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Dissertations / Theses on the topic 'Turbine compressor'

Author: Grafiati

Published: 3 June 2025

Last updated: 31 July 2025

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1

Khan, Jobaidur Rahman. "Fog Cooling, Wet Compression and Droplet Dynamics In Gas Turbine Compressors." ScholarWorks@UNO, 2009. http://scholarworks.uno.edu/td/908.

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During hot days, gas turbine power output deteriorates significantly. Among various means to augment gas turbine output, inlet air fog cooling is considered as the simplest and most costeffective method. During fog cooling, water is atomized to micro-scaled droplets and introduced into the inlet airflow. In addition to cooling the inlet air, overspray can further enhance output power by intercooling the compressor. However, there are concerns that the water droplets might damage the compressor blades and increased mass might cause potential compressor operation instability due to reduced

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2

Dong, Yuan. "Boundary layers on compressor blades." Thesis, University of Cambridge, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.278266.

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3

Farmakalides, C. D. "The effects of reaction on axial compressor performance." Thesis, Cranfield University, 1992. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.305299.

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4

Tain, Ludovic. "Compressor leading edges in incompressible and compressible flows." Thesis, University of Cambridge, 1998. https://www.repository.cam.ac.uk/handle/1810/272432.

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5

Afanasiev, Gennadiy. "DAMAGE MODELING METHOD FOR TURBINE COMPRESSOR BLADE TUNING." Master's thesis, University of Central Florida, 2004. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/4395.

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The thesis presents a method of evaluation for blade damage in Combustion Turbine Compressor Section. This method involves use of multiple domains within a single Finite Element Model to predict the effect of damage on the blade properties. This approach offers significant time and effort savings when compared to traditional evaluation methods of similar problems. It is demonstrated via examples that the multi-domain modeling approach yields acceptable accuracy results. The economical implications of described method are readily applicable to both the industrial and the aerospace Combustion Tu

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6

Krige, David Schabort. "Performance evaluation of a micro gas turbine centrifugal compressor diffuser." Thesis, Stellenbosch : Stellenbosch University, 2013. http://hdl.handle.net/10019.1/80119.

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Thesis (MScEng)--Stellenbosch University, 2013.<br>ENGLISH ABSTRACT: Micro gas turbines used in the aerospace industry require high performance with a compact frontal area. These micro gas turbines are often considered unattractive and at times impractical due to their poor fuel consumption and low cycle efficiency. This led to a joint effort to investigate and analyze the components of a particular micro gas turbine to determine potential geometry and performance improvements. The focus of this investigation is the radial vaned diffuser which forms part of a centrifugal compressor. The

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7

Doukelis, Angelos F. "Study of the flowfield in the tip clearance region of compressor bladings." Thesis, Cranfield University, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.267342.

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8

Vigueras, Zuniga Marco Osvaldo. "Analysis of gas turbine compressor fouling and washing on line." Thesis, Cranfield University, 2007. http://hdl.handle.net/1826/2448.

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This work presents a model of the fouling mechanism and the evaluation of compressor washing on line. The results of this research were obtained from experimental and computational models. The experimental model analyzed the localization of the particle deposition on the blade surface and the change of the surface roughness condition. The design of the test rig was based on the cascade blade arrangement and blade aerodynamics. The results of the experiment demonstrated that fouling occurred on both surfaces of the blade. This mechanism mainly affected the leading edge region of the blade. The

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9

Luiten, Ruben Vincent. "Performance improvement of the Rover 1S/60 Gas Turbine Compressor." Thesis, Stellenbosch : Stellenbosch University, 2015. http://hdl.handle.net/10019.1/97049.

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Thesis (MEng)--Stellenbosch University, 2015.<br>ENGLISH ABSTRACT: The use of gas turbines in central receiver solar power plant cycles has become an increasingly popular research topic. This has led to the need to investigate and analyse the effect of the solar receiver on the gas turbine cycle. The aim of this thesis is to construct an experimental gas turbine setup to accommodate further research on utilizing solar energy to power gas turbines. The gas turbine under consideration is the Rover Gas Turbines 1S/60. The focus of this investigation is the centrifugal compressor of the gas

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10

Branehög, Johan. "An investigation of the feasibility of composite turbine compressor blades." Master's thesis, University of Cape Town, 2000. http://hdl.handle.net/11427/4966.

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Includes bibliographical references.<br>A study has been conducted as to the feasibility of using a carbon fibre reinforced polymer (CFRP) composite to replace the titanium alloy (Ti-6Al-4V) for the manufacture of turbine compressor blades. These blades are used in the first compression stage of a gas turbine and suffer from high stresses at the roots and rotor discs induced by the high centrifugal forces during operation and are sensitive to vibrations. The blades are of a transonic type with typical rotational speeds of up to 10 000 rpm. The lighter composite blade will reduce stresses on th

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11

Abdullah, Abu Hasan. "The application of high inlet swirl angles for broad operating range turbocharger compressor." Thesis, University of Bath, 1996. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.320555.

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12

Boyer, Keith M. "An Improved Streamline Curvature Approach for Off-Design Analysis of Transonic Compression Systems." Diss., Virginia Tech, 2001. http://hdl.handle.net/10919/27507.

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A streamline curvature (SLC) throughflow numerical model was assessed and modified to better approximate the flow fields of highly transonic fans typical of military fighter applications. Specifically, improvements in total pressure loss modeling were implemented to ensure accurate and reliable off-design performance prediction. The assessment was made relative to the modeling of key transonic flow field phenomena, and provided the basis for improvements, central to which was the incorporation of a physics-based shock loss model. The new model accounts for shock geometry changes, with shoc

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13

Coldrick, Simon. "The influence of blade row aerodynamics on pneumatic gas turbine instrumentation." Thesis, Cranfield University, 2003. http://dspace.lib.cranfield.ac.uk/handle/1826/11295.

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Steady state, inter row measurements in multistage axial compressors are relevant to the current design process. The objective in obtaining such data is for evaluation of compressor blading as well as validation for the computer programmes used in compressor design. Multi-hole pressure probes are a reliable and economical method of collecting detailed flowfield data in compressors for these purposes. These probes are calibrated in a uniform flow in a wind tunnel prior to use, to determine their response to a range of flow angles and speeds. When the probe is subsequently used for measurements

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14

McDougall, Neil Malcolm. "Stall inception in axial compressors." Thesis, University of Cambridge, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.237803.

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15

Lyes, Peter A. "Low speed axial compressor design and evaluation : High speed representation and endwall flow control studies." Thesis, Cranfield University, 1999. http://hdl.handle.net/1826/4251.

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This Thesis reports the design, build and test of two sets of blading for the Cranfield University low speed research compressor. The first of these was a datum low speed design based on the fourth stage of the DERA high speed research compressor C 147. The emphasis of this datum design was on the high-to-low speed transformation process and the evaluation of such a process through comparing detailed flow measurements from both compressors. Area traverse measurements in both the stationary and rotating frame of reference were taken at Cranfield along with overall performance, blade surface sta

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16

Rayner, D. "A numerical study into the heat transfer beneath the stator blade of an axial compressor." Thesis, University of Sussex, 1992. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.239995.

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17

Abass, Kabir Oliade. "Techno-Economic Analysis of Gas Turbine Compressor Washing to Combat Fouling." Thesis, Cranfield University, 2015. http://dspace.lib.cranfield.ac.uk/handle/1826/9230.

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Among the major deterioration problems a gas turbine encountered while in operation is compressor blade fouling. This is the accumulation and adhesion of dirt and sediment on the compressor blade which contributes between 70 to 85% of gas turbine performance loss. Fouling reduces turbine air mass flow capacity, compressor pressure ratio and overall gas turbine efficiency. In most cases, its effect does not manifest immediately in gas turbine power output and efficiency since they are not measured directly. However, it is apparent on the gradual increase in Turbine Entry temperature (TET) and E

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18

Davitt, James A. "A baseline expert control system for marine gas turbine compressor surge." Thesis, Monterey, California. Naval Postgraduate School, 1989. http://hdl.handle.net/10945/26900.

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United States Navy gas turbine ships are in need of casualty control system updating to reduce demanding conditions on engineering watch standers, to increase equipment longevity, and reduce operating costs. This thesis presents a baseline computer-based expert system controller concept developed for the critical casualty control problem of gas turbine compressor surge. The controller design rests on the building-block components of real-time gas turbine simulation and compressor surge characterization, which is discussed. The logic and rules for the expert system design are presented, as is a

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19

Patounas, Dimitrios S. "Disc heat transfer in gas turbine H.P. compressor internal air systems." Thesis, University of Sussex, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.444011.

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20

Van, der Merwe Bosman Botha. "Design of a centrifugal compressor impeller for micro gas turbine application." Thesis, Stellenbosch : Stellenbosch University, 2012. http://hdl.handle.net/10019.1/71610.

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Thesis (MScEng)--Stellenbosch University, 2012.<br>ENGLISH ABSTRACT: The use of micro gas turbines (MGTs) for the propulsion of unmanned aerial vehicles (UAVs) has become an industry standard. MGTs offer better performance vs. weight than similar sized, internal combustion engines. The front component of an MGT serves the purpose of compressing air, which is subsequently mixed with a fuel and ignited to both power the turbine which drives the compressor, and to produce thrust. Centrifugal compressors are typically used because of the high pressure ratios they deliver per stage. The purpo

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21

Russell, Andrew D. "The manufacture of gas turbine compressor components by Metal Injection Moulding." Thesis, Edinburgh Napier University, 2015. http://researchrepository.napier.ac.uk/Output/9827.

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Gas turbine compressor components manufactured from nickel base alloys have traditionally been precision die forged in sequential thermo-mechanical processing operations in order to achieve the desired geometry and mechanical properties. Metal Injection Moulding (MIM) is a competing three dimensional forming technology with proven applications in both the automotive and medical industries for producing industrial quantities of small, net shaped components. To date, the Metal Injection Moulding process has had limited exposure as a manufacturing process for gas turbine compressor components. Th

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22

Alexiou, A. "Flow and heat transfer in gas turbine H.P. compressor internal air systems." Thesis, University of Sussex, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.402026.

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23

Goat, Christopher. "Erosion resistance in metal - ceramic multilayer coatings for gas turbine compressor applications." Thesis, Cranfield University, 1995. http://dspace.lib.cranfield.ac.uk/handle/1826/10717.

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The erosion resistance of 50 m metal-ceramic multilayer coatings has been investigated under impact conditions comparable to those in a gas turbine compressor cascade. lt was possible to improve upon the erosion resistance of Ti-6Al-4V by a significant margin. The influence of layer mechanical properties, layer thickness, ceramic content and coating process on erosion resistance has been studied over a range of impact conditions. The most suitable coating formulation for maximum erosion resistance changed with particle impact energy. Under low energy impact conditions (<55 joules) coatings wit

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24

EL-SAYED, MOHAMED A. "ADVANCING THE WORK COMPATIBILITY MODEL THROUGH THE ANALOGY WITH COMPRESSOR/TURBINE MODELS." University of Cincinnati / OhioLINK, 2007. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1186979872.

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25

Šíblová, Kamila. "Návrh spalovací turbíny pro osobní automobil." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2013. http://www.nusl.cz/ntk/nusl-230622.

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This diploma thesis deals about the combustion turbine, design, processing and utilization. This work can be divided into three parts. The first part focuses on the theoretical knowledge gained in the field of gas turbines and their applications. The second part addresses the design of combustion turbine and its integral part. The third section describes the expected characteristics of combustion turbines. The work also includes the annex, which includes the technical documentation.

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26

Knebl, Viktor. "Termodynamické tepelné čerpadlo." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2020. http://www.nusl.cz/ntk/nusl-417536.

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This diploma thesis deals with the design of thermodynamic heat pump, used to utilize thermal energy of flue gases arised from the combustion of natural gas in a heat exchanger. The flow rates of the compader compressor, bypass compressor and turbine are calculated. Part of this thesis is simplified design of gearbox and economical evaluation of heat pump installation. The appendix of the thesis contains technical documentation.

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27

Svensdotter, Susanne. "Investigation of boundary layer transition for transonic flow over compressor and turbine airfoils /." Stockholm : Tekniska högsk, 1998. http://www.lib.kth.se/abs98/sven1214.pdf.

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28

Gannan, Aiad. "Cascade Testing and CFD Applied to Gas Turbine Performance Improvement with Compressor Cleaning." Thesis, Cranfield University, 2010. http://dspace.lib.cranfield.ac.uk/handle/1826/4634.

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With the growing interest in life cycle costs for heavy-duty gas turbines, equipment operators are investigating the trade off between performance improvements and associated maintenance costs. One of the key factors leading to performance degradation during plant operation is compressor fouling especially in harsh environments. These results from the adherence of dust or sand particles mixed with small oil droplets to compressor blade surfaces. The result is a reduction in compressor pressure ratio and an overall loss in mass flow, compressor efficiency and, therefore, overall power output. T

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29

McNulty, Gregory Scott. "A study of dynamic compressor surge control strategies for a gas turbine engine." Thesis, Massachusetts Institute of Technology, 1993. http://hdl.handle.net/1721.1/47350.

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30

Napert, Gary Arthur 1956. "Fatigue performance of electroless nickel coatings on stainless steel gas turbine compressor rotors." Thesis, Massachusetts Institute of Technology, 1989. http://hdl.handle.net/1721.1/41318.

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31

Varelis, Angelos G. "Technoeconomic study of engine deterioration and compressor washing for military gas turbine engines." Thesis, Cranfield University, 2008. http://dspace.lib.cranfield.ac.uk/handle/1826/9584.

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Despite spending much of their operating life in clear air, aircraft gas turbine engines are naturally prone to deterioration as they are generally not fitted with air filters. Engines are particularly at risk during takeoff and landing, and whilst operating in areas of pollution, sand, dust storms, etc. The build-up of contaminants, especially on the compressor surfaces, leads to a dramatic reduction in compressor efficiency, which gives rise to a loss of available power, increased fuel consumption and increased exhaust gas temperature. These conditions can lead to flight delays, inspection f

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32

Khoramzad, Elham. "Fretting fatigue life analysis for a gas turbine compressor blade-disk material combination." Thesis, KTH, Hållfasthetslära, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-284357.

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In order to analyse fretting fatigue life of dove-tail joints used in the compressor stage of a gas turbine, experimental study of different material combinations was conducted using rectangular fatigue specimen and bridge type pads. Specimen and pad interaction was simulated numerically and obtained results was used as input for 2 different crack propagation life prediction methods. The combined effect of stress and fretting damage which was characterised by means of Ruiz parameter was used in order to estimate the crack initiation and finally numerical results were compared to experimental f

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33

Gillaugh, Daniel L. "As-Manufactured Modeling of a Mistuned Turbine Engine Compressor Evaluated Against Experimental Approaches." Wright State University / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=wright1557245676336916.

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34

De, Losier Clayton Ray. "Effects of Manufacturing Deviations on Core Compressor Blade Performance." Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/31340.

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There has been recent incentive for understanding the possible deleterious effects that manufacturing deviations can have on compressor blade performance. This is of particular importance in todayâ s age, as compressor designs are pushing operating limits by employing fewer stages with higher loadings and are designed to operate at ever higher altitudes. Deviations in these advanced, as well as legacy designs, could negatively affect the performance and operation of a core compressor; thus, a numerical investigation to quantify manufacturing deviations and their effects is undertaken. Data

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35

Lapáček, Martin. "Reverzační turbokompresor." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2015. http://www.nusl.cz/ntk/nusl-231809.

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This diploma thesis is dedicated to a design of a reversing turbo-compressor. The thesis is divided into several parts. The introductory part includes the relevant theory and categorization of turbomachines. The second part describes the storage system the machine is designed for. A separate chapter is devoted to other examples of possible use of this machine. The next chapter provides a detail description of modes and individual parts of the machine. The most comprehensive chapter is then devoted to the design of the compressor, turbine calculation and design of integrated gearbox. The thesis

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36

Scillitoe, Ashley Duncan. "Towards predictive eddy resolving simulations for gas turbine compressors." Thesis, University of Cambridge, 2017. https://www.repository.cam.ac.uk/handle/1810/270030.

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This thesis aims to explore the potential for using large eddy simulation (LES) as a predictive tool for gas-turbine compressor flows. Compressors present a significant challenge for the Reynolds Averaged Navier-Stokes (RANS) based CFD methods commonly used in industry. RANS models require extensive calibration to experimental data, and thus cannot be used predictively. This thesis explores how LES can offer a more predictive alternative, by exploring the sensitivity of LES to sources of uncertainty. Specifically, the importance of the numerical scheme, the Sub-Grid Scale (SGS) model, and the

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37

Lackner, Matthew 1980. "Vibration and crack detection in gas turbine engine compressor blades using Eddy current sensors." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/28895.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, September 2004.<br>Includes bibliographical references (p. 97).<br>(cont.) in the ECS signal, no definitive method for sensing blade vibration using an ECS has yet been developed.<br>High cycle fatigue (HCF) cracks generated by compressor blade vibrations are a common source of failure in gas turbine engines. Current methods for crack detection are costly, time consuming, and prone to errors. In-situ blade vibration detection would help operators avoid critical engine speeds, and help infer the presenc

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38

Al-Essa, Fouzi Khalid Sultan 1970. "An experimental study of compressor stability in a 450 kW helicopter gas turbine engine." Thesis, Massachusetts Institute of Technology, 1997. http://hdl.handle.net/1721.1/46101.

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39

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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40

Streďanská, Alexandra. "Návrh turbodmychadla." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2020. http://www.nusl.cz/ntk/nusl-417802.

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Diploma thesis focus on the design of turbocharger in SW MS Excel. For required flow and pressure ratio, the thermodynamics parameters were calculated for the turbocharger. From these, geometry was designed and the condition of mediums was calculated for each part of the turbine and compressor. At last basic characteristics of the turbine and compressor on varying the regime of engine operation the rotation was made and offered an idea about the working point position.

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41

Reding, Brian D. II. "Tubular and Sector Heat Pipes with Interconnected Branches for Gas Turbine and/or Compressor Cooling." FIU Digital Commons, 2013. http://digitalcommons.fiu.edu/etd/969.

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Designing turbines for either aerospace or power production is a daunting task for any heat transfer scientist or engineer. Turbine designers are continuously pursuing better ways to convert the stored chemical energy in the fuel into useful work with maximum efficiency. Based on thermodynamic principles, one way to improve thermal efficiency is to increase the turbine inlet pressure and temperature. Generally, the inlet temperature may exceed the capabilities of standard materials for safe and long-life operation of the turbine. Next generation propulsion systems, whether for new supersonic t

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42

Ozturk, Harun Kemal. "A computational study of flow and heat transfer in gas turbine axial compressor stator-wells." Thesis, University of Sussex, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.388675.

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43

Nishta, B. V. "Computer analysis of the stress-deformation state of the centrifugal compressor and gas turbine impellers." Thesis, Sumy State University, 2015. http://essuir.sumdu.edu.ua/handle/123456789/40623.

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Impellers are rotating components of a centrifugal compressor and gas turbine. Sometimes they have complex forms. They are mainly loaded by centrifugal forces. The wheels are heavy duty parts, often working for long time and their summary stresses may be so large that the analysis of the conditions of their strength is impossible without considering creep. At the same time the wheels are the most critical parts of machines and saving their strength should be provided with complete reliability. All this is defined by special difficulties and responsibilities of the compressor and turbine wheel

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44

Kais, G. "Heat transfer and fluid flow in the high pressure compressor drive cone cavity of an aeroengine." Thesis, University of Sussex, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.344070.

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45

Hansson, Edvin. "Creating a Dynamic Model of a Gas Turbine in the MVEM Framework Using an Ellipse Compressor Model." Thesis, Linköpings universitet, Fordonssystem, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-165062.

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The legislations on greenhouse gas emissions are getting tougher and tougher every year. This drives the demand for energy efficient gas turbines with as low emissions as possible. This poses the challenge to manufacturers of constructing gas turbines with lessened environmental impact, but with maintained performance. To obtain this, there is a need of optimization of current principles along with completely new ideas and solutions. One part of developing new, improved gas turbine configurations is to create prototypes and test them. However, creating and testing a gas turbine is a both expen

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46

DuoÌ, Pierangelo. "A predictive study of foreign object damage in gas turbine compressor blades under high cycle fatigue." Thesis, University of Oxford, 2005. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.418633.

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47

McGlumphy, Jonathan. "Numerical Investigation of Subsonic Axial-Flow Tandem Airfoils for a Core Compressor Rotor." Diss., Virginia Tech, 2008. http://hdl.handle.net/10919/26039.

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The tandem airfoil has potential to do more work as a compressor blade than a single airfoil without incurring significantly higher losses. Although tandem blades are sometimes employed as stators, they have not been used in any known commercial rotors. The goal of this work is to evaluate the aerodynamic feasibility of using a tandem rotor in the rear stages of a core compressor. As such, the results are constrained to shock-free, fully turbulent flow. The work is divided into 2-D and 3-D simulations. The 3-D results are subject to an additional constraint: thick endwall boundary layers at th

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48

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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49

Puttock-Brown, Mark Richard. "Experimental and numerical investigation of flow structure and heat transfer in gas turbine HP compressor secondary air systems." Thesis, University of Sussex, 2018. http://sro.sussex.ac.uk/id/eprint/75214/.

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50

Dominik, Dávid. "Návrh aeroderivátu pro využití v kompresních stanicích." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2020. http://www.nusl.cz/ntk/nusl-417593.

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This thesis is concerned with the calculation of the power turbine. This turbine should be used in the automatic drive of the compressor used for compression of natural gas in compressor stations. Flight engine aeroderivate from the Rolls-Roye company, type RB211-22B, was used as gas generator. The main aim of the thesis is to summarize of the base atributes of the combustion turbines and aeroderivates. They are used for automatic engine, application a thermodynamic calculation of the power turbine, for reaction stage and basic strength calculations.

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