Tesis sobre el tema "Inlet distortions"
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Guimaraes, Bucalo Tamara. "Fluid Dynamics of Inlet Swirl Distortions for Turbofan Engine Research". Diss., Virginia Tech, 2018. http://hdl.handle.net/10919/82921.
Texto completoPh. D.
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.
Texto completo"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 results demonstrated the first-of-a-kind capability for simulating short wavelength stall inception in multistage compressors. The adequacy of the model is demonstrated by its application to reproduce the following phenomena: (1) response of a compressor to a square-wave total pressure inlet distortion; (2) behavior of long wavelength small amplitude disturbances in compressors; (3) short wavelength stall inception in a multistage compressor and the occurrence of rotating stall inception on the negatively sloped portion of the compressor characteristic; ( 4) progressive stalling behavior in the first stage in a mismatched multistage compressor; (5) change of stall inception type (from modal to spike and vice versa) due to IGV stagger angle variation, and "unique rotor tip incidences at these points where the compressor stalls through short wavelength disturbances. The model has been applied to determine the parametric dependence of instability inception behavior in terms of amplitude and spatial distribution of initial disturbance, and intra-blade-row gaps. It is found that reducing the inter-blade row gaps suppresses the growth of short wavelength disturbances. It is also concluded from these parametric investigations that each local component group (rotor and its two adjacent stators) has its own instability point (i.e. conditions at which disturbances are sustained) for short wavelength disturbances, with the instability point for the compressor set by the most unstable component group. For completeness, the methodology has been extended to describe finite amplitude disturbances in high-speed compressors. Results are presented for the response of a transonic compressor subjected to inlet distortions.
by Yifang Gong.
Ph.D.
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.
Texto completoMaster of Science
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.
Texto completoLambie, David. "Inlet distortion and turbofan engines". Thesis, University of Cambridge, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.305300.
Texto completoLongley, John Peter. "Inlet distortion and compressor stability". Thesis, University of Cambridge, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.304354.
Texto completoHoopes, Kevin M. "A New Method for Generating Swirl Inlet Distortion for Jet Engine Research". Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/49545.
Texto completoA new method capable of recreating any arbitrary swirl distortion profile is needed in order to expand the capabilities of inlet distortion testing. This will allow designers to explore how an engine would react to a particular engine airframe combination as well as methods for creating swirl distortion tolerant engines. The following material will present such a method as well as experimental validation of its effectiveness.
Master of Science
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.
Texto completoIn civil aviation, the increasing exploration of innovative engine systems – such as ultra-high bypass ratio turbofan or open-rotor – and breakthrough engine-integration architectures – such as distributed propulsion or boundary-layer ingestion – require a coupled modeling of the aerodynamic and propulsion subsystems from the earliest design stages. Body-force models have proven capable of faithfully reproducing most of the coupling phenomena, such as the engine response to inlet flow distortions, at reduced computational cost. However, they lack an adjoint formulation to be efficiently used in gradient-based optimizations. The present PhD thesis focuses on the development of an adjoint approach for explicit body-force models. First, aero-propulsive optimizations of an academic distributed propulsion configuration are conducted using a lumped body-force model. Despite the simplicity of this model (of interest for conceptual design studies), 10.5% decrease in power consumption is achieved. Then the potential of this new methodology is investigated for the preliminary optimization of compressor stages, at first under clean inflow conditions. The Hall body-force model is considered for such purpose. The comparison of the blade shape gradients computed by the adjoint body-force with high-fidelity ones, obtained from blade-resolved computations, shows very good prediction for the rotor. This is observed over a large portion of the compressor characteristic, especially between near-design and surge operating conditions, while accuracy is reduced near the blockage. On the contrary, for stator shape gradients, only flow misalignment effects can be captured. At design conditions, the improvement of the compressor efficiency obtained by the adjoint body-force optimization has been confirmed through high-fidelity simulations. Optimization under radial inlet distortion are then investigated. Once again, the adjoint body-force approach is found capable of enhancing the compressor performances, by adapting its geometry to the off-design inflow conditions. According to high-fidelity analysis of the body-force optimized blade geometry, an increase in compressor isentropic efficiency between 1.16 and 1.47% is achieved, given the formulation of the optimization problem. Finally, an optimization of the compressor under full-annulus inlet distortion is conducted leading to very promising results, which are consistent with those found in the literature using advanced simulations
Van, Schalkwyk Christiaan Mauritz. "Active control rotating stall with inlet distortion". Thesis, Massachusetts Institute of Technology, 1996. http://hdl.handle.net/1721.1/10827.
Texto completoIncludes bibliographical references (p. 179-182).
by Christiaan Mauritz Van Schalkwyk.
Ph.D.
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.
Texto completoShang, Tonghuo. "Influence of inlet temperature distortion on turbine heat transfer". Thesis, Massachusetts Institute of Technology, 1995. http://hdl.handle.net/1721.1/47370.
Texto completoRyman, John Franklin. "Prediction of Inlet Distortion Transfer Through the Blade Rows in a Transonic Axial Compressor". Thesis, Virginia Tech, 2003. http://hdl.handle.net/10919/43207.
Texto completoMaster of Science
Zemp, Armin. "CFD investigation on inlet flow distortion in a centrifugal compressor". Zürich : Swiss Federal Institute of Technology, Turbomachinery Laboratory, 2007. http://e-collection.ethbib.ethz.ch/show?type=dipl&nr=308.
Texto completoSchulmeyer, Andreas. "Enhanced compressor distortion tolerance using asymmetric inlet guide vane stagger". Thesis, Massachusetts Institute of Technology, 1989. http://hdl.handle.net/1721.1/40144.
Texto completoFrohnapfel, Dustin Joseph. "Experimental Investigation of Fan Rotor Response to Inlet Swirl Distortion". Thesis, Virginia Tech, 2016. http://hdl.handle.net/10919/71323.
Texto completoMaster of Science
Lucas, James Redmond. "Effect of BLI-Type Inlet Distortion on Turbofan Engine Performance". Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/23272.
Texto completoFlow measurements at the AIP and the bypass nozzle exit plane provided information about the losses throughout the fan flow path. The presence of the distortion screen resulted in a 24% increase in mass-averaged entropy production along the entire fan flow path compared to the non-distorted test. A mass-averaged fan flow path efficiency was also calculated assuming an isentropic process as ideal. The non-distorted fan flow path efficiency was computed to be 60%, while the distorted fan flow path efficiency was computed to be 50.5%, a reduction in efficiency of 9.5%. The entropy generation between ambient conditions and the AIP was compared to the entropy production along the entire fan flow path. It was found that the majority of entropy generation occurred between the AIP and bypass nozzle exit. Based on flow measurements at the bypass nozzle exit plane, it was concluded that inlet flow distortion should be located away from the tip region of the fan in order to minimize losses in a very lossy region. It was also determined that the fan and bypass duct process the different regions of the total pressure distortion in different ways. In some regions the entropy production decreased for the distorted test compared to the clean test, while in other regions the entropy production increased for the distorted test compared to the clean test. Finally, it was found that small improvements in total pressure and total temperature variation at the bypass nozzle exit plane will greatly improve the fan flow path efficiency and entropy generation, thereby decreasing performance losses.
Master of Science
Smith, Katherine Nicole. "New Methodology for the Estimation of StreamVane Design Flow Profiles". Thesis, Virginia Tech, 2018. http://hdl.handle.net/10919/82039.
Texto completoMaster of Science
Orme, Andrew Dallin. "Analysis of Inlet Distortion Patterns on Distortion Transfer and Generation Through a Highly Loaded Fan Stage". BYU ScholarsArchive, 2020. https://scholarsarchive.byu.edu/etd/8649.
Texto completoBaig, Aman uz zaman. "Adjoint Design Optimization for Boundary Layer Ingesting Inlet Guide Vanes with Distorted Inlet Profiles in SU2". University of Cincinnati / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1613686047734509.
Texto completoAnderson, Jason Mitchell. "Non-Intrusive Sensing and Feedback Control of Serpentine Inlet Flow Distortion". Diss., Virginia Tech, 2003. http://hdl.handle.net/10919/27120.
Texto completoPh. D.
Warfield, Zachary (Zachary Greene) 1976. "Active control of separation induced distortion in a scaled tactial aircraft inlet". Thesis, Massachusetts Institute of Technology, 2001. http://hdl.handle.net/1721.1/82237.
Texto completoWalter, S. F. "Optimization of pressure probe placement and data analysis of engine-inlet distortion". Thesis, University of Colorado at Boulder, 2017. http://pqdtopen.proquest.com/#viewpdf?dispub=10244536.
Texto completoThe purpose of this research is to examine methods by which quantification of inlet flow distortion may be improved upon. Specifically, this research investigates how data interpolation effects results, optimizing sampling locations of the flow, and determining the sensitivity related to how many sample locations there are. The main parameters that are indicative of a "good" design are total pressure recovery, mass flow capture, and distortion. This work focuses on the total pressure distortion, which describes the amount of non-uniformity that exists in the flow as it enters the engine. All engines must tolerate some level of distortion, however too much distortion can cause the engine to stall or the inlet to unstart. Flow distortion is measured at the interface between the inlet and the engine.
To determine inlet flow distortion, a combination of computational and experimental pressure data is generated and then collapsed into an index that indicates the amount of distortion. Computational simulations generate continuous contour maps, but experimental data is discrete. Researchers require continuous contour maps to evaluate the overall distortion pattern. There is no guidance on how to best manipulate discrete points into a continuous pattern. Using one experimental, 320 probe data set and one, 320 point computational data set with three test runs each, this work compares the pressure results obtained using all 320 points of data from the original sets, both quantitatively and qualitatively, with results derived from selecting 40 grid point subsets and interpolating to 320 grid points. Each of the two, 40 point sets were interpolated to 320 grid points using four different interpolation methods in an attempt to establish the best method for interpolating small sets of data into an accurate, continuous contour map. Interpolation methods investigated are bilinear, spline, and Kriging in Cartesian space, as well as angular in polar space. Spline interpolation methods should be used as they result in the most accurate, precise, and visually correct predictions when compared results achieved from the full data sets.
Researchers were interested if fewer than the recommended 40 probes could be used – especially when placed in areas of high interest - but still obtain equivalent or better results. For this investigation, the computational results from a two-dimensional inlet and experimental results of an axisymmetric inlet were used. To find the areas of interest, a uniform sampling of all possible locations was run through a Monte Carlo simulation with a varying number of probes. A probability density function of the resultant distortion index was plotted. Certain probes are required to come within the desired accuracy level of the distortion index based on the full data set. For the experimental results, all three test cases could be characterized with 20 probes. For the axisymmetric inlet, placing 40 probes in select locations could get the results for parameters of interest within less than 10% of the exact solution for almost all cases. For the two dimensional inlet, the results were not as clear. 80 probes were required to get within 10% of the exact solution for all run numbers, although this is largely due to the small value of the exact result.
The sensitivity of each probe added to the experiment was analyzed. Instead of looking at the overall pattern established by optimizing probe placements, the focus is on varying the number of sampled probes from 20 to 40. The number of points falling within a 1\% tolerance band of the exact solution were counted as good points. The results were normalized for each data set and a general sensitivity function was found to determine the sensitivity of the results. A linear regression was used to generalize the results for all data sets used in this work. However, they can be used by directly comparing the number of good points obtained with various numbers of probes as well. The sensitivity in the results is higher when fewer probes are used and gradually tapers off near 40 probes. There is a bigger gain in good points when the number of probes is increased from 20 to 21 probes than from 39 to 40 probes.
Wallace, Robert Malcolm. "Modal Response of a Transonic Fan Blade to Periodic Inlet Pressure Distortion". Thesis, Virginia Tech, 2003. http://hdl.handle.net/10919/35158.
Texto completoMaster of Science
Reilly, Daniel Oliver. "Inlet Distortion Effects on the Unsteady Aerodynamics of a Transonic Fan Stage". Wright State University / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=wright1482139741887976.
Texto completoHorvath, Nathan Rosendo. "Inlet Vortex Formation Under Crosswind Conditions". Digital WPI, 2013. https://digitalcommons.wpi.edu/etd-theses/302.
Texto completoRabe, Angela C. "Effectiveness of a Serpentine Inlet Duct Flow Control Scheme at Design and Off-Design Simulated Flight Conditions". Diss., Virginia Tech, 2003. http://hdl.handle.net/10919/28653.
Texto completoPh. D.
Kozak, Jeffrey D. "3-D flow calculations of a bifurcated 2D supersonic engine inlet at takeoff". Thesis, This resource online, 1995. http://scholar.lib.vt.edu/theses/available/etd-03032009-040729/.
Texto completoChan, Keen Ian 1972. "An assessment of computational procedures for eleven-stage compressor response to inlet distortion". Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/82766.
Texto completoGraf, Martin Bowyer. "Investigation of the effect of radial inlet temperature distortion on turbine heat transfer". Thesis, Massachusetts Institute of Technology, 1993. http://hdl.handle.net/1721.1/12359.
Texto completoStrang, Eric James. "Influence of unsteady losses and deviations on compression system stability with inlet distortion". Thesis, Massachusetts Institute of Technology, 1991. http://hdl.handle.net/1721.1/42511.
Texto completoSpakovszky, Zoltán S. (Zoltán Sándor) 1972. "Active control of rotating stall in a transonic compressor stage with inlet distortion". Thesis, Massachusetts Institute of Technology, 1999. http://hdl.handle.net/1721.1/50522.
Texto completoIncludes bibliographical references (p. 101-103).
Rotating stall has been stabilized in a single-stage transonic axial flow compressor with inlet distortion using active feedback control. The experiments were conducted at the NASA Lewis Research Center on a single-stage transonic core compressor. An annular array of 12 jet-injectors located upstream of the rotor tip was used for forced response testing and to extend the compressor stable operating range. Results for radial and circumferential inlet distortion are reported. First, the effects of radial distortion on the compressor performance and the dynamic behavior were investigated. Control laws were designed using empirical transfer function estimates determined from forced response results. The transfer functions indicated that the compressor dynamics are decoupled with radial inlet distortion, as they are for the case of undistorted inlet flow. Single- input-single-output (SISO) control strategies were therefore used for the radial distortion controller designs. A circumferential total pressure distortion of about one dynamic head and a 120' extent (DC(60) = 0.61) introduced coupling between the harmonics of circumferential pressure perturbations, requiring multi-variable (MIMO) identification and control design techniques. A careful analysis of the coupled pre-stall compressor dynamics revealed a strong first spatial harmonic, dominated by the well known incompressible Moore-Greitzer mode. Constant gain control and more sophisticated MIMO robust control strategies were used for stabilization with circumferential inlet distortion. Steady axisymmetric injection of 4% of the compressor mass flow resulted in a reduction in stalling mass flow of 9.7% relative to the case with radial inlet distortion and no injection. Use of a robust H, controller with unsteady non-axisymmetric injection achieved a further reduction in stalling mass flow of 7.5%, resulting in a total reduction of 17.2%. Steady injection experiments with circumferential inlet distortion resulted in a 6.2% reduction of stalling mass flow. Constant gain feedback, using unsteady asymmetric injection, yielded a further range extension of 9%. Testing of MIMO robust controllers showed only 2% reduction in stalling mass flow. Instead of further tuning the complex MIMO controllers, the same robust H. controller used for radial distortion was tested. This controller achieved a reduction in stalling mass flow of 10.2% relative to steady injection, yielding a total reduction in stalling mass flow of 16.4%.
by Zoltán S. Spakovszky.
S.M.
Ferrar, Anthony Maurice. "Measurement and Uncertainty Analysis of Transonic Fan Response to Total Pressure Inlet Distortion". Diss., Virginia Tech, 2015. http://hdl.handle.net/10919/51747.
Texto completoPh. D.
Unrau, Mikkel Andreas. "Analysis of the Effects of Inlet Distortion on Stall Cell Formation in a Transonic Compressor Using CREATE-AV Kestrel". BYU ScholarsArchive, 2018. https://scholarsarchive.byu.edu/etd/7712.
Texto completoBoller, Shaun M. "One-Dimensional Dynamic Wake Response in an Isolated Rotor due to Inlet Total Pressure Distortion". Thesis, Virginia Tech, 1998. http://hdl.handle.net/10919/9587.
Texto completoMaster of Science
Weston, David Bruce. "High Fidelity Time Accurate CFD Analysis of a Multi-stage Turbofan at Various Operating Points in Distorted Inflow". BYU ScholarsArchive, 2014. https://scholarsarchive.byu.edu/etd/5604.
Texto completoFarge, Talib Z. "The effect of tip leakage, backswept blades and inlet distortion on centrifugal compressor flow". Thesis, University of Liverpool, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.304987.
Texto completoDefoe, Jeff (Jeffrey James). "Inlet swirl distortion effects on the generation and propagation of fan rotor shock noise". Thesis, Massachusetts Institute of Technology, 2011. http://hdl.handle.net/1721.1/68404.
Texto completoCataloged from PDF version of thesis.
Includes bibliographical references (p. 195-200).
A body-force-based fan model for the prediction of multiple-pure-tone noise generation is developed in this thesis. The model eliminates the need for a full-wheel, three-dimensional unsteady RANS simulation of the fan blade row, allowing Euler calculations to be used to capture the phenomena of interest. The Euler calculations reduce numerical wave dissipation and enable the simultaneous computation of source noise generation and propagation through the engine inlet to the far-field in non-uniform flow. The generated shock Mach numbers are in good agreement with experimental results, with the peak values predicted within 6%. An assessment of the far-field acoustics against experimental data showed agreement of 8 dB on average for the blade-passing tone. In a first-of-its-kind comparison, noise generation and propagation are computed for a fan installed in a conventional inlet and in a boundary-layer-ingesting serpentine inlet for a free-stream Mach number of 0.1. The key effect of boundary layer ingestion is the creation of streamwise vorticity which is ingested into the inlet, resulting in co- and counter-rotating streamwise vortices in the inlet. The fan sound power level increases by 38 dB due to this distortion, while the vortex whose circulation is in the same direction as the fan rotation enhances the sound power attenuation within the inlet duct such that the far-field overall sound pressure levels are increased by only 7 dB on average. The far-field spectra are altered in the following manner due to inlet distortion: (1) tones at up to 3 times the blade-passing frequency are amplified; and (2) tones above one-half of the blade-passing frequency are attenuated and appear to be cut-off. To quantify the effects of serpentine inlet duct geometry on the generation and propagation of multiple-pure-tone noise, a parametric study of inlets is conducted. The conclusions are that (1) the ingestion of streamwise vorticity alters multiple-pure-tone noise more than changes in inlet area ratio or offset ratio do; and (2) changes in the far-field spectra relative to the conventional inlet results are only weakly affected by the duct geometry changes investigated and are instead predominantly caused by flow non-uniformities. A response-surface correlation for the effects of inlet geometry on far-field noise is also developed.
by Jeff Defoe.
Ph.D.
Hale, Alan A. "A three-dimensional turbine engine analysis compressor code (TEACC) for steady-state inlet distortion". Diss., This resource online, 1996. http://scholar.lib.vt.edu/theses/available/etd-06062008-154548/.
Texto completoTraore, Abdoulaye S. "Mixed Network Interference Management with Multi-Distortion Measures". International Foundation for Telemetering, 2010. http://hdl.handle.net/10150/604294.
Texto completoThis paper presents a methodology for the management of interference and spectrum for iNET. It anticipates a need for heavily loaded test environments with Test Articles (TAs) operating over the horizon. In such cases, it is anticipated that fixed and ad hoc networks will be employed, and where spectrum reuse and interference will limit performance. The methodology presented here demonstrates how this can be accomplished in mixed networks.
Nelson, Michael Allan. "Stereoscopic Particle Image Velocimetry Measurements of Swirl Distortion on a Full-Scale Turbofan Engine Inlet". Thesis, Virginia Tech, 2014. http://hdl.handle.net/10919/64993.
Texto completoMaster of Science
Kennedy, Stefan Andrew. "A computational investigation into the effects of lipskin damage on inlet flow distortion in aircraft engines". Thesis, Queen's University Belfast, 2011. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.557636.
Texto completoFrohnapfel, Dustin Joseph. "Methodology Development and Investigation of Turbofan Engine Response to Simultaneous Inlet Total Pressure and Swirl Distortion". Diss., Virginia Tech, 2019. http://hdl.handle.net/10919/88866.
Texto completoDoctor of Philosophy
As a contribution to advancing turbofan engine ground test technology in support of propulsion system integration in modern conceptual aircraft, a novel inlet distortion generator (ScreenVaneTM) was invented. The device simultaneously reproduces combined inlet total pressure and swirl distortion elements in a tailored profile intended to match a defined turbofan engine inlet distortion profile. The device design methodology was intended to be sufficiently generic to be utilized in support of any arbitrary inlet distortion profile yet adequately specific to generate high-fidelity inlet distortion profile simulation. For the current investigation, a specific inlet distortion profile was defined using computational analysis of a conceptual boundary layer ingesting S-duct turbofan engine inlet. The resulting inlet distortion profile, consisting of both total pressure and swirl distortion elements, was used as the objective profile to be matched by the ScreenVane in a turbofan engine ground test facility. A ScreenVane combined inlet total pressure and swirl distortion generator was designed, computationally analyzed, and experimentally validated. The design process involved specifying a total pressure loss screen pattern and organizing a unique arrangement of swirl inducing turning vanes. Computational and experimental results indicated that the ScreenVane manufactured distortion profile matched the predicted S-duct turbofan engine inlet manufactured distortion profile with excellent agreement in pattern shape, extent, and intensity. Following the successful reproduction of the S-duct turbofan engine inlet manufactured distortion profile, a turbofan engine response evaluation was conducted using the validated ScreenVane inlet distortion generator. Flow measurements collected at discrete planes immediately upstream and downstream of the fan rotor isolated the component for performance analysis. Based on the results of this particular engine and distortion investigation, the adiabatic fan efficiency was negligibly altered while operating with distorted inflow conditions when compared to nominal inflow conditions. Fuel flow measurements indicated that turbofan engine inlet air mass flow specific fuel consumption increased in the presence of distortion. While a single, specific turbofan engine inlet distortion profile was studied in this investigation, the ScreenVane methodology, design practices, analysis approaches, manufacturing techniques, and experimental procedures are applicable to any arbitrary, realistic combined inlet total pressure and swirl distortion.
Ferrar, Anthony Maurice. "Measurements of Flow in Boundary Layer Ingesting Serpentine Inlets". Thesis, Virginia Tech, 2011. http://hdl.handle.net/10919/36408.
Texto completoMaster of Science
Eddy, Grant Lee. "Study of Steady-State Wake Characteristics of Variable Angle Wedges". Thesis, Virginia Tech, 2001. http://hdl.handle.net/10919/35205.
Texto completoMaster of Science
Schwartz, Jeffrey R. "An Experimental and Analytical Investigation of Dynamic Flow Response of a Fan Rotor with Distorted Inlet Flow". Thesis, Virginia Tech, 1999. http://hdl.handle.net/10919/44314.
Texto completoMaster of Science
Barton, Scott Andrew. "An experimental investigation of the influence of inlet distortion on the fluid borne noise of a centrifugal pump". Thesis, Massachusetts Institute of Technology, 1991. http://hdl.handle.net/1721.1/33251.
Texto completoPeterson, Marshall Warren. "Implementations of Fourier Methods in CFD to Analyze Distortion Transfer and Generation Through a Transonic Fan". BYU ScholarsArchive, 2016. https://scholarsarchive.byu.edu/etd/6384.
Texto completoHylton, Michael Ronnie. "Assessment of an Innovative Experimental Facility for Testing Diffusing Serpentine Inlets with Large Amounts of Boundary Layer Ingestion". Thesis, Virginia Tech, 2008. http://hdl.handle.net/10919/33969.
Texto completoMaster of Science
List, Michael G. "Numerical Quantification of Interaction Effects in a Closely-Coupled Diffuser-Fan System". University of Cincinnati / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1396530464.
Texto completoNovikov, Yaroslav. "Development Of A High-fidelity Transient Aerothermal Model For A Helicopter Turboshaft Engine For Inlet Distortion And Engine Deterioration Simulations". Master's thesis, METU, 2012. http://etd.lib.metu.edu.tr/upload/12614389/index.pdf.
Texto completo