018-76455","url":null,"abstract":"Accuracy when assessing mistuned forced response analyses is still a mayor concern. Since a full coupled analysis is still very computational expensive, several simplifications and reduced order models are carried out. The use of a reduction method, the assumptions and simplifications, generate different uncertainties that challenge the accuracy in the results. Experimental data are needed for validation and also to understand the propagation of these uncertainties. This paper shows a detailed mistuned forced response analysis of a compressor blisk. The blisk belongs to the Purdue Three-Stage (P3S) Compressor Research Facility. Two different stator-rotor-stator configurations of 38 and 44 upstream stator vanes are taken into consideration. Several loading conditions are analyzed at three different speed lines. A reduced order model known as subset nominal mode (SNM), has been used for all the analyses. This reduction takes as a basis a set of modes within a selected frequency spectrum. A detailed comparison between the predicted and measured results have been performed, showing a good agreement for the high loading conditions.","PeriodicalId":347795,"journal":{"name":"Volume 7C: Structures and Dynamics","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133859828","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Rig and Engine Validation of the Non-Linear Forced Response Analysis Performed by the Tool OrAgL OrAgL工具非线性强迫响应分析的钻机和发动机验证

Volume 7C: Structures and Dynamics Pub Date : 2018-06-11 DOI: 10.1115/gt2018-75186

A. Hartung, H. Hackenberg, M. Krack, J. Gross, Torsten Heinze, Lars Panning‐von Scheidt

{"title":"Rig and Engine Validation of the Non-Linear Forced Response Analysis Performed by the Tool OrAgL","authors":"A. Hartung, H. Hackenberg, M. Krack, J. Gross, Torsten Heinze, Lars Panning‐von Scheidt","doi":"10.1115/gt2018-75186","DOIUrl":"https://doi.org/10.1115/gt2018-75186","url":null,"abstract":"Since the first non-linear forced response validation of frictionally coupled bladed disks, more than 20 years have passed, and numerous incremental modeling and simulation refinements were proposed. With the present work, we intend to assess how much we have improved since then. To this end, we present findings of an exhaustive validation campaign designed to systematically validate the non-linear vibration prediction for the different friction joints at blade roots, interlocked shrouds and under-platform dampers.\u0000 An original approach for the identification of crucial contact properties is developed. By using the Dynamic Lagrangian contact formulation and a refined spatial contact discretization, it is demonstrated that the delicate identification of contact stiffness properties can be circumvented. The friction coefficient is measured in a separate test, and determined as unique function of temperature, preload, wear state.\u0000 Rotating rig and engine measurements are compared against simulations with the tool OrAgL, developed jointly by the Leibniz Universität Hannover and the University of Stuttgart, in which state of the art Component Mode Synthesis and Harmonic Balance methods are implemented.","PeriodicalId":347795,"journal":{"name":"Volume 7C: Structures and Dynamics","volume":"9 4","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131450911","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 2

Aeroelastic Analysis of Last Stage LP Steam Turbine Rotor Blades With Exhaust Hood for Various Non-Nominal Regimes 非标称工况下带排气罩的低压汽轮机末级转子叶片气动弹性分析

Volume 7C: Structures and Dynamics Pub Date : 2018-06-11 DOI: 10.1115/GT2018-75300

R. Rzadkowski, V. Gnesin, L. Kolodyazhnaya, R. Szczepanik

{"title":"Aeroelastic Analysis of Last Stage LP Steam Turbine Rotor Blades With Exhaust Hood for Various Non-Nominal Regimes","authors":"R. Rzadkowski, V. Gnesin, L. Kolodyazhnaya, R. Szczepanik","doi":"10.1115/GT2018-75300","DOIUrl":"https://doi.org/10.1115/GT2018-75300","url":null,"abstract":"Presented here are the numerical calculations of the 3D transonic flow of an ideal gas through an LP steam turbine last stage with exhaust hood, taking into account blade oscillations. The approach is based on a solution to the coupled aerodynamic-structure problem for 3D flow through a turbine stage using the partially integrated method. The blade oscillations and loads acting on the blades are a part of the solution. An ideal gas flow through the stator and moving rotor blades with periodicity on the whole annulus is described by unsteady Euler conservation equations, integrated with the Godunov-Kolgan explicit monotonous finite-volume difference scheme and a moving hybrid H-H rotor blade grid. The structural analysis uses the modal approach and a 3D finite element model of a blade. The proposed algorithm allows for the calculation of turbine stages with an arbitrary pitch ratio of stator and rotor blades, taking into account unsteady-load induced blade oscillations. The pressure distribution behind the rotor blades was non-uniform on account of the exhaust hood. As a result of the fluid-structure interaction and exhaust hood induced nonsymmetrical pressure distribution behind the rotor blades, the first blade mode was no longer bending but bending-torsion.","PeriodicalId":347795,"journal":{"name":"Volume 7C: Structures and Dynamics","volume":"24 3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116632679","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Influence of Geometric Design Parameters Onto Vibratory Response and HCF Safety for Turbine Blades With Friction Damper 几何设计参数对带摩擦减振器涡轮叶片振动响应及HCF安全性的影响

Volume 7C: Structures and Dynamics Pub Date : 2018-06-11 DOI: 10.1115/gt2018-75363

Matthias Hüls, Lars Panning‐von Scheidt, J. Wallaschek

{"title":"Influence of Geometric Design Parameters Onto Vibratory Response and HCF Safety for Turbine Blades With Friction Damper","authors":"Matthias Hüls, Lars Panning‐von Scheidt, J. Wallaschek","doi":"10.1115/gt2018-75363","DOIUrl":"https://doi.org/10.1115/gt2018-75363","url":null,"abstract":"Among the major concerns for high aspect-ratio turbine blades are forced and self-excited (flutter) vibrations which can cause failure by high-cycle fatigue. The introduction of friction damping in turbine blades, such as by coupling of adjacent blades via under platform dampers, can lead to a significant reduction of resonance amplitudes at critical operational conditions. In this paper, the influence of basic geometric blade design parameters onto the damped system response will be investigated to link design parameters with functional parameters like damper normal load, frequently used in nonlinear dynamic analysis. The shape of a simplified large aspect-ratio turbine blade is parameterized along with the under platform damper configuration. The airfoil is explicitly included into the parameterization in order to account for changes in blade mode shapes. For evaluation of the damped system response under a typical excitation, a reduced order model for non-linear friction damping is included into an automated 3D FEA tool-chain. Based on a design of experiments approach, the design space will be sampled and a surrogate model is trained on the received dataset. Subsequently, the mean and interaction effects of the true geometric blade design parameters onto the resonance amplitude and safety against high-cycle fatigue will be outlined for a critical first bending type vibrational motion. Design parameters were mainly found to influence the resonance amplitude by their effect onto the tip-to-platform deflection ratio. The HCF safety was affected by those design parameters with large sensitivity onto static and resonant vibratory stress levels. Applying an evolutionary optimization algorithm, it is shown that the optimum blade design with respect to minimum vibratory response at a particular node can differ significantly from a blade designed toward maximum HCF safety.","PeriodicalId":347795,"journal":{"name":"Volume 7C: Structures and Dynamics","volume":"361 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126963549","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 6

Numerical Investigation on Wide-Chord Fan Blade Forced Response due to Vortex Ingestion 涡吞下宽弦扇叶片强迫响应的数值研究

Volume 7C: Structures and Dynamics Pub Date : 2018-06-11 DOI: 10.1115/GT2018-76352

Zhonglin Wang, Yong Chen, Ouyang Hua, Anjenq Wang

{"title":"Numerical Investigation on Wide-Chord Fan Blade Forced Response due to Vortex Ingestion","authors":"Zhonglin Wang, Yong Chen, Ouyang Hua, Anjenq Wang","doi":"10.1115/GT2018-76352","DOIUrl":"https://doi.org/10.1115/GT2018-76352","url":null,"abstract":"When a turbofan engine is taxing or taking-off, a vortex can form between ground surface and the intake. As the diameters of engines increase, intakes are closer to the ground and as a result the possibility of vortex ingestion is increasing. The vortex starts from the ground surface and enters the inlet at high rotating speed. It is likely to draw in hard material or dust from the ground, which leads to blade erosion or impact damage. This is harmful to the engine durability and safety. Besides the vortex, inlet flow separation could induce high level of blade vibration, or aerodynamic instability, such as rotating stall. Cross wind may also lead to both vortex and flow distortion, which is more challenging for engine stability. Therefore, vibration characteristics and forced response under vortex ingestion should be evaluated to ensure the stability and safety of the engine in design phase.\u0000 This paper presents a computational study of the forced response of a wide-chord fan blade under vortex ingestion. A finite element model was built, and modal analysis was conducted to characterize the vibrating characteristics of the fan blade with a corresponding Campbell diagram. Transient simulations of vortex passing over the fan blade were conducted with and without the blade pre-vibration at the natural frequency of the first bending mode. The forced response level was evaluated under various conditions, including different hitting time and increasing intensity of vortex. Results showed that the ingested vortex is able to amplify the displacement and vibratory response to a significant level of 18% at most. Linear relation between vortex intensity and blade response was found. The results give a comprehensive prediction of forced response for a better blade design against vortex ingestion.","PeriodicalId":347795,"journal":{"name":"Volume 7C: Structures and Dynamics","volume":"39 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115286942","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1