Relevant bibliographies by topics / Turbomachinery aerodynamics

Academic literature on the topic 'Turbomachinery aerodynamics'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Contents

Consult the lists of relevant articles, books, theses, conference reports, and other scholarly sources on the topic 'Turbomachinery aerodynamics.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Journal articles on the topic "Turbomachinery aerodynamics"

1

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.

Full text
Abstract:
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.
APA, Harvard, Vancouver, ISO, and other styles
2

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.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

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.

Full text
Abstract:
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.
APA, Harvard, Vancouver, ISO, and other styles
4

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.

Full text
Abstract:
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.
APA, Harvard, Vancouver, ISO, and other styles
5

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.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

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.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

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.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

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.

Full text
Abstract:
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.
APA, Harvard, Vancouver, ISO, and other styles
9

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.

Full text
Abstract:
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.
APA, Harvard, Vancouver, ISO, and other styles
10

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_.

Full text
APA, Harvard, Vancouver, ISO, and other styles
More sources

Dissertations / Theses on the topic "Turbomachinery aerodynamics"

1

Gostelow, J. P. "Publications in turbomachinery aerodynamics and related fields." Thesis, University of Liverpool, 1987. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.384347.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

He, Li. "Unsteady flows around oscillating turbomachinery blades." Thesis, University of Cambridge, 1990. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.385407.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

Ning, Wei. "Computation of unsteady flow in turbomachinery." Thesis, Durham University, 1998. http://etheses.dur.ac.uk/4819/.

Full text
Abstract:
Unsteady flow analysis has been gradually introduced in turbomachinery design systems to improve machine performance and structural integrity. A project on computation of unsteady flows in turbomachinery has been carried out. A quasi 3-D time-linearized Euler/Navier-Stokes method has been developed for unsteady flows induced by the blade oscillation and unsteady incoming wakes, hi this method, the unsteady flow is decomposed into a steady flow plus a harmonically varying unsteady perturbation. The coefficients of the linear perturbation equation are formed from steady flow solutions. A pseudo-time is introduced to make both the steady flow equation and the linear unsteady perturbation equation time-independent. The 4-stage Runge-Kutta time-marching scheme is implemented for the temporal integration and a cell-vertex scheme is used for the spatial discretization. A 1-D/2-D nonreflecting boundary condition is applied to prevent spurious reflections of outgoing waves when solving the perturbation equations. The viscosity in the unsteady Navier- Stokes perturbation equation is frozen to its steady value. The present time-linearized Euler/Navier-Stokes method has been extensively validated against other well- developed linear methods, nonlinear time-marching methods and experimental data. Based upon the time-linearized method, a novel quasi 3-D nonlinear harmonic Euler/Navier-Stokes method has been developed. In this method, the unsteady flow is divided into a time-averaged flow plus an unsteady perturbation. Time-averaging produces extra nonlinear "unsteady stress" terras in the time-averaged equations and these extra terras are evaluated from unsteady perturbations. Unsteady perturbations are obtained by solving a first order harraonic perturbation equation, while the coefficients of the perturbation equation are forraed from time-averaged solutions. A strong coupling procedure is applied to solve the time-averaged equation and the unsteady perturbation equation simultaneously in a pseudo-time domain. An approximate approach is used to linearize the pressure sensors in artificial smoothing
APA, Harvard, Vancouver, ISO, and other styles
4

Melzer, Andrew Philip. "Aerodynamics of transonic turbine trailing edges." Thesis, University of Cambridge, 2018. https://www.repository.cam.ac.uk/handle/1810/276280.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Tsay, W. C. "The analysis and design methods for turbomachinery flows." Thesis, Cranfield University, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.233928.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

Brock, Jerry S. "A modified Baldwin-Lomax turbulence model for turbomachinery wakes." Thesis, This resource online, 1991. http://scholar.lib.vt.edu/theses/available/etd-09052009-040231/.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

Knapke, Clint J. "Aerodynamics of Fan Blade Blending." Wright State University / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=wright1567517259599736.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

Forhad, Md Moinul Islam. "Robustness analysis for turbomachinery stall flutter." Master's thesis, University of Central Florida, 2011. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/4894.

Full text
Abstract:
As compared with other robustness analysis tools, such as Hsubscript inf], the Mu analysis is less conservative and can handle both structured and unstructured perturbations. Finally, Genetic Algorithm is used as an optimization tool to find ideal parameters that will ensure best performance in terms of damping out flutter. Simulation results show that the procedure described in this thesis can be effective in studying the flutter stability margin and can be used to guide the gas turbine blade design.; Flutter is an aeroelastic instability phenomenon that can result either in serious damage or complete destruction of a gas turbine blade structure due to high cycle fatigue. Although 90% of potential high cycle fatigue occurrences are uncovered during engine development, the remaining 10% stand for one third of the total engine development costs. Field experience has shown that during the last decades as much as 46% of fighter aircrafts were not mission-capable in certain periods due to high cycle fatigue related mishaps. To assure a reliable and safe operation, potential for blade flutter must be eliminated from the turbomachinery stages. However, even the most computationally intensive higher order models of today are not able to predict flutter accurately. Moreover, there are uncertainties in the operational environment, and gas turbine parts degrade over time due to fouling, erosion and corrosion resulting in parametric uncertainties. Therefore, it is essential to design engines that are robust with respect to the possible uncertainties. In this thesis, the robustness of an axial compressor blade design is studied with respect to parametric uncertainties through the Mu analysis. The nominal flutter model is adopted from (9). This model was derived by matching a two dimensional incompressible flow field across the flexible rotor and the rigid stator. The aerodynamic load on the blade is derived via the control volume analysis. For use in the Mu analysis, first the model originally described by a set of partial differential equations is reduced to ordinary differential equations by the Fourier series based collocation method. After that, the nominal model is obtained by linearizing the achieved non-linear ordinary differential equations. The uncertainties coming from the modeling assumptions and imperfectly known parameters and coefficients are all modeled as parametric uncertainties through the Monte Carlo simulation.
ID: 030423207; System requirements: World Wide Web browser and PDF reader.; Mode of access: World Wide Web.; Thesis (M.S.)--University of Central Florida, 2011.; Includes bibliographical references (p. 44-47).
M.S.
Masters
Mechanical, Materials, and Aerospace Engineering
Engineering and Computer Science
APA, Harvard, Vancouver, ISO, and other styles
9

Sharpe, Jacob Andrew. "3D CFD Investigation of Low Pressure Turbine Aerodynamics." Wright State University / OhioLINK, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=wright1495872867696744.

Full text
APA, Harvard, Vancouver, ISO, and other styles
10

Chernysheva, Olga V. "Flutter in sectored turbine vanes." Doctoral thesis, KTH, Energy Technology, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3737.

Full text
Abstract:

In order to eliminate or reduce vibration problems inturbomachines without a high increase in the complexity of thevibratory behavior, the adjacent airfoils around the wheel areoften mechanically connected together with lacing wires, tip orpart-span shrouds in a number of identical sectors. Although anaerodynamic stabilizing effect of tying airfoils together ingroups on the whole cascade is indicated by numerical andexperimental studies, for some operating conditions suchsectored vane cascade can still remain unstable.

The goal of the present work is to investigate thepossibilities of a sectored vane cascade to undergoself-excited vibrations or flutter. The presented method forpredicting the aerodynamic response of a sectored vane cascadeis based on the aerodynamic work influence coefficientrepresentation of freestanding blade cascade. The sectored vaneanalysis assumes that the vibration frequency is the same forall blades in the sectored vane, while the vibration amplitudesand mode shapes can be different for each individual blade inthe sector. Additionally, the vibration frequency as well asthe amplitudes and mode shapes are supposed to be known.

The aerodynamic analysis of freestanding blade cascade isperformed with twodimensional inviscid linearized flow model.As far as feasible the study is supported by non-linear flowmodel analysis as well as by performing comparisons againstavailable experimental data in order to minimize theuncertainties of the numerical modeling on the physicalconclusions of the study.

As has been shown for the freestanding low-pressure turbineblade, the blade mode shape gives an important contributioninto the aerodynamic stability of the cascade. During thepreliminary design, it has been recommended to take intoaccount the mode shape as well rather than only reducedfrequency. In the present work further investigation using foursignificantly different turbine geometries makes these findingsmore general, independent from the low-pressure turbine bladegeometry. The investigation also continues towards a sectoredvane cascade. A parametrical analysis summarizing the effect ofthe reduced frequency and real sector mode shape is carried outfor a low-pressure sectored vane cascade for differentvibration amplitude distributions between the airfoils in thesector as well as different numbers of the airfoils in thesector. Critical (towards flutter) reduced frequency maps areprovided for torsion- and bending-dominated sectored vane modeshapes. Utilizing such maps at the early design stages helps toimprove the aerodynamic stability of low-pressure sectoredvanes.

A special emphasis in the present work is put on theimportance for the chosen unsteady inviscid flow model to bewell-posed during numerical calculations. The necessity for thecorrect simulation of the far-field boundary conditions indefining the stability margin of the blade rows isdemonstrated. Existing and new-developed boundary conditionsare described. It is shown that the result of numerical flowcalculations is dependent more on the quality of boundaryconditions, and less on the physical extension of thecomputational domain. Keywords: Turbomachinery, Aerodynamics,Unsteady CFD, Design, Flutter, Low-Pressure Turbine, Blade ModeShape, Critical Reduced Frequency, Sectored Vane Mode Shape,Vibration Amplitude Distribution, Far-field 2D Non-ReflectingBoundary Conditions. omain.

Keywords:Turbomachinery, Aerodynamics, Unsteady CFD,Design, Flutter, Low-Pressure Turbine, Blade Mode Shape,Critical Reduced Frequency, Sectored Vane Mode Shape, VibrationAmplitude Distribution, Far-field 2D Non-Reflecting BoundaryConditions.

APA, Harvard, Vancouver, ISO, and other styles
More sources

Books on the topic "Turbomachinery aerodynamics"

1

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Unsteady aerodynamic phenomena in turbomachines. Neuilly sur Seine, France: AGARD, 1990.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
2

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Unsteady aerodynamic phenomena in turbomachines. Neuilly-sur-Seine: AGARD, 1990.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
3

Verdon, Joseph M. Unsteady aerodynamic models for turbomachinery aeroelastic and aeroacoustic applications. Cleveland, Ohio: Lewis Research Center, 1995.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
4

Chen, Naixing. Aerothermodynamics of turbomachinery: Analysis and design. Hoboken, N.J: Wiley, 2010.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
5

Schobeiri, Meinhard. Turbomachinery flow physics and dynamic performance. 2nd ed. New York: Springer, 2012.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
6

Schobeiri, Meinhard. Turbomachinery Flow Physics and Dynamic Performance. 2nd ed. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
7

Montgomery, Matthew D. A three-dimensional linearized unsteady Euler analysis for turbomachinery blade rows. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1997.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
8

M, David. TIGGERC--turbomachinery interactive grid generator for 2-D grid applications and uers guide. [Washington, D.C.]: National Aeronautics and Space Administration, 1994.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
9

King, Paul I. Testing, analysis, and code verification of aerodynamics and heat transfer related to turbomachinery: Final report. [Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1991.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
10

King, Paul I. Testing, analysis, and code verification of aerodynamics and heat transfer related to turbomachinery: Final report. [Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1991.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
More sources

Book chapters on the topic "Turbomachinery aerodynamics"

1

Chupp, Raymond E., Robert C. Hendricks, Scott B. Lattime, Bruce M. Steinetz, and Mahmut F. Aksit. "Turbomachinery Clearance Control." In Turbine Aerodynamics, Heat Transfer, Materials, and Mechanics, 61–188. Reston, VA: American Institute of Aeronautics and Astronautics, Inc., 2014. http://dx.doi.org/10.2514/5.9781624102660.0061.0188.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

Atassi, H. M., and V. V. Golubev. "Unsteady Disturbances in Swirling Turbomachinery Flows." In Unsteady Aerodynamics and Aeroelasticity of Turbomachines, 131–46. Dordrecht: Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5040-8_9.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

Kahl, G. "Structural Mistuning and Aerodynamic Coupling in Turbomachinery Bladings." In Unsteady Aerodynamics and Aeroelasticity of Turbomachines, 335–46. Dordrecht: Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5040-8_22.

Full text
APA, Harvard, Vancouver, ISO, and other styles
4

Florea, R., K. C. Hall, and P. G. A. Cizmas. "Eigenmode Analysis of Unsteady Viscous Flows in Turbomachinery Cascades." In Unsteady Aerodynamics and Aeroelasticity of Turbomachines, 767–82. Dordrecht: Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5040-8_50.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Sbardella, L., A. I. Sayma, and M. Imregun. "Semi-Unstructured Mesh Generator for Flow Calculations in Axial Turbomachinery Blading." In Unsteady Aerodynamics and Aeroelasticity of Turbomachines, 541–54. Dordrecht: Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5040-8_35.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

Peitsch, D., H. E. Gallus, and H. P. Kau. "Prediction of Unsteady 2D-Flow in Turbomachinery Bladings." In Unsteady Aerodynamics, Aeroacoustics, and Aeroelasticity of Turbomachines and Propellers, 231–49. New York, NY: Springer New York, 1993. http://dx.doi.org/10.1007/978-1-4613-9341-2_12.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

Marshall, J. G., and M. B. Giles. "Some Applications of a Time-Linearized Euler Method to Flutter & Forced Response in Turbomachinery." In Unsteady Aerodynamics and Aeroelasticity of Turbomachines, 225–40. Dordrecht: Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5040-8_15.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

Weber, S., H. E. Gallus, and D. Peitsch. "Numerical Solution of the Navier Stokes Equations for Unsteady Unstalled and Stalled Flow in Turbomachinery Cascades with Oscillating Blades." In Unsteady Aerodynamics and Aeroelasticity of Turbomachines, 477–91. Dordrecht: Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5040-8_31.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Sieverding, C. H. "Aerodynamic Development of Axial Turbomachinery Bladings." In Thermodynamics and Fluid Mechanics of Turbomachinery, 513–65. Dordrecht: Springer Netherlands, 1985. http://dx.doi.org/10.1007/978-94-009-5153-2_15.

Full text
APA, Harvard, Vancouver, ISO, and other styles
10

Schobeiri, Meinhard T. "Turbine Aerodynamic Design and Off-Design Performance." In Turbomachinery Flow Physics and Dynamic Performance, 445–72. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-24675-3_17.

Full text
APA, Harvard, Vancouver, ISO, and other styles

Conference papers on the topic "Turbomachinery aerodynamics"

1

Reddy, T. S. R., Subodh Mital, and George Stefko. "Probabilistic aeroelastic analysis of turbomachinery components." In 19th AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-1453.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

VERDON, JOSEPH. "Linearized unsteady aerodynamics for turbomachinery aeroelastic applications." In 26th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-2355.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

Chochua, Gocha, Wei Shyy, and Jeffrey Moore. "Aerodynamics of Scallop Seal Flows in Turbomachinery." In ASME 2001 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2001. http://dx.doi.org/10.1115/imece2001/htd-24311.

Full text
Abstract:
Abstract Gas annular seals are commonly adopted for leakage control in turbomachinery applications. Scallop seal is an representative example of damper seals, and is attractive from rotordynamic stability viewpoint. To understand flow physics in such seals a computational analysis is developed to study compressible, turbulent flow in it. The following issues are addressed: (i) validation of results obtained using periodic boundary conditions accounting for turbulent and compressible flows, (ii) effect of the rotor rotation and inlet swirl ratio on flow development in the seal, (iii) extrapolation of the full-length results from limited periodic simulations, and (iv) breakdown of the friction factor on contributing pressure and shear stress components. The computational techniques presented can help address the design related issues more economically, and the findings offer insight into the fluid physics associated with a scallop seal.
APA, Harvard, Vancouver, ISO, and other styles
4

"Turbomachinery off-design performance improvement through spanwise variation of vane camber." In 5th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2639.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Watanabe, Toshinori, Eisuke Outa, Tsutomu Adachi, Ichiro Ariga, Yasushige Kashiwabara, Shimpei Mizuki, and Hideo Tanaka. "Advances in Unsteady Turbomachinery Aerodynamics in Japan: Professor Gallus’ Contribution." In ASME Turbo Expo 2005: Power for Land, Sea, and Air. ASMEDC, 2005. http://dx.doi.org/10.1115/gt2005-68695.

Full text
Abstract:
The present paper describes recent advances in turbomachinery aerodynamic research in Japan achieved by the researchers who studied under the supervision of the late Professor Gallus. His research work, way of thinking, and personality exerted great influence in Japan on the styles of research in the field of unsteady aerodynamics of turbomachines. The profound contribution by him to the research and development of Japanese gas turbine technologies is highly appreciated. The paper presents research results on the issues concerning cascade flutter suppression, rotating stall analysis and control for axial compressors, unsteady flow analysis and control for radial compressors and diffusers, as well as design studies of axial turbomachines.
APA, Harvard, Vancouver, ISO, and other styles
6

Hsiao, Entsung, Mahmood Naimi, Jeffrey Lewis, Keith Dalbey, Yifang Gong, and Choon Tan. "Actuator duct model of turbomachinery components for powered-nacelle Navier-Stokes calculations." In 18th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-4328.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

Hu, Jiasen, Tordten Fransson, Jiasen Hu, and Tordten Fransson. "Transition predictions for turbomachinery flows using Navier-Stokes solver and experimental correlation." In 15th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-2230.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

Balasubramanian, Ravishankar, Jen Ping Chen, and Robert Nichols. "Assessment of Turbulence Near-Wall Treatment Methods for Turbomachinery Flow Simulations." In 26th AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-7058.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Ekici, Kivanc, and Huang Huang. "An Assessment of Frequency-Domain and Time-Domain Techniques for Turbomachinery Aeromechanics." In 30th AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-3126.

Full text
APA, Harvard, Vancouver, ISO, and other styles
10

Seshadri, Pranay, Shahrokh Shahpar, Paul Constantine, Geoffrey Parks, and Mike Adams. "Turbomachinery Active Subspace Performance Maps." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-64528.

Full text
Abstract:
Turbomachinery active subspace performance maps are 2D contour plots that illustrate the variation of key flow performance metrics with different blade designs. While such maps are easy to construct for design parameterizations with two variables, in this paper maps will be generated for a fan blade with twenty-five design variables. Turbomachinery active subspace performance maps combine active subspaces — a new set of ideas for dimension reduction — with fundamental turbomachinery aerodynamics and design spaces. In this paper, contours of (i) cruise efficiency, (ii) cruise pressure ratio, (iii) maximum climb flow capacity and (iv) sensitivity to manufacturing variations, are plotted as objectives for the fan. These maps are then used to infer pedigree design rules: how best to increase fan efficiency; how best to desensitize blade aerodynamics to the impact of manufacturing variations? In the present study, the former required both a reduction in pressure ratio and flow capacity — leading to a reduction of the strength of the leading edge bow wave — while the latter required strictly a reduction in flow capacity. While such pedigree rules can be obtained from first principles, in this paper these rules are derived from the active subspaces. This facilitates a more detailed quantification of the aerodynamic trade-offs. Thus, instead of simply stating that a particular design is more sensitive to manufacturing variations; or that it lies on a hypothetical ‘efficiency cliff’, this paper seeks to visualize, quantify and make precise such notions of turbomachinery design.
APA, Harvard, Vancouver, ISO, and other styles

Reports on the topic "Turbomachinery aerodynamics"

1

Fleeter, Sanford. Unsteady Aerodynamics & Aeormechanics of Multi-Stage Turbomachinery Blading. Fort Belvoir, VA: Defense Technical Information Center, November 2002. http://dx.doi.org/10.21236/ada412022.

Full text
APA, Harvard, Vancouver, ISO, and other styles
You might also be interested in the extended bibliographies on the topic 'Turbomachinery aerodynamics' for particular source types:
Journal articles Dissertations / Theses Books
We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!

To the bibliography