Journal articles: 'Turbomachinery aerodynamics'

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Jahn, Ingo, and Peter Jacobs. "Using Meridional Streamline and Passage Shapes to Generate Radial Turbomachinery Geometry and Meshes." Applied Mechanics and Materials 846 (July 2016): 1–6. http://dx.doi.org/10.4028/www.scientific.net/amm.846.1.

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An important aspect for structural and aerodynamics design of radial flow turbomachinery is the definition of the geometry and the generation of meshes for computational analysis. Particularly in the area of computational design and optimization, the way the geometry is defined is important, as it can limit design space. Traditionally, radial compressors and radial turbine rotors are defined using a mechanical design approach. Effectively a hub and shroud profile, followed by a rotorblade geometry are defined and the shape is adjusted in order to meet certain aerodynamic boundary conditions. The current paper presents an alternative approach, in which the overall geometry is defined starting from an aerodynamic requirement. The corresponding rotor and blade geometry is generated automatically, based on certain constraints. The advantage of this approach is the ability to define directly the aerodynamic requirements, which may allow a simpler efficient optimization of the aerodynamics.

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Verdon, Joseph M. "Linearized unsteady aerodynamics for turbomachinery aeroelastic applications." Journal de Physique III 2, no. 4 (April 1992): 481–506. http://dx.doi.org/10.1051/jp3:1992143.

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Joslyn, H. D., and R. P. Dring. "Axial Compressor Stator Aerodynamics." Journal of Engineering for Gas Turbines and Power 107, no. 2 (April 1, 1985): 485–92. http://dx.doi.org/10.1115/1.3239754.

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Axisymmetric, through-flow calculations, currently the “backbone” of most multistage turbomachinery design systems, are being pushed to their limit. This is due to the difference between the complex, three-dimensional flows that actually occur in turbomachinery and the two-dimensional flow assumed in this type of analysis. To foster the development of design analyses that account more accurately for these three-dimensional effects, there is a need for detailed flow field data in a multistage environment. This paper presents a survey of the initial results from a detailed experimental study of the aerodynamics of the second stage of a large scale, two-stage axial compressor. Data were acquired over a range of flow coefficients. The data presented here are for the second stator and include airfoil and endwall flow visualization, and radial-circumferential traverse measurements presented in the form of fullspan contour plots of total pressure. Also presented are the spanwise distributions of total and static pressures, axial velocity, air angles, and blockage. The effect of increased loading on the growth of the hub corner stall and its impact on these parameters is discussed.

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Sobieczky, Helmut. "Research on Inverse Design and Optimization in Germany." Applied Mechanics Reviews 41, no. 6 (June 1, 1988): 239–46. http://dx.doi.org/10.1115/1.3151895.

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This article tries to illustrate efforts to develop and apply design and optimization methods in German universities, research institutes and the aerospace industry. Applications are shown solely in turbomachinery and aircraft aerodynamics. With restriction to aerodynamic problems, it is shown that efforts to improve theoretical models to become knowledge-based computational tools overlap with operational methods based on the designer’s experience but resulting in hardware concepts for next generation aircraft components.

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Li, Zhihui, and Xinqian Zheng. "Review of design optimization methods for turbomachinery aerodynamics." Progress in Aerospace Sciences 93 (August 2017): 1–23. http://dx.doi.org/10.1016/j.paerosci.2017.05.003.

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Cumpsty, N. A., and E. M. Greitzer. "Ideas and Methods of Turbomachinery Aerodynamics: A Historical View." Journal of Propulsion and Power 20, no. 1 (January 2004): 15–26. http://dx.doi.org/10.2514/1.9176.

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Zhao-Chun, Wu, and Feng Jin-Mei. "A Note on the Pseudo Functions for Turbomachinery Aerodynamics." Energy Procedia 16 (2012): 615–18. http://dx.doi.org/10.1016/j.egypro.2012.01.099.

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Michaud, Mathias, Petro Jr Milan, and Huu Duc Vo. "Low-Cost Rotating Experimentation in Compressor Aerodynamics Using Rapid Prototyping." International Journal of Rotating Machinery 2016 (2016): 1–10. http://dx.doi.org/10.1155/2016/8518904.

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With the rapid evolution of additive manufacturing, 3D printed parts are no longer limited to display purposes but can also be used in structural applications. The objective of this paper is to show that 3D prototyping can be used to produce low-cost rotating turbomachinery rigs capable of carrying out detailed flow measurements that can be used, among other things, for computational fluid dynamics (CFD) code validation. A fully instrumented polymer two-stage axial-mixed flow compressor test rig was designed and fabricated with stereolithography (SLA) technology by a team of undergraduate students as part of a senior-year design course. Experiments were subsequently performed on this rig to obtain both the overall pressure rise characteristics of the compressor and the stagnation pressure distributions downstream of the blade rows for comparison with CFD simulations. In doing so, this work provides a first-of-a-kind assessment of the use of polymer additive technology for low-cost rotating turbomachinery experimentation with detailed measurements.

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Dowell, Earl H., Kenneth C. Hall, and Michael C. Romanowski. "Eigenmode Analysis in Unsteady Aerodynamics: Reduced Order Models." Applied Mechanics Reviews 50, no. 6 (June 1, 1997): 371–86. http://dx.doi.org/10.1115/1.3101718.

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In this article, we review the status of reduced order modeling of unsteady aerodynamic systems. Reduced order modeling is a conceptually novel and computationally efficient technique for computing unsteady flow about isolated airfoils, wings, and turbomachinery cascades. Starting with either a time domain or frequency domain computational fluid dynamics (CFD) analysis of unsteady aerodynamic or aeroacoustic flows, a large, sparse eigenvalue problem is solved using the Lanczos algorithm. Then, using just a few of the resulting eigenmodes, a Reduced Order Model of the unsteady flow is constructed. With this model, one can rapidly and accurately predict the unsteady aerodynamic response of the system over a wide range of reduced frequencies. Moreover, the eigenmode information provides important insights into the physics of unsteady flows. Finally, the method is particularly well suited for use in the active control of aeroelastic and aeroacoustic phenomena as well as in standard aeroelastic analysis for flutter or gust response. Numerical results presented include: 1) comparison of the reduced order model to classical unsteady incompressible aerodynamic theory, 2) reduced order calculations of compressible unsteady aerodynamics based on the full potential equation, 3) reduced order calculations of unsteady flow about an isolated airfoil based on the Euler equations, and 4) reduced order calculations of unsteady viscous flows associated with cascade stall flutter, 5) flutter analysis using the Reduced Order Model. This review article includes 25 references.

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FURUKAWA, Hirotaka, Takuya MORI, Jyunichi MIWA, Kei SAKAGUCHI, Naoki MATUDUKA, and Toshiyuki TORIYAMA. "PS09 Design consideration for rotor structure and aerodynamics of micro turbomachinery." Proceedings of the Materials and Mechanics Conference 2008 (2008): _PS09–1_—_PS09–2_. http://dx.doi.org/10.1299/jsmemm.2008._ps09-1_.

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Pereira, Luiz Antonio Alcântara, Miguel Hiroo Hirata, and Nelson Manzanares Filho. "Wake and aerodynamics loads in multiple bodies—application to turbomachinery blade rows." Journal of Wind Engineering and Industrial Aerodynamics 92, no. 6 (May 2004): 477–91. http://dx.doi.org/10.1016/j.jweia.2004.02.001.

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Kądrowski, Damian, Michał Kulak, Michał Lipian, Małgorzata Stępień, Piotr Baszczyński, Karol Zawadzki, and Maciej Karczewski. "Challenging low Reynolds - SWT blade aerodynamics." MATEC Web of Conferences 234 (2018): 01004. http://dx.doi.org/10.1051/matecconf/201823401004.

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One of the main issues related to the design and development of small wind turbines (SWTs) is the low Reynolds number. Operation in the transitory regime makes the rotor aerodynamic analysis a challenging task. Project GUST (Generative Urban Small Turbine) realized currently at the Institute of Turbomachinery (Lodz University of Technology, Poland) is devoted to the development of SWT (D = 1.6 m) for low-Reynolds number (low wind speed) flow conditions. The emphasis is on the blade design, aiming at improving the rotor aerodynamic efficiency. The paper will highlight the rotor design process, based on contemporary methods of experiment-simulation integration approach and use of rapid manufacturing techniques. In-house wind tunnel measurements of a scaled model performance were executed. A numerical analysis using dedicated software (QBlade) was conducted in parallel. A comparison between the obtained results indicated that the chosen numerical tools are capable of providing a reliable output, even in complex, transitional flow conditions. Bearing in mind the above observations, QBlade was incorporated into the development process of a completely new blade geometry which would increase rotor performance. The selected design has indeed prove to show better power outcome in an additional experimental campaign.

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Tran, D. M., C. Liauzun, and C. Labaste. "Methods of fluid–structure coupling in frequency and time domains using linearized aerodynamics for turbomachinery." Journal of Fluids and Structures 17, no. 8 (July 2003): 1161–80. http://dx.doi.org/10.1016/s0889-9746(03)00068-9.

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Gregory, J. W., K. Asai, M. Kameda, T. Liu, and J. P. Sullivan. "A review of pressure-sensitive paint for high-speed and unsteady aerodynamics." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 222, no. 2 (February 1, 2008): 249–90. http://dx.doi.org/10.1243/09544100jaero243.

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The current paper describes the development of pressure-sensitive paint (PSP) technology as an advanced measurement technique for unsteady flow fields and short-duration wind tunnels. Newly developed paint formulations have step response times approaching 1 μs, making them suitable for a wide range of unsteady testing. Developments in binder technology are discussed, which have resulted in new binder formulations such as anodized aluminium, thin-layer chromatography plate, polymer/ceramic, and poly(TMSP) PSP. The current paper also details modeling work done to describe the gas diffusion properties within the paint binder and understand the limitations of the paint response characteristics. Various dynamic calibration techniques for PSP are discussed, along with summaries of typical response times. A review of unsteady and high-speed PSP applications is presented, including experiments with shock tubes, hypersonic tunnels, unsteady delta wing aerodynamics, fluidic oscillator flows, Hartmann tube oscillations, acoustics, and turbomachinery. Flowfields with fundamental frequencies as high as 21 kHz have been successfully measured with porous PSP formulations.

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Clark, William S., and Kenneth C. Hall. "A Time-Linearized Navier–Stokes Analysis of Stall Flutter." Journal of Turbomachinery 122, no. 3 (February 1, 1999): 467–76. http://dx.doi.org/10.1115/1.1303073.

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A computational method for predicting unsteady viscous flow through two-dimensional cascades accurately and efficiently is presented. The method is intended to predict the onset of the aeroelastic phenomenon of stall flutter. In stall flutter, viscous effects significantly impact the aeroelastic stability of a cascade. In the present effort, the unsteady flow is modeled using a time-linearized Navier–Stokes analysis. Thus, the unsteady flow field is decomposed into a nonlinear spatially varying mean flow plus a small-perturbation harmonically varying unsteady flow. The resulting equations that govern the perturbation flow are linear, variable coefficient partial differential equations. These equations are discretized on a deforming, multiblock, computational mesh and solved using a finite-volume Lax–Wendroff integration scheme. Numerical modeling issues relevant to the development of the unsteady aerodynamic analysis, including turbulence modeling, are discussed. Results from the present method are compared to experimental stall flutter data, and to a nonlinear time-domain Navier–Stokes analysis. The results presented demonstrate the ability of the present time-linearized analysis to model accurately the unsteady aerodynamics associated with turbomachinery stall flutter. [S0889-504X(00)00203-8]

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Lipian, Michal, Michal Kulak, and Malgorzata Stepien. "Fast Track Integration of Computational Methods with Experiments in Small Wind Turbine Development." Energies 12, no. 9 (April 29, 2019): 1625. http://dx.doi.org/10.3390/en12091625.

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In general, standard aerodynamic design is divided into two paths—numerical analysis and empirical tests. It is crucial to efficiently combine both approaches in order to entirely fulfill the requirements of the design process as well as the final product. An effective use of computational analysis is a challenge, however it can significantly improve understanding, exploring and confining the search for optimal product solutions. The article focuses on a rapid prototyping and testing procedure proposed and employed at the Institute of Turbomachinery, Lodz University of Technology (IMP TUL). This so called Fast Track approach combines preparation of numerical models of a wind turbine rotor, manufacturing of its geometry by means of a 3D printing method and testing it in an in-house wind tunnel. The idea is to perform the entire procedure in 24 h. The proposed process allows one to determine the most auspicious sets of rotor blades within a short time. Owing to this, it significantly reduces the amount of individual subsequent examinations. Having fixed the initial procedure, it is possible to expand research on the singled-out geometries. The abovementioned observations and the presented overview of the literature on uses of 3D printing in aerodynamic testing prove rapid prototyping as an innovative and widely-applicable method, significantly changing our approach to experimental aerodynamics.

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Manwaring, S. R., and D. C. Wisler. "Unsteady Aerodynamics and Gust Response in Compressors and Turbines." Journal of Turbomachinery 115, no. 4 (October 1, 1993): 724–40. http://dx.doi.org/10.1115/1.2929308.

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A comprehensive series of experiments and analyses was performed on compressor and turbine blading to evaluate the ability of current, practical, engineering/analysis models to predict unsteady aerodynamic loading of modern gas turbine blading. This is part of an ongoing effort to improve methods for preventing blading failure. The experiments were conducted in low-speed research facilities capable of simulating the relevant aerodynamic features of turbomachinery. Unsteady loading on compressor and turbine blading was generated by upstream wakes and, additionally for compressors, by a rotating inlet distortion. Fast-response hot-wire anemometry and pressure transducers embedded in the airfoil surfaces were used to determine the aerodynamic gusts and resulting unsteady pressure responses acting on the airfoils. This is the first time that gust response measurements for turbines have been reported in the literature. Several different analyses were used to predict the unsteady component of the blade loading: (1) a classical flat-plate analysis, (2) a two-dimensional linearized flow analysis with a ‘frozen gust’ model, (3) a two-dimensional linearized flow analysis with a “distorted gust” model, (4) a two-dimensional linearized Euler analysis, and (5) a two-dimensional nonlinear Euler analysis. Also for the first time, a detailed comparison of these analyses methods is made and the importance of properly accounting for both vortical and potential disturbances is demonstrated. The predictions are compared with experiment and their abilities assessed to help guide designers in using these prediction schemes.

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Blinov, Vitalii L., Oleg V. Komarov, and Egor A. Zaslavskiy. "Estimation of the driven gas turbine unit technical performance using the standard measuring systems." E3S Web of Conferences 178 (2020): 01044. http://dx.doi.org/10.1051/e3sconf/202017801044.

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In large pipeline gas transport systems the operation and maintenance of gas pumping units are carried according to the current number of equivalent working hours of centrifugal gas compressors and gas turbines. Modern terms of lean production require the maintenance procedure to be done according to the current technical performance of equipment. The paper presents a designed and verified methodology of technical performance estimation of gas turbine units using the standard measuring systems. This method includes a verified high-order mathematical model based on the gas dynamic function for the precise analytical description of turbomachinery aerodynamics. The models are defined for different types of multi-shaft gas turbines. In this article the results of technical performance estimation of different gas turbine units are discussed.

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LIU, Qian, Hanru LIU, Jiahui LI, Xun SHANG, Nanshu CHEN, and Yangang WANG. "Research on aerodynamics and aeroacoustics of propeller based on panel-vortex particle method." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 40, no. 4 (August 2022): 778–86. http://dx.doi.org/10.1051/jnwpu/20224040778.

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The highly-efficient and unsteady aerodynamic simulation of turbomachinery is urgently required. The panel-vortex particle method is coupled with a far free field sound model established with the Lowson method and aims to fast predict aerodynamic and acoustic properties. The aerodynamic results show that, compared with the aerodynamic results acquired with the finite volume method, the use of the panel-vortex particle method may obtain appropriate pressure distribution and velocity distribution in the downstream region of a propeller and that the overall thrust prediction is accurate enough. The vortex distribution features show that the panel-vortex particle method has less numerical diffusion. Therefore, the velocity gradient is more accurate near the wake vortex. Compared with the sound pressure level acquired with the finite volume method, the sound pressure level simulated with the panel-vortex particle method has the same directivity pattern. The relative error of sound pressure in the 60° forward direction is 5% under 1BPF(blade passing frequency), which satisfies acoustic analysis requirements. As for time consumption, the use of the panel-vortex particle method consumes 10% of time when the finite volume method is used, proving that the panel-vortex particle method coupled with the Lowson method can satisfy the design and application needs of unsteady aerodynamic and aeroacoustic noise of a distributed electric propulsion system.

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Benichou, Emmanuel, Guillaume Dufour, Yannick Bousquet, Nicolas Binder, Aurélie Ortolan, and Xavier Carbonneau. "Body Force Modeling of the Aerodynamics of a Low-Speed Fan under Distorted Inflow †." International Journal of Turbomachinery, Propulsion and Power 4, no. 3 (August 21, 2019): 29. http://dx.doi.org/10.3390/ijtpp4030029.

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New propulsive concepts, such as boundary layer ingestion, involve stronger interactions between the engine and its environment, and are thus more complex flows compared to classical architectures. Usual turbomachinery design tools are inadequate, and new numerical methodologies are needed to accurately predict the engine performance with affordable CPU resources. The present paper examines the relevance of a reduced-order modeling approach—the body force modeling (BFM) method—for a low-speed cooling fan with inflow distortion. The formulation itself accounts for the blade metal blockage and compressibility effects, and it relies on a semiempirical loss model, independent of computational fluid dynamics (CFD) calibration. The BFM results obtained in the present work are assessed against full-annulus unsteady Reynolds-averaged Navier-Stokes (URANS) results and experiments. The comparison shows that the BFM approach successfully quantifies the fan stage performance. Furthermore, the distortion transfer across the stage is examined and the flow patterns observed are found to be the same as in the URANS results and in the measurements. Hence, this methodology, coming at a low CPU cost, is well-adapted to the early design phase of an innovative propulsion system.

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Javed, Yaser, Mohtashim Mansoor, and Irtiza Ali Shah. "A review of principles of MEMS pressure sensing with its aerospace applications." Sensor Review 39, no. 5 (September 16, 2019): 652–64. http://dx.doi.org/10.1108/sr-06-2018-0135.

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Purpose Pressure, being one of the key variables investigated in scientific and engineering research, requires critical and accurate measurement techniques. With the advancements in materials and machining technologies, there is a large leap in the measurement techniques including the development of micro electromechanical systems (MEMS) sensors. These sensors are one to two orders smaller in magnitude than traditional sensors and combine electrical and mechanical components that are fabricated using integrated circuit batch-processing technologies. MEMS are finding enormous applications in many industrial fields ranging from medical to automotive, communication to electronics, chemical to aviation and many more with a potential market of billions of dollars. MEMS pressure sensors are now widely used devices owing to their intrinsic properties of small size, light weight, low cost, ease of batch fabrication and integration with an electronic circuit. This paper aims to identify and analyze the common pressure sensing techniques and discuss their uses and advantages. As per our understanding, usage of MEMS pressure sensors in the aerospace industry is quite limited due to cost constraints and indirect measurement approaches owing to the inability to locate sensors in harsh environments. The purpose of this study is to summarize the published literature for application of MEMS pressure sensors in the said field. Five broad application areas have been investigated including: propulsion/turbomachinery applications, turbulent flow diagnosis, experimentalaerodynamics, micro-flow control and unmanned aerial vehicle (UAV)/micro aerial vehicle (MAV) applications. Design/methodology/approach The first part of the paper deals with an introduction to MEMS pressure sensors and mathematical relations for its fabrication. The second part covers pressure sensing principles followed by the application of MEMS pressure sensors in five major fields of aerospace industry. Findings In this paper, various pressure sensing principles in MEMS and applications of MEMS technology in the aerospace industry have been reviewed. Five application fields have been investigated including: Propulsion/Turbomachinery applications, turbulent flow diagnosis, experimental aerodynamics, micro-flow control and UAV/MAV applications. Applications of MEMS sensors in the aerospace industry are quite limited due to requirements of very high accuracy, high reliability and harsh environment survivability. However, the potential for growth of this technology is foreseen due to inherent features of MEMS sensors’ being light weight, low cost, ease of batch fabrication and capability of integration with electric circuits. All these advantages are very relevant to the aerospace industry. This work is an endeavor to present a comprehensive review of such MEMS pressure sensors, which are used in the aerospace industry and have been reported in recent literature. Originality/value As per the author’s understanding, usage of MEMS pressure sensors in the aerospace industry is quite limited due to cost constraints and indirect measurement approaches owing to the inability to locate sensors in harsh environments. Present work is a prime effort in summarizing the published literature for application of MEMS pressure sensors in the said field. Five broad application areas have been investigated including: propulsion/turbomachinery applications, turbulent flow diagnosis, experimental aerodynamics, micro-flow control and UAV/MAV applications.

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Bühler, Johannes, Sebastian Leichtfuß, Heinz-Peter Schiffer, Thomas Lischer, and Simon Raabe. "Surge Limit Prediction for Automotive Air-Charged Systems." International Journal of Turbomachinery, Propulsion and Power 4, no. 4 (October 1, 2019): 34. http://dx.doi.org/10.3390/ijtpp4040034.

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Compressor surge has been investigated and predicted since the early days of turbomachinery research. Experimental testing of turbomachinery applications is still needed to determine whether stable compressor operation is possible in the expected application regime. Measuring compressor maps and operating ranges on hot gas test stands is common. The test benches are designed and optimized to ensure ideal inflow and outflow conditions as well as low measurement uncertainty. Compressor maps are used to match turbocharger and application. However, a shift in surge limit, caused by the piping system or application, can only be adequately addressed with full engine tests. Ideal measurements use the corresponding piston engine in the charged-air system. This can only take place in the development process, when surge detection is unfavorable from an economic perspective. The surge model for turbochargers presented here is an extension of the Greitzer’s surge model, which considers the effect of inlet throttling. Application components, such as air filters, pipe elbows and flow straighteners, reduce pressure in front of the compressor and flow conditions might differ from those in laboratory testing. Experimental results gathered from the hot gas test stand at TU Darmstadt indicate strong variation in surge limit, influenced by inlet throttling. An extension to the surge model is developed to explain the observed phenomena. The model was validated using extensive experimental variations and matches the experienced surge limit shift. Additional measurements with a piston engine downstream of the turbocharger demonstrated the validity of the surge model. The results also show that surge is a system-dependent phenomenon, influenced by compressor aerodynamics and boundary conditions.

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Chiang, 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.

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A frequent cause of turbomachinery blade failure is excessive resonant response. The most common excitation source is the nonuniform flow field generated by inlet distortion, wakes and/or pressure disturbances from adjacent blade rows. The standard method for dealing with this problem is to avoid resonant conditions using a Campbell diagram. Unfortunately, it is impossible to avoid all resonant conditions. Therefore, judgments based on past experience are used to determine the acceptability of the blade design. A new analysis system has been developed to predict blade forced response. The system provides a design tool, over and above the standard Campbell diagram approach, for predicting potential forced response problems. The incoming excitation sources are modeled using a semi-empirical rotor wake/vortex model for wake excitation, measured data for inlet distortion, and a quasi-three-dimensional Euler code for pressure disturbances. Using these aerodynamic stimuli, and the blade’s natural frequencies and mode shapes from a finite element model, the unsteady aerodynamic modal forces and the aerodynamic damping are calculated. A modal response solution is then performed. This system has been applied to current engine designs. A recent investigation involved fan blade response due to inlet distortion. An aero mechanical test had been run with two different distortion screens. The resulting distortion entering the fan was measured. With this as input data, the predicted response agreed almost exactly with the measured response. In another application, the response of the LPT blades of a counterrotating supersonic turbine was determined. In this case the blades were excited by both a wake and a shock wave. The shock response was predicted to be three times larger than that of the wake. Thus, the system identified a new forcing function mechanism for supersonic turbines. This paper provides a basic description of the system, which includes: (1) models for the wake excitation, inlet distortion, and pressure disturbance; (2) a kernel function solution technique for unsteady aerodynamics; and (3) a modal aeroelastic solution using strip theory. Also, results of the two applications are presented.

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Moore, J. J., and A. B. Palazzolo. "Rotordynamic Force Prediction of Whirling Centrifugal Impeller Shroud Passages Using Computational Fluid Dynamic Techniques." Journal of Engineering for Gas Turbines and Power 123, no. 4 (March 1, 1999): 910–18. http://dx.doi.org/10.1115/1.1385829.

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The demand for higher efficiencies and performance of modern centrifugal turbomachinery requires improved knowledge of critical design factors in strength of materials, aerodynamics, and rotordynamics. While tremendous strides in finite element stress analysis and computational fluid dynamics (CFD) have addressed the first two areas, the lack of accurate prediction tools for centrifugal impellers typically leaves rotordynamics out of the design loop. While several authors have analyzed the rotordynamic forces arising from shrouded centrifugal impellers, there has been no study to couple the secondary shroud passage with the three-dimensional primary flow model. The strong interaction between these domains makes this approach advantageous. The current study utilizes CFD techniques to analyze the full three-dimensional viscous, primary/secondary flow field in a centrifugal pump impeller to determine rotordynamic forces. Multiple quasi-steady solutions of an eccentric three-dimensional model at different precessional frequency ratios yield the rotordynamic impedance forces. Performing a second-order least-squares analysis generates the skew-symmetric stiffness, damping, and mass matrices. The results show good correlation with experiment for both performance and rotordynamic forces.

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Makarov, Vladimir, Gennadii Boiarskikh, Nikolai Makarov, German Dyldin, and Aleksandr Ugolnikov. "Turbomachine criteria for similarity of natural size proportionality." Izvestiya vysshikh uchebnykh zavedenii Gornyi zhurnal 1, no. 8 (December 21, 2020): 81–89. http://dx.doi.org/10.21440/0536-1028-2020-8-81-89.

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Introduction. It is possible to give rise to synergy as a result of science-intensive industries combination with innovative eco-technologies for subsoil use only by developing a brand new approach to nature-like auxiliary technologies. Insufficient adaptability of turbomachines that ensure industrial safety increases the production cost of the mining and oil and gas complexes of the Russian Federation by more than 15%, reducing its competitiveness. Research methodology. Based on the hypothesis of the hydrodynamic analogy of the mechanisms of deceleration of the flow around the airfoil and the formation of its profile resistance, Karman's theory of attached and free vortices, the Zhukovsky-Chaplygin-Kutta hypothesis, the method of conformal transformations, the theory of similarity, the method of singular points by Chaplygin S. A., the criteria for the similarity of natural proportionality are obtained, that is, for the hydrodynamic similarity of the mechanism of energy interaction between the blades of the turbomachine impeller and the wing of a bird. Results. It has been proved that the dominant control over the nature-like proportionality of the aerodynamics of turbomachines is the ratio between the speed and flow acceleration circulation around the airfoil. It has been established that the coefficients of the airfoil resistance, lift and aerodynamic quality of the airfoil cascade are hydrodynamic analogs of the coefficients of the circulation of the velocity and acceleration of the flow and their ratio. Conclusions. It has been experimentally confirmed that the use of the proposed criterion of natural proportionality in the design of turbomachines increases their coefficient of aerodynamic adaptability by more than 2 times, increasing the area of economical operation by 83%.

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Greitzer, E. M., and D. E. Newland. "Sir William Rede Hawthorne. 22 May 1913—16 September 2011." Biographical Memoirs of Fellows of the Royal Society 66 (December 19, 2018): 309–28. http://dx.doi.org/10.1098/rsbm.2017.0036.

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William Rede Hawthorne was a pioneer in gas turbine aerodynamics and thermodynamics, a sought-after technology advisor to industry and government, and a generous and enthusiastic teacher who encouraged students to excel. His outstanding contributions included resolution of combustion problems that limited the operation of the original Whittle jet engine, early in-depth descriptions of compressible channel flow that still inform engineers today, innovative and wide-ranging analyses of secondary flows in turbomachinery that defined the field, and creation of some of the first notes on gas turbine cycle analysis. A theme in the many areas of engineering in which he had impact was the satisfaction from the growth of understanding that can accompany making things work—in his words, ‘machines produce ideas just as surely as ideas produce machines’. A Cambridge graduate, he was a professor at MIT when, in 1951, he was recruited to a newly established chair at Cambridge, where he later had leadership roles as head of the engineering department (1968–73) and Master of Churchill College (1968–83). He retained strong ties to MIT, however, and fostered lasting collaborations between the two universities. Among his numerous awards and honours were the US Medal of Freedom (1947), a Royal Society Medal (1982) and a knighthood (1970) for ‘services to thermodynamics’, a citation that pleased him greatly.

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Zaidi, Sohail H., and Robin L. Elder. "Flow Studies using Laser Anemometry Technique in a Small Power Unit Radial Inflow Turbine." International Journal of Rotating Machinery 3, no. 2 (1997): 107–15. http://dx.doi.org/10.1155/s1023621x97000110.

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T-100 is a multipurpose small power unit developed by Sundstrand Power Systems (USA). An extensive research programme was launched for the detailed tests of the rig components including inlet protection system, Compressor stage, Combustor and the Turbine stage. Turbomachinery Group at Cranfield was involved in the study of the Turbine unit used in this programme. From the design point of view, detailed aerodynamics in these small units are of great interest especially where high velocities and narrow passages are involved. Experimental study was carried out to investigate the flow in the region between the nozzle guide vanes and the turbine rotor entry. The main concern was to find out how the nozzle guide vane flow was modified by the rotor and how the rotor flow was affected by the nozzle guide vanes. Laser measurements were taken at these positions for various flow conditions. An other area which needs considerable attention is downstream of the turbine rotor where the turning of flow and mixing process make the situation very complicated. Laser studies were undertaken in that region and to gain more confidence on laser results, a Cobra pressure probe was traversed at these stations. This paper describes various steps undertaken to obtain laser results within the machine. At the end typical laser results have been presented and discussed.

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Gundy-Burlet, K. L., M. M. Rai, R. C. Stauter, and R. P. Dring. "Temporally and Spatially Resolved Flow in a Two-Stage Axial Compressor: Part 2—Computational Assessment." Journal of Turbomachinery 113, no. 2 (April 1, 1991): 227–32. http://dx.doi.org/10.1115/1.2929090.

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Fluid dynamics of turbomachines are complicated because of aerodynamic interactions between rotors and stators. It is necessary to understand the aerodynamics associated with these interactions in order to design turbomachines that are both light and compact as well as reliable and efficient. The current study uses an unsteady, thin-layer Navier–Stokes zonal approach to investigate the unsteady aerodynamics of a multistage compressor. Relative motion between rotors and stators is made possible by the use of systems of patched and overlaid grids. Results have been computed for a 2 1/2-stage compressor configuration. The numerical data compare well with experimental data for surface pressures and wakes. In addition, the effect of grid refinement on the solution is studied.

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Adamczyk, John J. "Aerodynamic Analysis of Multistage Turbomachinery Flows in Support of Aerodynamic Design." Journal of Turbomachinery 122, no. 2 (February 1, 1999): 189–217. http://dx.doi.org/10.1115/1.555439.

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This paper summarizes the state of 3D CFD based models of the time-averaged flow field within axial flow multistage turbomachines. Emphasis is placed on models that are compatible with the industrial design environment and those models that offer the potential of providing credible results at both design and off-design operating conditions. The need to develop models free of aerodynamic input from semiempirical design systems is stressed. The accuracy of such models is shown to be dependent upon their ability to account for the unsteady flow environment in multistage turbomachinery. The relevant flow physics associated with some of the unsteady flow processes present in axial flow multistage machinery are presented along with procedures that can be used to account for them in 3D CFD simulations. Sample results are presented for both axial flow compressors and axial flow turbines that help to illustrate the enhanced predictive capabilities afforded by including these procedures in 3D CFD simulations. Finally, suggestions are given for future work on the development of time-averaged flow models. [S0889-504X(00)02002-X]

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Makarov, Vladimir, Nikolai Makarov, Alexandr Lifanov, Artem Materov, and Nikolay Kosarev. "Aerodynamic adaptivity criterion in the production methodology of the energy-efficient mine turbomachines." E3S Web of Conferences 177 (2020): 03004. http://dx.doi.org/10.1051/e3sconf/202017703004.

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Competitive growth of enterprises in the mining and oil and gas industries of the Russian economy, combined with industrial safety requirements, updates the task of developing the design and production methodology for the aerodynamically adaptive turbomachines with a nature-like dominance. Such machines adequately and economically soundly establish the necessary parameters of the air environment in the technological space that implement the concept of optimal subsurface management ecotechnology. This article proposes a production methodology for the energy-efficient turbomachines using the aerodynamic adaptability criterion that determines the relations between the velocity circulation and flow acceleration around the vane cascade profiles as the nature-like dominance of the process for converting the mechanical rotational energy of impeller into the internal energy of the air flow. The Karman theory of bound and free vortices, the Chaplygin-Joukowski-Kutta hypothesis, the conformal mapping method, and curve irregularities are used for development of a mathematical model for controlling the aerodynamic adaptability. It is proved that the control dominant is the intensity of the sources distributed over the turbomachine impeller vane profile that determine the flow diffusivity and as a result the acceleration circulation around the profile. It has been experimentally confirmed that the use of profiles obtained using the proposed technique increases the aerodynamic adaptability coefficient of the turbomachine by 51%, while increasing the area of its cost-effective performance by at least 2 times.

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Stauter, R. C., R. P. Dring, and F. O. Carta. "Temporally and Spatially Resolved Flow in a Two-Stage Axial Compressor: Part 1—Experiment." Journal of Turbomachinery 113, no. 2 (April 1, 1991): 219–25. http://dx.doi.org/10.1115/1.2929087.

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The fluid dynamics of turbomachines are extremely complex, due in part to the aerodynamic interactions between rotors and stators. It is necessary to acquire fluid dynamic data that reflect the interactive nature of a turbomachine to correlate with the fluid dynamics predicted from modern analyses. The temporal and spatial variations in the midspan aerodynamics of the second stage of a two-stage compressor have been studied with a two-component LDV system. Spatial variations were examined by traversing the LDV probe volume through a dense matrix of both axial and circumferential positions, while temporal resolution was achieved by acquiring all data as a function of the instantaneous rotor position. Hence, the data set reveals rotor and stator wake structure and decay in both the stationary and rotating frames of reference. The data also compared very favorably with extensive pneumatic measurements previously acquired in this compressor. In Part 2 of the paper, the data are used in the assessment of a prediction of the flow in the compressor using a time-accurate, thin-layer, two-dimensional Navier–Stokes analysis.

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Fujita, Hajime. "Aerodynamic Noise in Turbomachinery." Transactions of the Japan Society of Mechanical Engineers Series B 61, no. 591 (1995): 3804–10. http://dx.doi.org/10.1299/kikaib.61.3804.

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Kupferschmied, Peter, Pascal Ko¨ppel, Christian Roduner, and Georg Gyarmathy. "On the Development and Application of the Fast-Response Aerodynamic Probe System in Turbomachines—Part 1: The Measurement System." Journal of Turbomachinery 122, no. 3 (February 1, 1999): 505–16. http://dx.doi.org/10.1115/1.1303702.

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This contribution gives an overview of the current state, performance, and limitations of the fast-response aerodynamic probe measurement system developed at the Turbomachinery Lab of the ETH Zurich. In particular, the following topics are addressed: • Probe technology: Miniature probes with tip diameter ranging from 0.84 to 1.80 mm (one-sensor and three-sensor probes, respectively) have been developed. New technologies derived from microelectronics and micromechanics have been used to achieve an adequate packaging of the microsensor chips used. Both the sensor packaging and the sensor calibration (time-independent and time-dependent) are crucial issues for the DC accuracy of any measurement. • Aerodynamic probe calibration: The methods used for the sensor calibration and the aerodynamic probe calibration, the pertinent automated test facilities, and the processing of the output data are briefly presented. Since these miniature probes are also capable of measuring the mean flow temperature, aspects related to the effective recovery factor and the self-heating of the probe tip are treated and some recommendations related to sensor selection are given. • Measurement system and data evaluation: The early measurement chain described in Gossweiler et al. (1995) has evolved into the fast-response aerodynamic probe system. This automatic system incorporates dedicated measurement concepts for a higher accuracy and a more efficient operation in terms of time and failures. An overview of the data evaluation process is given. The fast-response aerodynamic probe system has been tested in real-sized turbomachines under industrial conditions within the temperature limits of 140°C imposed by the sensor technology (axial-flow turbofan compressor, axial-flow turbine, centrifugal compressor). These applications confirmed the potential of the system and encouraged its further development. Now, the system is routinely used in the facilities of the Turbomachinery Lab and in occasional measurement campaigns in other laboratories. Part 2 of this contribution (Roduner et al.) will focus on the application of the fast-response aerodynamic probe system in a transonic centrifugal compressor of the ETH Turbomachinery Laboratory, while Part 3 (Ko¨ppel et al.) treats more sophisticated data analysis methods. [S0889-504X(00)01003-5]

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SUGIMURA, Kazuyuki. "Aerodynamic Shape Optimization of Turbomachinery." Journal of the Society of Mechanical Engineers 109, no. 1050 (2006): 403–4. http://dx.doi.org/10.1299/jsmemag.109.1050_403.

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Schobeiri, Meinhard T., Burak Öztürk, and David E. Ashpis. "On the Physics of Flow Separation Along a Low Pressure Turbine Blade Under Unsteady Flow Conditions." Journal of Fluids Engineering 127, no. 3 (February 24, 2005): 503–13. http://dx.doi.org/10.1115/1.1905646.

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The present study, which is the first of a series of investigations dealing with specific issues of low pressure turbine (LPT) boundary layer aerodynamics, is aimed at providing detailed unsteady boundary flow information to understand the underlying physics of the inception, onset, and extent of the separation zone. A detailed experimental study on the behavior of the separation zone on the suction surface of a highly loaded LPT-blade under periodic unsteady wake flow is presented. Experimental investigations were performed at Texas A&M Turbomachinery Performance and Flow Research Laboratory using a large-scale unsteady turbine cascade research facility with an integrated wake generator and test section unit. To account for a high flow deflection of LPT-cascades at design and off-design operating points, the entire wake generator and test section unit including the traversing system is designed to allow a precise angle adjustment of the cascade relative to the incoming flow. This is done by a hydraulic platform, which simultaneously lifts and rotates the wake generator and test section unit. The unit is then attached to the tunnel exit nozzle with an angular accuracy of better than 0.05°, which is measured electronically. Utilizing a Reynolds number of 110,000 based on the blade suction surface length and the exit velocity, one steady and two different unsteady inlet flow conditions with the corresponding passing frequencies, wake velocities and turbulence intensities are investigated using hot-wire anemometry. In addition to the unsteady boundary layer measurements, blade surface pressure measurements were performed at Re=50,000, 75,000, 100,000, and 125,000 at one steady and two periodic unsteady inlet flow conditions. Detailed unsteady boundary layer measurement identifies the onset and extent of the separation zone as well as its behavior under unsteady wake flow. The results presented in ensemble-averaged and contour plot forms contribute to understanding the physics of the separation phenomenon under periodic unsteady wake flow. Several physical mechanisms are discussed.

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Sandberg, Richard D., and Vittorio Michelassi. "Fluid Dynamics of Axial Turbomachinery: Blade- and Stage-Level Simulations and Models." Annual Review of Fluid Mechanics 54, no. 1 (January 5, 2022): 255–85. http://dx.doi.org/10.1146/annurev-fluid-031221-105530.

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The current generation of axial turbomachines is the culmination of decades of experience, and detailed understanding of the underlying flow physics has been a key factor for achieving high efficiency and reliability. Driven by advances in numerical methods and relentless growth in computing power, computational fluid dynamics has increasingly provided insights into the rich fluid dynamics involved and how it relates to loss generation. This article presents some of the complex flow phenomena occurring in bladed components of gas turbines and illustrates how simulations have contributed to their understanding and the challenges they pose for modeling. The interaction of key aerodynamic features with deterministic unsteadiness, caused by multiple blade rows, and stochastic unsteadiness, i.e., turbulence, is discussed. High-fidelity simulations of increasingly realistic configurations and models improved with help of machine learning promise to further grow turbomachinery performance and reliability and, thus, help fluid mechanics research have a greater industrial impact.

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Lenherr, Christian, Martin Oschwald, Anestis I. Kalfas, and Reza S. Abhari. "Flow adaptive aerodynamic probe for turbomachinery flows." E3S Web of Conferences 345 (2022): 01007. http://dx.doi.org/10.1051/e3sconf/202234501007.

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In order to enable turbomachinery research to obtain data highly resolved in space and time, a novel flow adaptive aerodynamic probe concept has been developed and presented in this paper. The algorithm selects the measurement positions of the probe automatically and therefore provides higher measurement fidelity compared to traditional methods. The development of the adaptive algorithm has been done in several steps. First an automatic 1Dtraversing algorithm has been developed. The following steps dealt with the subject of a 2D adaptive flow concept development, whereas primarily visual programming language-computer package simulations of the new 2D algorithm have been done based on data from previous test series at the Turbomachinery Laboratory. The new 2D traversing algorithm is fully selfcontrolled and requires minimal input such as blade count and hub and tip diameters. Furthermore, areas of interest (e.g. secondary flows, wake) are detected automatically and higher measuring point resolutions are ensured in these regions. After the successful simulations, the intelligent 2D algorithm has been adapted to an object oriented programming environment used for automated data acquisition and reduction. An evaluation of the flow adaptive aerodynamic flow concept has been done on a pressure turbine facility by means of a steady pneumatic probe. The measurement results show that the new 2D algorithm has the potential to detect new flow phenomena. In contrast to traditional algorithms, which in case of a possible enhancement demand a knowledge of the position of interesting areas such as the wake and vortical structures before starting the measurement, the new algorithm detects the right areas and enhances the resolution fully self controlled in these areas. Furthermore, the new 2D flow adaptive probe concept shows a significant improvement regarding the needed time for one measurement.

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Chasoglou, Alexandros C., Michel Mansour, Anestis I. Kalfas, and Reza S. Abhari. "A novel 4-sensor fast-response aerodynamic probe for non-isotropic turbulence measurement in turbomachinery flows." Journal of the Global Power and Propulsion Society 2 (May 17, 2018): UALS07. http://dx.doi.org/10.22261/jgpps.uals07.

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Abstract In modern computational studies for turbomachinery applications, time, length scales and isotropy of turbulent structures are important for representative modelling. To this end, experimental data are essential to validate the numerical tools. The current article presents the development and application of a newly designed 4-sensor Fast Response Aerodynamic Probe (FRAP-4S) enabling time-resolved measurement of the three-dimensional unsteady flow velocity vector in turbomachines. The miniature multi-sensor probe demonstrates a 4 mm probe-tip. In the first part of this article the design, manufacturing and calibration results of the FRAP-4S are presented in detail. To assess the newly developed probe accuracy, comparison against traditional instrumentation developed at the Laboratory for Energy Conversion is also provided. In the second part of this work, measurements are performed at the rotor exit of a one-and-a-half stage, unshrouded and highly-loaded axial turbine configuration. The results showed increased level of unsteadiness and turbulence levels with peak-to-peak fluctuation from 5 to 35%. More importantly, in some regions stream-wise unsteadiness was found to be ten times higher, compared to the cross-wise components, an indication of the high degree of anisotropy.

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Dring, R. P., and H. D. Joslyn. "Through-Flow Modeling of Axial Turbomachinery." Journal of Engineering for Gas Turbines and Power 108, no. 2 (April 1, 1986): 246–53. http://dx.doi.org/10.1115/1.3239895.

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Through-flow analysis, which is at the heart of the aerodynamic design of turbomachinery, requires as aerodynamic input a row-by-row description of the airfoil loss, deviation, and blockage. Loss and deviation have been investigated extensively in both cascades and rotating rigs as well as in numerous two- and three-dimensional analytical studies. Blockage, however, has received far less attention. As defined herein, blockage is a measure of the departure of the flow field from the condition of axisymmetry which is assumed in the through-flow analysis. The full-span blockage distributions calculated from measured single-stage rotor wake data were used to provide the input to the through-flow analysis, along with the measured full-span distributions of loss and deviation. Measured and computed results are compared for the single-stage rotor operating with both thick and thin inlet hub and tip boundary layers. It is demonstrated that both the level and the spanwise and streamwise distributions of blockage have a strong impact on the computed rotor exit flow field.

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Xu, Shenren, Pavanakumar Mohanamuraly, Dingxi Wang, and Jens-Dominik Müller. "Newton–Krylov Solver for Robust Turbomachinery Aerodynamic Analysis." AIAA Journal 58, no. 3 (March 2020): 1320–36. http://dx.doi.org/10.2514/1.j058523.

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Lenherr, C., A. I. Kalfas, and R. S. Abhari. "A flow adaptive aerodynamic probe concept for turbomachinery." Measurement Science and Technology 18, no. 8 (July 11, 2007): 2599–608. http://dx.doi.org/10.1088/0957-0233/18/8/035.

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KATO, Chisachi. "1626 Numerical Prediction of Aerodynamic Noise of Turbomachinery." Proceedings of the JSME annual meeting 2007.7 (2007): 121–22. http://dx.doi.org/10.1299/jsmemecjo.2007.7.0_121.

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Ekici, Kivanc, Robert E. Kielb, and Kenneth C. Hall. "The effect of aerodynamic asymmetries on turbomachinery flutter." Journal of Fluids and Structures 36 (January 2013): 1–17. http://dx.doi.org/10.1016/j.jfluidstructs.2012.08.009.

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Chen, Naixing, Hongwu Zhang, Weiguang Huang, and Yanji Xu. "Study on aerodynamic design optimization of turbomachinery blades." Journal of Thermal Science 14, no. 4 (December 2005): 298–304. http://dx.doi.org/10.1007/s11630-005-0048-5.

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Gossweiler, C. R., P. Kupferschmied, and G. Gyarmathy. "On Fast-Response Probes: Part 1—Technology, Calibration, and Application to Turbomachinery." Journal of Turbomachinery 117, no. 4 (October 1, 1995): 611–17. http://dx.doi.org/10.1115/1.2836579.

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A system for fast-response probe measurements in turbomachine flows has been developed and tested. The system has been designed for 40 kHz bandwidth and used with various in-house built probes accommodating up to four piezoresistive pressure transducers. The present generation of probes works accurately up to several bar pressure and 120°C temperature. The probes were found to be quite robust. The use of a miniature pressure transducer placed in the head of a probe showed that a precise packaging technique and a careful compensation of errors can considerably improve the accuracy of the pressure measurement. Methods for aerodynamic probe calibration and off-line data evaluation are briefly presented. These aimed, e.g., in the case of a four-hole probe, at measuring the velocity fluctuations as characterized by yaw, pitch, total pressure, and static pressure and at deriving mean values and spectral or turbulence parameters. Applications of the measuring system to turbomachinery flow in a radial compressor and to a turbulent pipe flow demonstrate the performance of the measuring system.

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Abed, Cheikh Brahim, Sofiane Khelladi, Michael Deligant, Abdellatif El Marjani, Moisés Solis, and Farid Bakir. "Experimental Validation of the Aerodynamic Performance of an Innovative Counter-Rotating Centrifugal Compressor." Energies 14, no. 9 (April 30, 2021): 2582. http://dx.doi.org/10.3390/en14092582.

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Turbomachinery with double counter-rotating impellers offers more degrees of freedom in the choice of design and control parameters compared to conventional machines. For these innovative machines, the literature review shows that more publications concerning axial type turbomachines are available than centrifugal ones. This work deals with a design and experimental performance analysis, applied to two counter-rotating impellers of a centrifugal compressor “CRCC”. CRCC was designed with a specifically developed tool based on mean-line approach coupled with optimization algorithms and a stream-curvature through-flow method to satisfy the design criteria. This paper presents an experimental validation of the CRCC design tool and its performances against the baseline “SR”, composed of one centrifugal impeller and a volute for which experimental data are available. CRCC numeric simulations are also validated by experimental data. For a fair comparison between CRCC and SR, the same volute is used for both configurations. The CRCC studied here includes a first conventional impeller with an axial inlet and a radial outlet, while the second impeller is parametrically designed and can be considered a rotating bladed diffuser with a radial inlet and outlet. The obtained results show that CRCC can deliver a pressure rise increase of two compared to SR, along with an increase of isentropic efficiency and also validate the design method of this novel layout. The experimental results also show that the speed ratio of CRCC has a positive effect on the surge and shock margin.

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Wilcock, R. C., J. B. Young, and J. H. Horlock. "The Effect of Turbine Blade Cooling on the Cycle Efficiency of Gas Turbine Power Cycles." Journal of Engineering for Gas Turbines and Power 127, no. 1 (January 1, 2005): 109–20. http://dx.doi.org/10.1115/1.1805549.

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A thermodynamic cycle analysis computer code for the performance prediction of cooled gas turbines has been used to calculate the efficiency of plants with varying combustor outlet temperature, compressor pressure ratio, and turbomachinery polytropic efficiency. It is shown that the polytropic efficiency exerts a major influence on the optimum operating point of cooled gas turbines: for moderate turbomachinery efficiency the search for enhanced combustor outlet temperature is shown to be logical, but for high turbomachinery efficiency this is not necessarily so. The sensitivity of the cycle efficiency to variation in the parameters determining the cooling flow rates is also examined. While increases in allowable blade metal temperature and film cooling effectiveness are more beneficial than improvements in other parameters, neither is as important as increase in turbomachinery aerodynamic efficiency.

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Li, 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.

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Aerodynamic damping predictions are critical when analyzing aeroelastic stability. A novel method has been developed to predict aerodynamic damping by employing two single time-domain simulations, specifically, one with the blade impulsed naturally in a vacuum and one with the blade impulsed in flow. The focus is on the aerodynamic damping prediction using modal excitation and the logarithmic decrement theory. The method is demonstrated by considering the first two bending modes with an inter-blade phase angle (IBPA) of 0° on a transonic compressor. The results show that the flutter boundary prediction is basically consistent with the experiment. The aerodynamic damping prediction with an IBPA of 180° is also performed, demonstrating that the method is suitable for different traveling wave mode representations. Furthermore, the influence of the amplitude of modal excitation and mechanical damping using the Rayleigh damping model for aerodynamic damping was also investigated by employing fluid-structure coupled simulations.

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Samad, Abdus, and Kwang-Yong Kim. "Surrogate Based Optimization Techniques for Aerodynamic Design of Turbomachinery." International Journal of Fluid Machinery and Systems 2, no. 2 (June 1, 2009): 179–88. http://dx.doi.org/10.5293/ijfms.2009.2.2.179.

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Yang, J., Y. Liu, X. Wang, and H. Wu. "An improved steady inverse method for turbomachinery aerodynamic design." Inverse Problems in Science and Engineering 25, no. 5 (May 11, 2016): 633–51. http://dx.doi.org/10.1080/17415977.2016.1178259.

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Journal articles on the topic 'Turbomachinery aerodynamics'

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