Gotowe bibliografie tematyczne / Inlet distortions

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Gotowa bibliografia na temat „Inlet distortions”

Autor: Grafiati

Data publikacji: 7 grudnia 2024

Data aktualizacji: 31 lipca 2025

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Artykuły w czasopismach na temat "Inlet distortions"

Ariga, I., S. Masuda, and A. Ookita. "Inducer Stall in a Centrifugal Compressor With Inlet Distortion." Journal of Turbomachinery 109, no. 1 (1987): 27–35. http://dx.doi.org/10.1115/1.3262066.

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The effects of inlet distortion on the inducer stall in a centrifugal compressor are investigated. Cases of both radial and circumferential distortion are investigated. It is shown that the rotating stall onset is amplified by radial distortions, and restrained by circumferential distortions. These results are compared with calculations based on the small disturbance theory. The authors find that the stall onset is governed by the characteristic parameters related to the lower flow rate region for radial distortions, but affected by those of the higher flow rate region for circumferential dist

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Lowe, K. Todd. "Laser velocimetry for turbofan inlet distortion applications." Aircraft Engineering and Aerospace Technology 92, no. 1 (2020): 20–26. http://dx.doi.org/10.1108/aeat-11-2018-0285.

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Purpose The purpose of this paper is to assess state-of-the-art techniques for quantifying flow distortion in the inlets of turbofan engines, particularly with respect to the prospects for future flight applications. Design/methodology/approach To adequately characterize the flow fields of complex aircraft inlet distortions, the author has incorporated laser velocimetry techniques, namely, stereoscopic particle image velocimetry (PIV) and Doppler velocimetry based on filtered Rayleigh scattering (FRS), into inlet distortion studies. Findings Overall, the results and experience indicate that th

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Pazur, W., and L. Fottner. "The Influence of Inlet Swirl Distortions on the Performance of a Jet Propulsion Two-Stage Axial Compressor." Journal of Turbomachinery 113, no. 2 (1991): 233–40. http://dx.doi.org/10.1115/1.2929091.

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Aeroengine intakes containing S-shaped diffusers produce different types of inlet swirl distortions and essentially a combination of a twin swirl and a bulk swirl. The main object of this investigation was to assess the influence of inlet swirl distortions on the performance of a transonic two-stage axial compressor installed in a turbo jet bypass engine Larzac 04. A typical inlet swirl distortion was simulated by a delta-wing in front of the engine. An experimental method was investigated to measure the performance map of the installed low-pressure compressor for different engine operating li

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Fang, Yibo, Dakun Sun, Xu Dong, and Xiaofeng Sun. "Effects of Inlet Swirl Distortion on a Multi-Stage Compressor with Inlet Guide Vanes and Stall Margin Enhancement Method." Aerospace 10, no. 2 (2023): 141. http://dx.doi.org/10.3390/aerospace10020141.

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Inlet swirl distortion is generally considered as a type of velocity distortion, and inlet guide vanes (IGVs) are widely used in the multi-stage compressor of aero-engines to eliminate the tangential velocity of the swirl flow. However, few studies have explored whether there still exists some negative influence of inlet swirl distortion on the compressor, even after the installation of IGVs. Therefore, in this study, the influence of various types of inlet swirl distortions on a multi-stage compressor with the installation of IGVs is investigated. A swirl distortion generator installed in the

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Hah, C., D. C. Rabe, T. J. Sullivan, and A. R. Wadia. "Effects of Inlet Distortion on the Flow Field in a Transonic Compressor Rotor." Journal of Turbomachinery 120, no. 2 (1998): 233–46. http://dx.doi.org/10.1115/1.2841398.

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The effects of circumferential distortions in inlet total pressure on the flow field in a low-aspect-ratio, high-speed, high-pressure-ratio, transonic compressor rotor are investigated in this paper. The flow field was studied experimentally and numerically with and without inlet total pressure distortion. Total pressure distortion was created by screens mounted upstream from the rotor inlet. Circumferential distortions of eight periods per revolution were investigated at two different rotor speeds. The unsteady blade surface pressures were measured with miniature pressure transducers mounted

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Pečinka, Jiří, Gabriel Thomas Bugajski, Petr Kmoch, and Adolf Jílek. "JET ENGINE INLET DISTORTION SCREEN AND DESCRIPTOR EVALUATION." Acta Polytechnica 57, no. 1 (2017): 22–31. http://dx.doi.org/10.14311/ap.2017.57.0022.

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Total pressure distortion is one of the three basic flow distortions (total pressure, total temperature and swirl distortion) that might appear at the inlet of a gas turbine engine (GTE) during operation. Different numerical parameters are used for assessing the total pressure distortion intensity and extent. These summary descriptors are based on the distribution of total pressure in the aerodynamic interface plane. There are two descriptors largely spread around the world, however, three or four others are still in use and can be found in current references. The staff at the University of De

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Leinhos, Dirk C., Norbert R. Schmid, and Leonhard Fottner. "The Influence of Transient Inlet Distortions on the Instability Inception of a Low-Pressure Compressor in a Turbofan Engine." Journal of Turbomachinery 123, no. 1 (2000): 1–8. http://dx.doi.org/10.1115/1.1330271.

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While studies on compressor flow instabilities under the presence of inlet distortions have been carried out with steady distortions in the past, the investigation presented here focuses on the influence of transient inlet distortions as generated by variable geometry engine intakes of super- and hypersonic aircraft on the characteristic and the nature of the instability inception of a LPC. The flow patterns (total pressure distortion with a superimposed co- or counterrotating swirl) of the distortions are adopted from a hypersonic concept aircraft. A LARZAC 04 twin-spool turbofan was operated

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Ng, Eddie Yin-Kwee, Ningyu Liu, Hong Ngiap Lim, and Daniel Tan. "An Improved Integral Method for Prediction of Distorted Inlet Flow Propagation in Axial Compressor." International Journal of Rotating Machinery 2005, no. 2 (2005): 117–27. http://dx.doi.org/10.1155/ijrm.2005.117.

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An improved integral method is proposed and developed for the quantitative prediction of distorted inlet flow propagation through axial compressor. The novel integral method is formulated using more appropriate and practical airfoil characteristics, with less assumptions needed for derivation. The results indicate that the original integral method (Kim et al., 1996) underestimated the propagation of inlet flow distortion. The effects of inlet flow parameters on the propagation of inlet distortions as well as on the compressor performance and characteristic are simulated and analyzed. From the

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Schmid, Norbert R., Dirk C. Leinhos, and Leonhard Fottner. "Steady Performance Measurements of a Turbofan Engine With Inlet Distortions Containing Co- and Counterrotating Swirl From an Intake Diffuser for Hypersonic Flight." Journal of Turbomachinery 123, no. 2 (2000): 379–85. http://dx.doi.org/10.1115/1.1343466.

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The influence of distorted inlet flow on the steady and unsteady performance of a turbofan engine, which is a component of an air-breathing combined propulsion system for a hypersonic transport aircraft, is reported in this paper. The performance and stability of this propulsion system depend on the behavior of the turbofan engine. The complex shape of the intake duct causes inhomogeneous flow at the engine inlet plane, where total pressure and swirl distortions are present. The S-bend intakes are installed axisymmetrically left and right into the hypersonic aircraft, generating axisymmetric m

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Engeda, Abraham, Yunbae Kim, Ronald Aungier, and Gregory Direnzi. "The Inlet Flow Structure of a Centrifugal Compressor Stage and Its Influence on the Compressor Performance." Journal of Fluids Engineering 125, no. 5 (2003): 779–85. http://dx.doi.org/10.1115/1.1601255.

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The performance of centrifugal compressors can be seriously degraded by inlet flow distortions that result from an unsatisfactory inlet configuration. In this present work, the flow is numerically simulated and the flow details are analyzed and discussed in order to understand the performance behavior of the compressor exposed to different inlet configurations. In a previous work, complementary to this present work, experimental tests were carried out for the comparison of a centrifugal compressor stage performance with two different inlet configurations: one of which was a straight pipe with

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Rozprawy doktorskie na temat "Inlet distortions"

Guimaraes, Bucalo Tamara. "Fluid Dynamics of Inlet Swirl Distortions for Turbofan Engine Research." Diss., Virginia Tech, 2018. http://hdl.handle.net/10919/82921.

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Significant effort in the current technological development of aircraft is aimed at improving engine efficiency, while reducing fuel burn, emissions, and noise levels. One way to achieve these is to better integrate airframe and propulsion system. Tighter integration, however, may also cause adverse effects to the flow entering the engines, such as total pressure, total temperature, and swirl distortions. Swirl distortions are angular non-uniformities in the flow that may alter the functioning of specific components of the turbomachinery systems. To investigate the physics involved in the inge

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Gong, Yifang 1964. "A computational model for rotating stall and inlet distortions in multistage compressors." Thesis, Massachusetts Institute of Technology, 1999. http://hdl.handle.net/1721.1/9733.

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Thesis (Ph.D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999. "February 1999." Includes bibliographical references (p. 175-182). This thesis presents the conceptualization and development of a computational model for describing three-dimensional non-linear disturbances associated with instability and inlet distortion in multistage compressors. Specifically, the model is aimed at simulating the non-linear aspects of short wavelength stall inception, part span stall cells, and compressor response to three-dimensional inlet distortions. The computed

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Eisemann, Kevin Michael. "A Computational Study of Compressor Inlet Boundary Conditions with Total Temperature Distortions." Thesis, Virginia Tech, 2005. http://hdl.handle.net/10919/35969.

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A three-dimensional CFD program was used to predict the flow field that would enter a downstream fan or compressor rotor under the influence of an upstream thermal distortion. Two distortion generation techniques were implemented in the model; (1) a thermal source and (2) a heated flow injection method. Results from the investigation indicate that both total pressure and velocity boundary conditions at the compressor face are made non-uniform by the upstream thermal distortion, while static pressure remains nearly constant. Total pressure at the compressor face was found to vary on the orde

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Giuliani, James Edward. "Jet Engine Fan Response to Inlet Distortions Generated by Ingesting Boundary Layer Flow." The Ohio State University, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=osu1468564279.

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Lambie, David. "Inlet distortion and turbofan engines." Thesis, University of Cambridge, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.305300.

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Longley, John Peter. "Inlet distortion and compressor stability." Thesis, University of Cambridge, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.304354.

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Hoopes, Kevin M. "A New Method for Generating Swirl Inlet Distortion for Jet Engine Research." Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/49545.

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Jet engines operate by ingesting incoming air, adding momentum to it, and exhausting it through a nozzle to produce thrust. Because of their reliance on an inlet stream, jet engines are very sensitive to inlet flow nonuniformities. This makes the study of the effects of inlet nonuniformities essential to improving jet engine performance. Swirl distortion is the presence of flow angle nonuniformity in the inlet stream of a jet engine. Although several attempts have been made to accurately reproduce swirl distortion profiles in a testing environment, there has yet to be a proven method to do so.

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Dosne, Cyril. "Development and implementation of adjoint formulation of explicit body-force models for aero-propulsive optimizations." Electronic Thesis or Diss., Institut polytechnique de Paris, 2024. http://www.theses.fr/2024IPPAX026.

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Dans le domaine de l’aéronautique civile, les études de plus en plus nombreuses portant sur les nouveaux systèmes moteurs, tels que les turbofans à très haut taux de dilution et les open-rotors, ainsi que sur les architectures d'intégration motrice innovantes, telles que la propulsion distribuée ou les systèmes à ingestion de couche limite, nécessitent une modélisation couplée de l’aérodynamique externe et du système propulsif, et ce dès les premiers stades de la conception. Les modèles body-force se sont avérés capables de reproduire fidèlement la majeure partie des phénomènes de couplage aér

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Van, Schalkwyk Christiaan Mauritz. "Active control rotating stall with inlet distortion." Thesis, Massachusetts Institute of Technology, 1996. http://hdl.handle.net/1721.1/10827.

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Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1996. Includes bibliographical references (p. 179-182). by Christiaan Mauritz Van Schalkwyk. Ph.D.

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Papamarkos, Ioannis. "Inlet distortion generation for a transonic compressor." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2004. http://library.nps.navy.mil/uhtbin/hyperion/04Sep%5FPapamarkos.pdf.

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Książki na temat "Inlet distortions"

A, Ladd J., Yuhas A. J, and United States. National Aeronautics and Space Administration., eds. Dynamic inlet distortion prediction with a combined computational fluid dynamics and distortion synthesis approach. National Aeronautics and Space Administration, 1996.

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M, Greitzer Edward, and Lewis Research Center, eds. Final technical report on grant NAG3-1567 entitled Inlet distortion in engines on VSTOL aircraft. The Center, 1994.

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Yuhas, Andrew J. Design and development of an F/A-18 inlet distortion rake: a cost and time saving solution. Dryden Flight Research Center, 1995.

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United States. Army Aviation Research and Technology Activity. and United States. National Aeronautics and Space Administration., eds. Effects of inlet distortion on the development of secondary flows in a subsonic axial inlet compressor rotor. National Aeronautics and Space Administration, 1991.

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H, Anderson Bernhard, Shaw Robert J. 1946-, and United States. National Aeronautics and Space Administration., eds. A full Navier-Stokes analysis of subsonic diffuser of a a bifurcated 70/30 supersonic inlet for high speed civil transport application. National Aeronautics and Space Administration, 1994.

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D, Baust Henry, Agrell Johan, and NASA Glenn Research Center, eds. Management of total pressure recovery, distortion and high cycle fatigue in compact air vehicle inlets. National Aeronautics and Space Administration, Glenn Research Center, 2002.

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H, Anderson Bernhard, and United States. National Aeronautics and Space Administration., eds. A study on vortex flow control on inlet distortion in the re-engined 727-100 center inlet duct using computational fluid dynamics. National Aeronautics and Space Administration, 1992.

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1945-, Levy R., and United States. National Aeronautics and Space Administration., eds. A design strategy for the use of vortex generators to manage inlet-engine distortion using computational fluid dynamics. National Aeronautics and Space Administration, 1991.

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Center, Ames Research, ed. Sea level static calibration of a compact multimission aircraft propulsion simulator with inlet flow distortion. National Aeronautics and Space Administration, Ames Research Center, 1991.

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Części książek na temat "Inlet distortions"

Iseler, Jens, Andreas Lesser, and Reinhard Niehuis. "Numerical Investigation of a Transonic Axial Compressor Stage with Inlet Distortions." In High Performance Computing in Science and Engineering, Garching/Munich 2009. Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-13872-0_16.

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Kurzke, Joachim, and Ian Halliwell. "Inlet Flow Distortion." In Propulsion and Power. Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-75979-1_6.

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Kurzke, Joachim, Ian Halliwell, and Robert Hill. "Inlet Flow Distortion." In Propulsion and Power. Springer Nature Switzerland, 2025. https://doi.org/10.1007/978-3-031-65026-0_6.

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Wartzek, Fabian, Felix Holzinger, Christoph Brandstetter, and Heinz-Peter Schiffer. "Realistic Inlet Distortion Patterns Interacting with a Transonic Compressor Stage." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-21127-5_17.

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Qu, Yaoyao, and Xiaoqing Qiang. "Design and Test of an Aero-Engine Inlet Distortion Screen Facility." In Lecture Notes in Electrical Engineering. Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-99-0651-2_12.

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Theune, Marius, Dirk Schönweitz, and Rainer Schnell. "Sensitivity of a Low Pressure Ratio Jet Engine Fan to Inlet Distortion." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27279-5_6.

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Li, Ruiyu, Limin Gao, and Lei Zhao. "Application of DES-Series Method in Inlet Distortion Generator Flow Field Analysis." In Detached-Eddy Simulation Series Methods for Compressor Internal Flow. Springer Nature Singapore, 2025. https://doi.org/10.1007/978-981-96-0255-1_7.

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Zhang, Bohan, Qiang Wang, Haiyang Hu, and Yahua Zhang. "The Simulation of Compressor Performance of Inlet Distortion Using Split Actuator Disk Model." In Lecture Notes in Electrical Engineering. Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_23.

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Lesser, Andreas, Sonja Schulze, Reinhard Niehuis, Christian Kähler, and Jan Lieser. "Analytical Design of an Inlet Distortion Generator and Its Experimental and Numerical Validation." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-35680-3_5.

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Li, Jun, Youtian Zhou, and Guoxing Song. "Experimental and Numerical Studies on Compressor Nonlinear Behaviors with Inlet Distortion and Their Interaction." In Nonlinear Systems and Complexity. Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-94301-1_6.

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Streszczenia konferencji na temat "Inlet distortions"

Defoe, J. J., and D. K. Hall. "Fan Performance Scaling With Inlet Distortions." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-58009.

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Applications such as boundary-layer-ingesting fans, and compressors in turboprop engines require continuous operation with distorted inflow. A low-speed axial fan with incompressible flow is studied in this paper. Previous work in the literature has shown that the same flow mechanisms contributing to the response of a fan to distortion are at play in incompressible and transonic flows. The objective is to determine how fan performance scales as the type and severity of inlet distortion varies at the design flow coefficient. A distributed source term approach to modeling the rotor and stator bl

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Lesser, Andreas, and Reinhard Niehuis. "Transonic Axial Compressors With Total Pressure Inlet Flow Field Distortions." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-26627.

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Non-uniform inlet flow has come back into focus of research during the last years due to the need of increasing the operational range of airborne engines. Higher climbing rates for lower noise pollution at airports as well as boundary layer ingesting inlet designs lead to the demand of inlet distortion resistant engines and compressors, in particular. To fulfill this design task, a deep understanding of the dominant flow physics of the distortion transport through the compressor as well as the influence of the compressor on the upstream flow field is needed. This paper starts with the transpor

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Toracchio, Riccardo, Sina Stapelfeldt, Koen Hillewaert, and Fabrizio Fontaneto. "Forced Response Analysis of a Highly-Loaded Low-Pressure Compressor Stage With Inlet Distortions." In ASME Turbo Expo 2023: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2023. http://dx.doi.org/10.1115/gt2023-103881.

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Abstract Due to modern evolutions in propulsion, in view of obtaining higher propulsive efficiency, turbofan engines are subjected to ever higher inlet flow distortions. In these systems, structural damage can be induced by distortion patterns with excitation close to the blade natural frequency. To fill the gap currently present in literature about the impact of inlet distortions on the aeroelastic behaviour of engine components, this paper presents an aerodynamic damping and forced-response analysis on a highly-loaded axial compressor subjected to intake total pressure distortions. First, a

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Fortin, J., and W. C. Moffatt. "Inlet Flow Distortion Effects on Rotating Stall." In ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1990. http://dx.doi.org/10.1115/90-gt-215.

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For many years there has been a significant effort to better understand rotating stall/surge phenomena in axial compressors, as well as the effects of inlet flow distortions. Most experimental investigations to date, whether on laboratory compressors or on full scale jet engines, have tended to focus separately on the effects of these two flow disturbances on compressor performance. The purpose of the present study was to experimentally assess the influence of inlet flow distortions on the inception and nature of rotating stall in a full scale engine compressor. This paper reports results obta

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Longley, J. P., H. W. Shin, R. E. Plumley, et al. "Effects of Rotating Inlet Distortion on Multisage Compressor Stability." In ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1994. http://dx.doi.org/10.1115/94-gt-220.

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In multi-spool engines, rotating stall in an upstream compressor will impose a rotating distortion on the downstream compressor, thereby affecting its stability margin. In this paper experiments are described in which this effect was simulated by a rotating screen upstream of several multistage low-speed compressors. The measurements are complemented by, and compared with, a theoretical model of multistage compressor response to speed and direction of rotation of an inlet distortion. For co-rotating distortions (i.e., distortions rotating in the same direction as rotor rotation), experiments s

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Han, Fenghui, Jiajian Tan, Yijun Mao, Datong Qi, and Yiyun Zhang. "Effects of Flow Loss and Inlet Distortions Caused by Radial Inlet on the Performance of Centrifugal Compressor Stage." In ASME/JSME/KSME 2015 Joint Fluids Engineering Conference. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/ajkfluids2015-09693.

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Radial inlet is a typical upstream component in centrifugal compressors. Compared to axial inlet, radial inlet generates additional flow loss and introduces inlet distortions to the impeller inlet, which negatively impacts the performance of the whole centrifugal compressor. In this paper, two centrifugal compressor stages with different radial inlets were investigated with numerical simulations. Three computational models, (i) with radial inlet (ii) without flow loss and inlet distortions (iii) with flow loss but no inlet distortions, were built for each compressor stage, and calculations wer

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Pazur, Wolfram, and Leonhard Fottner. "The Influence of Inlet Swirl Distortions on the Performance of a Jet Propulsion Two-Stage Axial Compressor." In ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1990. http://dx.doi.org/10.1115/90-gt-147.

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Aeroengine intakes containing S-shaped diffusers produce different types of inlet swirl distortions and essentially a combination of a twin swirl and a bulk swirl. The main object of this investigation was to assess the influence of inlet swirl distortions on the performance of a transonic two-stage axial compressor installed in a turbo jet bypass engine Larzac 04. A typical inlet swirl distortion was simulated by a delta-wing in front of the engine. An experimental method was investigated to measure the performance map of the installed low pressure compressor for different engine operating li

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Sureshkumar, Prathiban, Kuen-Bae Lee, Ricardo Puente, and Sina Stapelfeldt. "Impact of the Spatial Arrangement of Inlet Distortions on Resonant Fan Response." In GPPS Chania22. GPPS, 2022. http://dx.doi.org/10.33737/gpps22-tc-132.

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Predicting the resonant forced response of aero-engine fans from inlet distortions in crosswind conditions is challenging, primarily due to the difficulty in correctly characterising and modelling the inlet distortion. To overcome this difficulty, an understanding of the distortion parameters which influence fan response is necessary. It is generally accepted that the amplitude of the total pressure distortion is an important factor. However, little is known about the importance of spatial arrangement of flow features in the intake. This paper hence presents a systematic study into the range o

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Hah, Chunill, Douglas C. Rabe, Thomas J. Sullivan, and Aspi R. Wadia. "Effects of Inlet Distortion on the Flow Field in a Transonic Compressor Rotor." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-547.

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The effects of circumferential distortions in inlet total pressure on the flow field in a low-aspect-ratio, high-speed, high-pressure-ratio, transonic compressor rotor are investigated in this paper. The flow field was studied experimentally and numerically with and without inlet total pressure distortion. Total pressure distortion was created by screens mounted upstream from the rotor inlet. Circumferential distortions of 8 periods per revolution were investigated at two different rotor speeds. The unsteady blade surface pressures were measured with miniature pressure transducers mounted in t

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Leinhos, Dirk C., Norbert R. Schmid, and Leonhard Fottner. "The Influence of Transient Inlet Distortions on the Instability Inception of a Low Pressure Compressor in a Turbofan Engine." In ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/2000-gt-0505.

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While studies on compressor flow instabilities under the presence of inlet distortions have been carried out with steady distortions in the past, the investigation presented here focuses on the influence of transient inlet distortions as generated by variable geometry engine intakes of super- and hypersonic aircrafts on the characteristic and the nature of the instability inception of a LPC. The flow patterns (total pressure distortion with a superimposed co- or counter-rotating swirl) of the distortions are adopted from a hypersonic concept aircraft. A LARZAC 04 twin-spool turbofan was operat

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Raporty organizacyjne na temat "Inlet distortions"

Sedlock, Dennis. Improved Statistical Analysis Method for Prediction of Maximum Inlet Distortion. Defense Technical Information Center, 1985. http://dx.doi.org/10.21236/ada153767.

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Martinez, Melissa. Visual Patching and Imaging Chambers. ConductScience, 2022. http://dx.doi.org/10.55157/cs20220507.

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Specimens obtained from brain slicing experiments, cell research, and skin studies are sensitive to temperature variations, humidity, and air quality. Proper temperature control is crucial to prevent cell distortion and necrosis, ensuring accurate observations and data collection. A visual patching and imaging chamber is introduced as a vital tool for maintaining optimal specimen temperature in behavioral, neuroimaging, and electrophysiological studies. The chamber features an aluminum heat exchanger plate with precise temperature control, gas inlet, and perfusate tubes. It's used in rodent re

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Davoudzadeh, F., N. S. Liu, S. J. Shamroth, and S. J. Thoren. A Navier-Stokes Study of Cascade Flow Fields Including Inlet Distortion and Rotating Stall. Defense Technical Information Center, 1987. http://dx.doi.org/10.21236/ada193109.

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Bidier, S., U. Khristenko, A. Kodakkal, C. Soriano, and R. Rossi. D7.4 Final report on Stochastic Optimization results. Scipedia, 2022. http://dx.doi.org/10.23967/exaqute.2022.3.02.

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This deliverable report focuses on the final stochastic optimization results obtained within the EXAscale Quantification of Uncertainties for Technology and Science Simulation (ExaQUte) project. Details on a novel wind inlet generator that is able to incorporate local wind-field data through a deep-learned rapid distortion model and generates the turbulent wind data during run-time is presented in section 2. Section 3 presents the results of the overall stochastic optimization procedure applied to a twisted tapered tower with multiple design parameters within an uncertain synthetic wind field.

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