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Autor: Grafiati

Data publikacji: 7 grudnia 2024

Data aktualizacji: 31 lipca 2025

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1

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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2

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.<br>"February 1999."<br>Includes bibliographical references (p. 175-182).<br>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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3

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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4

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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5

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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6

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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7

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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8

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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9

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.<br>Includes bibliographical references (p. 179-182).<br>by Christiaan Mauritz Van Schalkwyk.<br>Ph.D.

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10

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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11

Shang, Tonghuo. "Influence of inlet temperature distortion on turbine heat transfer." Thesis, Massachusetts Institute of Technology, 1995. http://hdl.handle.net/1721.1/47370.

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12

Ryman, 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.

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Inlet total pressure non-uniformities in axial flow fans and compressors can contribute to the loss of component structural integrity through high cycle fatigue (HCF) induced by the excitation of blade vibratory modes. As previous research has shown total pressure distortion to be the dominant HCF driver in aero engines [Manwaring et al, 1997], an understanding of its transfer through, and impact on, subsequent turbomachine stages and engine components is an important topic for assessment. Since current modeling techniques allow for total pressure distortion magnitudes to be directly related

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13

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.

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14

Schulmeyer, Andreas. "Enhanced compressor distortion tolerance using asymmetric inlet guide vane stagger." Thesis, Massachusetts Institute of Technology, 1989. http://hdl.handle.net/1721.1/40144.

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15

Frohnapfel, Dustin Joseph. "Experimental Investigation of Fan Rotor Response to Inlet Swirl Distortion." Thesis, Virginia Tech, 2016. http://hdl.handle.net/10919/71323.

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Next generation aircraft design focuses on highly integrated airframe/engine architectures that exploit advantages in system level efficiency and performance. One such design concept incorporates boundary layer ingestion which locates the turbofan engine inlet near enough to the lifting surface of the aircraft skin that the boundary layer is ingested and reenergized. This process reduces overall aircraft drag and associated required thrust, resulting in fuel savings and decreased emissions; however, boundary layer ingestion also creates unique challenges for the turbofan engines operating in

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16

Lucas, James Redmond. "Effect of BLI-Type Inlet Distortion on Turbofan Engine Performance." Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/23272.

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Boundary Layer Ingestion (BLI) is currently being researched as a potential method to improve efficiency and decrease emissions for the next generation of commercial aircraft. While re-energizing the boundary layer formed over the fuselage of an aircraft has many system level benefits, ingesting the low velocity boundary layer flow through a serpentine inlet into a turbofan engine adversely affects the performance of the engine. The available literature has only yielded studies of the effects of this specific type of inlet distortion on engine performance in the form of numerical simulations

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17

Smith, Katherine Nicole. "New Methodology for the Estimation of StreamVane Design Flow Profiles." Thesis, Virginia Tech, 2018. http://hdl.handle.net/10919/82039.

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Inlet distortion research has become increasingly important over the past several years as demands for aircraft flight efficiency and performance has increased. To accommodate these demands, research progression has shifted the emphasis onto airframe-engine integration and improved understanding of engine operability in less than ideal conditions. Swirl distortion, which is considered a type of non-uniform inflow inlet distortion, is characterized by the presence of swirling flow in an inlet. The presence of swirling flow entering an engine can affect the compression systems performance and op

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18

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.

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Characterization of distortion transfer and generation through fans with distorted inlet conditions enables progress towards designs with improved distortion tolerance. The abruptness of transition from undistorted to distorted total pressure regions at the inlet impacts the induced swirl profile and therefore the distortion transfer and generation. These impacts are characterized using URANS simulations of PBS Rotor 4 geometry under a variety of inlet distortion profiles. A 90° and a 135° sector, both of 15% total pressure distortion, are considered. Variants of each sector size, with decreas

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19

Baig, 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.

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20

Anderson, Jason Mitchell. "Non-Intrusive Sensing and Feedback Control of Serpentine Inlet Flow Distortion." Diss., Virginia Tech, 2003. http://hdl.handle.net/10919/27120.

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A technique to infer circumferential total pressure distortion intensity found in serpentine inlet airflow was established using wall-pressure fluctuation measurements. This sensing technique was experimentally developed for aircraft with serpentine inlets in a symmetric, level flight condition. The turbulence carried by the secondary flow field that creates the non-uniform total pressure distribution at the compressor fan-face was discovered to be an excellent indicator of the distortion intensity. A basic understanding of the secondary flow field allowed for strategic sensor placement to

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21

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.

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22

Walter, 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.

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<p> The 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. A

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23

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.

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A new method for predicting forced vibratory blade response to total pressure distortion has been developed using modal and harmonic analysis. Total pressure distortions occur in gas turbine engines when the incoming airflow is partially blocked or disturbed. Distorted inlet conditions can have varying effects on engine performance and engine life. Short-term effects are often in the form of performance degradation where the distorted airflow causes a loss in pressure rise, and a reduction in mass flow and stall margin. Long-term effects are a result of vibratory blade response that can ul

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24

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.

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25

Horvath, Nathan Rosendo. "Inlet Vortex Formation Under Crosswind Conditions." Digital WPI, 2013. https://digitalcommons.wpi.edu/etd-theses/302.

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A jet engine operating near the ground at low aircraft speeds, high thrust, and subject to a crosswind, can experience a flow separation region on the windward inlet lip and the formation of a vortex that extends from the ground to the engine fan face, known as the inlet vortex. This structure forms from a single point on the ground and is ingested by the engine. Inlet vortices are often observed during engine power-up at the start of the take-off run. They create considerable stagnation pressure losses and flow distortions at the engine fan face, compromising fan efficiency, thrust, and incre

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26

Rabe, 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.

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An experimental investigation was conducted in a static ground test facility to determine the flow quality of a serpentine inlet duct incorporating active flow control for several simulated flight conditions. The total pressure distortion at the aerodynamic interface plane (AIP) was then used to predict the resulting stability for a compression system. This study was conducted using a model of a compact, low observable, engine inlet duct developed by Lockheed Martin. A flow control technique using air injection through microjets at 1% of the inlet mass flow rate was developed by Lockheed Ma

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27

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/.

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28

Chan, 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.

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29

Graf, 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.

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30

Strang, 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.

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31

Spakovszky, 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.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999.<br>Includes bibliographical references (p. 101-103).<br>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 circumferenti

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32

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.

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Distortion tolerant fans represent the enabling technology for the successful implementation of highly integrated airframe propulsion system vehicles. This investigation extends the study of fan-distortion interactions to an actual turbofan engine with a total pressure distortion profile representative of a boundary-layer ingesting (BLI) embedded engine. The goal was to make a series of flow measurements that contribute to the overall physical understanding of this complex flow situation. Proper uncertainty analysis is critical to extracting meaning from the data measured in this study. The i

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33

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.

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Accurately predicting fan performance, including bounds of operation, is an important function of any Computational Fluid Dynamics (CFD) package. The presented research uses a CFD code developed as part of the Computational Research and Engineering Acquisition Tools and Environment (CREATE), known as Kestrel, to evaluate a single stage compressor at various operating conditions. Steady-state, single-passage simulations are carried out to validate capabilities recently added to Kestrel. The analysis includes generating speedlines of total pressure ratio and efficiency, as well as radial total t

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34

Boller, 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.

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An experimental investigation of the wake of a low-speed axial-flow compressor rotor was conducted with and without the presence of steady inlet total pressure distortions. The steady three-dimensional rotor inlet flow was obtained by a five-hole pneumatic pressure probe, while the one-dimensional rotor exit data were obtained using a piggyback steady/unsteady total pressure probe in non-nulling mode. Both inlet and exit flow conditions were measured in the stationary frame of reference. Results indicate increases in wake thickness and magnitude of total pressure defect as blade loading inc

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35

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.

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Inlet distortion is an important consideration in fan performance. Distortion can be caused through flight conditions and airframe-engine interfaces. The focus of this paper is a series of high-fidelity time accurate Computational Fluid Dynamics (CFD) simulations of a multistage fan. These investigate distortion transfer and generation as well as the underlying flow physics of these phenomena under different operating conditions. The simulations are performed on the full annulus of a 3 stage fan. The code used to carry out these simulations is a modified version of OVERFLOW 2.2 developed as

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36

Farge, 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.

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37

Defoe, 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.

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Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2011.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (p. 195-200).<br>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

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38

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/.

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39

Traore, Abdoulaye S. "Mixed Network Interference Management with Multi-Distortion Measures." International Foundation for Telemetering, 2010. http://hdl.handle.net/10150/604294.

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ITC/USA 2010 Conference Proceedings / The Forty-Sixth Annual International Telemetering Conference and Technical Exhibition / October 25-28, 2010 / Town and Country Resort & Convention Center, San Diego, California<br>This 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

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40

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.

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There is a present need for simulation and measuring the inlet swirl distortion generated by airframe/engine system interactions to identify potential degradation in fan performance and operability in a full-scale, ground testing environment. Efforts are described to address this need by developing and characterizing methods for complex, prescribed distortion patterns. A relevant inlet swirl distortion profile that mimics boundary layer ingesting inlets was generated by a novel new method, dubbed the StreamVane method, and measured in a sub scale tunnel using stereoscopic particle image veloci

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41

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.

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Damage to the lipskin of an engine nacelle can have a significant impact on engine performance and safety, especially in combination with other sources of inlet flow distortion. While the degradation of performance in aircraft propulsion systems as a result of inlet distortion has been well-studied, the impact of lipskln damage upon inlet distortion levels is not well understood. Current practice can result in the grounding of aircraft in order to perform repairs if the damage exceeds the specified tolerance in size and the position on the lip, with these tolerances varying from aircraft to ai

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42

Frohnapfel, 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.

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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 distor

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43

Ferrar, Anthony Maurice. "Measurements of Flow in Boundary Layer Ingesting Serpentine Inlets." Thesis, Virginia Tech, 2011. http://hdl.handle.net/10919/36408.

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Highly integrated airframe-propulsion systems featuring ingestion of the airframe boundary layer oer reduced noise, emissions, and fuel consumption. Embedded engine systems are envisioned which require boundary layer ingesting (BLI) serpentine inlets to provide the needed air ow to the engine. These inlets produce distorted ow proles that can cause aeromechanical, stability, and performance changes in embedded engines. Proper design of embedded engine systems requires understanding of the underlying uid dynamics that occur within serpentine inlets. A serpentine inlet was tested in a speciall

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44

Eddy, Grant Lee. "Study of Steady-State Wake Characteristics of Variable Angle Wedges." Thesis, Virginia Tech, 2001. http://hdl.handle.net/10919/35205.

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Current methods of creating inlet total pressure distortion for testing in gas turbine engines are only able to simulate steady-state distortion patterns. With modern military aircraft it is becoming necessary to examine the effects of transient inlet distortion on engines. One alternative being evaluated is a splitting airfoil that is essentially a wedge that can be set at different opening angles. An array of such devices would be placed in front of the engine for testing that would be capable of creating steady-state distortion patterns as well as transient distortion patterns by changin

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45

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.

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An experimental and analytical investigation was conducted to gain insight and ultimately predict the dynamic flow response of a fan rotor with inlet flow distortion. Rotor exit total pressure circumferential profiles were accurately predicted using frequency response functions derived from experimental rotor response data. Using these predicted profiles, an initial attempt was made at predicting the dynamic (distorted) stage characteristics of the test machine with promising results. The first step of this research was an experimental investigation to gather unsteady rotor response data.

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46

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.

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47

Peterson, 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.

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Inlet flow distortion is a non-uniform total pressure, total temperature, or swirl (flow angularity) condition at an aircraft engine inlet. Inlet distortion is a critical consideration in modern fan and compressor design. This is especially true as the industry continues to increase the efficiency and operating range of air breathing gas turbine engines. The focus of this paper is to evaluate the Computational Fluid Dynamics (CFD) Harmonic Balance (HB) solver in STAR-CCM+ as a reduced order method for capturing inlet distortion as well as the associated distortion transfer and generation. New

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48

Hylton, 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.

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An innovative experimental facility was developed for testing flush-mounted, diffusing serpentine inlets intended for use on blended-wing-body aircraft. The static ground test facility was able to simulate the boundary layer profile expected to be ingested by inlets mounted on the aft sections of these aircraft. It generated Mach numbers ranging from 0.19 to 0.4 and boundary layer thicknesses between 36% and 45%. The circumferential distortions at the aerodynamic interface plane of the serpentine inlet were also calculated, and ranged between 0.0042 for the lowest Mach number, to 0.0098 for

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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.

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Novikov, 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.

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Presented in this thesis is the development of a high-fidelity aerothermal model for GE T700 turboshaft engine. The model was constructed using thermodynamic relations governing change of flow properties across engine components, and by applying real component maps for the compressor and turbines as well as empirical relations for specific heats. Included in the model were bleed flows, turbine cooling and heat sink effects. Transient dynamics were modeled using inter-component volumes method in which mass imbalance between two engine components was used to calculate the inter-component pressur

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